★★★银河警哨：“宇宙的第三大类涡旋”（奇异涡环），及未来航空航天理论

地球全力

★★★银河警哨：“宇宙的第三大类涡旋”（奇异涡环），并全新“电磁控制等离子体空气动力学”，及相关未来飞行器（包括“飞碟和雪茄型太空母舰”）

1.吹响地球历史最高“警哨”！
    美国海军2019年9月及美国国防部2020年4月，正式承认：其战斗机数十年来一直被“超级飞行器”挑逗！而中国“少数民族学者”立刻表示已破解此谜！并拿出“少数派报告”，以助我地球文明尽快摆脱“银河动物园试验品理论”：
    “外星人”很可能早已用10%到20%光速，且以反物质核能为燃料的机器人飞船探测器等，自动化地统一了整个银河系！“外星人飞碟”的飞行原理较完整的被破解，其是用一种较类似于“烟圈和蒲公英种子及昆虫翅膀上的环形分离涡旋（涡环）”，但这是人类发明的“宇宙的第三大类涡旋”（奇异涡环）。“飞碟和雪茄型太空母舰”，主要用“金属态或冷凝超导态的反物质氢”为太空发动机的核燃料，其核能发电机和离子电推进器合成最强的宇宙飞船发动机，而也同时采用全新的“电磁控制等离子体空气动力学的涡旋和激波”的升力体和乘波体。

2.第二个“全世界和平哨声”！
    在此呼吁全世界和平，希望世界各国能团结在中国的领导下，共同对抗2020年开始的“新冠肺炎疫情”，且以中国为中心恢复世界经济，并向太空经济发展！从“新冠病毒”的完美特性上看出，这不可能是现有地球生物医学科技可以创造出的，而现在从美国正式承认“超级飞行器挑逗”一事上，中美两国有理由相信：
    很可能有“外星人势力”参与了这次“新冠肺炎疫情”？！进一步，“新冠病毒”更可能是“外星人”创造出来的？！那么，如果美国不能诚心与中国合作对抗疫情，也许这将是“外星人”为了淘汰美国的“原世界霸主地位”，并挑选中国成为下一任世界领导，的一次重要的“地球的公共卫生灾难和经济重启的试验”？！

3.第三个“向太空进军哨声”！
    “外星人之谜”已基本破解，希望国内外的物理学者联合航空航天学者和政府及私企，大力发展太空科技和经济，地球文明通过向太空发展（重点发展太空机器人和人工智能及太阳能源转换成核能和太空基地的建设），可以上亿倍的提升地球总的生产力，真正摆脱在“先进星际文明的外星人”眼中的“银河动物园试验品”的角色！尽快成为“银河系的星际文明”！



资料：

美国官宣UFO引全球围观，美军飞行员大喊：这到底是什么鬼东西？
环球网军事04-29
【环球网军事报道 环球时报驻美国特约记者 杨征 特约记者 赵迪】新冠肺炎疫情期间居家集体围观外星人？美国军方送上福利。当地时间27日，美国国防部解密了三段不明飞行物（UFO）的视频，并官宣视频本身的真实性。这些视频拍摄于2004年到2015年间，之前曾被泄露过，引发大量UFO迷的追捧。国防部称，此次解密是为了澄清公众对视频是否属实、是否有更多内容的误解。不过，英国《卫报》28日称，五角大楼亲自出面证实UFO视频的真实性，势必引发更多关于人类与外星人互动的猜测和遐想。



2004年美国海军F/ A-18战机遭遇UFO视频截图。


据美国有线电视新闻网（CNN）27日报道，五角大楼当天正式公布了三段UFO视频。视频由美国海军人员通过红外摄像机拍摄，画面中的UFO移动速度之快令人咋舌。去年9月17日，美国海军曾承认这些视频的真实性。五角大楼发言人高夫27日在一份声明中表示，现在正式公布这些视频，是为了澄清公众对于流传视频真实性的质疑以及误解。声明说，经过彻底调查，国防部已经确认，授权发布的这些非机密视频不会泄露美军任何敏感军力或武器系统，也不会影响对“不明飞行现象”的入侵行为的后续调查。

这些视频拍摄于2004年到2015年之间，2017年12月至2018年3月间陆续被一家名为“星之来客科学艺术学院”的美国民间UFO研究组织曝光。视频中可清楚看到，UFO突然出现在8万英尺（1英尺约合0.3米）高空，向海平面疾速俯冲，又在2万英尺处停下，并在空中盘旋，速度相当惊人，片中还可听到美国海军战机飞行员大喊：“这到底是什么鬼东西？”“太惊人了！”还有人在视频中问道，这个UFO是不是无人机？

曾在2004年目睹了UFO的美国海军飞行员戴维·弗拉沃尔中校2017年告诉《纽约时报》，当时他与战友驾驶“超级大黄蜂”战机执行常规训练，中途接到海军一艘巡洋舰通知，指该舰发现神秘飞行器踪迹，他们已追踪该飞行器长达两周，指示2人前往调查。随后他发现，海面上方漂浮着1个12米长的椭圆形白色物体。于是他开始下降，物体跟着上升，好像要到半路与他会合，接下来这个物体加速离开。弗拉沃尔对CNN表示，这种飞行器的移动方式无法用常理解释，“当我靠近它时，它迅速向南加速，不到两秒钟就消失了。非常突然，就像乒乓球撞到墙上后突然弹到另一边”。

美国政府在对待UFO问题上的态度一向讳莫如深。美国《新闻周刊》说，五角大楼起初也并没有打算对公众开放这些视频，但突然承认视频真实性，或许跟国内UFO粉丝的专业化程度越来越高有很大关系——他们正倒逼美国政府公布真相，这其中就包括“星之来客科学艺术学院”。该机构的创始人德隆称，他曾听到有人说，美国政府保管着外星人尸体的机密情报。他还说，“有几个不同种族的外星人以寻找资源为目的来过地球。为了推动人类的进化，外星人会定期操控人类的遗传基因。”

像德隆这样对UFO着迷的美国人可不少。《新闻周刊》称，每年大约有成千上万名美国人向警方、五角大楼、媒体等报告自己看到了UFO。据统计，1905年以来美国报告目击UFO的人数已经超过10万人。但这些所谓的UFO目击事件最终被确认是云、流星、鸟、气象观测气球等。不过，无论官方给出多么合情合理的解释，只能让其中一部分着迷的人坚信：“政府在故意隐瞒真相，我看到的就是UFO”。哈佛大学天文学院院长洛布指出，看到这种完全有悖常识的东西，他更相信这是人类自己所造成的现象，跟自然界没有关系。

《新闻周刊》提到，2007年五角大楼为研究空中遭遇UFO的事件，曾成立秘密研究项目——“先进飞行威胁辨识计划”。该项目的发起人是时任参议院多数党领袖的里德，执行人则是五角大楼官员伊莱松多。从2007年到2012年，五角大楼与位于内华达州的军需企业比奇洛航空航天共同投入2200万美元研究UFO。不过，因为五角大楼拒绝继续提供经费以及美国政府在UFO问题上一贯的保密原则，该项目于2012年终止，伊莱松多随后也向国防部提交了辞呈。

2017年，离职后的伊莱松多在接受CNN采访时表示，“虽然这些不明飞行物可能会对美国的安全保障造成严重威胁，但国防部强烈反对进行进一步调查。有非常令人信服的证据表明，这些我们称之为飞行物的物体，其所显示出的一些飞行特征，在美国装备库和目前已知的外国装备库中都无法找到有类似的装备”。

即使官方的秘密研究项目被终止，一些美国国会议员仍然对UFO问题很感兴趣，CNN报道说，去年夏天，不少参议员收到了美军人员关于UFO的机密简报。民主党参议员华纳的发言人科恩当时就表示，“如果飞行员在大洋洲或其他地方报告出现危险，干扰了他们的训练或是让他们陷入险境，参议员华纳就会想要得到答案。无论是气球、‘小绿人’还是什么其他东西，我们都不能让飞行员冒不必要的生命危险”。

由于飞行员报告见到UFO的个案增加，美国海军已于去年4月制定相关指引，规定飞行员认为他们可能看到了UFO时，该如何报告、跟踪以及汇总和保存数据。UFO事件增多也惊动了美国总统特朗普。据美国《福布斯》杂志28日报道，他去年接受媒体采访时表示，即使关于飞行员发现不明飞行物体（UFO）的报道有所增加，他还是不太能相信UFO真实存在。他说，就海军有关UFO的报道，“我见过、阅览过、听过，甚至开过一次简短的会议。不过，人们说他们见到UFO时，我相信吗？不。”

地球全力

1 未来航空航天飞行的需求
1 The future flying requests on the Aeronautics and the Astronautics.

1.1 在太阳上和木星、土星、天王星、海王星等气态行星上飞行，与在地球大气层中飞行的相似性和差异性，特别是对垂直起降的太空战斗机的要求
1.1 The diversities and the similarities of flying in the atmosphere of Sun,Jupiter,Saturn,Uranus,Neptune，and Earth，especially the requests on the VTOL (vertical takeoff and landing) Space Fighter.

Fig.1

需求1

a.在未来，我们地球文明的飞行器将不得不在大气环境极其恶劣的太阳上和木星、土星、天王星、海王星等气态行星上进行航空飞行和战斗，这事比进行太阳系外的星际旅行更加困难和重要！因为我们的太空事业是首先向着开发太阳系内的各大行星的方向发展的，最后还要开发利用太阳本身的物质和能源！可以说，航天学必然永远以航空学为基础，那么，“空气动力学”未来将会更加重要！
a.In the future,our earth civilization’s spacecraft will have to be flying and fighting in the atmosphere of Sun,Jupiter,Saturn,Uranus,Neptune,on which the atmosphere environments are too bad.This fact is more diffcult and more important than the interstellar-travel in the outer space.Because our space industry will at first develop towards the plannets of solar-system ,and eventually exploit the source and energy of the Sun itself.As it were,the Astronautics development will have to base on the aeronautics forever,so the Aerodynamics will be more important in the future.

b.毫无疑问，太阳的外层（对流层和大气层）是宇宙中最恶劣的可飞行环境，一是因为太阳表面的稠密高温等离子体流（6000K温度）和光热辐射及核辐射，二是因为“太阳风暴”的能量和速度极高（“太阳黑子”的磁场“磁重联”过程产生“太阳耀斑”，可为一百万倍以上地球风暴（台风/飓风）的总能量，其粒子流的射流速度经常在1000公里每秒以上，有巨大的冲击力），三是太阳的引力巨大，其表面重力是地球的28倍。可见，未来飞行器要在太阳上飞行，不但要对抗高温、强辐射和巨大引力，还必须要有强大的“装甲防护”！这是现今的地球文明的各种航空航天飞行器无法想像的条件和困难！另外也要求能防止飞行器的“升力面”和机翼“附面层”在受到高速射流和太阳风暴的冲击时，出现空气动力学方面的“失速或尾旋”现象，使其失去升力！这要求现今的“空气动力学”出现革命性创新！
b.There is no doubt,the troposphere and the atmosphere of the Sun are surely the most bad environments to fly.First of all,there are too thick and too high temperature plasma-flow and too strong electromagnetic radiation and nuclear radiation on the sun surface (The temperature is 6000K),and secondly,there is often too high speed of the ion beam and great energy in the solar-storm (The magnetic reconnection process of the sunspot will generate the solar-flare which could have a million times energy of earth's giant storm (hurricane/typhoon),and the speed of the ion beam will often reach a speed of 1000 to 2000 kilometre per second which have great impact force or momentum;),and thirdly,the Sun have too strong gravity,the sun's gravity is 28 times the earth's gravity.It is clear that the future spacecraft will need to struggle against the high temperature and strong radiation and great gravity,and have to require a very thick armor protection as well.These diffculties and conditions are more than our present spacecraft and aircraft could bear.In addition,we will also need to protect the lifting surface of craft and the boundary layer of the wing from the impact and disturbance of the ion beam and the solar-storm,which will cause the aerodynamic stall/spin,that means losing the aerodynamic lift.So it will request a revolutionary innovation in the present area of Aerodynamics.

c.其次，在木星、土星、天王星、海王星等巨型气态行星上，不但温度很低，而且有强烈的风暴，比如海王星上的风暴速度可以达到2100公里每小时，是地球上的龙卷风流体速度的四倍，而其大气的温度低至-218℃。所以，在海王星上飞行，飞行器不但要对抗高速低温的流体风暴，还要对抗在风暴中混杂着的如同子弹一般的两倍音速的固体冰雹和冻雨！这也要求飞行器必须有强大的“装甲防护”！另外也要求能防止飞行器的“升力面”和机翼“附面层”在受到气态行星上的“三相流体（气体、液体、固体）”风暴的冲击和扰动时，出现空气动力学方面的“失速或尾旋”现象，使其失去升力！这同样要求现今的“空气动力学”出现革命性创新！
c.In the next place,there is not only a very low temperature but also many great strom or hurricane on the gas giants of Jupiter,Saturn,Uranus,and Neptune.The giant storm of Neptune will reach a speed of 2100 kilometre per hour ,which will be about four times the speed of Earth's tornado ,and its atmosphere temperature will often reach -218 degree Celsius.It is clear that the future spacecraft will need to not only struggle against the low temperature and high speed fluid,but also against the hail and sleet which reach twice the speed of sound as fast as the rifle bullet.The spacecraft will have to require a very thick armor protection as well.In addition,we will also need to protect the lifting surface of craft and the boundarylayer of the wing from the impact and disturbance of the flowing three-phase-fluids(gas,liquid and solid) storm,which will cause the aerodynamic stall/spin,that meanslosing the aerodynamic lift.So it will also request a revolutionary innovation in the present area of Aerodynamics.

d.目前在地球的大气层内飞行的飞行器，都采用现今的“空气动力学”，同样很难对抗大风和风暴的气流扰动和冲击，特别是在起飞降落阶段遇上“垂直切变风”时容易“失速”而失去升力！证明现今航空飞行器的“空气动力学”仍有很大的缺陷！
d.So far,all the aircraft of our earth flying in the atmosphere still apply the present Aerodynamics,also will not resist the impact and disturbance of the strong wind and the storm (hurricane) as well.Expecially in the takeoff and landing,the aircraft could be stalling and crashing if be caught in the vertical wind shear.This will be proving a great flaw that the present Aerodynamics has.

e.我们地球的军事航空史上曾经出现不少“垂直起降战斗机”，而“垂直起降”性能一直是航空固定翼飞机所追求的性能，但是这些战斗机在起飞降落时更多依赖于喷气发动机的推力，更少采用“空气动力学的升力”，所以有很多难以克服的缺陷，比如悬停时间短耗油大、载油量少航程短、死重较大机动性差、体内空间小机体肥大。。。并且在起飞降落时也一样容易受大风和风暴及低空风切变的的冲击和扰动！所以现今航空飞行器的“空气动力学”，对航空固定翼飞行器的“垂直起降”性能帮助不大（除了风扇或螺旋桨提供的推力或拉力仍然是直升机和旋翼机所必需），而把“垂直起降”的全部希望放在提高喷气发动机的推力和直径上是远远不够的！
e.During our aviation history there appear so many kinds of VTOL (vertical takeoff and landing) fighter plane (fixed-wing aircraft but not helicopter).The characteristics of VTOL (vertical takeoff and landing) has always been a pursuit on the fixed-wing aircraft.But the takeoff and landing of these fighter would often rely more on the thrust of the jet engine,less on the lift about Aerodynamics.So there are many flaws,such as with higher oil consuming and shorter time  when it takeoff and landing,with smaller oil loading and shorter voyage,with larger deadweight and lower maneuverability,with narrower inner space and bigger airframe...and  could be easy to be impacted and disturbed by the strong wind,the giant storm(hurricane) and the low-level wind shear as well.So the present Aerodynamics has hardly help for the characteristics of VTOL (vertical takeoff and landing) of thefixed-wing aircraft (excepting that the propellers and the fans also provide thethrust to the helicopter and the rotary-wing aircraft).But it is not enough to put all our hope in increasing the thrust and the diameter of the jet engine.

综上所述，要想让未来战斗机在太阳上和木星、土星、天王星、海王星等气态行星上飞行和战斗，并且要求有很理想的垂直起降和机动性能，那么现今的“空气动力学”和航空飞行学有必要出现革命性的创新！但是前提我们要能抵制“反引力反重力反质量”的诱惑！
To summarize,if we want to make a flying and a fighting in the atmosphere of Sun,Jupiter,Saturn,Uranus,Neptune，and Earth,and to request an ideal characteristics of VTOL (vertical takeoff and landing) and maneuverability,it will also request a revolutionary innovation in the present area of Aerodynamics and Aeronautics.But the premise is that we will resist the temptations of the theories about anti-gravity and anti-mass.



1.2.太阳系内各大行星之间的交通航行，对太空飞行器的喷射推进发动机（离子电推进器）和核能源的要求，特别是对太空战斗机的要求
1.2.The requests of jet-propelled engine (ion electric thruster) and atomic energy on spacecraft which making an interstellar-travel in the solar-system，especially on the spacefighter.

Fig.2

需求2

a.近年来世界航天业提倡的“全电推进型卫星”不仅是一个航天学进展，也是空间发动机（喷射推进发动机）的一次革命，即用离子电推进器代替所有的化学火箭推进发动机。在假设卫星可以用太阳能电池板无限的接收太阳光能量的前提下，则采用离子电推进器推进的卫星相比用化学火箭可以大幅度节约推进介质的数量或质量，当然在太空深空探测器上早已经用核能电池供电给离子电推进器了。这是人类航天科技发展的必然方向和结果。
a.The all-electric propulsion satellites that was resently advocated by the space industry will not only be a development of Astronautics，but also a revolution of space engine （jet-propelled engine）.Namely we will replace all the rocket-propelled engine with ion electric thruster in the future.On the premise of being capable of endlessly absorbing sunlight with the solar-panel,then the ion electric thruster will use less quantity and mass of the propelling medium than the chemical rocket.Of course the atomic battery have already supplied electricity to the ion electric thruster in the deep space probe.This will be the direction and the result of the advancement of aerospace science and technology.

b.离子电推进器有很多种类，各有各的优点和缺点，但是基本的原理都是用太阳能电池的电力加速电离后的粒子而向外喷射得到推力。而目前的空间飞行器的推进器技术受到能源的限制，尚不能提供在航天上需要的十万甚至百万以上的比冲量，也不能提供如航空发动机一般的大推力。但是，未来航空航天两用飞行器或者是战斗机，却不但需要在航空飞行器的小比冲大质量的喷气发动机的特点，也同样需要在空间飞行器的大比冲小质量的离子推进器的特点。这是一个很大的矛盾！
b.There are so many kinds of ion-electric thruster at present,and each one have its  advantages and disadvantages,but their fundamental principles will always be gaining the thrust from spraying out the ion，which is the particle will be ionised by using only electric power supplied by solar-cells.As the propulsion technology of spacecraft will till be confined to the power,it will not be able to achieve one hundred thousands to millions of specific impulse which the spacecraft need,and willnot create the large thrust of jet engine of aircraft as well.But the future aerospace vehicle or fighter will require both the characteristic of aircraft's lowspecific impulse and large thrust,and the characteristic of spacecraft's high specific impulse and small thrust.So there is a huge contradiction between them.

c.现有的卫星用离子电推进器喷射的粒子速度60公里每秒，比冲超过3000秒，最大推力不到10牛。而未来在太阳系内任意飞行和战斗的太空战斗机，想要得到成吨的推力，并且尽可能的减少推进介质的数量或质量，则必须尽可能的提高喷射粒子速度到接近光速，则“环形的同步加速器”最合适用作推进器或发动机来加速离子。“环形同步加速器”本身不但可以加速离子到接近光速，也可以用于发射各种强大的激光和粒子束流，两者都将作为一种“定向能武器”。
c.The speed of the particles ejecting from the satellite's ion-electic thruster will reach 60 kilometers per second，and the specific impulse is already larger than 3000,but its biggest thrust is not more than 10 newtons.If we want to achieve several tons of thrust on the spacecraft flying in the inner space of solar-system,and as far as possible to reduce the quantity of working medium,then we shall have to increace the speed of the ejected particle as close as possible to the speed of light.So the toroidal synchrotron should be the best thruster or engine which will be use to accelerate the ion.The toroidal synchrotron should not only accelerate the speed of the ion as near as to the speed of light,but also will be use to emit a laser or shot an ion beam,both of them will be used as a kind of directed energy weapon.

d.太空航行和星际旅行最重要的是能源，公认的能源是三种核能，即核裂变、核聚变、正/反物质反应。而其中核裂变能的发展正在成熟，但是核反应堆比较笨重，不适合用于小形太空飞行器或战斗机上。而可控核聚变能也获得很多进展，也许惯性约束聚变较容易实现，但似乎很少用于研究等离子体的长时间控制约束。而磁约束聚变中的托卡马克装置内等离子体流的稳定时间已经接近两分钟，仿星器内的等离子体流也许更稳定，虽然二者都不太可能大幅度提高发电效率，但是托卡马克装置却可以结合环形同步加速器一起成为一种理想的太空飞行器的推进发动机！可以在太空航行时把较大质量的推进介质加速到接近光速并喷射而出得到较大推力，也可以在大气层中飞行时吸入大质量的空气并电离加速后（远低于光速）喷出得到巨大的推力。所以这是理想的离子电推进发动机的机电一体化构造。另外，现今已有不少设计，即把托卡马克装置的能安全容纳上亿度高温等离子体的原理应用在未来太阳上登陆的探测器上，以对抗太阳的高温流体环境；还有不少理论，要把托卡马克装置中的高温强电流的压缩等离子体环流整个个体加速后喷射出去再击中目标后自动爆炸，而做为一种也许类似于“球形闪电”的称为“环形等离子体流的炮弹或炸弹”，可用于中近程的防御武器。
d.The most important thing is the energy source when flying in the space or making a interstellar travel.These energy will include three varieties ,that is the nuclear fission and the nuclear fusion and the antimatter/matter reaction.Among them,the development of the nuclear fission have been maturing，but the nuclear reactor is too heavy to be used in the small spacecraft.The controllable nuclear fusion have already achieved many developments,perhaps the inertial confinement fusion will be easier to achieve,but it is less used to study the control and confine of the plasma for a long time.Among the magnetic confinement fusions,the stable time of the plasma-flow in the tokamak devices have lasted two minutes,the stability of the plasma-flow in the stellarator might be better.Although both of them will not be capable of increasing substantially the power generation efficiency，but if the tokamak devices will be combined with the toroidal synchrotron,then it will become an ideal ion electric thruster in the spacecraft,and achieving larger thrust by accelerating larger numbers of propulsive working medium as close as possible to the speed of light in the space,or creating largest thrust by accelerating largest numbers of fresh air which the engine absorbing to a lower speed in the atmosphere.So it is a wonderful electromechanical construction of ion electric thruster.In addition,there are many designs that have been put forward,which put the theory that capable of containing one hundred million degrees of plasma-flow inthe tokamak devices to use in the prober landing on the sun,that will resist the high temperature of sun.And there are many other theories,that want to accelerate the toroidal plasma-flow which have been compressing by strong electric current,and then shot it out to attack the military target and will be automatically explosive.This will be used as an intermediate or short range weapon of defence which will be called the bomb and shell about the toroidal plasma-flow that might be as similar as the ball lightning.

e.目前公认的最有希望的未来太空飞行器的能源是“反物质核能”。因为相比于核裂变和核聚变反应只有很小一部分质量转化为能量，而反物质的核反应却可以把百分之百的质量转化为能量。但是，反物质能源的应用目前有几个很大的困难，一个是反物质的生产成本巨大的问题，二个是如何安全稳定地贮存大量反物质的问题，三个是正反物质核反应产生的伽玛射线如何屏蔽或转化为无害的问题。
e.It has been known to all in the astronautics field that the ideal power of the future spacecraft will come from the antimatter/matter reaction.Beacause the nuclear fission and the nuclear fusion have only a tiny fraction of masses to be converted to power,but conversion of energy of the antimatter/matter reaction will reach 100 per cent.There are several diffculty in this antimatter.Firstly,it is the problem of the great cost of production,secondly,the problem of how to store a large quantity of the antimatter steadily and safely，thirdly，the problem of how to shield the γ–ray coming from the antimatter/matter reaction.

综上所述，要想未来在太阳系内八大行星之间实现高速航行，对喷射推进发动机（离子推进器）和核能源的技术要求已经很明确了，即太空战斗机只能采用超大功率得到大推力的环形同步加速器作为一种发动机，以及反物质为其上的核能源，同时能提供高能激光束和离子束流等“定向能武器”。那么，我们将可以在此理论上做出进一步的创新，为下一步在工程方面的实践和创新做出指引！但是前提我们要能抵制“超光速和反相对论”的诱惑！
To summarize,if we want to cover the long distance between the eight major planets of the solar-system with a high speed，the request about the ion electric thruster and the atomic power technology has been clear.Namely,the spacefighter will only use the toroidal synchrotron as a kind of engine which will provide high power and high thrust，and the antimatter as a kind of atomic power in it，meanwhile,it will provide a laser or an ion beam as a kind of directed energy weapon.Then we will make further innovation on the basis of this theory,and guide a better development in the engineering innovatively and practically in the next step.But the premise is that we will resist the temptations of the theories about faster-than-light and anti-theory of relativity

地球全力

2 未来太空战斗机（飞碟）太空飞行作战原理
2 The flying and fighting principle of the future spacefighter（the saucer-shaped spacecraft) in the space.

Fig.1

太空1

2.1. 太空战斗机要在太空的真空环境中飞行战斗，首先要求的是飞行姿态和航向的稳定性，很需要机体中有部分的质量能像地球卫星一样“自旋稳定”，而对雷达探测隐身的要求和装甲防护的要求等，进一步要求机体的在“攻击水平面”的360度各向视图都比较扁平，即“受弹面积最小”，所以必然选择了“扁锥形陀螺体的结构”，并且机体是分成上下两个陀螺体组成“双自旋体空间飞行器”。另外，“环形同步加速器与托卡马克装置相结合”成为一种理想的太空战斗机的离子电推进发动机，飞碟机体中部自然可容纳这种“圆盘形离子推进器”，并有360度角布置的“推力矢量喷口”，以得到最高机动性。而飞碟顶部可以把“球形座舱”用“磁悬浮作用”布置在机体内部中心的旋转轴之上并自由滚转，实现“三维稳定”。所以飞碟的机体结构最合适在太空飞行战斗。
2.1 The spacefighter will be flying in the vacuum environment of the space,the first request is the flight attitude and the directional stability,then it will require to make some sectional mass of the airframe into spinning stability of satellites.And the request of using radar to detect the stealth aircraft or the request of armor protection,it will further require that the airframe will be flattening on a 360-degree view of the attackable horizontal.Namely the attacked shell area will be smallest.So we chose the airframe of flattening cone-shape top.And the airframe is divided into the upper and lower top which consisting of a double spinning spacecraft.The tokamak-devices will be combined with the toroidal synchrotron,then it will become an ideal ion electric thruster in the spacefighter,and the saucer-shaped spacecraft exactly right have an intermediate part to fit in this disc-shaped thruster,and there is plenty of the thrust-vector-nozzle which will be arranged on a 360-degree,that will make it easier to get the highest maneuverability.A spherical cockpit will be fitted on the saucer-shaped spacecraft's top with the magnetically suspended effect,and will be free-roll on the axis of rotation in the middle part of the airframe.This will get the three-dimensional stability.So the airframe of the saucer-shaped spacecraft is best suitable flying and fighting in the space.

Fig.2

太空2

2.2 “环形同步加速器与托卡马克装置相结合”成为一种理想的太空战斗机的离子电推进发动机，虽然在加速离子流时其能量损耗方面比较“圆柱型远程太空运输船的直线式加速器作为推进发动机”而言要大得多，但是却最适合“飞碟型的中近程太空战斗机”。其首先是将可电离物质粒子用圆心处的大量简单的“霍尔效应离子推进器”进行电离和初步加速后，由“普通的直线加速器”引导进入类似“环形同步加速器与托卡马克装置相结合”的容器中进行容纳、压缩和再加速，其中的“等离子体环流”含有“感生电流”而保持箍缩，并可以以高速回旋流动的形式保留在环形容器内很长时间，直到被“推力矢量喷口”的磁场引导喷射而出，当然，如果长时间不被喷出的等离子环流也可以被加速器和环形容器自身去进行减速、削弱、吸纳、再回收等等，以减少在太空飞行中的对推进介质和能源的浪费。而当其中的“等离子体环流”被加速到接近“光速”时，可以提供离子束流作为一种“定向能武器”，做为太空中的中近程防御武器（如果全部采用反物质离子构成的此“离子束武器”则更理想）；也可以构造出类似地球大气层内的某些“球形闪电”的“压缩等离子体球”，其内含有较强的感生电流击中目标后可如同普通炸弹一样爆炸，可做为一种远程武器（如果全部采用反物质离子构成的此“球形闪电”则更理想）；另外，“等离子体环流”在加速过程中产生的“同步辐射和回旋辐射”会产生“X射线激光”，如果在加速的磁流体中注入“反物质离子”而发生“正反物质湮灭”后将会产生更加高能量、高侵彻力的“伽玛射线激光”，其在太空中有更大的远程杀伤力。
2.2 The tokamak-devices will be combined with the toroidal synchrotron,then it will become an ideal ion electric thruster in the spacefighter,in spite of the more higher energy losses than the long-range cylinder-shaped spacetransporter which use a linear accelerator as its thruster when accelerating the ion-flows,but it is best suitable for the middle/short-range saucer-shaped spacecraft.In the first place,the particles of the ionizable substances will be ioned and accelerated preliminarily by a lots of simple hall effect thrusters at the center of the circular ring,and then this ion will be guided by the linear accelerator into the toroidal container of the the toroidal synchrotron combined with the tokamak-devices,inside it,the ion-flows will be cotained,and compressed,and reaccelerated.There is a strong induced-electric-current in the plasma-circumfluence,so it will keep on pinching,and it will be maintained in the toroidal container which is circling round in a high speed for a long time, before it will be guided and spouted out by the magnetic-field of the thrust-vector nozzle.If the plasma-circumfluence maintained in the toroidal container will not be spouted out,it will be decelerate ,and absorbed, and recycled,that to reduce the wastes of the propelling medium an the energy.When this plasma-circumfluence has being accelerated to close to the speed of light,it will provide an ion beam as a kind of directed energy weapon，it is a kind of middle/short-range weapon of defence(It will be optimal if it use all the ion of antimatter as the ion beam weapon.).We will construct a kind of compressing plasma ball which like some ball lightning in the earth's atmosphere,that it will be shotted out to attack the military target and will be automatically explosive as a bomb or shell,because it contains a strong induced-electric-current,it is a kind of long-range weapon(It will be optimal if it use all the ion of antimatter as the ball lightning.).In addition,this plasma-circumfluence will create the X-ray laser coming from the synchrotron radiation or the cyclotron radiation when it is being accelerate.And if we spout the ion of antimatter in it,it will create the more powerful and penetrable γ–ray laser coming from the antimatter/matter reaction,which will be a more stronger long-range weapon.

Fig.3

太空3

2.3 现有的战斗机设计中几乎都是使用两台主要发动机，这是一种基本准则，有很多原因，包括力矩的平衡、安全性和耐损性的保证、推力和加速性的要求等等，在飞碟上也一样有两台主要发动机，是呈水平放置的环形的离子推进发动机，在总体上看是圆盘形状，两台相互叠加布置于机体中部的“中心转轴”周围，机体上方顶部和下方底部都有围绕着中心转轴的环形的“吸气口”，而大量的“推力矢量喷口”环绕着圆盘形的发动机的圆周外缘且相互不受影响，发动机的推力轴线也很容易经过机体的质量重心，而上下两台发动机内的加速等离子体环流的旋转方向相反，则得到的反向扭矩也相反而获得平衡，所以是最理想的发动机与机体的配合形式。发动机所含的三种加速器的构造及布置也很有规律和合理性高，各构件完全电器化而可靠性高、不容易损坏也易检易修。当飞碟的发动机工作时，会出现两种情况，一种是高速瞬间爆发时以获得高加速力，则上下两台发动机喷射的大质量大速度的喷射流体在机体后方呈“燕尾形”尾喷流，另一种是较低速的持续平飞时，其喷射流体是小质量小速度而呈“棒状或带状”尾喷流。
2.3 It is almost a general principle to fit two major engines in the fighter plane.There are plenty of causes which include the equilibrium of torque,the guarantee of security and vulnerability resistant,the request of thrust and andacceleration.Then the saucer-shaped spacecraft will also be fitted two major ion electric thruster which will be positioned horizontally,and seen as a whole,they look like two piece of discs.This two piece of discs(ion electric thruster) will overlap with each other and lay around the rotating shaft in the center.There are air entries both on the top and the bottom of the airframe which will appear as a ring-shape.There are a plenty of the thrust-vector nozzles wounding round the circumferential edge of the ion electric thruster,which will not affect each other.The thrust-axis of the engine will cut through the center of mass in the airframe.The direction of the accelerated plasma circumfluence in the engine will be opposite,then the two reverse torques will also be opposite that will achieve an equilibrium,so the form of fitting between the engine and the airframe is optimal.The three varieties of ion accelerator in the engine have a good regularity and rationality in fitting and structure,the construction members have been completely electrified,so that it has a high reliability and firmness, and easy to overhaul.When the two engines of the saucer-shaped spacecraft are working,it will appear two kinds of wakes,one will like the swallow-tail when it want to achieve a high acceleration after sprouting out the large mass and great speed of ion-flows,and the other will like the rod/band when it want to achieve a constant low speed after sprouting out the small mass and low speed of ion-flows.

Fig.4

太空4

2.4 太空战斗机最大的问题是“能源问题”，毫无疑问，只有最高效的“反物质核能”才是太空战斗机能源的唯一选择。我们在此是把“反物质”材料理想化，假设人类文明已经进入太空时代，核聚变技术和机器人及人工智能技术高度成熟，在太空中能广泛产生和利用聚变能和太阳光能（甚至能开采太阳上的氢和氦的同位素），而机器人及人工智能也广泛应用于太空开发的工作中，则人类的生产力将上亿倍的提高，则一定量的生产“反物质”将不再是一个梦想，那么，我们进一步不妨把“反氢物质”在低温高压下形成“超导体金属态反氢”（“金属氢”是一种超导体），则可以用“真空磁场陷阱”将其容纳和保存。飞碟战斗机在太空飞行作战中把推进介质用完之时，将来还可以用“正反物质湮灭”的伽马射线在一种特别坚固的“爆炸反应室”中形成“光压”(爆炸反应室要能够抵抗伽马射线的穿透作用），即反射电磁波得到“光压推动”或“光子推进发动机”，当然也可以让正反物质湮灭产生的能量和吸入的太空空间粒子或垃圾粒子混合后，从飞碟的中心转轴下部的大型喷口向下喷射高速介质而得到更大更高效的推力，
    如果吸附得到的宇宙尘埃或气体分子或离子流较少，也可以直接把“正反物质湮灭反应”后产生的“介子流”在磁场的约束下从底部喷口喷射出去得到推力。
    其中有一种全新设计的“环管形超导电磁悬浮式反物质贮存装置”，特别适合于在低温的真空容器内贮存大质量的超导体物质，能承受各个方向的高加速度而不让容器内贮存的反物质（当处于超导状态）与器壁碰撞。
2.4 The most important thing of the spacefighter flying in the space is the energy source. There will be no doubt that the only selection of the spacefighter will come from the antimatter/matter reaction. In this place,we will idealize the substance of antimatter. Suppose the civilization of human being have entered the space age, the technologies about the nuclear fusion and the robot and the artificial intelligence have been highly matured, the energies of the sunlight and the nuclear fusion will be widely created and used(Even the hydrogen isotope and helium isotope will be exploited.), the robot and the artificial intelligence technology will be used in exploiting the space, then the future productive forces of human being will be as several hundreds million times as that of nowadays, then it will not be an imagine to product a certain amount of the substance of antimatter. If we will make further efforts to turn the anti-hydrogen to metallized superconductor under the low temperature and high pressure conditions(The metallized hydrogen is a superconductor.), then we will have the metallized anti-hydrogen be contained and preserved in a vacuum magnetic trap. When the thrust media of the saucer-shaped spacecraft have been used up, we will achieve the light pressure in a special explosion chamber coming from the γ-rays of the antimatter/matter reaction(This special explosion chamber will resist the penetration of the γ-rays.), and it become a photon propulsion. We might as well mix the γ-rays with the space particles or the space trash to spout out from the great nozzle on the bottom of airframe, and this will achieve a higher thrust and efficiency;  
    If the adsorbed cosmic-dusts or gas-molecule or ion-flows are relatively few, it will sprayed directly the "meson-flow" out of the bottom spout to obtain thrusts that under the constraint of magnetic field.
    Among them there is a kind of ring-tubular storage-box of superconducting magnetic levitation, which will specially preserve a large mass of superconducting material, and it will sustain a great acceleration in every direction and not to touch the superconducting antimatter with the wall of this storage-box.

Fig.5

太空5

2.5 作为真正的太空战斗机，飞碟不但要在太空真空环境中对抗各种高能射线的集中爆发，特别是对抗伽玛射线激光和离子束武器等“定向能武器”的打击，更要在太阳的大气层中飞行战斗，太阳的大气层是时刻有高温的等离子体流和强磁场的相互作用的爆发现象（“太阳风暴”），所以在飞碟的机体表面要进行高效的冷却或隔热。而推论的最后，出现了把具有一定旋转速度的、内含感生电流进行压缩的“等离子体环流”（光环）产生之后被释放出机体表面，并从圆心向边缘扩张成密集的多圈套环的流体结构方式。但是首先要在飞碟的顶部和底部各设置一个“开放式等离子体环流发生器”，这个发生器有点类似“核聚变托卡马克装置”，能够产生同样的“等离子体环流”，但是这个等离子体环流的温度不算高，也不要求产生核聚变反应，还会有一定的旋转速度，当然也有强大的感生电流和磁场，让其保持箍缩，而最不同之处在于此发生器可以把其内的等离子体环流释放出外面来。此开放式等离子体环流发生器在最初是全封闭式的，当把有一定速度的离子流注入此发生器的环形容器中时，容器内外的电场和磁场把离子流箍缩起成一个流动的压缩等离子体环，接着环形容器的管壁的外缘在稳定减弱的磁场下打开，让容器内的等离子体环流在离心力作用和稳定减弱的磁场约束下一个接一个地自由扩张和释放出去,但是此光环在机体表面仍然被一个均匀的“机体表面固定磁场”所约束，并在圆盘外边缘处自动破裂。
2.5 The saucer-shaped spacecraft will have to resist the concentrated bursts of all sorts of high power rays/ions when flying in the space,especially resist the attack of the directed energy weapon such as the laser of γ-rays and the ion beam weapon.And it will have to fly in the atmosphere of the sun which always create a plenty of strong solar storms that generally consist of the high temperature plasma-flows and the strong magnetic-fields intertwining each other which will burst finally,so it will need to make a cooling and insulate the heats on the surface of the airframe.In the end of the inference,we present a structure of taking the plasma-circumfluence(a ring of light) containing the strong induced-electric-current out to the surface of the airfame,and this plasma-circumfluence(a ring of light) will be expanded from the center to the periphery which is a multi-ring structure.First of all,we will fit an openable plasma-circumfluence generator in the top and bottom of the saucer-shaped spacecraft,which is same as the tokamak-device, and will creat the same kind of plasma-circumfluence.But this kind of plasma-circumfluence has not too high temperature,and is not required to produce a nuclear fusion reaction,and it will also have a certain speed and a strong induced-electric-current/magnetic ,that will keep pinching it.The most difference between them is that the plasma-circumfluence will be release out of the generator.This openable plasma-circumfluence generator will be close at the beginning,then we will spout a certain speed of plasma-flows in the toroidal container of this generator,the electric-field and the magnetic-field of this generator will pinch the plasma-flows into a compressed plasma-circumfluence(a ring of light),and then the outer margin of the wall of this generator will open which is under a reducing magnetic-field,and be freely released outward the plasma-circumfluence under the actions of the centrifugal force and a reducing magnetic-field one after another.But this plasma-circumfluence(a ring of light) will also be steadily constrained by a symmetrical fixed-magnetic-field of the airframe's surface,till it be broken by self at the outer margin of airframe.

Fig.6

太空6

2.6 此“等离子体环流”（光环）被释放出来并被挤压着稳定的向外扩张，且在机体表面磁场的约束中与表面蒙皮相隔离，甚至可以在机体蒙皮表面与释放出的等离子体环流之间形成的“附面层”内充入“低温液氮/氦”进行冷却，而等离子体环流本身不但具有的一定旋转流动速度及高温、还有最大强度的感生电流和磁场等，含有较大的可爆炸能量，远比一般的“球形闪电”的威力大，使之成为一种“磁流体装甲”，当碰上较小的物体陨石或弹片时可以产生爆炸和剪切作用，而类似于一种坦克上采用的“爆炸反应式装甲”，也更像是一种“电磁装甲”，但是其更主要用于在太阳上飞行时可对抗强大的太阳风暴形成的各种高速射流和磁场爆炸（“磁重联过程”），并且可以阻隔太阳表面的高温高热强辐射！而这些机体表面的“等离子体环流”（光环）在机体表面仍然被一个均匀的“机体表面固定磁场”所约束，并在圆盘外边缘处自动破裂，破裂后的离子流才会更好的受到“机体表面固定磁场”的约束而向圆心内挤压流动而形成一个“平面涡旋”，并可以被重新吸附后再利用。其实飞碟作为太空战斗机，要对抗的攻击种类很多，包括“陨石或垃圾”、“穿甲或破甲弹”、“中子核弹或太空雷”、“带电离子束武器”、“中性粒子束武器”、“伽马射线激光武器”，还有最大威力的“碟形反物质导弹或无人机”等等。所以飞碟作为太空战斗机还要求有更多种类的和更强大的装甲，其中我们还在机体表面使用了用通电的超导螺线管构成的“固定磁棒束”作为另一种类的电池和装甲，因为通电的超导体导线本身可以对入侵的物体用电流加热和磁场力扰动产生爆炸和剪切作用，所以在机体表面蒙皮下紧密布置的“固定磁棒束”也是一种“电磁装甲”。当然飞碟还会有通常意义上的“复合装甲”等，也还会有别的装甲和更多的主动式防御手段。
2.6 This plasma-circumfluence(a ring of light) will be released and squeezed outward,and will be separated from the skin of the airframe under the constrain of the symmetrical magnetic-field of the airframe's surface.And we will even spout the liquid nitrogen/helium to cool the boundary layer between the plasma-circumfluence and the skin of the airframe.This plasma-circumfluence will have not only a certain flow-speed but also the strongest induced-electric-current/magnitic，so it has a more stronger explosible energy than the ball lightning,then make it become a magnetofluid armor,which will be a new kind of armor.When this plasma-circumfluence(a ring of light) is colliding with the small meteorolite or shrapnel,it will produce an exploding and shearing action.And this action of the plasma-circumfluence(a ring of light) is same as the explosive reactive armor (ERA) of the tank，which is more like a new kind of electromagnetic armor.But it will be used to resist all kinds of the high-speed ion beam and the magnetic blast(the magnetic reconnection) of the solar storm,and it will insulate the airframe from the high heats and strong radiations.This plasma-circumfluence(a ring of light) will also be steadily constrained by a symmetrical fixed-magnetic-field of the airframe's surface,till it be broken by self at the outer margin of airframe.The broken plasma-circumfluence will be constrained more steadily by a symmetrical fixed-magnetic-field of the airframe's surface,and then flows towards the centre of a circle,which will become a planar vortex whose substances will be reused again.In fact,the saucer-shaped spacecraft will have to resist too many kinds of attack which including the meteorolite/space trash, armor piercing shell/high explosive antitank projectile,neutron bomb/space mine,ion beam weapon,particle beam weapon,gamma-ray laser weapon,and the most powerful saucer-shaped antimatter missile/unmanned aerial vehicle.So the saucer-shaped spacecraft will have to fit more kinds of and stronger armors.We will also use the fixed-magnetic rod beams made up of the electrified superconducting-solenoids which are fitted under the surface of the airframe as another kind of batterie and the armor.Beacause the electrified superconducting-wires will produce an exploding and shearing action with the electric heating and the magnetic-field fluctuations when it colliding with the small intruder,so the fixed-magnetic rod beams fitted under the surface of the airframe is also another kind of electromagnetic armor.Of course the saucer-shaped spacecraft also has the usual kind of composite armor,the other kind of armor and active defence technology.

Fig.7

太空7

2.7 如果太空战斗机采用了“反物质核能”为主要能源，那么还要将核能转化为电能才行，并且在飞行器的日常运行中机体内还要保持有大容量高密度的储电电池。另外，在空无一物的宇宙深空中（而不是各大行星附近）战斗飞行，其发动机的推进介质也有限。尽管我们不能确定飞碟上会采用多少种储电电池，但是有一种电池一定是客观存在的，即是飞碟机体内部大量的通电超导螺线管组成的“超导电池”。如在飞碟机体表面蒙皮下紧密布置的“固定磁棒束”不但是一种“电磁装甲”，而且也是一种“超导电池”，为了让机体表面的“固定磁场”的分布更加均匀而且超导螺线管的长度更长，这些“固定磁棒束”不应该是“直线式”布置，而应该是按照“阿基米德螺线式”布置。这样，当飞碟发动机的推进介质缺乏时，“阿基米德螺线式布置的超导体通电螺线管”也可以变形伸展开来并伸出机体，呈“倒锥形”分布，因为螺线管内含有一股强大电流而可形成一个“磁场漏斗”，可以将其高速旋转着，将太阳附近的电离流体、以及气态行星的大气层顶端的气体分子、甚至是宇宙尘埃等等经电离后（用喷射高速电子束或高能激光的方式去电离）吸附进来做为发动机的推进介质,和“正反物质湮灭反应”的“正物质”一方（如果吸附得到的宇宙尘埃或气体分子或离子流较少，也可以直接把“正反物质湮灭反应”后产生的“介子流”在磁场的约束下从底部喷口喷射出去得到推力）。
    而飞碟底部的大型喷口可以把“正反物质湮灭”后的辐射能量与推进介质相互混合而经加热加压后喷射出去得到推力，或者在大气层内飞行战斗时也可以用此辐射能量混合吸入的气体而经加热加压后喷射出去得到向下的推力以补偿气动升力。这方面的推力技术对太空战斗机的生存也很重要。
    出于效率、节能、安全和机动的需要，飞碟在太阳系内飞行的最大速度一般不超过百分之十光速（甚至可能的巡航速度只是百分之一光速），而更多时候是用太阳或主要气态行星的大气层或电离层来进行飞行的减速或停止等，而在太阳系的整个黄道面内都可以分布有“太空加油站及停泊港”，其可以使用“纳米微粒或气凝胶式磁流体的减速轨道”等把飞碟进行安全阻拦减速和停止。
2.7 If the spacefighter use the antimatter nuclear energy as the major energy, we will need to convert the nuclear energy into the electricity,and we have to maintain the high-capacity and high-density batteries. In addition,when we are flying and fighting in deep space with nothing(but not in the near of the major planets),the thrust medium of the thruster will be  very limited. Althought we will not confirm how many varieties of the batteries will possess the saucer-shaped spacecraft, but one kind of battery will be fitted in it. Namely it is the plenty of the electrified superconducting solenoids fitted in the airframe, which may be acted as a kind of superconducting magnetic energy-storage-system/battery. Such as the fixed-magnetic rod beams fitted under the surface of the airframe is not only a kind of electromagnetic armor, but also a kind of superconducting magnetic energy-storage-system/battery. For the sake of making the fixed-magnetic-field become more symmetrical and the superconducting solenoids become more long, this fixed-magnetic rod beams will be fitted in a form of archimedes spiral, instead of a form of straight line. When the thrust-media's quantities of the saucer-shaped spacecraft are small, this form of archimedes-spiral's electrified superconducting solenoids will be stretched out the airframe which will become a form of funnel. Beacause this solenoids have a stream of strong electric in it, so it become a magnetic funnel. When this magnetic funnel will be twirled with a hign speed, it will adsorb the ion-flows near the sun, or the gas-molecules on the atmosphere's top of the major planets, or the ionized cosmic-dusts in space (that we will use the high energy laser or spout out the high speed's electron beam to get the ionization.), and use them as the thrust medium of the thruster,
    or as the "positive-matter" side of "positive and antimatter annihilation-reactions"(if the adsorbed cosmic-dusts or gas-molecule or ion-flows are relatively few, it will sprayed directly the "meson-flow" out of the bottom spout to obtain thrusts that under the constraint of magnetic field.).
    The great bottom spout of the saucer-shaped spacecraft will mix the radiant energy of the antimatter/matter reaction with the thrust medium and spout out after heating and pressing to get the thrust, or will mix the radiant energy of the antimatter/matter reaction with the absorbed the gas when flying in the atmosphere and spout out after heating and pressing to get the downward thrust. This aspect of the thrust technology will be very important for the survival of the spacecraft.
    For the efficiency, safety,energy saving and maneuverability purposes, the highest speed of the saucer-shaped spacecraft flying in the solar system will be no morn than ten percent of the speed of light(even its cruising speed will be about one percent of the speed of light). And it will achieve the eceleration or stopping of flight useing the atmosphere and the ionosphere of the sun or the gaseous planets. And there will be a lot of space filling-stations/harbors in the ecliptic plane of the solar system, that it will achieve the deceleration or stopping of flight using a kind of nanometre-particles/aerogel structural magnetic-fluid's decelerating-orbit in safety.

Fig.8

太空8

2.8 现有的核能转化为电能的设备相当庞大复杂笨重,比如核裂变的高温气冷核反应堆，不适合装备在轻小型的太空战斗机上，只适合装备在大型的太空母舰上，或装备于注重能源效率和经济性的大型远程行星际客/货运飞船上。那么，飞碟上的“正反物质反应”产生的能量要更高效更简便地转化为电能，还是离不开“光伏效应发电”、“热电效应发电”、“霍尔效应发电”（“磁流体发电”）和“冲压空气涡轮发电”等原理；其中要解决“反物质核能”的三大问题中的两个，即实现“大质量高密度的反物质的安全储存问题、和湮灭反应产生的高能伽马射线在人工控制下的定向发射及安全吸收转化问题”，但这里未涉及反物质的大规模制造问题。
    第一个问题在前面已经描述过了，将用“环管式反物质储箱Loop-tubular storage-box of superconducting magnetic-levitation about antimatter”中的超导体强磁场，来约束在超低温真空环管内的“超导态的反物质金属氢（可以同时储存着大电流）”（超导态反物质环Superconducting antimatter-loop）；而第二个问题将在此发电装置中解决，是让“正反物质湮灭反应”产生的近光速的“介子流”，在类似“同步加速器辐射装置”的强磁场中被约束和加速，产生并最后全部转化为伽马射线，此伽马射线以“同步辐射”的原理有极强的方向性或准直性，可以全部冲击着“涡轮发电机中的涡轮叶片和周围的各种发电装置的高密度抗辐射吸收物质层”，是由一个三维方向的伽马射线辐射被约束限制转变为二维方向的辐射，从而更高效的发电并防止高强度的伽马射线的全方向的辐射破坏。
    也许其上的紧凑型发电装置(光伏/磁流体/冲压空气涡轮的发电系统)未来的发电效率仍然可以超过百分之五十，这将需要我们长期的探索过程。
2.8 The present equipments converting nuclear power into electric power are always too huge and too heavy, so it will not be suitable for fitting in the future miniature spacecraft, and will only be suitable for fitting in the future large-size spacecraft carrier, or will also be suitable for fitting in the future interstellar passenger/cargo spacecraft which emphasizing the energy efficiency and economical efficiency. Then the energy of the antimatter/matter reaction in the saucer-shaped spacecraft intend to be converted into electric power efficiently and expediently, that it will not do without the photoelectric effect electricity generation， thermoelectric effect electricity generation,hall effect electricity generation(magnetohydrodynamic electricity generation), and ram air turbine electricity generation； Among them, we want to solve the two problems of the three major problems about the antimatter-energy; Namely to realize the problem of storaging safely the large-mass and high-density antimatter, and the problem of emiting directionally and absorbing/converting safely the high-energy gamma-rays under manual-control; But here we will not involved the problem of the large-scale-manufacturing-technology of the antimatter.
    The first problem has been described earlier, we will confined the Superconducting-antimatter-metal-hydrogen(which will store large currents at the same time.) in the ultralow-temperature vacuum-loop-tubular by strong superconductor-magnetic-fields of the Loop-tubular storage-box of superconducting magnetic-levitation about antimatter; And the second problem will be solved in this power generator, namely the near-light-speed's meson-flows generated by the "positive and antimatter annihilation-reactions", which will been constrained and accelerated in a strong magnetic-fields similar to the Synchrotron-Radiation-Device, and them will generate and eventually convert all of themselfs into the gamma-rays, and these  gamma-rays with the principle of "synchrotron radiation" has strong directivity or collimation, which will all impact on the "high-density radiation-resistant absorbing-material-layer of various power-generation-devices around them and the turbine-blades in turbogenerators", and that it will convert the gamma-rays-radiation from three-dimensional direction to two-dimensional direction through constraint and acceleration of the magnetic-fields, so to get more efficient generation and prevent all-directional radiation-damage of high-intensity gamma-rays.  
    Perhaps the future efficiency of the compact-size energy conversion system will still reach more than fifty percent, but there will be a long time process to be explored.

地球全力

3 未来太空战斗机（碟形飞行器）在太阳和各大行星的大气层内飞行作战的升力原理
3 The lift principle of the future spacefighter(the saucer-shaped spacecraft) which will be flying in the atmospheres of sun and all the planets in our solar system.

Fig.1

升力1

3.1 碟形飞行器作为一种在太阳系内的未来太空战斗机，其主要任务是在最冰冷最强大的“气液固三相流体风暴”的木星、土星、天王星、海王星等气态行星上飞行和战斗（随着未来对气态行星资源的争夺），还要在最高温最狂暴的“电磁等离子体风暴”及可怕引力的伟大太阳上面去飞行和战斗（随着未来对太阳资源的争夺）。即碟形飞行器必须在太阳和各大行星的大气层内飞行，如果物理学能坚决拒绝“反重力反引力反质量”，则碟形飞行器必须依靠空气动力学来飞行（特别是通过“空气动力学升力”来对抗星球的引力，以及得到高过载或向心力矩等）。但在空气动力学中，“涡旋”（具有涡量或环量）是机翼绕流的重要现象，正是依靠“涡旋”才使低速机翼获得主要的“升力”；那么碟形飞行器在低速飞行或中低空悬停时，其上用以产生主要“气动升力”的“涡旋”，也必须要和这些无比强大的行星级风暴和恒星级风暴的强大程度和控制性同等级才行。而这些强大的风暴或巨型涡旋，在物理方面也都有一些相似的基本特征。比如，地球上的台风/飓风，在其中心处都有一个管状的“粘性涡核”，是由管状的侧壁气流柱组成，是由于外部周围四面八方的低速来流向中心挤压，流体由于角动量守恒定律而加速，和机械能守恒定律的伯努利原理而减低气压（流体的动压增加而静压减少）到最大，高速的流体沿圆周旋转就有一个“向心力的反作用力”（“离心力”）而形成了一个管状的“涡核”（是“涡量”最密集的区域），并且，其内圆柱状的空腔是一个“中心无风低压区”，这是由于其侧壁的高速旋转的圆管形的气流柱的“粘性”，大量“吸附（剪切、诱导、扰动、渗混）了中心的空气进入侧壁流体而造成了低气压，出现“中心低压区”，以及在台风/飓风的上部利用流体的“粘性”把“涡核的涡量”在上部向外传递耗散时形成的有序流动流体（同时，如果没有流体的“粘性”也不会得到低速机翼上表面的主要的“低静压区或气动升力”）。
3.1 As a kind of future spacefighter which will be flying in our solar system,the major task of the saucer-shaped spacecraft will be flying and fighting on the gas giants of Jupiter,Saturn,Uranus,and Naptune which always have the iciest and mightiest of three-phase fluids(gas,liquid and solid) storm (when we will be able to compete for resources on the gas giants),and on the sun which always have the hottest and fiercest of electromagnetic-plasma-storm(solar-storm) and tremendous gravity(when we will be able to compete for resources on the sun).Then it will have to be flying in the atmospheres of sun and all the planets.If the physics will firmly reject the theories about anti-gravity and anti-mass,the saucer-shaped spacecraft's flight will have to rely on the Aerodynamics(especially use the lift-force to against the gravity of planet or star, and obtain the high overload and concentric-torque). In the Aerodynamics，the vortex（possessing the vorticity or circulation） is an important phenomenon in the flow field around the low-speed airfoils and wings,and the low-speed airfoils and wings will obtain the lift-force which is precisely relyed on the vortex.So when the saucer-shaped spacecraft will be flying at low speed or hovering in mid and low level,the vortex that generating the lift-force on it will have to be the same grade of the intensity and controllability as the planetary-storm and solar-storm. These strong storms and great vortexes always have some similarly fundamental character in physics.For instance,the hurricane/typhoon always have a tubular "viscous-vortex-core" that consisted of a large amount of tubular side-wall-fluids,which is due to the circular low-speed inflow squeeze each other towards the center.Then the low-speed inflow will be accelerated owing to the law of conservation of angular momentum,and the air-pressure will be lowered to the maximum extent according to Bernoulli equation under the law of conservation of mechanical energy (when the dynamic-pressure will be rised then the static-pressure will be lowered at the same time).The high-speed fluids will rotate along the circumference and obtain a reaction-force of centripetal-force (centrifugal-force),then form a tubular "viscous-vortex-core" (which is the greatest concentrations of the vorticity).And the cylindrical cystic-spaces is a calm low-pressure central-area.Because the viscosity of the tubular high-speed-rotating side-wall-fluids will be absorbing (shearing or inducing) a large quantity of the cystic-spaces airs to cause the low-air-pressure,and forming the calm low-pressure central-area.And the viscosity of the fluids will deliver and dissipate the vorticity of vortex-core towards outside in the upper hurricane/typhoon to form an orderly-flow-fluids.(In the same time,if there is not the vorticity of fluids,the low-speed airfoils and wings will not obtain the low-static-pressure-area or aerodynamic-lift.)

Fig.2

升力2

3.2 一般认为，流体中的宏观“涡旋”只能以两种形态体系存在(即“自然界两大类涡旋”)：一种形态体系的“涡旋”在其两端终止于壁面（“二维的旋涡”），就像水里的漩涡，终止于水面或水底，以及正像上述的台风/飓风，终止于海面及对流层顶部。另一种形态体系的“涡旋”围成一个封闭的“涡环”（“三维的涡环”），比如空中的烟圈和蒲公英种子上的“环形分离涡或分离涡环”。其中，蒲公英种子上方的流体形成的是一个“环形分离涡”，内含一个比较稳定的“涡核”，其整个“涡环”可以在比较宽的风速范围内稳定存在，为蒲公英种子提供“升力”（明显优于军用降落伞），并且气动效率高，节约材料，流动稳定性高，对风向突变的适应性好，其作为一种产生“升力”的“涡环”的飞行机理一经公开就已被广泛的猜想可能为“飞碟之谜”的“升力相关的涡旋或升力涡”。另外，空中的烟圈的“涡环”一旦在空中成型，则其内“涡核”的旋转流体因为有“粘性”而把“涡量”持续向外传递耗散，直到“涡核”消失，整个“涡环”接着溃散，空中的烟圈的稳定性较差，容易受风扰动变形。但上述两种“涡环”结构上类似，都有一个“涡核”（是“涡量”最密集的区域）。差别只是，蒲公英种子上的“涡环”是一种附着在物体表面的“分离涡”，而空中的烟圈的“涡环”是一种脱离开物体表面的“脱体涡”。
3.2 It is generally recognized that the macroscopic-vortex in the fluids will only exist in two forms（namely natural two-broad-categories of vortexes.）.And the first kind of macroscopic-vortex will be terminated in both ends (two-dimensional vortex),just like an eddy in the water which will be terminated in the surface or bottom of the water,or like the hurricane/typhoon which will be terminated in the surface of the ocean or the top of the troposphere.Then the second kind of macroscopic-vortex will enclose a vortex-ring (three-dimensional vortex),just like a smoke-ring in the air and the separated-vortex-ring (the annular-separation-vortex) above the dandelion seeds.Among them,the fluids above the dandelion seeds will form a annular-separation-vortex,which contains a single relative stable vortex-core,that will exist in a wide speed-range of wind,and generate a stable aerodynamic-lift (that is obviously better than that of the service parachute).It is inferred that it has advantages of high aerodynamic-efficiency,flow-stability,wind-direction-mutation adaptability and saving materials.It is speculated that its flight mechanism generating aerodynamic-lift using the vortex-ring could be the vortex-about-lift (the lift-vortex) of the mystery of flying saucers.In addition,once the vortex-ring of the smoke-ring in the air will be generated,the viscosity of the rotating fluids in the vortex-core will deliver and dissipate the vorticity of vortex-core towards outside.Until the vortex-core disappear,the vortex-ring or smoke-ring will collapse.The flow-stability of the smoke-ring in the air is often low,and easy to deform under the wind disturbance.But both the above-mentioned vortex-ring have the similar structure,and have a vortex-core which is the greatest concentrations of the vorticity.The difference is that the vortex-ring above the dandelion seeds is a kind of attached-vortex attaching to the outer surface of body,and the vortex-ring of the smoke-ring in the air is a kind of detached-vortex detaching to the outer surface of body.

Fig.3

升力3

3.3 昆虫翅膀也是利用“涡旋”产生高效率的“气动升力”。其翅膀向前下方拍动时其前缘形成了一种“前缘分离涡”，是一种“螺线管型涡旋”，在小尺寸小速度的空气运动中的流体的“粘性”比通常强得多，当然这个“前缘分离涡”也形成一个“涡核”。“涡核”的流体高速旋转流动的“向心力的反作用力”（“离心力”）和“粘性”形成了涡核内的空气分子的低密度低压区，也诱导出一个从翼尖到翼根的高速的“附着流”，两者因符合机械能守恒定律的伯努利原理其动压增大则静压减小，两者合成的低压区就是翅膀上表面的主要升力区。不过，昆虫翅膀上的这种分离涡到了后部想要离开边缘也有“下洗趋势”，初看来这个分离涡的“下洗趋势”仍然保持着强烈的旋转，这将会有高阻力和低效率，但实际观察出此时翼尖形成的“脱体涡”（也叫“尾涡”）的尾端已经接续起了前缘分离涡的尾端（两个涡旋的旋转轴相连接且流体的旋转方向一致），这类似于飞机机翼后缘的一种“起动涡”，所以两者的接续形成了一个典型的“涡环”，也符合一种经典机翼的“涡环”结构的等效气动模型。那么，昆虫翅膀向后上方返回拍动时，通过一种所谓的“尾涡捕获”机理，让“尾涡”中的能量得到重复利用，最终形成一个消除了“尾涡”流体的旋转性质后的单一直线的斜下方向的“下洗流”。在此推测为由昆虫翅膀的上表面在向后上方返回拍动时在横向上去阻断“尾涡”，“尾涡”的流体在昆虫的“网状翅脉reticulate vein”之间因受高压而形成的一种类似“伞状凹陷”的结构中被阻断和冲压并反射喷出，从而得到高压喷射流（特别是有时候当两个翅膀在后上方合拢相拍，形成了类似“发动机燃烧室和收敛喷管”的形状，从而压缩流体后再喷出一种向后的纵向射流，这与与鱼类的尾鳍利用“反向的Karman涡街”得到推进射流的情况有一定的相似性），这是一种高推力，也造成了某些情况下翅膀后拍时得到了更高的升力或向前加速的现象。所以这就造成了现实中昆虫翅膀的高升力高加速和高效率。
3.3 The insect wings will also be using the vortex to obtain the aerodynamic-lift. It will be formed a leading-edge-vortex above the insect wings when it is flapping toward fore-downwards,which is a solenoidal-vortex.And the viscosity of the small-size and low-speed fluids in the air is much high than usual.Of cause,this leading-edge-vortex also have a viscous-vortex-core.The viscosity and reaction-force of centripetal-force(centrifugal-force) of the rotating fluids in the vortex-core will construct low density/pressure area in the vortex-core，then it will induce a attached-flow from wingtip to wing-root,both them meet the Bernoulli equation under the law of conservation of mechanical energy (when the dynamic-pressure will be rised then the static-pressure will be lowered at the same time),and together they forming a low density/pressure area will be the main aerodynamic-lift area above the insect-wings.This leading-edge-vortex of the insect wings will also have a downwash tendency when it will leave the trailing edge,but it seem to hold a high-speed rotation.It will has a poor efficiency and high resistance.But in fact,both the tail of the detached-vortex (wake-vortex) of the wingtip and the tail of the leading-edge-vortex have been connected when they are observed (together this two vortexes have a same axis/direction of rotation.),this is like the starting-vortex of the trailing edge of aircraft wing.So the connection of this two vortexes will form a typical separated-vortex-ring,which will meet an equivalent aerodynamic-model under a classical vortex-ring structure of aircraft wing.When the insect wings is flapping toward back-upwards,the energy of wake-vortex will be reused by a wake-vortex-capture mechanism.In the end,the rotating character of the wake-vortex have been eliminated,and there is a single straight downwash-flow inclined downward.And it has been infered that the wake-vortex has been blocked by the insect wings when flapping toward back-upwards,the fluids of wake-vortex under high-pressure has been blocked/punched/reflected and been ejected in the structure of umbrella-shaped-depression between the reticulate-vein of insect wings，so there is a single straight high-pressure jet (downwash-flow) inclined downward (especially when the insect wings are flapping toward back-upwards and closured(clap-fling mechanism),it will form a shape of engine-combustor/convergent-nozzle,and compress the fluids to spout a kind of backward longitudinal-jet,which is similar to the circumstance that the caudal-fin of fish obtain the propulsive jet using the reverse karman-vortex-street.).This is a kind of high thrust,and it will appear a circumstance which will generate a far higher lift-force or acceleration,when the insect wings are flapping toward back-upwards.So it has developed the reality that the insect wings always obtain a high efficiency,a high acceleration and a high lift-force.

Fig.4

升力4

3.4 大鸟的滑翔和低速飞机等也是利用“涡旋”产生气动升力的，和昆虫翅膀一样，也符合一种经典机翼的“涡环”结构的等效气动模型，这个抽象的机翼“涡环”可以看成由四部分组成，其中围绕机翼的部分的涡称之为“附着涡”，“附着涡”终止于翼稍，拖出两组“脱体脱”（尾涡或尾迹涡）他们与“起动涡”一起形成一组封闭的“涡环”。其中“附着涡”可以具体化为当机翼前缘在前方来流的冲压下因“上洗”作用而形成附着于机翼上部的曲率较大的凸面上的流体，“附着涡”的流体由角动量守恒定律而加速，和机械能守恒定律的伯努利原理而减低气压（流体的动压增加而静压减少），“附着涡”在机翼上表面的较平坦部分可诱导出较平直的“附着流”（其下与机翼表面蒙皮之间还有一个“附面层或边界层”的流体层），因为流体的“粘性”，而“吸附（剪切、诱导、扰动、渗混）”了机翼表面的“附面层”的空气分子一起流走，也“剪切”了机翼上方大量的来流成为“剪切流”向后下方流动，“附着涡”和“附着流”的降低的静压因而传导于“附面层”而形成机翼上表面的“低压区”，产生主要升力。“附着流”流向后下方，就有一个“下洗”的趋势，在机翼翼梢的“尾涡”的影响下可形成机翼后方的“下洗流”。根据动量定理和动量守恒，“升力”在此可以简单考虑成，一个等效于机翼动量的“附着涡”的“涡量”（“环量”），诱导出上方来流在垂直方向的“动量的变化量”。机翼的“总环量”等于上表面“附着涡”加上后上方“剪切流”的“总涡量”，与机翼的主要“升力”直接相关，而机翼蒙皮表面流体的“附面层”的流动形式和压强，也与机翼的“升力”最终相关。因为机翼上表面的“附着涡”和“附着流”要把低静压传导于附面层的流体才能得到机翼的低压区（主要升力），而如果附面层以“层流附面层”的形式流动则可以得到升力，但是如果附面层以“湍流附面层”的形式流动则静压提高了就失去了升力，当机翼的迎角超过了“失速迎角”时，机翼上表面的附面层就是全部成了“湍流附面层”，即飞机会因“失速”（失去升力）坠落。所以，低速机翼的流体方面主要研究的是“附着涡”（和“附着流”）和“附面层”。
3.4 The gliding of big bird and the low-speed aircraft also rely on the vortex that generating the lift-force to flight.It's the same with the insect wings,this will meet an equivalent aerodynamic-model under a classical vortex-ring structure of aircraft wing.This abstract vortex-ring of low-speed aircraft wings will consist of  four parts,among them the vortex around the wing's surface is usually called the attached-vortex which terminates in the wingtip,and it continue to drag behind two detached-vortex (wake-vortex or trailing-vortex),and they aroud a vortex-ring together with the starting-vortex. Among them,the attached-vortex will concrete into the fluids attaching above the convex surface with larger curvature when the leading-edge of wings are punched by the incoming-flow.The fluids of the attached-vortex will be accelerated as it meet the law of conservation of angular momentum,and the air-pressure will be lowered to the maximum extent according to Bernoulli equation under the law of conservation of mechanical energy (when the dynamic-pressure will be rised，then the static-pressure will be lowered at the same time).The attached-vortex will induce a relative straight attached-flow above the flat surface of wings (between this attached-flow and the surface-skin also has a boundary-layer.).Because the viscosity of the fluids will be absorbing (shearing or inducing) a large quantity of the air-molecules in the boundary-layer to flow away,and shearing the incoming-flow (become the shear-flow) above the wings to flow towards back-downwards.Then the low-air-pressure of the attached-vortex/attached-flow will be transmitted to the boundary-layer,and forming the low-pressure-area above the wings.The attached-flow will flow towards back-downwards,then have a downwash tendency,and it will form a downwash-flow behind the wings as the effect of the wingtip's wake-vortex.According to Momentum Theorem and Momentum Conservation，the lift-force will be recognized to be a vorticity(circulation) of the attached-vortex equivalent to wing's momentum,that induce a momentum change of the incoming-flow in the vertical direction.The total circulation of the wings equals the total vorticity coming from the upper-surface's attached-vortex plusing the rear shear-flow,that is tightly related to the main lift-force of wings.And the flow-pattern and dynamic-pressure/static-pressure of the boundary-layer above the wings is also related to obtaining the lift-force.Only the low-air-pressure of the attached-vortex/attached-flow will be transmitted to the boundary-layer,then the low-pressure-area (the main lift-force) above the wings will be formed.The wings will maintain the lift-force if the boundary-layer will be the laminar-boundary-layer,otherwise will lose the lift-force if be the turbulent-boundary-layer.When the wing's angle-of-attack will be larger than the stall-angle-of-attack,the boundary-layer of the upper-surface of the wings will be wholly the turbulent-boundary-layer,then the aircraft will crash due to stall (losing the lift-force).So the fluid-study about the low-speed airfoils and wings will always mainly relate to the attached-vortex(attached-flow) and the boundary-layer.

Fig.5

升力5

3.5 低超声速的飞机机翼很多是大后掠三角翼，有较大的后掠角和尖锐的前缘，而不像低速机翼那么平直和前缘钝圆，其在起飞和降落的需要高升力的低速时段中，可以采用较大的迎角而让机翼下部来流从前缘分离，并卷成一种“前缘分离涡”（“螺线管形涡旋”），此分离涡有一个“主要核涡”（甚至还有“第二涡旋”），当然三角翼前缘的这个分离涡“吸附（剪切、诱导、扰动、渗混）”了大量的周围气流并向后下方旋转流动（也同时诱导出机翼上表面的比较平直流动的“附着流”，此“附着流”流速高则动压高而静压降低可产生机翼上表面的主要升力），就有一个“下洗”的趋势，并可以与“翼尖脱体涡”相混合，但是无法让其最终“消除旋转性质”（比平直机翼形成的翼尖涡的流体旋转性要强得多），所以是浪费了更大的能量，此时因产生升力而引起的阻力（诱导阻力）明显更大（相较于低速的平直机翼）。此“前缘分离涡”的涡核流速很高则动压很高而静压很低，有助于提高机翼上表面的升力。而三角翼总升力等于附着流的升力和前缘分离涡的升力之和。
3.5 The wing of low-supersonic aircraft is mostly the high-sweepback-delta-wing,which has high angle-of-sweepback and sharp leading-edge.It is unlike the low-speed airfoil-and-wing which has usually straight-wing and blunt leading-edge.When it require high lift-force at the time of take-off and landing,it will adopt a high angle-of-attack to induce the incoming-flow separating from the sharp leading-edge and becoming the leading-edge-vortex (separated-vortex or solenoidal-vortex).This separated-vortex has always a primary-vortex-core (even has a secondary-vortex),and it will be absorbing (shearing or inducing) a large quantity of the air-molecules in the boundary-layer to flow away,and shearing the incoming-flow (become the shear-flow) above the wings to flow towards back-downwards.Then the low-air-pressure of the attached-vortex/attached-flow will be transmitted to the boundary-layer,and forming the low-pressure-area above the wings.The attached-flow will flow towards back-downwards,then have a downwash tendency,and it will form a downwash-flow behind the wing as the effect of the wingtip's wake-vortex.And this leading-edge-vortex will mix with the wingtip's wake-vortex behind the wing,but the fluid's rotating-characteristic will not be eliminated (the fluid's rotation will be more violent than that of the straight-wing-wingtip's wake-vortex.).So it will be consuming more energies than usual,then the aerodynamic-resistance (induced-drag) will be obviously larger than that of the straight-wing at the time of low-speed.The primary-vortex-core of this leading-edge-vortex will be flowing at high-speed,so the dynamic-pressure is high and the static-pressure is low that will contribute to generate a larger lift-force of the wing's upper-surface.Then the total lift-force of the high-sweepback-delta-wing will be equal the lift-force of the attached-flow plusing the lift-force of the leading-edge-vortex.

Fig.6

升力6

3.6 超声速甚至高超声速飞行的升力（包括阻力），其与宏观大尺寸的“涡旋”的关系越来越少，而越来越多是“激波”的世界（高空飞行因为空气密度低则激波后的压缩空气是高超声速飞机产生升力的主角，中低空因为空气密度高则“膨胀波”也是主角）。超声速和高超声速的机翼可以等效于一个很薄的平板（一定程度类似于“风筝”），飞行时有一个不大的迎角，来流流过有迎角的平板的前缘在上部形成“膨胀波”，超声速空气流经过膨胀波后得到加速和静压强降低，则上部形成“低压区”得到上表面的升力；而机翼的前缘在下部却是形成“激波”，超声速空气流经过激波后是减速的和静压强增加，激波后的空气分子密度和温度增加明显，则机翼下部形成“高压区”得到下表面的升力，特别是在高超声速的“乘波体”飞行器采用了“附体激波”,通过贴近下表面的“激波”来压缩空气产生所谓的“激波升力”或“压缩升力”。高超声速时的“激波”是被压缩成了一层很薄的高密度高温高压强的空气分子层。而飞行速度越高（高超声速）下部的“激波”越倾斜越接近表面，则会有一个机体下部的压力或升力的突然增大现象，主要是“激波”可以在贴近机体下表面时使飞行器得到高效率的升力（气动阻力只会随着飞行速度的提高而略微的提升），这相当于“飞行器乘着激波飞行”（乘波体）。同时高超声速前方来流经过“激波”后其大量的“动能”被消耗成“热能”，则“激波”就产生了总的飞行阻力的主要部分。另外，在机体下部的“激波”后的高密度高温高压强的附面层，也会由“层流”转化成“湍流”，而出现升力的异常、高脉动和传热异常现象。高超声速的“乘波体”飞行时就像是在一个“激波”之上滑翔，如同在水里的冲浪板的滑行，而如果是在大气层的高层与太空边缘，有导弹弹头或空天飞机可以一个波谷下降冲入大气层内,再以一个大迎角得到高升力，以一个波峰上升冲出大气层，的反复的“正弦波跳跃滑翔式飞行”（“sanger弹道”），就像旋转的扁圆的碟形石片在水面上不断“打水漂”，可以更有效更节能更高机动性。
3.6 The aerodynamic-lift and aerodynamic-resistance (air-resistance) under the supersonic and hypersonic flight will have less and less relation to the macroscopical vortex,but more and more relation to the shock-wave (the compressed-air behind the shock-wave will be the main-source of lift-force as the low-air-density when hypersonic-flighting on the upper-air,and the expansion-wave will also be the main-source of lift-force as the high-air-density when hypersonic-flighting on the upper-air when supersonic-flighting in mid/low-level-air.).The wing under the supersonic and hypersonic flight will be equal to a thin flat plate (which is similar to a kite.).This flat-plate-wing will have a modest angle-of-attack when flighting,and the incoming-flow flowing through its leading-edge will generate a expansion-wave above the wing,the supersonic air-fluids flowing through the expansion-wave will rise its dynamic-pressure and lower its static-pressure,then a low-pressure-area will be formed and the lift-force will be generated above the upper-surface of wing.But the flat-plate-wing will form a shock-wave above its leading-edge,the supersonic air-fluids flowing through the shock-wave will rise its static-pressure and lower its dynamic-pressure,the density and temperature of the air-molecule behind the shock-wave will rise obviously,then a high-pressure-area will be formed and the lift-force will be generated under the down-surface of wing.Especially the hypersonic-vehicle/waverider will adopt the attached-shock-wave which is a shock-wave attaching the down-surface of wing,and it will compress the air behind the shock-wav to generate the so-called shock-lift or compression-lift.The shock-wave under the hypersonic flight will be compressed into a very thin layer of high temperature/pressure/density air-molecule-layer.The shock-wave will be closer and closer to the down-surface of wing when the speed of the hypersonic-vehicle will be higher and higher,it will present a phenomenon that the pressure (lift-force) under the down-surface of wing (airframe) will suddenly rise,and it is due to the shock-wave will attach to the down-surface of wing (airframe) then generate a high efficient lift-force (but the air-resistance and the aerodynamic-resistance will have a slight rise along with the increase of flying-speed.),this is equal to taking a flight that riding on the attached-shock-wave.In the same time,the hypersonic incoming-flow will flow through the shock-wave,a large number of its energies will be consumed or converted into heat,then the shock-wave will generate the main aerodynamic-resistance and air-resistance.In addition,the high temperature/pressure/density boundary-layer behind the shock-wave will be converted from laminar-flow to turbulent-flow,then present the abnormality and the high pulsation of the lift-force and heat-transfer-rate.The flight of hypersonic-waverider will feel like to be as gliding over the shock-wave as skiing on the water with the ski,and if it will be flying on the upper-air or the edge-of-space,the missile warhead and the aerospace plane will be diving sharply down a Sine-wave-trough into the atmosphere,and then adopting a high angle-of-attack to get a high lift-force and rise again upon a Sine-wave-peak out of the atmosphere,which is an iterative process of Sine-wave-jumping/gliding flight (Sanger-trajectory),that will feel like to play ducks and drakes on the water with a rotating-oblate-dishing-flake,which will obtain a high maneuverability/efficiency/energy-saving.

Fig.7

升力7

3.7 现在航空或气动力控制领域中有很多的利用或主动流动控制和加强机翼上面“附着涡”的方法（“环量控制”）。在一个向上凸起的曲面吹气，气流会沿着圆弧面走一个大弯好像流体粘贴着弯曲表面一样，叫“射流附壁效应（康达效应）”（其实质也属于“涡旋”和其“粘性”的范畴）。利用价值在于当用高速喷气流在凸起曲面吹出这种“附着涡”时，高速流动的涡旋因为粘性可以吸附（剪切、诱导、扰动）更大质量的周围气流一起变向流动，（并可使机翼后缘的附面层增加动能和速度从而推迟分离），而产生“超环量”，当飞机有一定的速度之后其机翼的升力效率会比起用喷气发动机或涵道风扇直接向下喷气的升力效率明显要高（飞机速度越快则吹气的增升效率越高）。如果想要在垂直起飞降落的飞行器上使用吹气增升原理，又要像直升机的旋翼一样在圆周边360度范围产生各向同性的升力，则也有例子是把直升飞行器的升力面做成一个半球形。如图用涵道风扇/螺桨或离心式喷气机向凸起的翼面吹气提高喷气的升力效率，虽然其效率的提高也有限，其外形如同降落伞而提高了失去动力或失速坠落时的安全性，并在一定程度上降低垂直风切变的上升和下击气流影响其升力产生的能力，其最大的缺陷是，如此巨大的迎风面积让其水平前飞的阻力巨大，此半球形机体和表面的射流吹气的流场对于水平风切变和横向风也过于敏感而无法使升力平衡和稳定姿态，所以至今得不到发展。
3.7 There are so many kinds of methods to use,intensify or active-flow-control the attached-vortex of wing (circulation-control) in the aviation and aerodynamic-control fields.When we are blowing on a upward-protruding-convex,the air/fluids will walk along the arc making a long turn,which is like the air/fluids to be sticking the curved surface,that is so called air-jet-theory and wall-attachment-effect （Coanda effect） (and its essence also belong to the domain of vortex and viscosity).The real value is in blowing into this attached-vortex on a upward-protruding-convex with a high-speed-jet-flow,because the viscosity of the fluids will be absorbing (shearing or inducing) a large quantity of the surrounding air-molecules or the boundary-layer to flow away and change direction (and increasing the energy (kinetic-energy and velocity) of the boundary-layer on the wing's trailing-edge and delay the separation of boundary-layer.),then generate the supercirculation.So the lift-force-efficiency of the high-speed-wing will be more higher than that of the jet-engine or ducted-fan which jeting straight downwards (the higher the blowing-lift-enhancement-efficiency,the higher is the speed of aircraft.).If we want to apply the air-jet-theory and wall-attachment-effect on the aircraft of vertical take-off and landing (VTOL) aircraft,and generate the isotropic lift-forces within the 360-degree circle periphery,then there are some aviation-models which lifting-surface has been be replaced by a hemispherical surface.As shown in the figure,for example,we will use the ducted-fan/propeller or the centrifugal-compressor to blow on a upward-protruding-convex,then to rise the lift-force-efficiency which will be very less in fact.It looks like a parachute that will increase the security when it lose power or stall crash，and it will reduce the lift-force-generating influence of the upward and downward airflow under the vertical-wind-shear.Then its bigest drawback will be that its windward area is so large that the air-resistance under horizontal forward flight will be great.The hemispherical airframe and the flow-field with high-speed-jet-flow will be too sensitive to the horizontal wind shear and crosswind that will not balance the lift-force and stabilize its attitude,so far it has not been developed.

Fig.8

升力8

3.8 近来磁流体力学（等离子体和离子流）结合空气动力学的领域有些研究，主要在太空飞船返回大气层时有所设想以及在等离子隐身技术上有所研究，但受制于“飞行器全电化”或飞行器的化学能转化为电能的发展迟缓。近年来出现了带有“大气压低温电离装置”(介质阻挡放电(Dielectric-Barrier-Discharge) 和 辉光放电（Glow-Discharge）)和“离子风发生器”（电晕放电（Corona-Discharge）和射流低温等离子体放电(Low-Temperature-Plasma-Jet-Discharge）及射频低温等离子体放电(Radio-Frequency-Plasma-Discharge)）的技术的大气层内飞行器的气动力部件和推进系统，做成没有旋转部件的“固态发动机/推进器”和气动力控制部件，类似于航天飞船的“离子电推进发动机”和普通飞机的副翼襟翼。例如，其中生成“离子风”（电晕放电（Corona-Discharge））的一种电离装置，其正电极导线的高压电场就会让正极把电子从周围的氮气分子上剥离出来，变成了带正电的离子，又被吸引向着去负电极，在赶去负极的路上，氮离子又会撞上其他氮气分子，把它们变成正离子，就好像“雪崩”一样。正离子在高电压作用下飞向飞机尾部，形成一种离子组成的“风”。但是目前来看，正电极通过这种“离子风”得到的推力很小，即发动机推力小，但是负电极可以做成理想化二维机翼的形式，则“离子风”可以在负电极的机翼上诱导出含有离子流的“涡旋”（“附着涡”），可以提高飞行器的“气动力升力”，是一种可用电场来控制的“离子风涡旋”，成为气动力控制部件。未来更进一步可以加入磁场来控制此“离子风的附着涡和附面层”，提高气动力可控性能。总之，“离子风固态发动机和离子风气动力控制部件”的提出和实践，不但为未来的“飞行器全电化”的发展提供了信心，更是让离子流和磁流体参与空气动力学领域做出范例，为不远的未来“磁流体空气动力学(或电磁空气动力学)”的出现做了铺设。
3.8 Currently,there are some studies in the field of combining the aerodynamics and magneto-hydrodynamics (MHD) （plasma and ion-flow),it is mainly conceived to apply on the spacecraft returning to the atmosphere and the technologies of plasma-stealth.But it is limited by the delayed development of the all-electrification of aircraft or the conversion of chemical to electrical energy.In recent years，there have been presenting some aerodynamic-components and propulsion-systems with the technologies of low-temperature-ionization-device at atmospheric pressure in air (Dielectric-Barrier-Discharge and Glow-Discharge) and the technologies of ionic-wind-generator (Corona-Discharge,Low-Temperature-Plasma-Jet-Discharge,and Radio-Frequency-Plasma-Discharge)，that to make it into a kind of solid-state-engine/thruster (without the rotating-components) or the aerodynamic-control-unit,which are like the ion-electric-thrusters of the spacecrafts or the ailerons and flaps on the airplanes.For instance,one of the ionization-device generating the ionic-winds （Corona-Discharge）,the high-voltage-electric-field of its positive-electrode-wire will strip the electron from the nitrogen-molecule around its positive-electrode,which will become a positively-charged-atom （positive-ions） and be attracted towards the negative-electrode.When it is running towards the negative-electrode,it will dash against the other nitrogen-molecules and convert them into positively-charged-atoms （positive-ions）.Then it is the same as the avalanche.The positive-ions will be flying towards the aircraft's tail under the high-voltage-electric-field,and becomming a blast of ionic-wind.But at present,the thrust that the positive-electrode-wire getting will be very small (the engine's thrust will be too small),but the negative-electrode will be made into the ideal two-dimensional-wing,then the ionic-wind will induce a kind of vortex (attached-vortex) with the ion-flow on the negative-electrode-wing,which will increase the aerodynamic-lift-force of the aircraft.And that is also a ionic-wind-vortex under the control of the high-voltage-electric-field,and becomming a aerodynamic-control-unit.In the future we will add the magnetic-field to contral this ionic-windy attached-vortex/boundary-layer and rise its aerodynamic-controllability.In brief,because the proposals of the ionic-wind-solid-state-engine/thruster and the ionic-wind-aerodynamic-control-unit have been offered and the experiments have been done,it will not only provide confidences in the all-electrification of aircraft,but also let the ion-flow and magneto-fluids combine in the field of the aerodynamics as a successful example,and it will pave the way to the present of the magneto-fluid-aerodynamics (or the electromagnetic-aerodynamics) in the near future.


Fig.9

升力9

3.9 对机翼进行“环量控制或主动流动控制”，以及产生和控制机翼上的涡旋，一直是空气动力学的发展方向，当与高超声速飞行、飞船再入大气层和等离子体隐身相关的“磁流体空气动力学(或电磁空气动力学)”正在出现时，终于有可能构思和创造出一种部分甚至完全电离化的“磁流体涡旋(离子流涡旋或离子风涡旋)”，并可以用电场和磁场进行更好控制。那么，这里描述了一种最适合低速及垂直起降飞行的“电磁场控制的磁流体涡旋(离子流涡旋或离子风涡旋)”，构形上看是一种“特异性二三维结合环形分离涡”（“奇异涡环”），这将是人工创造出的“第三大类涡旋”。其是以自然界中唯二的两大类形态或体系的“涡旋”（分别是“二维的旋涡”和“三维的涡环”）有机结合而成，可看作为台风/飓风和空中的烟圈的结合体，由电离化的空气射流在电磁场的约束和控制下“自组织”构成的整个涡旋，而且其流动是完全处于一个复杂有序的强大电磁场的控制之下的。而最可取之处在于其有巨大的增加升力、效率、安全、强壮和可控性的潜力，用于垂直起降飞行器最佳。唯一需重视的缺点就是电离空气的耗能高。首先，我们地球人第一次设计在一个水平放置的相对规整（可以是多边形最好是圆形）的薄平板（边缘也没有上翘或下弯）上实现空气动力学的升力涡旋,当然我们更可以在一个圆锥面或球面上产生这种涡旋和升力,更进一步还得考虑“附面层”流体运动才有可能得到“气动力升力”，这是空气动力学和流体力学方面的一种全新思路。如果我们用射流吹气制造的“附着涡”、“分离涡”、“脱体涡”等，想要在一个机翼上表面产生“气动力升力”，则必须有两个关键，一个是涡旋所形成的“涡核”内的低压强可以很好的传导到“附面层或边界层”流体中，另一个是要在机翼后缘形成“下洗流”（前方来流的“动量的变化量”的垂直向下方的分量）。那么，在此我们可以电离空气制造离子射流，用电磁场约束控制这些离子射流，在一个水平放置的圆盘面上构成一个“特异性二三维结合环形分离涡”（“奇异涡环”），其不但可以形成典型的两种不同的“涡核”，更可以吸附（剪切、诱导、扰动、渗混）大量的周围空气（都被电离以后）在圆盘面的尾部边缘形成“下洗流”。这种“奇异涡环”的两种不同的“涡核”，分别类似于“台风中心的涡核”（“第二涡核”）和“烟圈内部的涡核”（“第一涡核”）。而正是这个“第二涡核”的存在，为大幅度增加升力和效率提供了无限可能。这种“特异性二三维结合环形分离涡”（“奇异涡环”）是大自然中不可能天然存在的（包括太阳或各大气态行星上都不可能存在），是第一次在地球人的空气动力学（流体力学）中创造出来的完美对象。
3.9 The research of circulation-control or active-flow-control about the wing and the generation/control of the vortex on the wing which always the developing direction of the aerodynamics.When the magneto-fluid-aerodynamics (or the electromagnetic-aerodynamics) relating to the hypersonic-flight,spacecraft reentry into the atmosphere,and the technologies of plasma-stealth are developing,we will conceive and create a partly/wholly-ionized magneto-fluid-vortex (ion-flow-vortex or ion-flow-vortex),and will be more controllable in the electric-field and the magnetic-field.So we will describe a electric-field/magnetic-field controlling magneto-fluid-vortex which is the best fit for low-speed flight and for vertical take-off and land (VTOL),and it will be looked as a kind of specific two-dimensional and three-dimensional combined annular-separation-vortex (singular-vortex-ring) on its structure，and it will be the artificially-created third-broad-categories of vortexes.And it will be made combining the two forms(two-broad-categories) of vortexes (one form of two-dimensional-vortex and another form of three-dimensional-vortex) in the nature,which will be looked as a combination of hurricane/typhoon and smoke-ring,and this vortex will be made up of the ionized air-jet under the control of magnetic-field due to the self-organization.Its flow-motion will be under the control of a complex and orderly strong-magnetic-field,the most important merit of it will has the great potential of increasing the lift-force,efficiency,safety,strength and controllability.And it will be most suitable for the vertical take-off and land (VTOL) aircraft,but its sole drawback will be the much too high electric-energy-consumption when ionizing the air.In the first place,we will construct a lift-force-vortex on a relatively regular flat (polygon/circle-plate,and the edge has not been upturned or recurved).We will also construct this vortex on the circular-cone-surface or hemispherical-surface,but we must consider the flow-motion of the boundary-layer and make it possible for us to get the aerodynamic-lift-force.This is a new thinking in Aerodynamics and Hydrodynamics.If we use the air-jet-blowing to construct the attached-vortex,separated-vortex,detached-vortex above the wing,and want to generate the aerodynamic-lift-force,there are two keys: one thing will be that the low-air-pressure of the vortex-core will be conducted into the boundary-layer fluids;the other thing will be that the downwash-flow will be formed around the trailing-edge of wing (the vertical-downward-component of momentum-variation about the incoming-flow.).So we will ionize the air and generate the ion-jets,then we will use the magnetic-field to constraint and control these ion-jets,and to construct this specific two-dimensional and three-dimensional combined annular-separation-vortex (singular-vortex-ring) on a horizontally-placed-disc-surface.Then it not only will form two kinds of typical vortex-cores,but also will be absorbing (shearing or inducing) a large quantity of the surrounding air-molecules  to form the downwash-flow around the trailing/outside-edge of disc-surface.These two kinds of vortex-cores about the singular-vortex-ring,which are respectively similar to the vortex-core of hurricane/typhoon-center (the second vortex-core) and the vortex-core of smoke-ring-internal (the first vortex-core).But just because of the existence of the second vortex-core,that make it limitlessly possible to effectively enhance the lift-force and efficiency.This specific two-dimensional and three-dimensional combined annular-separation-vortex (singular-vortex-ring) willnot be existence in nature (on Sun,and all gaseous-planets.),and it will be a perfect object create be human-being in the earthman's aerodynamics or hydrodynamics for the first time.

Fig.10

升力10

3.10 空气动力学发展到高超声速阶段和飞行器隐身性的需要，必然推动空气电离化（低温电离）和主动流动控制技术的广泛应用。我们先在这个圆盘升力面内构造一个磁场，并通过内部的电离和加速的装置把空气电离后，再将一定速度的离子流从圆盘表面的喷嘴处贴着表面沿圆周切向有序的喷射而出（喷嘴可以很多并有序分布），电离流体（正负不同电荷的流体喷射的方向相反）在圆盘内的磁场中受到约束并逐渐改变方向，最终形成我们所预期的“特异性二三维结合环形分离涡”（“奇异涡环”），但是“第一涡核”及“第二涡核”的产生过程都有自组织的特征（甚至最后还会在圆盘尾部边缘形成“下洗流”）。其中，在圆盘的圆心处还装设有大功率的电子枪和激光向上照射，可以把圆心处的“第二涡核”所要吸附的上部空气更充分的电离。又比如，这里有两个磁场（一种是“固定磁场”另一种是“可旋转磁场”），都由“超导磁棒束”来构造，在圆盘上由圆中心向外360度辐射性均匀分布的磁棒束所构成的是“固定磁场”，而在圆盘的中心由一圈垂直竖立的磁棒束是可以高速旋转的，其所构成的是一个“可旋转磁场”，正是圆盘中心这个可旋转磁场在高速旋转时可大大增加“第二涡核”吸附上方电离空气的质量从而增加升力和效率（比如可以在飞行器垂直起降或悬停时，将“第二涡核”的高度大幅度增高，并提高圆盘中心的“可旋转磁场”的强度和旋转速度，及提高电离空气的激光和电子枪的功率，而主动吸入更大质量的上方电离空气）。

3.10 Beacause of the pressing need in the stage of development about the hypersonic-flight and the technologies of plasma-stealth,it must promote the wide application about the technologies of air-ionization (low-temperature-ionization) and active-flow-control.We will construct a magnetic-field on this disc-surface first of all,then ionize the air through the internal ionizing/accelerating-device,and spout a certain speed ion-flow towards circumferential-tangential-direction from the ion-jet-nozzle above the disc-surface-edge (the ion-jet-nozzle's number will be great and be orderly distributed.),so the ionizing fluids (the jet-flow-directions of the positive/negative-charge-fluids will be contrary.) will be magnetically-confined in the magnetic-field on this disc-surface,and gradually change itself directions,and construct the specific two-dimensional and three-dimensional combined annular-separation-vortex (singular-vortex-ring) which we have expected in the end,but the generating-processes of the first vortex-core and the second vortex-core will have a self-organization feature （even there will be a downwash-flow being formed around the trailing/outside-edge of disc-surface in the end.）.Among them,there will be some high-power electron-guns/laser-devices in the center of the disc-surface which will irradiate upwards,and will ionize a large number of absorbed-air above the second vortex-core at the center of the disc-surface.for example,there are two kinds of magnetic-fields (one kind is the fixed-magnetic-field,and another kind is the rotating-magnetic-field.) which will be made of the superconducting-magnetic-rod-beams.The fixed-magnetic-field will be made up of the superconducting-magnetic-rod-beams which will be uniform distributed from the center to the outside of the disc-surface with 360-degree-angle,and the rotating-magnetic-field will be made up of the superconducting-magnetic-rod-beams which is vertically circular erected and will be rotating at high speed aroud the center of the disc-surface.Just because this rotating-magnetic-field will be rotating at high speed,and which will greatly increase the number/mass of upper-ionized-air absorbed by the second vortex-core,and effectively enhance the lift-force and efficiency (for instance,when our aircraft will be in the state of vertical-take-off-and-land( VTOL) or hover,we will greatly increase the height of the second vortex-core and the strength-and-rotating speed of the rotating-magnetic-field，and enhance the power of the electron-guns/laser-devices which ionizing the upper-air,so it will proactively absorb the greater number/mass of upper-ionized-air.)

Fig.11

升力11

3.11 我们在图示描述了两种磁场（“固定磁场”和“可旋转磁场”）的构造及其与电离流体的相互作用，我们是从圆盘内用“正离子喷口”沿着圆周切向喷出已经电离的空气射流的，电离的正离子流体就开始切割固定磁场而受“洛伦兹力”向圆盘中心改变流动方向，在横切面上看，正离子流在磁场中的加速（改变方向），是一个从圆盘的外边缘表面底部——向圆盘中心——再向中心上方——再向外上方——再向外下方——回到圆盘外边缘，然后是一个不断迭代回旋的过程，正离子受磁场的洛伦兹力经过一个螺旋线形的压缩和加速过程，最后形成了“第一涡核”。但实际上，在这个“第一涡核”的形成之前，从圆盘边缘向中心流动的电离流体会先一步受挤压加速形成了更强更明显的“第二涡核”，然后是由“第二涡核”的流体再向外翻转（分离）而形成的“第一涡核”。而“升力”的产生过程，主要可以看作是由圆盘中心的“第二涡核”从上方“吸附（剪切、诱导、扰动、渗混）”大量空气，再混入整个涡旋中得到两个涡核所传导来的动能和速度（“涡量”和动量），最后在圆盘的边缘形成“下洗流”。一般来说，出于节省能源的目的，“下洗流”最后离开圆盘升力面的边缘时候，都已经还原为空气分子流（不再处于电离态），但是因为用磁场来偏转离子流的不完全性，所以“下洗流”还多少带一点“旋转性质”（而非垂直向下方流动），这算是一种“诱导阻力”吧。图中已另外给出了电磁学“左手定则”的图示，有助于理解正离子流在磁场中运动受“洛伦兹力”而改变方向最终形成两个“涡核”的过程。
3.11 In the illustration,we have described the construction of two kinds of magnetic-fields (one kind is the fixed-magnetic-field,and another kind is the rotating-magnetic-field.),and the interaction between them.We will spout a certain speed ion-flow towards circumferential-tangential-direction from the positive-ion-jet-nozzle above the disc-surface-edge,so the ionizing fluids will be magnetically-confined by lorentz-force in the magnetic-field on this disc-surface,and gradually change itself directions.Looking at the cross-section,the positive-ion-flow in the magnetic-field will be a process which is changing itself speed from the trailing/outside-edge of disc-surface towards the center of disc-surface,towards above the center,towards above the outside,towards beneath the outside,and return to the trailing/outside-edge of disc-surface in the end.And this will be a process of continuous iteration and convolution.In the process,the positive-ion-flow magnetically-confined by lorentz-force will be helically compressed,accelerated,and changed itself directions,and finally form the first vortex-core.But before the generation of the first vortex-core,the positive-ion-flow which flowing from the trailing/outside-edge of disc-surface towards the center of disc-surface will have to form a stronger second vortex-core under compressing and accelerating,then the fluids of the second vortex-core will be turned outwards (be separated) and form the first vortex-core.The generating-process of the aerodynamic-lift will be looked like that this second vortex-core be absorbing (shearing or inducing) a large quantity of the surrounding air-molecules to form the downwash-flow around the trailing/outside-edge of disc-surface,into which this two kinds of vortex-cores will transmit the kinetic-energy and velocity (momentum and vorticity).Generally speaking,for the purpose of energy-savings,when the downwash-flow leave around the trailing/outside-edge of disc-surface that its fluids have been returned to the air-molecules (no longer in the ionized state).But because of the magnetic-field-deflecting incompleteness of the ion-flow,so the downwash-flow will have some rotating-properties (rather than flowing straight downward.),which will be looked as a kind of induced-drag.There have been presented the Left_hand Rule in Electromagnetics in the illustration,which will help to understand the process of the generation about this two kinds of the vortex-cores.

Fig.12

升力12

3.12 高速的离子喷流分别从正、负离子喷口喷出，要在一个上述特定的圆盘形机体表面“固定磁场”约束下，形成这个圆盘上的这种“特异性二三维结合环形分离涡”（“奇异涡环”），有几个阶段的流动形式。最开始是离子流受到指向圆心的“洛伦兹力”而相互剪切挤压向中心，形成一个类似水漩涡的“平面旋涡”，接着离子流体在其中心处向上堆挤升起形成类似飓风/台风的中心的涡核（“第二涡核”）,这是一个“二维涡旋和中心涡管”，并一边受“洛伦兹力”而向外翻卷和收缩，不断重复迭代这个过程，最后形成了类似烟圈的涡核（“第一涡核”），这是一个“三维的涡环”。而所谓的“涡量”大部分就集中在这两个不同的“涡核”的流体里。其中的“第二涡核”（中心涡管）可以人为的堆起得很高大，并且增加中心的“旋转磁场”的转速，可以大幅度增加吸附上部的电离空气的量和提高“磁流体的粘性”，主要是为了航空飞行器在低速飞行或直升起降悬停时提高升力和效率。注意，这种“升力涡旋”的“涡量”都来自于初始的正负离子喷流（完全电离）的动能和动量，但是完全电离的离子喷流的质量密度仍然比较低，所以要求其速度很大才能得到升力所需的“涡量”（动量），所以对于碟形飞行器来说，其产生升力所消耗的能量（初始正负离子喷流的动能加上电离的耗能）是远大于现代的旋翼直升机的耗能的，但是却得到了无可比拟的空气动力学特性（高度的可控性、适用性、通用性、安全性，以及升力强度和效率的宽范围可调性等等）。
3.12 The high-speed ion-flow will be spouted out from the positive/negative-ion-jet-nozzles,and be magnetically-confined in the fixed-magnetic-field on this disc-surface,and construct the specific two-dimensional and three-dimensional combined annular-separation-vortex (singular-vortex-ring),which have several phases of flowing.In the beginning the ion-flow will be sheared and compressed by the lorentz-force towards the center,and form a likeness of water-eddy (planar-vortex),then it squeeze up the heap to form a likeness of vortex-core of hurricane/typhoon-center (the second vortex-core) which is a two-dimensional-vortex or center-vortex-tube,then be turned outwards (be separated) and be compressed towards the center by the lorentz-force,and by this process of continuous iteration and convolution,then form a likeness of the vortex-core of smoke-ring-internal (the first vortex-core) which is a three-dimensional-vortex.And the so-called vorticity will be mostly concentrated upon these two kinds of vortex-cores.Among them,the second vortex-core (center-vortex-tube) will be heaped up very high，and increase the rotating-speed of the rotating-magnetic-field at the center,then be increasing the viscosity of magneto-fluids and the absorbed number/mass of upper-ionized-airs,which be in order to greatly enhance the lift-force and efficiency when aircraft in the state of vertical-take-off-and-land (VTOL) or hover or low-speed-flying.Please note that the vorticity of this vortex-about-lift (the lift-vortex) will come from the initial kinetic-energy and momentum of high-speed positive/negative-ion-flow (wholly-ionized),but the mass-density of the wholly-ionized ion-flow will be very low,so it require the initial speed of the ion-flow be very high and to get the enough vorticity (momentum) the lift-force needed.So for the saucer-shaped spacecraft,the energies (initial kinetic-energy plus ionizing-energy of the ion-flow) consumed by generating the lift-force will be more larger than that of the modern-helicopter,but obtain the incomparable Aerodynamic characteristics (include the high ontrollability,applicability,generality，security，adjustability of lift-strength and efficiency at a wide range.)

Fig.13

升力13

3.13 虽然我们可以直接将上述这种“特异性二三维结合环形分离涡”（“奇异涡环”）用于现代的飞机机体表面产生“气动升力”，因为我们更多时候是采用了“低温电离方式”（喷射高速负电子流碰撞上方空气分子），而其整个涡旋流体的平均温度不高，所以一般情况下可以在机表蒙皮下用普通的“冷却剂循环系统”即可冷却蒙皮。但考虑到未来在太空飞行战斗时，碟形飞行器的战场主要是在太阳和各大行星的大气层内。所以碟形飞行器的“升力涡旋”的电离流体的温度要大幅度提高,得采用“高温电离方式”(比如“电弧电离”)才能更好的用更强的磁场控制流体以对抗各种强大的风暴，这会让最贴近机体表面蒙皮的“附面层”（边界层）流体的温度也很高（因对流现象），导致出现对机表蒙皮的冷却困难。所以这里采用了“开放式等离子体环流发生器”，分别处于机体的上顶部和下底部圆心周围，其产生一种类似于“核聚变托卡马克装置”的“等离子体环流”（光环）（含有强大的感生电流），并可以将其放出装置让其在离心力作用和稳定减弱的磁场约束下一个接一个地自由扩张和释放出去,但是此光环在机体表面仍然被一个均匀的“机体表面固定磁场”所约束，并在圆盘外边缘处自动破裂（现代的核聚变装置中的等离子体环流的存在时间已经超过数分钟,但是现在的困难是如何让此“光环”在大气压下的空气中保持一定时间）。其破裂后的电离流体再在机体表面的“固定磁场”约束下形成碟形飞行器的“奇异涡环”。上述的这种“可开放的等离子体环流发生器”在现代科学中已经有数十年的设计历史了，其主要是用于武器系统的研究，作为一种“防御性磁流体武器”，比如很多设计中是将其产生的“等离子体环流”（光环）（含有强大的感生电流）放出装置，并进行压缩和加速后喷射而出，其内的高压缩性的电磁能量可以在近距离爆炸击毁来袭导弹。但是，这里我们只是将“等离子体环流”（光环）用来把碟形飞行器上面的“升力涡旋”与其“附面层”（边界层）流体相互隔离，（当然其中这种“光环”因为含有强大的感生电流也在太空战斗时作为一种装甲），一圈圈一层层的这种“等离子体环流”（光环）是高度压缩性和有大电流和强磁场的，所以可以说具有在磁场中高度“硬化或固化”的特性，可以看成一个“磁场悬挂着的板块”，即碟形飞行器的机体相当于用磁场悬挂在这个板块下方，所以机体表面蒙皮的附面层（边界层）流体可以非常厚，甚至于碟形飞行器的升力可基本不受到其附面层（边界层）的流体厚度和流动情况的影响了（不管是层流或湍流），这样我们就可以在附面层流体中注入低温的“液氮”（或“液氦”）而冷却体表蒙皮，而大幅度减少上部高温流体对机体的直接导热，从而让碟形飞行器可以在极高温度的太阳上和极低温的气态行星上长时间飞行了，飞行器上面的“升力涡旋”是在强磁场的控制之下可以对抗高速风暴流体的吹袭，更不要说“等离子体环流”（光环）（含有强大的感生电流）作为一种装甲可以对抗太阳的“百万倍电磁风暴”和气态行星上的“气液固三相流体风暴”的射流和固体的高速撞击。也不用说这种完全电离化和电磁控制的“升力涡旋”产生的“升力”可轻易克服太阳上的巨大引力了。
3.13 Although we will use the specific two-dimensional and three-dimensional combined annular-separation-vortex (singular-vortex-ring) on the surface of modern-aircraft to get the lift-force,because we will usually use the way of low-temperature-ionization (to spout the high-speed-negative-ion-flow colliding the upper-air-molecule.),then the average fluids-temperature of the vortex willnot be very high,so the we will use the ordinary coolant-circulating-system cooling the skin of the lift-force-surface.But considering the saucer-shaped spacecraft will often be flying in the atmosphere of sun/gasous-planets in the future,the average fluids-temperature of the vortex will have to be greatly increased by using the way of the high-temperature-ionization (for example the arc-discharge-ionization.),and only then will resist all sorts of powerful storms by means of stronger magnetic-field better-controlling the fluids of vortex,and this will also increase the temperature of the boundary-layer which most close to the skin of the lift-force-surface (because of the Thermal-Convection-Effect ),then cause the cooling-difficulty of the airframe-skin.So we will fit an openable plasma-circumfluence generator in the top and bottom of the saucer-shaped spacecraft,which is same as the tokamak-device，and will creat the same kind of plasma-circumfluence (a ring of light) which have a strong induced-electric-current/magnetic.And this plasma-circumfluence (a ring of light) will be freely released out of the generator under the actions of the centrifugal force and a weakening magnetic-field one after another.But this plasma-circumfluence(a ring of light) will also be steadily constrained by a symmetrical fixed-magnetic-field of the airframe's surface,till it be broken by self at the outer margin of airframe （the plasma-circulation of modern tokamak-devices will be kept several minutes,but the new difficult will be how this ring of light will keep for some time in the air under one bar pressure.）.The ion-flow after the break will form the singular-vortex-ring which constrained by a symmetrical fixed-magnetic-field of the airframe's surface.The ideational history of above-mentioned openable plasma-circumfluence generator has lasted for decades,and it often be used in the study of weapon,and as a kind of defensive magnetic-fluid weapon.For instance,there are many weapon'design which will release this plasma-circumfluence (a ring of light)(which has a strong induced-electric-current) out of the generator,and will be recompressed and reaccelerated,and then spout it as a shell/bomb to destroy incoming missile with the hypercompressive electromagnetic-energy.But here we will only use this plasma-circumfluence (a ring of light) as a isolation layer between the vortex-about-lift （the lift-vortex）on the saucer-shaped spacecraft and the fluids of boundary-layer (meanwhile,this ring of light will be used as a new kind of armor (magnetic-fluid-armor) due to possessing a strong induced-electric-current.).Circle by circle,layer by layer,this plasma-circumfluence (a ring of light) will be looked as a plate suspended in the magnetic-field which have a highly hardening/solidifying characteristic due to possessing strong induced-electric-current,strong magnetic-field,high compressibility.Then it will be looked as that the airframe of saucer-shaped spacecraft be suspended under this plate in the magnetic-field.So the fluids of boundary-layer on the airframe's skin will be far more thicker than usual，even the lift-force of the saucer-shaped spacecraft willnot be effected by the thickness and motion of the fluids in the boundary-layer (whether it be laminar-flow or turbulent-flow.).Then we will spout the liquid nitrogen/helium to cool the boundary layer and the airframe's skin,so substantially lower thermal-conducting from the upper-high-temperature-fluids to the airframe's skin.So the saucer-shaped spacecraft will be flying on the extremely-high-tempreture sun and all the badly-cold gaseous-planets for a long time.And the vortex-about-lift （the lift-vortex）on the saucer-shaped spacecraft will not only resist the striking of ordinary storm under the contral of the strong magnetic-field,but also this plasma-circumfluence(a ring of light) will resist the solar-storm which be more than the million times energy of earth's giant storm (hurricane/typhoon) as a kind of armor with a strong induced-electric-current,and resist the impact and disturbance of the flowing three-phase-fluids(gas,liquid and solid) storm on all the badly-cold gaseous-planets.Needless to say the lift-force generated by this vortex-about-lift （the lift-vortex） will be able to overcome the great sun's gravity under wholly-ionizing and electric-field/magnetic-field controlling.

Fig.14

升力14

3.14 根据“动量定理”和“牛顿第三运动定律”，空气动力学的涡旋在机翼上产生升力，必须对来流向下方“吸附（剪切，诱导）”（下洗作用），形成“下洗流”，其在垂直方向的动量的分量就是升力。但是不管是机翼、风扇、螺旋桨等，都在翼尖处形成“翼尖涡”，有强烈的旋转性质。其实在碟形飞行器的“升力涡旋”形成的“下洗流”也保留有一定的“旋转性质”，这是用磁场“洛伦兹力”偏转离子流方向时不可避免的一种能量浪费。这会在历史上的“碟形飞行器目击案例”中出现一些不同的机体下部的空气动力学现象，比如碟形飞行器下部在城市郊区或沙漠的地面悬停时会出现明显的“尘卷风”（风力较弱），而碟形飞行器在水面低速飞行或悬停时会出现“水龙卷”等，前者是常见的典型现象即形成的“下洗流”是向外自由扩散的旋转风，后者是当碟形飞行器的机体下部的“下洗流”仍然保留有相当的电离程度时，机体下部的磁场会将“下洗流”向内吸引收缩形成风力比较强烈和窄小的柱状旋转风，其内的“管状流动低压区”可以把海水等变成水蒸汽而向上倒吸作用，也可以把人体向上平稳吸离地面而不旋转或伤害人体。碟形飞行器在超声速及高超声速飞行时，产生“气动升力”的情况要更复杂一些，其在低超声速时，可以同时由机体上部的“奇异涡环”产生“负压的升力”和机体下部的“旋转性质的下洗流”与来流之间的压缩而生成的激波来产生“正压的升力”；但是随着飞行速度的增加，其机体上部的“奇异涡环”的“第二涡核”的高度会逐渐降低并减少产生“负压的升力”，而更多是由机体下部的“旋转性质的下洗流”与来流之间的压缩而生成的激波来产生“正压的升力”；甚至在高空的高超声速飞行时其气动升力，可以完全由机体下部比较平坦的表面与来流之间产生的“激波升力”（压缩升力）来提供，但是机体的“飞行纵轴”与前方来流之间的“相对迎角”将会一直保持甚至会增大。而机体下部比较平坦将有利于把“旋转性质的下洗流”用磁场收缩后，与来流在下部的“激波”后的流体相互压缩作用，形成以下表面360度角的比较均匀的“正压的升力”，所以碟形飞行器机体下部一般都比机体上部更平坦，这是为了在超声/高超声速时和适当的“飞行迎角”条件下，更好地用“激波”和“下洗流”形成“下表面的升力”。比如在唯一的碟形飞行器的两倍声速飞行的照片中，当其机体表面的附面层（边界层）和蒙皮采用“液氮/氦”来进行冷却（一种飞行器的视觉遮掩及红外隐身技术）时，则的机体上部的“第二涡核”因为被超声速来流强力吹袭而向后倾斜拖曳，则此涡核内会出现“回流流体团”（旋转性气团）的现象，而其机体下部则会因为“旋转性质的下洗流”被来流压缩而成为倾斜向后的扁管形流体，并在此扁管内有“倒吸流”现象（比如下部机体表面的液氮/氦形成的雾气中出现动态凹陷现象）。但是在高速飞行时，不管是上部的“奇异涡旋”还是下部的“旋转性质的下洗流”都仍然处于电离态，所以在白天的阳光下仍然不可见，一般只是见到碟形飞行器表面的用于冷却附面层的液氮/氦雾气，只有在黑夜里才可见到电离流体在磁场中运动时发光现象。
3.14 According to the Momentum-theorem and Newton's Third Law of Motion,if aerodynamic-vortex want to generate the lift-force on wing,it will must absorb (shear or induce) the incoming-flow downwards (downwash-tendency)，and form the downwash-flow,then the vertical-direction-component of the downwash-flow's momentum will be the lift-force.But this downwash-flow behind the wingtips of the wings,fans,and airscrews will never avoid generating the trailing-vortex (wake-vortex) in which the fluids be posessing a violent rotating-characteristic.And this is an inevitable energy-waste as a result of the lorentz-force of magnetic-field has deflected the direction of the ion-flow.This have left many different Aerodynamic-phenomenon about the witness-case of saucer-shaped spacecraft in history.For example,the saucer-shaped spacecraft will generate an obvious dust-devil beneath its airframe when it hovering on the ground of the city suburbs or the deserts,and it will generate an obvious waterspout beneath its airframe when it hovering or low-speed-flying on the sea-surface.The former will be a typical phenomenon that the downwash-flow be a rotating-wind diffusing outwards.The latter will be a rare phenomenon that the downwash-flow be kept ionizing-state and be contracted inwards by the under-magnetic-field to form a stronger/narrower columnar-rotating-wind,and the tubular-flowing-low-pressure-area in it will suck-back the water-vapour converting from sea-water upwards,and the tubular-lowing-pressure-area  will also steadily suck the human-body upwards to leave the ground but not hurt or rotate the body.The aerodynamic-lift-force-generating under the supersonic and hypersonic flight about the saucer-shaped spacecraft that will be more complex,and its upper-surface-lift-force about negative-air-pressure will be supplied by the singular-vortex-ring,and its down-surface-lift-force about positive-air-pressure will be supplied by the shock-wave generating from the compressing between the incoming-flow and the rotating-characteristic downwash-flow.But with the increasing of the flying-speed,the height of the second vortex-core will decrease gradually and reduce its upper-surface-lift-force,and more of down-surface-lift-force.Even under hypersonic flight,its aerodynamic-lift-force will be wholly generated by its down-surface-lift-force about positive-air-pressure of the shock-wave （the so-called shock-lift or compression-lift）,but the relatively angle-of-attack between the incoming-flow and its longitudinal-axis in flying will be kept and even increased.And the down-surface-airframe will always be relatively flat,that it will use the lorentz-force of magnetic-field to shrink the rotating-characteristic downwash-flow inwards,and then compress with the incoming-flow behind the shock-wave,to form the relatively uniform positive-air-pressure about down-surface-lift-force on the down-surface-airframe at 360 degree angle.It is so often that the down-surface-airframe will be more flater than the upper-surface-airframe about the saucer-shaped spacecraft,then it will better use the shock-wave and the downwash-flow to form the down-surface-lift-force which be under the supersonic and hypersonic flight and the relatively angle-of-attack.For instance,in the only photo of flying at twice the speed of sound about the saucer-shaped spacecraft,that the boundary-layer and the airframe'skin will be cooled by the liquid nitrogen/helium (a kind of visual-concealed and infrared-stealth technology of aircraft.)，then the second vortex-core will be dragged and tilted backwards by the blowing of supersonic incoming-flow,and there will be some back-flow fluid-mass (rotating-characteristic air-mass) appearing in this second vortex-core,but the rotating-characteristic downwash-flow under the airframe will be compressed by the incoming-flow and form a backward-inclined flat-tube-shaped-fluids，and there will be some inverted-sucting-fluids phenomenon in this flat-tube-shaped-fluids (for example,there will be an obviously transient-dimple-phenomenon in the liquid nitrogen/helium fog under the airframe.).But under high-speed flight,whether the singular-vortex-ring or the rotating-characteristic downwash-flow will always be ionized,so they willnot be visible under the sunlight,so it will usually be watched the liquid nitrogen/helium fog on the saucer-shaped spacecraft's airframe,and only in the dark of night will it be observed the luminescence-phenomenon when the lorentz-force of magnetic-field deflecting the direction of the ion-flow.

地球全力

4.未来太空战斗机（碟形飞行器）在太阳和各大行星的大气层/海洋内飞行作战的空气/水阻力原理
4.The air/water-resistance principle of the future spacefighter(the saucer-shaped spacecraft) which will be flying in the atmospheres/oceans of sun and all the planets in our solar system.

Fig.1

阻力1

4.1.在低速空气流中的物体当不考虑“因产生升力导致的阻力”（诱导阻力）的情况下，主要考虑的是“压差阻力”（形状阻力），与各种“涡旋”和“附面层流动状态”有关。如图，用正面抵抗气流的平板，其前后表面的压强差最大，不仅其前板面得到的的是最大的正压强，而且后板面因为形成了最剧烈的分离涡旋和最大范围的分离流而得到最大的负压强，所以得到最大的压差阻力；用尖端面对前方来流的尖锥体，不仅其前部表面的正压强不高，而且后部的表面因为形成的分离涡相对不太剧烈而范围也不大，所以压差阻力明显减小(但是会出现大型的顺序地脱离开机体的脱体涡（类似“卡门涡街”）)；用椭圆头面对前方来流的弹头体，不仅其前部表面的正压强进一步减小，因为沿着弧面已经出现了附着涡，附着涡使前部表面的静压减小，而且后部形成的分离涡的强度和分离流的范围也变化不大，所以总的“压差阻力”（形状阻力）会进一步减小(但是仍可能出现大型的顺序地脱离开机体的脱体涡（类似“卡门涡街”）)；用水滴形的流线体面对前方来流，其压差阻力最小，不仅其前部表面形成的附着涡减小了正压强，而且其后部的拉长变尖的弧面推迟了附面层气流的分离，让明显的分离涡很难出现或出现但不剧烈且范围很小；而底部向内凹陷的底凹弹头（亚声速）面对前方来流，则其压差阻力接近水滴形流线体，不仅其底部内凹的空腔内形成的大型的分离涡的流动很缓慢很稳定(不会出现大型的顺序地脱离开机体的脱体涡（类似“卡门涡街”）)，而且后部很难形成剧烈的分离涡，所以负压强相对较小(那么其前头后尾之间的压差也相对较小。)。现代研究“压差阻力”（形状阻力）已经很成熟，而最近的技术创新在于用边界层抽吸效应对飞行器后部机体表面的附面层进行吸除、减薄及避免分离，并提高前部机体表面附面层流体的速度等。比如在涡轮-电混合推进的未来的客机上后置附面层抽吸风扇可以显著降低空气阻力。
4.1.When we do not considered the drag-due-to-lift(induced-drag),the moving-object in the low-speed-flowing that will be main considered the pressure-drag (profile-drag),and it be connected with the boundary-layer's flowing-state and the vortexes.As shown in figure,the pressure-difference of the front-surface and rear-surface about the flat-plate will be the largest when it front-resist the incoming-flow,not only its front surface will get the maximum positive-pressure,but also its rear-surface will get the maximum negative-pressure,so it get the maximum pressure-drag (profile-drag) because of forming the most violent of separated-vortex and the biggest range of separated-flow;the pressure-difference of the front-surface and rear-surface about the cone will be reduced obviously,not only its front surface will get the reduced positive-pressure,but also its rear-surface will get the reduced negative-pressure because of forming the gentle separated-vortex and the smaller range of separated-flow(which will form a series of large orderly-detached-from-airframe detached-vortex behind its rear-surface,similar to the Karman-vortex-street.);the pressure-drag (profile-drag) of the warhead-body with oval-shaped head confronting the incoming-flow will be reduced further,not only its front surface will get the further-reduced positive-pressure,because the attached-vortex have been generated on the cambered-surface and reduced the static-pressure,but also its rear-surface will be forming the gentler separated-vortex and the smaller range of separated-flow further(which may still form a series of large orderly-detached-from-airframe detached-vortex behind its rear-surface,similar to the Karman-vortex-street.);the pressure-drag (profile-drag) of the droplet-shaped streamline-body will be minimum,not only its front surface will get the further-reduced positive-pressure,because the attached-vortex have been generated on the cambered-surface and reduced the static-pressure,but also its rear cambered-surface will be elongated and be tapered which postponed flow-separation of the boundary-layer,and the present of separated-vortex will either be very seldom or gentle/small;the pressure-drag (profile-drag) of the projectile with base-cavity(subsonic-speed) will be closed to that of the droplet-shaped streamline-body when it front-resist the incoming-flow,not only its caved-in-bottom-cavity will be generating the large-separated-vortex which be flowing very slow and stable(which willnot form a series of large orderly-detached-from-airframe detached-vortex behind its rear-surface,similar to the Karman-vortex-street.),but also the violent separated-vortex will form very diffcultly above its rear-surface,so the negative-pressure be relatively small(then the pressure-difference between front-surface and rear-surface will also be relatively small.).The morden study about the pressure-drag (profile-drag) has matured,and the recent innovative technology about it is using the Boundary-Layer-Inhalation（BLI） Effect by absorbing and thinning the boundary-layer,and avoiding the boundary-layer's flowing-separation above the airframe's rear-surface,and increasing the boundary-layer's flowing-speed above the airframe's front-surface.For instance,the postpositioned boundary-layer-inhalating-fan will remarkably reduce the airframe's air-resistence of the future passenger-plane under the turbine-electric hybrid-propulsion.

Fig.2

阻力2

4.2.高速飞行时，超过声速的以后会出现“激波和波阻”，这时“激波阻力”（也属于压差阻力）成为最主要的阻力。波阻的大小同激波的形状有关，而激波的形状主要有正激波和斜激波两种（也许还有弓形激波）。如果物体的头部尖削的，将形成斜激波；如果物体的头部是方楞的或圆钝的，形成的则是正激波。气流穿过正激波，消耗的动能很大则产生的波阻很大，总是由超音速降低到亚音速，在这里形成一个亚音速区；而气流穿过斜激波，对气流的阻滞较小，气流速度降低不多，动能的消耗也较小，因而波阻也较小，斜激波倾斜的越厉害，波阻就越小。如图中，专门设计用于超声速飞行的飞机，其机体上各处都尽可能的形成斜激波而非正激波，其机翼上下表面都尽量平缓以减低激波强度，比如美国的X-15实验飞机的激波图，可以看到，短粗的梯形机翼躲在机头的主激波锥之后，机翼的激波就减弱了。另外，激波形成的“音爆”对地面环境和飞行隐身性都会造成不良影响。
4.2.The shock-wave and the shock-wave-resistance(wave-drag) will present under supersonic flight,and the shock-wave-resistance(belong to the pressure-drag) will be the main air-resistance.The scale of the shock-wave-resistance(wave-drag) will connect with the shape of the shock-wave,and which will mainly consist of the normal-shock-wave and the oblique-shock-wave (maybe there is the bow-shock-wave).If the head-shape of the object be cone-shape it will present the oblique shock-wave,and if the head-shape of the object be rectangular-shape or round/blunt-shape it will generate the normal-shock-wave.If the air-flow be flowing through the normal-shock-wave,the consumed kinetic-energy will be very large and the shock-wave-resistance be the same large,and its flight-speed will always be reduced from supersonic-speed to subsonic-speed that there be a subsonic-area behind the normal-shock-wave.If the air-flow be flowing through the oblique shock-wave,and this oblique shock-wave will not strongly block the air-flow,then its flight-speed will be reduced to some extent and its direction be parallelled to this oblique shock-wave,and the consumed kinetic-energy will be less and the shock-wave-resistance be the same less.The larger the oblique-angle of this oblique shock-wave,the lesser the shock-wave-resistance. As shown in figure,the air-plane  designing for supersonic-flight will form the oblique shock-wave (instead of the normal-shock-wave)on every place of the airframe as far as possible,and the wing's upper/down-surface also be gentle as far as possible so that weakening the strenth of the shock-wave.As the stubby-trapezoid-wing of the Ameriwill X-15 experimental-aircraft hide behind the main shock-wave,then the strength of the wing's shock-wave will be weakened.On the other hand,the sonic-boom coming from the shock-wave will cause negative-effects on the ground-environment and stealth-performance about military-aircraft.

Fig.3

阻力3

4.3.数十年前英法的“协和号”超声速客机一开始就因为“音爆”问题而使其航行范围受到极大限制，业界直到现在也没有能很好的解决这个问题，所以超声速客机目前成了空白，但并不能说这不重要。在航空发达国家一直断断续续有一些这方面的研究，比如美国的降低音爆强度的Quiet Spike（安静长钉）音爆锥技术，音爆锥安装在机头，外形像长矛，主要结构包括三段不同直径的细长筒段，最前端一段直径最小，最后段直径最较大，前端都有锥形过渡段。整个音爆锥能够伸缩，三段全部伸出时形成一个阶梯形的锥形体。音爆锥产生三组相互平行的激波，最后传播到地面，音爆锥形成的激波强度要低于超声速喷气飞机头部附体激波。又比如一种抑制音爆的理论证实，在不增加重量的情况下，尽可能的延长飞机机身能大幅降低音爆的强度，甚至可能将噪音压制到听不到音爆的程度。再比如另一种抑制音爆的理论，飞机机首必须比纯粹的空气动力学原理建议的更钝，而在实验中将飞机机首设计成鹈鹕的喙状，飞机机首产生稍大的气压有助于降低绕整个飞机机身产生的激波的气压。上述理论都是对低超声速飞行领域的减弱音爆的研究，而对于高超声速飞行时更强的激波和音爆的情况的研究却仍然缺少，但是这正是碟形飞行器的消除音爆的特有技术所不惧的。
4.3.The British-French Concorde supersonic-passenger-airliner decades ago that has been greatly limited on the range of navigation because of the sonic-boom problem for the first time,which has not been solved in the field of aviation up to now.So the supersonic-passenger-airliner field has been made up of a blank,but we will not say it is unimportant.There were some studies on this problem have been carried out all the time.For example,The Ameriwill Quiet-Spike research about weakening the strength of the sonic-boom that will fit the sonic-boom-cone on aircraft-nose which look like a spear,and it be made up of three stages of different-diameter-cylinders,in which the  forefrontest stage of cylinder will be the thinnest，and the rearmost stage of cylinder will be the thickest,and both of them have a conical transition-section.This
sonic-boom-cone will wholly stretch out and draw back,and when all three stages be strethed out that it will become a terraced-cone-body.This sonic-boom-cone will generate three conical shock-waves paralleled by each other,then they will be spreaded to the ground,so the strength of shock-waves generated by this sonic-boom-cone will be much less than that of the general supersonic-aircraft's nose.For one instance,one restrict-sonic-boom-theory confirms that the extension of airframe as long as possible will greatly weaken the strength of sonic-boom in the case of without increasing the weight,and even be able to restrict the sonic-boom noise to the extent that human ear willnot hear it.For another instance,another restrict-sonic-boom-theory confirms that the supersonic-aircraft's nose have to be more blunt than the customary proposal of Aerodynamics，and design the supersonic-aircraft's nose into a shape of peliwill's beak in the experiment,then the relative higher air-pressure of the aircraft's nose will help to reduce the air-pressure of shock-wave generating from the whole airframe.The above-mentioned theories will be the study on weakening the sonic-boom of low-supersonic-flight,and the research on weakening the sonic-boom of hypersonic-flight is still suffering from a shortage,but this will be a signifiwillt breakthrough made by the original technology of the saucer-shaped spacecraft.

Fig.4

阻力4

4.4.如果超声速飞行器在不增加重量的情况下，尽可能的延长机身来降低音爆的强度，这种理论在一些民用客机上有一定的实用性，但是在大型的军用飞行器上没有多少价值（只有一些小型导弹可以容忍），因为在机体结构强度和结构重量、内部有效载荷和装载空间等方面都有不可调和的矛盾。一些在设计上不得不又短又粗的大型导弹，如美国的“三叉戟”潜射弹道导弹，就在导弹头部采用可伸缩的“激波杆”（减阻杆）来减小激波阻力，（如作为民用技术也等于降低音爆强度）。其原理是在超声速飞行时将减阻杆伸出，减阻杆的顶端有一耐高热的金属小圆盘，可以在其正前方形成一小范围的正激波，因为减阻杆周围空无一物，所以此正激波演变为弓形激波和斜激波，可以大幅度减弱后部弹体形成的激波强度和阻力。减阻杆的存在相当于大幅度延长了导弹弹体的长度（增加细长比）而减弱了激波。但其在结构强度和结构重量方面却没有太大的牺牲，是一种大型弹道导弹上的实用的设计，但是，其难以进行长时间高超声速机动飞行，因为减阻杆其狭窄的内部无法容纳“冷却循环系统”以对顶端的高温高热进行冷却，其纤细脆弱的结构和角度调节机构难以承受高超声速时的剧烈的机动飞行和激波扰动，这些方面都是用纯机械方式减弱激波的通病。英国油电混合动力技术的超声速公务机概念方案，动力系统采用超导发电机-电动机和航空涡轮发动机原理的全新油电混合推进系统，飞机机鼻前方和机尾后方均安装有可电动控制伸缩的“激波杆”（减阻杆），主要用于来管理高马赫数飞行时产生的激波形状和位置，可以有效稀释和削弱激波压力、改变激波结构，从而获得更好的气动效率；同时该装置可利用机载大功率电源来加热和电离来流空气，产生等离子体，通过等离子体加热来改变局部流场和当地马赫数，进一步降低激波强度，从而达到气动减阻和降低声爆的目的。
4.4.Although the extension of airframe as long as possible will greatly weaken the strength of sonic-boom in the case of without increasing the weight of supersonic-aircraft,and this theory will only be applicable for the supersonic-passenger-airliner,but not be applicable for the large military-aircraft (except for some small missile.). Because of numerous paradoxes between the structural-strength and structural-weight of airframe,between the payload and loading-space in the interior.Some large missiles which have been designed to be short and thick,such as the Ameriwill Trident submarine-launched-ballistic-missile（SLBM）,which will use a scalable shock-wave-rod (resistance-reducing-rod) to reduce the shock-wave-resistance  (or reduce the sonic-boom-strength on the supersonic-passenger-airliner).The theory of this shock-wave-rod is that the aircraft's nose will be stretching out this rod under supersonic-flight,and the top of this rod has a heat-resisting metal-disc,which will generate a small range of normal-shock-wave straight-ahead;because the surrounding of this rod will always be empty space under supersonic-flight,so the normal-shock-wave will always be translated into the bow-shock-wave and the oblique-shock-wave,which will largely reduce the resistance and strength of shock-wave.The existence of this shock-wave-rod will be the equivalent of largely extending the lenght of the missile (increasing the slenderness-ratio.),then weakening the shock-wave.And there is a few sacrifice on the structural-strength and structural-weight of airframe,so it is a actual-designed-method of large-short-thick-pattern ballistic-missile,But it willnot flexibly maneuver-fly for a long time under hypersonic-flight,because its slender-fragile structure and angle-adjusting-apparatus willnot bear the violent maneuver-fly and shock-wave-disturbance,and these aspects will always the common-failing that weakening the shock-wave with pure-mechanical-mode.For instance,a conceptual-design of Supersonic-Business-Jet (SSBJ) in British with petrol-electric hybrid-drive propulsion-system which combining principles of aero-turbine-engine and superconducting-generator-motor,and its nose and tail will both be fited a scalable-power-driven shock-wave-rod,which will control the shape and place of the shock-wave generating under supersonic-flight,and weaken the sonic-boom-strength or alter the shock-wave-structure，then to reduce the shock-wave-resistance.At the same time,it will heat and ionize the air-molecule to generate a plasma-flow with a high-power-supply loading on the plane,and this plasma-flow will alter the local air-flow and flowing-speed to weaken the sonic-boom-strength or alter the shock-wave-structure and reduce the sonic-boom-resistance,then to weaken the sonic-boom-strength in the end.

Fig.5

阻力5

4.5.高超声速飞行器正在发展,一类是“乘波体飞行器”（仍属于一种“高速的升力体”），是用楔形/锥形激波形状用“反设计方法”进行切割组成的楔形/锥形部分体,有三个显著的气动特性：低阻、高升力和大的升阻比;同时， 乘波体的下表面常常设计得较平（甚至下表面向内凹陷），相对常规轴对称飞行器，平坦下表面的乘波飞行器的上/下表面的气压差要大得多，所以升力也大得多；乘波体飞行时超声速气流在下方形成一个激波面，激波面后的气流形成高压区，由此导致高升力；其前缘下表面与所生成的激波的上表面相贴，就象骑在激波（附体激波）的波面上，依靠激波的压力产生高升力。如果把地球的大气层边缘看作水面，乘波体飞行时就像是在水面上冲浪板的冲浪滑行或甚打水漂跳跃式飞行；不过这种乘波体飞行器在高超声速飞行时的姿态调节性能和机动性都比较一般，虽然其“升阻比”较高，却不如一些大型弹道导弹的高机动弹头的飞行姿态更稳定可靠；这是因为高超声飞行都只是在高空的空气稀薄的环境中进行，其各种控制翼面的气动力控制能力都因只与激波和稀薄气体效应有关而会出现异常和不足，而让气动舵面失效;所以“乘波体飞行器”的气动升力和气动控制及机体设计仍有很多矛盾之处。另一类是很多大型弹道导弹的高超声速高机动弹头采用的“双锥形弹头体”设计，再加上适应低速飞行的“十字形气动控制翼面”，到采用“变质心控制技术”，高超声速导弹弹头的姿态和航向的气动控制技术和机动性的发展越来越完善（但双锥体弹头的升力系数及升阻比不高所以横向机动能力不太高），比如美国的潘兴-II导弹到中国的“东风-15A、B、C”系列导弹的发展。但是，因为这些高超声速飞行器都要充分利用激波产生的高升力来进行“低升阻比的滑翔飞行”，所以几乎没有明显的减弱激波（包括减低音爆）的设计，那么其“防热设施”就难以满足更长时间更高超声速巡航的需要。乘波体下表面的“激波”更贴近机体，高温和热量更容易传导进机体内，所以其“气动加热”很严重;有证据表明当飞行速度超过十倍声速后，最困难的技术反而是机体的防热技术，所以似乎仍然有减低激波强度和温度的必要性，而如果减弱了机体下表面的附体激波则升力也同时减小，这很矛盾。而且，所有这些高超声速飞行器的设计都不能在低速时得到高的升阻比，而高速声速飞行器的低速飞行特别是起飞降落时，对升力特性的要求更复杂。
4.5.The studies about hypersonic-aircraft/flight is carrying out recently,and one kind is the waverider（also belonging to a kind of high-speed lift-force-body.） which will use the wedge/cone-shock-wave-shape to make up of a cut-wedge/cone-partial-body with inverse-design-method；and it have three obvious aerodynamic characteristics which will be low air-resistance,high lift-force,and high lift-drag-ratio；And the down-surface of this waverider will be designed to be relatively flat comparing with the usual-axisymmetric-aircraft（even its down-surface will sunken inwards.）,because the upper/down air-pressure-difference of this flat-down-surface-waverider will be more large than usual，so its lift-force will also be larger than usual；The supersonic air-flow will form a planar-shock-wave under the waverider,and the flowing behind this planar-shock-wave will form a high-air-pressure-area,which bring about the high-lift-force；And its leading-edge of airframe-down-surface will close to this planar-shock-wave,which is like riding on the surface of the shock-wave,and that will get a high-lift-force utilizing the high-air-pressure of shock-wave；If we regard the earth's atmosphere-edge as a surface of seawater,the hypersonic-flight of waverider will be looked like a surf-board-surfing or playing ducks-and-drakes on the water；But the maneuverability and attitude-adjustment-performance about the waverider will be very general,although its lift-drag-ratio be quite high,but it willnot as good as the high-maneuver-warhead of large-pattern ballistic-missile which have better stability and reliability of flight-attitude；Because the hypersonic-flight will be flying in the thin-air of upper-atmosphere，and the aerodynamic-control about controlling-wing will be abnormal and deficiency due to the relativity with the shock-wave and the rarefied-gas-effect,then losing efficacy on the controlling-wing;So the aerodynamic-lift-force,the aerodynamic-control,and the airframe-design about the waverider will have many contradictions.
    The other kind is the bicone-warhead-body using on the large-pattern ballistic-missile for high-speed and high-maneuverability;And it add the cross-shaped aerodynamic-control-wing,or adopt the moving-centroid control-technology;Then the attitude/heading-control and the maneuverability about hypersonic-missile-warhead have developed more and more perfect(but the lift-coefficient and the lift-drag-atio about the bicone-warhead-body willnot be high,lateral-maneuverability will also be low.),for instance developing from the Ameriwill Pershing-I,II series missiles to the Chinese DF-15A,B,C series missiles.
    But the flight of these hypersonic-aircraft will only need the shock-wave to generate the high-lift-force and to gliding-fly with lift-drag-ratio,so it has not supply any of the design of shock-wave-weakening(includeing sonic-boom-weakening).Then their thermal-protection-system will do not meet the needs of a more long/highspeed cruise.The down-surface of waverider will be more close to its airframe,so the high temperature and heat will be more easy to conduct into it,and then its aerodynamic-heating will be very serious.There are many evidences confirming that the largest diffculty will be aerodynamic-heating about the airframe when flying at over ten times of sonic-speed,so there is the need of continually reducing strength/temperature-shock-wave,but this will also reduce the lift-force of the hypersonic-aircraft,so it is a contradiction.And all these hypersonic-aircrafts willnot get a high lift-drag-ratio when flying at low-speed,and when it take-off and landing that its needs about aerodynamic-characteristics will be more complicated.

Fig.6

阻力6

4.6.“空天飞机”或“航空航天两用飞行器”要能在大气层内和太空中长时间飞行和如普通飞机一样稳定平衡的起飞降落，但是有时候它们也面临着一个同“高超声速滑翔飞行器”一样的“气动力加热”问题(“防热难题”)，比如其在以高速从太空轨道返回大气层时。美国的航天飞机虽然从太空返回时不能在大气层内以高超声速滑翔，而是下降到中低空时以低速（亚音速）滑翔，但是其返回大气层时的防热技术也很复杂很不成熟而风险很高，还不如一次性运载火箭的飞船返回舱防热技术那么简单可靠和成熟完善。数十年来主要航天强国的大多数宇宙飞船返回舱都有一个凸透镜（大钝头）形体在其底部，圆碟形的大钝头体可以形成大范围的脱体的正激波（或弓形激波），能够得到最大程度的减速,也是最好的防止和对抗激波加热的机体结构（防热面积大易冷却且不与高温激波面接触），也容易通过“自旋”来调节飞行姿态的稳定性参数，而且可以方便的调节“再入角度”而得到纯粹的阻力进行剧烈的减速，或者得到更大的升力以进行所谓的“sanger弹道”机动飞行（美国的“阿波罗”号飞船的再入过程也是如此）。这很能说明一个问题，即“可自旋稳定的圆碟形的飞行器”非常适合返回大气层时的减速和机动飞行。高超声速的“乘波体”飞行时就像是下部脚踩着一个“激波”在滑翔，如同在水里的冲浪板的滑行，而如果是在大气层的高层与太空边缘，有导弹弹头或空天飞机可以一个波谷下降冲入大气层内得到高升力，再以一个波峰上升冲出大气层的反复的“S形跳跃滑翔式飞行”（“sanger弹道”），就像旋转的扁圆的碟形石片在水面上不断“打水漂”，可以更有效更节能,和飞行的更高机动性稳定性安全性。
4.6.The aerospace-planes (or the aerospace-dual-purpose-aircraft) will be required to fly in space and atmosphere for a long time,and also to take-off and landing as stable as the general planes.But they will occasionally confront with the same problem of aerodynamic-heating(or thermal-protection) that facing the Hypersonic-Glide-Vehicle(HGV),for example when it will be coming back into the atmosphere from the space.Although the America's space shuttles willnot be gliding in the atmosphere at hypersonic-speed,and will only be gliding at low-speed(subsonic-speed) when it fall to the middle-lower altitude,but its thermal-protection-technologies have not been mature and safe,and its technologies willnot be as simple/mature as that of the re-entry-module about expendable-launch-vehicle.The most re-entry-modules from the main-space-power-countries that have always had a convex-lens-shaped(or large-blunt-head)-body at its bottom for decades;And this saucer-shaped large-blunt-head-body will generate a large range of detached normal-shock-waves(or bow-shock-wave),and it will get the greatest degree of speed-reducing and the best structure of preventing/resisting shock-wave-heating (because its thermal-protection-area will be big enough,then be easy to cooling the airframe and not to touch the high-temperature shock-wave.),and it will be easy to adjust the stability-parameter of flight-attitude by self-rotating when it re-entrying,and it will also adjust the re-entrying-angle to get the variable air-resistance about speed-reducing,or it will get the larger lift-force to carry out a maneuver-flight of so-call Sanger-trajectory （the re-entrying process about the Ameriwill Apollo-spacecraft will also be the same.）.This proofs that the self-rotating-stable saucer-shaped spacecraft will be very adaptive to carry out a maneuver-flight or speed-reducing when it re-entrying the atmosphere.The hypersonic-flight of waverider will be looked like a surf-board-surfing on the water as it trampling on the shock-wave.If it fly on the earth's atmosphere-edge,then the aerospace-plane or the missile-warhead will fell into the atmosphere with a sinusoidal-trough and get a high-lift-force,and it will once again rush out of the atmosphere with a sinusoidal-peak which will be a repeated S-shape-jumping/gliding-flight(so-call Sanger-trajectory),and it will look like playing ducks-and-drakes on the water with a saucer-shaped stone-flake,so it will be higher efficiency and energy-saving；And it will have the higher maneuverability,stability,and reliability of flight.

Fig.7

阻力7

4.7.“超空泡鱼雷技术理论”下的子弹或导弹或鱼雷要在水下稳定飞行，必须要有一个“气泡”包裹住整个弹体，此气泡可以是高速前进的弹体的特定头部构造在高阻力下拉拽出的一个内部是水蒸汽的低压强的“超空泡”（低压空泡），或者主动往这个空泡内注入大量气体形成一个大型的高压强的气泡;前者多可由小尺寸弹体在高速下自动产生，而后者可以应用于大尺寸船体和低速下的情况，原理都是用空气将物体表面与水体相隔离而大幅减小了阻力。目前这类技术固有的一些缺陷仍未完全克服，比如“超空泡”的尾部碎裂难以控制，以及噪音问题影响武器的隐身性能，而水中飞行的姿态和航向的稳定性/可控制性也太差。
4.7.Under the super-empty-bubble-torpedo-technique theory,bullets or missiles or torpedoes must need a large air-bubble to wrap up the entire projectile-body,and this air-bubble will be a inner-containing-water-vapour supercavity (low-pressure-empty-bubble) with a specific head of high-speed-projectile-body draging forwards under the high-water-resistance,or will proactively pour a great number of gas in it and form a large high-pressure-air-bubble;The former will be generated by a small size projectile-body under high-speed,the latter will be applyed to a large size ship-hull under low-speed;And all the principles will be of insulating the object-surface from water and reducing the water-frictional-resistance.But there were some inherent-defects about these technologies that had not been overcomed until recently,for instance the fracture-process of this supercavity's tail willnot be controlled easily,and the problem of noise will influence the stealth-performance of relative weapons,and the flight-attitude and course-stability/controllability about them will always be very low-level.

Fig.8

阻力8

4.8.考虑到气动力升力、气动力加热、气动力减阻,再加上飞行的机动性、稳定性和安全性等的综合要求，高超声速飞行器的设计概念的难点在于，我们需要导弹弹头或空天飞机以一个波谷下降冲入大气层内得到高升力，再以一个波峰上升冲出大气层的反复的“S形跳跃滑翔式飞行”（“sanger弹道”），更要求其能够“单级入轨和再返回大气层”（多次重复），而不仅只是要求飞行器长时间在大气层内高超声速的平飞滑翔，当然还要考虑其起飞降落的问题。比如美国的X-17实验火箭是首架把钝形头锥与“激波杆”（减阻杆）相融合的再入飞行器，但有一个高超声速飞行器设计的普遍问题就是机体太过细长而容积率太低则结构设计不理想。其他的高超声速再入飞行器的概念设计也越来越成熟（除了过于纯粹的“乘波体”设计多用于理论研究之外，更多的工程实验设计只是在“双锥形弹头体”的基础上的修改性削平设计和补充加入机翼的设计等），但是因为仍然采用化学燃料和现有空气动力学的限制，及耐热材料和冷却技术的落后，这些问题都很难解决。又比如英国的“云霄塔”（SKYLON）概念设计是一种水平起降、单级入轨空天飞行器，目前已取得预冷器技术突破，但只是证明其用化学燃料的吸气式组合发动机原理可行和冷却技术的很大进展，而上述问题仍在。不妨拿一个球体做成火箭来研究，因为可以分析高超声速飞行时“激波”和“减阻增升”（减小阻力、增加升力）的一些关系。“球体”做火箭以高超声速飞行时，在其前方形成的是一个“正激波”，（正激波然后向旁边演化成“弓形激波”），正激波对飞行器的激波阻力在所有形式的激波中最大，所以要减小激波阻力就需要将其变成“斜激波”，这可以是通过前部加上一个机械的“激波杆”（减阻杆）来实现，而前方来流经过斜激波后的流动方向都会被向外偏斜一个角度，所以此利用多重斜激波来减阻的原理可粗略看作一事，即在多重斜激波之后的被偏斜的前方来流将减少与后方机体的正面相撞（前方来流的动能损失将较小，前部机体表面的静压的增长率将不太高。）如图所示，“激波杆”（减阻杆）在球体前方形成多重（至少三重）斜激波，而最后在球体前面形成的只是一个“很弱的正激波”（此正激波的强度、温度、密度等都已大幅减低），而高超声速时“气动加热”的强烈性让减阻杆必须做得较粗大以容纳复杂的“强制循环冷却系统”。但是一个纯粹的球形火箭的机体本身在空气稀薄的高空以高超声速飞行时不会产生升力（激波升力），（一个纯粹的球形的飞行器只能在亚声速（低速）飞行时用自身的旋转产生附着涡而得到涡旋升力，即所谓“马格努斯效应”或“香蕉球效应”），所以此时产生主要的激波升力的只有前部的粗大的圆柱形减阻杆（以一定飞行迎角时）;但是其前部加了一个粗大又长的“激波杆”（减阻杆）之后，因为前部此杆的阻挡前方来流的效应（有较大的迎角飞行时），所以让后部的球形体的上部激波减弱而下部激波增强而得到了“上下压差升力”（下部产生的是激波升力）。那么，这会是一种机体内部有较大容积和空间的火箭及可以在大气层内持续平飞的高超声速飞行器；因为其内有大容积和空间可以载人而成为一个载人飞船的返回舱，也算是那种经典的“钟形返回舱”相似物；但是其有更多的优点，即其在返回大气层后还可以像“航天飞机”一样持续平飞较长时间并像“可回收火箭”一样的垂直降落。而为了在飞行时增加升力，可以把此球体火箭的下半部削得比较平坦，使其成为一个更好的“升力体”或“乘波体”，或者更可以干脆用一个扁碟体来代替（特别是碟体的下部比上部更加平坦），则产生的激波和得到的激波升力比较理想（碟形飞行器仍然需要在超声速飞行时有一定的飞行迎角），如果其下部的激波比较贴近下部机体表面蒙皮而成为“附体激波”，则此扁碟体就是一个“乘波体飞行器”，其上部和下部机体可以以相反的方向旋转而得到飞行稳定性，而中部机体有多个“矢量喷口”可以调节飞行姿态和航向稳定性/可控制性等，这就是“碟形飞行器”在高超声速飞行时的机械式的原始模型。
4.8.In consideration of the comprehensive requirements about aerodynamic-lift-force,aerodynamic-heating and aerodynamic-resistance-reducing,plus maneuverability,stability,and reliability of flight;The difficulties of Design-concepts about hypersonic-aircraft will lie in that we will need the aerospace-plane or the missile-warhead,which will fell into the atmosphere with a sinusoidal-trough and get a high-lift-force;And it will once again rush out of the atmosphere with a sinusoidal-peak,which will be a repeated S-shape-jumping/gliding-flight(so-call Sanger-trajectory);And the further requirements will be the technologies of Single-stage-to-orbi(SSTO) and reentry-atmosphere（multiple repetitions）；Not just require it will be flying-level and gliding in the atmosphere under hypersonic-flight;Of course the problem of taking-off and landing have also to be considered.For instance,the X-17 experimental rocket in the United States had been the first reentry-vehicle which will mix together the blunt-nose with the resistance-reducing-rod(shock-wave-rod);But there is a general problem of designing the hypersonic-aircraft,that the airframe will be too slender and the capacity rate will be too low,then the structural design will be not ideal.And the other concept-designs have also be more and more mature (except for the too-pure waverider-concept-designs will be more regarded as the research-objects of theory,but the designs on engineering-experiments will more often be the designs of modified-flattening or the supplementary-wing on the basis of bicone-warhead-body.).But because of the limits about the chemical-fuel and the Aerodynamics at present,and the backwardness about the heat-resistant material and the cooling-technology,solving these problems had been very difficult.For another instance,the British Skylon aerospace-plane had been a concept-design for horizontal take-off and landing（HOTOL）,Single-stage-to-orbi(SSTO);And it had achieved a technological breakthrough about precooler-technology,but it had only proved the feasibility about the Airbreathing-Combined-Engine and the great progress about the precooler-technology(cooling-technology),then the above problem will still be there.For instance,we will design a missile made by spheroid,then to study the relativity between the shock-wave and resistance-reducing/lift-force-increasing under hypersonic-flight.When this spherical-missile will be flying at hypersonic-speed in the atmosphere,there will be a detached normal-shock-waves right in front of its airframe(and this normal-shock-waves will evolve into the bow-shock-wave towards both sides.);The normal-shock-wave will generate the largest shock-wave-resistance against the aircraft in all kinds of shock-wave,so we will only replace it with a series of oblique-shock-wave if we want to reduce the shock-wave-resistance;And this practice will be carried out by fiting a shock-wave-rod(resistance-reducing-rod) in front of its nose(head),and the incoming-flow will be obliqued outwards a angle when flowing through the oblique-shock-wave;So the principle of multiple-oblique-shock-wave-resistance-reducing will be roughly regarded as something,that the obliqued incoming-flow behind the multiple-oblique-shock-wave will reduce the positive-impact to the airframe(the incoming-flow's kinetic-energy will loss less,and the growth-rate of the static-pressure about front-airframe-surface will not be too high.).As shown in the figure，the resistance-reducing-rod(shock-wave-rod) will form the multiple(at least threefold)-oblique-shock-wave on its oblique-surface,and in the end it form a very weak normal-shock-wave in front of the spheroid(and this normal-shock-wave's strength,temperature,and density have been very low.)；and the violent aerodynamic-heating under hypersonic-flight will oblige this resistance-reducing-rod(shock-wave-rod) to be enlarged to the extent that be able to contain a complicated forced-circulatory-cooling-system.But a pure spherical-missile willnot generate the aerodynamic-lift-force(shock-wave-lift-force) under hypersonic-flight (and a pure spherical-aircraft will only generate the vortex-lift-force by rotating itself and generating the attached-vortex under subsonic/low-speed-flight,which will be so-call Magnus-effect （banana-ball-effect）.);So at this moment,the main component generating the shock-wave-lift-force will only be the large/long part of this resistance-reducing-rod(shock-wave-rod) (when flying at a certain angle-of-attack.)；But when this large/long resistance-reducing-rod(shock-wave-rod) has been added to the front of this spheroid,and its obstruct-effect on the incoming-flow(when flying at a relatively large angle-of-attack.),so it get the lift-force of upper/down-air-pressure-difference,which weankening the down-shock-wave-strength and strengthening the upper-shock-wave-strength (its underpart will get the shock-wave-lift-force.).And then it will be a missile which have relatively large volume and space,or be a hypersonic-aircraft which will be flying-level for a long time；Because it have relatively large volume and space that it will carry people and become a kind of re-entry-module about manned-spacecraft,which will also be regarded as the kind of classical Bell-shaped-re-entry-module likeness；But it has a lot of advantages,namely when it re-entry into the atmosphere it will be flying-level for a long time as the space-shuttle,and will be vertically taking-off and landing (VTOL) as the recoverable-rocket.If we want to add the lift-force to this spherical-aircraft when flying under hypersonic-flight, we will flatten the bottom of this spheroid,and make it become a better lifting-body（or waverider）,or we will replace it with a saucer-shaped-body (especially that its under-part will be more flatter than its upper-part.)，then it will be generating the relatively ideal shock-wave and getting the relatively ideal shock-wave-lift-force (when flying at a certain angle-of-attack under hypersonic-flight.);If its down-shock-wave will close to the skin of airframe-down-surface and become the attached-shock-wave,that it will become a kind of lifting-body（or waverider）;and its airframe-upper/under-part will get the flight-stability by respectively self-rotating on opposite directions with each other;And on the middle-part-circumference-edge of airframe,there will be a lot of thrust-vectoring-nozzles to adjust the flight-attitude and course-stability/controllability.It will be the initial-model and mechanicaland-model about the saucer-shaped spacecraft.

Fig.9

阻力9

4.9.由上述分析得知，“碟形飞行器”机械式模型对激波、升力、减阻、防热等的处理技术也是机械的和被动的方法，难以进一步发展，也不要说消除音爆。但随着近来磁流体力学（等离子体和离子流）结合空气动力学方面和“全电化飞行器”方面的新进展，其为电磁流体空气动力学（电磁空气动力学）提供了信心。“碟形飞行器”将被完全电器化、电磁化、电离化、全电化，包括了流体和流场的电离化，以及电场和磁场对流体控制方面。“碟形飞行器”前部设有一种类似“激波杆（管）”的装置，为“等离子体激波管（兼X射线激光器及旋转超导线圈磁芯）”，但因为“碟形飞行器”中部圆盘形离子推进发动机也是一种“离子束武器”，让其从前部的激波管中喷射出经电磁作用箍缩的高速“离子束”（多梯度多层次多脉冲的），得以在前方的空气中激发出多重的“斜激波”，而且“碟形飞行器”已经先一步从激波管中向前方喷射出高速“电子束”和“锥形的X射线激光”，正是为把这些多重的斜激波完全“电离化”，那么，进一步将激波管内的通电超导线圈的磁芯（一组环绕成圆周形式的）高速旋转起来，即是形成一个机体头部的“旋转磁场”，此磁场高速旋转可以把上下方的斜激波内的正离子流全都向飞行的中轴方向拉拽，即把斜激波“变弯、变厚、减弱、分解”，而“碟形飞行器”的顶部和底部也各有一个强大的高速旋转的“旋转磁场”，最终把上下方的所有斜激波的尾部完全分解消失掉。如果“碟形飞行器”的中部的推进发动机工作时，其喷射出的离子喷流也是经电磁方式箍缩的高速“离子束”，而不会形成“喷流中的激波”，那么“碟形飞行器”的整个飞行流场都没有“音爆”和“激波”（及膨胀波）从天空向地面和各方向的传导，将有可能达到真正“声音隐身”。
4.9.The above analysis shows that mechanicaland-model about the saucer-shaped spacecraft will have to dispose the shock-wave,lift-force,resistance-reducing,and thermal-protection with mechanism-methods and passive-methods,and willnot develop further,and not to speak of the sonic-boom-weakening.But in the wake of fresh developments in the aspect of Magneto-hydrodynamics (MHD)（magneto-fluid-mechanics）（plasma and ion-flow) combining with Aerodynamics and the aspect of all-electrification of aircraft in Aeronautics recently,it will provide confidences in the present of the magneto-fluid-aerodynamics (or the electromagnetic-aerodynamics).The saucer-shaped spacecraft will be completely electrifyed,electromagnetized,ionized,and all-electrifyed.And this will be included the ionization about fluid and flow-field，and controlling the fluid and flow-field with the electric and magnetic fields.The front-head(nose) of the saucer-shaped spacecraft will be fited a shock-wave-rod(tube) likeness,which be so-called the plasma-shock-tube(including a X-ray-laser and a rotating superconducting-coil-magnetic-core);And because the central section disc-shaped ion-thruster about the saucer-shaped spacecraft will be a kind of ion-beam-weapon,and it will spout forward a beam of high-speed ion-beam （multi-gradient，multi-level，and multi-pulse） which be pinched by electric and magnetic fields from this plasma-shock-tube,and this will stimulate the multiple oblique-shock-waves in the incoming-flow,and the high-speed electron-beam and the conical-X-ray-Laser will have been spouted forward by its plasma-shock-tube one step ahead,then to completely ionize this multiple oblique-shock-waves. Then we will rotate the electrified superconducting-coil-magnetic-core(a group of it surround into a circle.) in this plasma-shock-tube with high-speed,and it will generate a rotating-magnetic-field on the nose(head) of the airframe;And this high-speed-rotating rotating-magnetic-field will drag the positive-ion-flow in this oblique-shock-waves towards the flight-central-axis from both of top and bottom;Namely we will be bending,thickening,weakening,and decomposing this multiple oblique-shock-waves;On the same time,there is a strong high-speed-rotating rotating-magnetic-field respectively on the top and bottom about this saucer-shaped spacecraft,so it will completely decompose all the tails of this multiple oblique-shock-waves in the end.And when the central section disc-shaped ion-thruster about this saucer-shaped spacecraft will be working,if its plasma-jet-flow will also be pinched by the electric and magnetic fields and willnot generate the shock-wave-in-jet，then the whole flow-field of this saucer-shaped spacecraft will have not the conduction of sonic-boom from sky to ground and towards all directions,so it will may achieve the real sound-stealth.

Fig.10

阻力10

4.10.根据激波的空气动力学特性，前方来流经过多重斜激波之后将会很大程度的被偏斜和被减速，而碟形飞行器表面的“升力涡旋”和“附面层”也会受到前方来流的扰动并出现一些人眼可观察到的“气动力现象”，比如在唯一的碟形飞行器的两倍声速飞行的照片中，其提示出很多与我们现代空气动力学原理上的相似现象。如图所示，碟形飞行器的在低空低速飞行时的升力是由“升力涡旋”产生的，其叫做“特异性二三维结合环形分离涡”（“奇异涡环”）;而在升力涡旋与机体表面之面有一层“附面层”（边界层）流体，而这个附面层可以很厚和停滞（不影响升力值）并注入“低温液氮/氦”进行冷却。在图中可看出，此照片中的飞行物应该是与我们的设计一样是用了低温液氮/氦来注入表面的附面层，不但可以冷却而且可以伪装成云团；但是因为此云在两倍声速来流的吹袭下,此云仍然不太过于变形，则可以看出云团内有碟形的固体物；并且因为该物体以两倍声速飞行下，机体表面的云雾仍不被吹散，说明机体表面周围一定有一个稳定的透明的流体层形成的一个流场来保护着它。而且，在高速飞行物体的顶部中心向后上方脱离着一小团云团，而这个小云团也很稳定不被高速的来流吹散，可见这个顶部的小云团也一定是被一个管状的流动流体层所保护着。其实从上述我们的设计中可找到答案，即这个碟形的被云团保护的飞行物的顶部小云团正处于“第二涡核”之内并受其保护着，而“第二涡核”（就像“台风中心的涡核的管壁”）的内部是一个稳定的“管状流动的低压区（或回流区）”可以维持和保护这个小云团（不被高速来流吹散），其实这个小云团也只是一个现代工业通常意义上很常见的“管形旋流中心的回流流体团”。这个顶部小云团的出现说明了碟形飞行器在两倍声速飞行时，其机体上部表面的“升力涡旋”也没有被消融散去，也许仍然用于产生部分升力。但从图中看到此“升力涡旋”的“第二涡核”很低矮，不但说明其在两倍声速平飞时机体上表面产生“气动力升力”的作用已经大幅度减少，而且其被前方来流吹袭的严重程度不大，也说明了前方来流确实是被前方的多重斜激波所减低速度和偏斜了流动的方向，所以才可以保留了机体上表面的此“奇异涡环”和其中的“第二涡核”。如图所示我们在原有照片基础上作了有关碟形飞行器超声速平飞时机体前方有关斜激波和弓形激波的虚拟图，一个机体头部的“旋转磁场”高速旋转，可以把上下方的斜激波内的正离子流全都向飞行的中轴方向拉拽，即把斜激波“变弯、变厚、减弱、分解”，而“碟形飞行器”的顶部和底部也各有一个强大的高速旋转的“旋转磁场”，最终把上下方的所有斜激波的尾部完全分解消失掉。所以在科学研究的方法上，我们是可以通过照片来分析碟形飞行器的空气动力学特性的，也可以初步证实我们的设计上的正确性。
4.10.According to the aerodynamic-characteristic about the shock-wave,the incoming-flow will be decelerated and deflected to a great extent after passing through the multiple oblique-shock-waves；And the lift-force-vortex and the boundary-layer will also be disturbed by this incoming-flow and represent some obviously visible aerodynamic-phenomenoa.For example,in the unique photo about the saucer-shaped spacecraft under the twice sonic-speed-flight,there are a lot of similar phenomena about Aerodynamics.As shown in the figure,the lift-force of the saucer-shaped spacecraft that flying at low-speed and low-level will be generated with lift-force-vortex,which will be so-called the specific two-dimensional and three-dimensional combined annular-separation-vortex (singular-vortex-ring);And there will be the boundary-layer between this singular-vortex-ring and its airframe's surface,which will be very thick and standstill(but not influence the lift-force.),and this boundary-layer will be injected the low-temperature liquid-nitrogen/helium for cooling the airframe-surface.As shown in the photo,this flying-object will be sure that inject the liquid-nitrogen/helium into its boundary-layer,and it will be not only for cooling but also for disguising itself as a cloud;But because this cloud willnot still be too deformed when flying at twice sonic-speeds,so it will be seen that there is a saucer-shaped solid-object in this cloud;And because this saucer-shaped solid-object will be flying at twice sonic-speeds and the cloud/mist on its surface willnot still be blown away,so it shows that its airframe-surface will be surrounded by a stable and transparent fluid-layer which is forming a flow-field to protect it.And there is a small detached-cloud towards the back above the top of this high-speed-flying object,and this cloud seem to be very stable and willnot be blowed away by incoming-flow,so it show this cloud must be being protected by a tubular-flowing-fluid.We will find out the answer from the above-mensioned design about the saucer-shaped spacecraft,and this small cloud above the top of this saucer-shaped protected-in-cloud aircraft seem to be protected in the second vortex-core（hurricane/typhoon likeness） of the singular-vortex-ring,and there is a stable tubular-flowing-low-pressure-area(or recirculation-zone) in this second vortex-core (which will look like the vortex-core-tube-wall of hurricane/typhoon-center.),which will protect and maintain this small cloud.In fact,this small cloud will be a common back-flow fluid-mass in the tubular-rotating-flow-center in industrial field.The present of this small cloud above the top of this saucer-shaped spacecraft shows that the lift-vortex willnot still be dissvolved,and it may still be used to generate a part of lift-force;But we will see from the figure that the second vortex-core in the lift-vortex about this saucer-shaped spacecraft seem to be very low,and the generated-lift-force of the airframe-upper-surface has been substantially reduced when it has been flying at twice sonic-speeds,and its lift-vortex willnot still be substantially blowed by the incoming-flow,and at the same time it will illustrate that this incoming-flow has been actually decelerated and deflected by the front multiple-oblique-shock-wave,so it will protect and maintain its whole lift-vortex(singular-vortex-ring) and its second vortex-core within.As shown in the figure,we have drawn a virtual gragh about the multiple-oblique-shock-wave and bow-shock-wave in front of this saucer-shaped spacecraft on the basis of the original photo;So we will see that there is a high-speed-rotating rotating-magnetic-field,which will drag the positive-ion-flow in this oblique-shock-waves towards the flight-central-axis from both of top and bottom;Namely we will be bending,thickening,weakening,and decomposing this multiple oblique-shock-waves;On the same time,there is a strong high-speed-rotating rotating-magnetic-field respectively on the top and bottom about this saucer-shaped spacecraft,so it will completely decompose all the tails of this multiple oblique-shock-waves in the end.So it seem to confirm that we will analyse the Aerodynamic-characteristics about the saucer-shaped spacecraft with the photo on the scientific-research-methods,and it will initially prove the correctness of our design about it.

Fig.11

阻力11

4.11.为了消除“音爆”和“激波噪声”，如上所述已经对碟形飞行器飞行前方产生的激波进行了处理，是用旋转磁场和固定磁场对电离化的激波进行约束和减弱分解掉了，机体上下部都不会有激波再向地面传导。另外，碟形飞行器的中部的“离子电推进发动机”，在用“推力矢量喷嘴”向后方喷射时，也需要采用消除“喷流激波噪声”的技术；其发动机内的离子流是通过“推力矢量喷嘴”的磁力线的引导约束下才喷出的;喷射的离子流必须有很高的压缩性（细小的束流）和不能在短距离内扩散也不能有“排气羽流(羽焰)”，防止高速喷流与周围环境的空气相互作用形成“喷流激波”;其在“射流喷管”（推力矢量喷嘴）管壁上用超导线圈形成约束磁场，并首先向尾部的远距离喷射高速负电子流在远方形成带负电荷的空气区域或负电场，而在碟形飞行器机体表面布置成带正电荷的电场区域;当在喷管管壁上的超导线圈外形成一个脉冲磁场时(在超导线圈中通入脉冲电流)，同时机体表面的正电场与远方负电场的空气区域之间形成了一个电压差，则矢量喷口喷射出的等离子体流内部就形成了感生电流和恒定电流，从而强电流使得等离子体喷流受到箍缩和压缩;而等离子体喷流本身也是一个优良的导电体，所以机体表面的正电场与后方远处被电离的空气区域的负电场之间也形成了一个恒定电流，则包围住此等离子体喷流的周围的被电离空气容易被向着轴线方向箍缩,即等离子体喷流的内外压力达到平衡，而不会让喷流与周围空气之间相干而形成一系列的“喷气马赫环”（菱形激波或马赫盘shock diamonds or Mach disks）;所以碟形飞行器的发动机喷射的等离子体流及其周围的空气流场也都保持箍缩和压缩状态一直到远方而不容易扩散（也不会出现尾部的排气羽流(羽焰)），则其在大气层中可以成为中近程的离子束武器（还需用激光加热前方的空气通道）。所以碟形飞行器的喷流尾迹可以呈现为一个很长的连续的发光条带而不散乱，所以其超音速喷流中不会产生喷流激波噪声。那么碟形飞行器就在高速飞行中机体的前后都消除了激波噪声和普通噪声，而达到真正的“声音隐身”。
4.11.In order to eliminate the sonic-boom and the shock-wave-noise,as mentioned above,we have deal with the shock-wave that generating in front of the airframe,and we will restrict,weaken,and decompose the ionizing shock-wave with the rotating-magnetic-field and the fixed-magnetic-field,and there willnot be shock-wave that generating from above or below it to conduct towards the ground.On the other hand,when the thrust-vector-nozzle about the central section disc-shaped ion-thruster spout backward the ion-flow,that it will also have to eliminate the jet-flow-shock-wave-noice;And the ion-flow in the ion-thruster will be spouted out under the restricting and conducting of the magnetic-field inside the thrust-vector-nozzle；The spouted-ion-flow must have been compressed at large extent and not be spreaded in short distance and not form the exhaust-plume behind its nozzles,to prevent the high-speed-jet from the surrounding air to generate the jet-flow-shock-wave with each other;And there are some superconducting-coils that forming the restrictive-magnetic-field on the pipe-wall of its jet-nozzle(thrust-vector-nozzle),and it will firstly spout the high-speed negative-electron-flow towards the rear distance to form a negative-electric-field or a negative-charge air-area,and will fit a positive-electric-field on the airframe's surface of the saucer-shaped spacecraft;When we form a pulsed-magnet-field aroud the superconducting-coil on its pipe-wall of jet-nozzle(thrust-vector-nozzle)(when we flow a pulsed-electric-current into this superconducting-coil.),and at the same time there is a voltage-difference that generating between the positive-electric-field and the negative-electric-field,then there will be a induced-electric-current and a steady-electric-current that forming inside the plasma-jet-flow spouted from the jet-nozzle(thrust-vector-nozzle),so the strong electric-current will pinch and compress this plasma-jet-flow；And this plasma-jet-flow will also be a good conductor of electric-current,so there will be a steady-electric-current that forming between the positive-electric-field of the airframe's surface and the negative-electric-field of the rear distance,so the ionized-surrounding-air around this plasma-jet-flow will also be pinched towards the axial-line-direction;Namely the internal and external pressure of this plasma-jet-flow will achieve an equilibrium,so it willnot generate the interaction-effects between this plasma-jet-flow and its surrounding-air that to form a series of shock-diamonds or Mach-disks;So this plasma-jet-flow and its surrounding-air-flow-fields will always be pinched and compressed up to the rear distance and not easy to spread towards all direction and generate the exhaust-plume behind the airframe，then it will also be used to act as a an intermediate or short range of Ion-Beam-Weapon (but it will also need to be heating the front-air-passage.).So the wake-flow of jet-flow about the saucer-shaped spacecraft will be being presented a continuous-luminescent-strip and not to spread out;So there will not be the jet-flow-shock-wave-noice in its supersonic/hypersonic jet-flow;Then the saucer-shaped spacecraft will eliminate the shock-wave-noice and general-noice at the front and rear of airframe under high-speed-flight in the atmosphere,so to achieve the real sound-stealth.

Fig.12

阻力12

4.12.碟形飞行器最适合在水中飞行，可以克服现有一切“水下超空泡航行器”的缺点;碟形飞行器可以在围绕机体表面形成的“等离子体环流（光环）”;此一圈圈的等离子体环流都从机体顶部或底部的“等离子体环流（光环）发生器”处产生，但是此光环在机体表面仍然被一个均匀的“机体表面固定磁场”所约束，并在圆盘外边缘处自动破裂（通常地此机体边缘的光环的的破裂不会产生强的噪声）;破裂后的离子流体在机体表面磁场的约束下再次从外围向圆心处挤压成一个“平面涡旋”，并由顶部或底部的“吸气口”再吸入而循环使用;其中，碟形飞行器的前部伸出一个“水蒸汽喷嘴”喷出的是“高温水蒸汽”注入到上述的高温等离子体流形成的“平面涡旋”中，与其一起形成一个由“高温水蒸汽和离子流混合的超空泡”(即组成一个水中的“磁场控制的磁流体超空泡”)。上述包裹住整个碟形飞行器的超空泡是一个高温高压的扁球体形，其中大部分流体被电离则处于强磁场的约束下，并最后被“吸气口”吸入再使用，所以不会破裂形成小气泡和噪声，而且超空泡的高压强适用于低速水下航行或暂停时保持其完整性。水下高速航行时碟形飞行器的姿态和航向的调节都由中部离子电推进发动机的大量“推力矢量喷嘴”喷射出高速且压缩的等离子束流来进行，不但灵敏度和机动性高而且不会产生“喷气激波噪声”（但也许会在尾迹中产生大量高温水蒸汽汽泡）。碟形飞行器在水下高速航行时，机体表面一圈圈的“等离子体环流（光环）”在强磁场的约束作用下，被当成为整个“超空泡”的坚固的“骨架”（也是一种含有强大的感生电流的“磁流体装甲”），而离子流动的“平面涡旋”被当成为坚韧的“肌肉”，所以此“磁场控制的磁流体超空泡”不会在高速水下航行时过度变形破损而影响其机动性和稳定性。
4.12.The saucer-shaped spacecraft will be most suitably flying under water,and to overcome the same defect of all the submarine Supercavity-Vehicle;And it will form the plasma-circumfluences(a ring of light) around the airframe's surface which generated by the plasma-circumfluence(ring-of-light) generator that lie in the airframe's top/bottom,and that these plasma-circumfluences(ring-of-light) will be expanded from the center to the periphery which is a multi-ring structure;but this plasma-circumfluence(a ring of light) will also be steadily constrained by a symmetrical fixed-magnetic-field of the airframe's surface,till it be broken by self at the outer margin of airframe(generally its breaking willnot generate a strong noice.);The broken ion-flow will be squeezed from the periphery to the center about airframe under the constraining of the fixed-magnetic-field,and to form a planar-vortex，then these fluids will be inhaled and reused by the air-entry that lie in the airframe's top/bottom;Among them,there is a steam-nozzle will be stretched forward in front of its airframe,which will spout out the high-temperature-water-vapour and injet to the planar-vortex that made up of ion-flow,and form together a supercavity that made up of mixture of high-temperature-water-vapour and ion-flow(namely made up of a maginetic-field-controlled magnetic-fluid-supercavity under water).The supercavity that packaging the whole saucer-shaped spacecraft that will be a high-temperature/pressure oblate-spheroid among which a majority of fluids will be restrained by the strong magnetic-field,and will be inhaled and reused by the air-entry in the end,so there will not beminute-bubbles/vacuoles and noise that will be generated，and the high-pressure of the supercavity will be suitable for the underwater-navigation at low-speeds and for keeping its integrity when it is suspending;Its adjustment of attitude and course while underwater-navigating at high-speeds will be carried out by spouting  out the high-speed ion-flow from the jet-nozzle(thrust-vector-nozzle) of the saucer-shaped spacecraft,and it will not only have the high sensitivity and maneuverability but also have not the jet-flow-shock-wave-noice,but perhaps it will generate a lots of high-temperature water-vapour-bubble in its wake.When the saucer-shaped spacecraft is navigating under water at high-speeds，the plasma-circumfluences(a ring of light) around the airframe's surface constrained by a strong magnetic-field that will be acted as the firm skeletons of the whole supercavity(which will be a strong magnetic-fluid-armor with the induced-electric-current.),and the ion-flowing planar-vortex will be acted as the tough muscles of the whole supercavity,so this maginetic-field-controlled magnetic-fluid-supercavity willnot be badly deformed and broken to influence its stability and maneuverability while navigating under water at high-speeds.

地球全力

据前述，“飞碟”作为宇宙中最强大的战斗机！主要是在太阳系或恒星系内飞行和战斗，其主要的战场反而不是太空中的真空环境！反而是要在有可怕的电磁风暴和引力的太阳上和巨型气态行星的冰冷狂暴的大气层内飞行和战斗！那么，这种人类发明的“宇宙的第三大类涡旋”（奇异涡环），就是专门为此两种宇宙中最艰难的飞行环境而特别创造的专用品！而“飞碟”在太阳系内飞行和战斗的速度自然不能太快，其最大速度一般不超过百分之十光速（甚至可能的巡航速度只是百分之一光速），而更多时候是用太阳或主要气态行星的大气层或电离层来进行飞行的减速或停止等，而在太阳系的整个黄道面内都可以分布有“太空加油站及停泊港”，其可以使用“纳米微粒或气凝胶式磁流体的减速轨道”等把飞碟进行安全阻拦减速和停止。这主要也是与“飞碟”的主要核发电机只有一种即“反物质核发电机”有关，这是最浪费能源的一种发动机，但这是战斗机的机动性要求所决定的没办法！

那么，下一步我们将谈到更复杂更恐怖的“雪茄型太空母舰”的结构设计和创造！“雪茄型太空母舰”才是能实现“恒星际远程航行”的目标飞船，其上同时包含了“三大类的核能发电机或者反应堆”！这是为了在更高的“恒星际远程航行的终极速度”下更好的节减能耗！而“雪茄型太空母舰”的“星际航行结尾”的减速原理则将更加复杂！另外，“雪茄型太空母舰”和“飞碟”上都装备有的“反物质核发电机”，也是多种原理相较之下的精选精品，是真正实现“星际文明”的最后保障！

地球全力

上述有关“电磁控制激光等离子体减阻”的图片发错了，修改了一下图片。其实“超声速减阻”这方面本来没有多少新东西，因为听说国外研究超声速飞行器的“激光等离子体减阻”，从上世纪七十年代的第一代激光装置出现的十年后就开始了，而在前两个十年里，我国国内似乎也做了不少研究算是成熟了吧。现在我只是在“激光或局部能量点源”、“等离子体逆向喷流”之后再加上了一些“稳恒电磁场和旋转电磁场”罢了，没什么太多的新意。
不过，从破解“先进星际文明飞碟”的“电磁控制激光等离子体减阻”机理，也许可以证明我们地球的现代空气动力学的发展方向是正确的。而上述的所谓全新的学科--“电磁控制等离子体空气动力学”，其实也早在国外上世纪美苏冷战时期，当苏联美国的宇宙飞船返回舱以高速返回大气层时，形成包裹舱体的高温等离子体造成的高温烧蚀问题，大家就开始构思“未来可用强磁场控制等离子体解决返回舱的烧蚀问题”了，只不过是受制于“航空航天器的核能发电机小型化问题”和“超导磁体的常温化轻量化问题”等等，没有进展。
而且，如果说未来航空航天领域真的会形成一个全新的学科--“电磁控制等离子体空气动力学”，那么不仅仅是要有“电磁场激光等离子体减阻”，还得有核发电机系统内部的“电磁控制等离子体的涡轮发电和磁流体发电”，最后还得有“先进星际文明飞碟”的产生中低速飞行时主要气动升力的“宇宙的第三大类涡旋”(奇异涡环)，这是个核心问题。

地球全力

下面就来简单描述一番‘太空母舰’的飞行情况，包括其在各行星和太阳上大气层中的机动作战飞行，和数十年上百年时间的数光年远的恒星际航行。
主要是这种宇宙最高级别的飞行器结构和原理太难太复杂了，所以只能在此简化图形ｐｐｔ表示，其中的物理逻辑暂时提到的也不算多，仍值得有创造力的学者先一步去思考辨别之。
但今后有的是时间慢慢研究讨论，航空航天界对此的争吵辩论也许可以长久到未来数十亿年后太阳变成白矮星为止。

地球全力

5.“雪茄型太空母舰”作为“碟形飞行器”的母舰，可以带领大群机队在恒星系的太空中、大气层内、海面下飞行和作战。
5.The cigar-shaped spacecraft-carrier will be the mothership of the saucer-shaped spacecraft,will carry a large fleet fighting in the space,in the atmosphere,and under the sea surface about a stellar system.

如前所述，“碟形飞行器”只是作为一种“航空航天两用战斗机”，只能在一个恒星系内飞行作战，而想要跨跃到另一个恒星系去作战就力所不能了，所以必要有一种大型的“太空母舰”作为其载运母舰，就如同现代的普通海上的“航空母舰和其舰载机”一样的角色。

As shown previously,the saucer-shaped spacecraft which as a aerospace dual-purpose fithter,will only fight in one stellar system.And if it want to stride to another stellar system for fighting,it will need one kind of large spacecraft-carrier that as a mothership, which will play the roles of the modern aircraft-carrier and its carrier-based aircrafts.

如前所述，“碟形飞行器”的内外结构和功能都已经被明确剖析，那么与其在同一科技水平的“太空母舰”的结构和功能也类似。比如，“太空母舰”在恒星际的空间飞行时，其主要能源是“核聚变核能”(但在太阳系内飞行时可以是“反物质核能”）；其推进发动机也是“离子电推进发动机”；而且也包括了“普通直线式离子流加速器”和“圆盘形(包含环管形)离子推进发动机（类似托卡马克装置）”，都兼作为进攻或防御性的定向能武器（粒子束武器和伽马射线激光武器）；而其在大气层内飞行时产生空气动力学的升力和控制阻力，也是采用了电场磁场控制的电离化的“奇异涡环和激波”，特别是在垂直起飞降落（V/STOL）或低速时采用这种全新的“奇异涡环”得到气动升力；而其在海面下航行时也一样是采用电场磁场控制的含有强的感生电流并成为箍缩状态的“等离子体环流（光环）”作为超空泡的“骨架”，及与“离子流和高温蒸汽混合成的旋性流体”组成一个水中的“磁场控制的磁流体超空泡”。

As mentioned earlier，the structure and function of the saucer-shaped spacecraft have been clearly dissected,then that of the spacecraft-carrier will also be revealed,because both of which have the same level of science and technology. For example,when the spacecraft-carrier navigating in the space between the stars,its major energy will be the nuclear-energy of nuclear-fusion（but will be the antimatter-nuclear-energy when flying in the solar-system.）;And its propulsion-engine will also be the ion-electric-thruster,which also include the ordinary linear-accelerator and the disc-shaped(include loop-tube-shaped) ion-thruster(tokamak-devices likeness),and both of which will be acted as the offensive/defensive Directional-Energy-Weapon(ion-beam/neutral-particle-beam-weapon or gamma-rays-laser). And its mathods of generating the aerodynamic-lift and controlling the air-resistance that will also be of controlling the ionized singular-vortex-ring and shock-wave with the electronic-magnetic field，especially adopting this whole new singular-vortex-ring to get the aerodynamic-lift when in vertical-taking-off-and-landing（V/STOL）or in low-speed flying in the atmosphere;And it will also use the plasma-circumfluence(ring-of-light) (which containing strong-induced-current and becoming pinch-state and controlled by the electronic-magnetic field) as the major skeleton of the supercavity,which will make up of a maginetic-field-controlled magnetic-fluid-supercavity when combining with the mixture of ion-flow and high-temperature-steam,when it navigating under the sea surface.

而有所不同的是，“太空母舰”还采用了普通的“核裂变堆发电机”和“核聚变堆发电机（兼离子流加速器和防御性粒子束武器）”，其中核聚变堆的反应原理，是采用了“反物质诱导核聚变”的方式，其利用太阳的普通核燃料是为了能够维持非战时或飞出恒星系时的能量需求，而在战斗时更可以直接使用“反物质核燃料”，即采用类似“碟形飞行器”一样的“反物质发电机”。另外两者的机体的旋转结构也有所不同，则“太空母舰”虽然大部分的机体结构组成部分都是可以旋转而得到各方向上的飞行稳定性（机体内另外还装备有多种三轴姿态控制系统），但同时也是为了在太空失重地飞行时通过机体各部分的旋转得到“惯性力”和“离心力”，而形成大型太空船所必须的“人造重力环境”。再有“太空母舰”的安全性设计、人工智能系统、机器人维护系统、工作生活环境、和乘员救生系统及战时损管系统都是完善和独特的。

What's different is that the spacecraft-carrier will also use the nuclear-fission-reactor electric-generator and the nuclear-fusion-reactor electric-generator(which will also be the ion-flow-accelerator and the defensive particle-beam-weapons.);And the nuclear-reaction-principle of the nuclear-fusion-reactor will be of using the antimatter to induce the nuclear-fusion-reaction;And it will be applying the general-nuclear-fuel of sun so as to sustain the demand of energy during the non-wartime or when flying out of the stellar-system；And it will be adopting the antimatter-nuclear-fuel during the wartime, namely using the same antimatter/matter-reaction electric-generator which is like that of the spacecraft.On the other hand,both of which have some differents on the rotating structure, then the most components of airframe's structure about the spacecraft-carrier will be rotating and geting the flight-stability in all directions（These airframes are also equipped with a variety of three-axis-attitude-control-systems）, but it is also for geting the inertial-force and the centrifugal-force by rotating its airframe's components when weightlessly flying in the space,so to achieve the necessary artificial-gravity-environment on the large spacecraft.What's more,the security-design,the artificial-intelligence-system,the robot-maintenance-system,the working/living-environment,the crew-lifesaving-system,and the wartime-damage-control-system about the spacecraft-carrier will also be perfect and unique.

“太空母舰”在大气层中飞行时，其飞行原理与“碟形飞行器”有所不同处。母舰因为不设计有轮子和着陆支架以及机体尺寸庞大，所以一般不在地面上作水平停泊，而主要是在水面或海面上以漂浮的姿态停泊。当需要在没有水面的星球上停泊时，太空母舰可以从机体中间自动分离为两个巨大的火箭并竖立着降落停泊。当母舰从水面水平起飞或者在空中悬停时，其气动升力一般由前述的“奇异涡环”提供，同时机体中部的“反物质诱导核聚变堆”可以用喷射大质量高速离子流的方式提供较大的向上推力。母舰在飞行时主要采用机体前部和中部的发动机的喷射的反推力实现空中制动，而在转弯时由于其独特的机体结构强度和气动特性及前后双重发动机布局，所以将主要采用空中制动后再进行直角转弯或者锐角转弯，比通常的用气动力产生向心力而进行转弯的方式更高效，且机体强度更有利于在轴向上承受高过载的G数。母舰在空中飞行时，气动升力来自于“奇异涡环”和机体下表面以及“可变形式蒙皮”下表面产生的激波（在高空空气密度低的低超声速飞行时，可把四对巨大的“散热片”张开当作“边条机翼”产生更多升力）。而飞行时的直接升力和直接侧力，主要来自于机体中部的“反物质诱导核聚变堆”喷射大质量高速离子流产生的推力。母舰的各部分分离机体在大气层中飞行时，其也是和“碟形飞行器”一样稳定灵活安全及拥有“升力和推力的多重冗余”，其虽然不能“倒飞”，但是却可以利用气动力和发动机及推进器的喷射推力，实现整体竖直悬停和上升。当在大气层中高超声速飞行时，“碟形飞行器”将以竖直的姿态旋转着从“太空母舰”的机体腹部向下方以自由落体方式地安全分离。而当母舰回收子机时，“太空母舰”的机体腹部用机械手握住“碟形飞行器”，并将之翻转成竖直姿态再收回机体内部。

When the spacecraft-carrier is flying in the atmosphere,its principles of flight differ from the saucer-shaped spacecraft. Because there are no wheels and no landing trestles,and because the airframe size is huge,so the spacecraft-carrier is not horizontal berthing on the ground and often berth in a floating position on the water or sea.When the spacecraft-carrier need to park on a planet without water,it is automatically separated from the middle of the airframe into two huge rockets,and landing or berthing upright.When the spacecraft-carrier takes off from the water level or hovers in the air,the aerodynamic-lift is generally provided by the aforementioned 'singular-vortex-ring'.The antimatter-induced-nuclear-fusion-reactor locating in the middle of the airframe provide large upward thrust by spraying large mass and high-speed ion-current.Air braking is realized by jet reaction thrust of the engine or thruster at the front and middle of the airframe,when the spacecraft-carrier is flighting.And when the spacecraft-carrier is turning,its air braking will be mainly performed before right angle turning or acute angle turning.It is more efficient than the usual way of turning with centripetal force generated by aerodynamic force,and the airframe strength is more beneficial to the G number bearing high overload in the axial direction.When the spacecraft-carrier is flying in the atmosphere,the aerodynamic lift comes from the 'strange vortex ring' and the shock waves generated on the lower surface of the airframe and the lower surface of the 'deformable skin'(When flying at low supersonic speed with low air density at high altitude,the four pairs of huge 'heat-sink' can be used as 'strake-wing' to generate more lift.).The direct lift and direct side force in flight mainly comes from the thrust generated by the jet of high-mass and high-speed ion-current from the 'antimatter-induced-nuclear-fusion-reactor' in the middle of the airframe. When the separated parts of airframe of the spacecraft-carrier flying in the atmosphere,it is also as stable, flexible and safe as 'the saucer-shaped spacecraft',and having the 'multiple redundancy of lift and thrust'.Although it can't 'inverted flight',but it can use aerodynamic force and jet thrust of engine and thruster to realize overall vertical hover and rise. When flying at hypersonic speeds in the atmosphere，the saucer-shaped spacecraft will rotate in a vertical attitude and safely separate from the belly of the spacecraft-carrier in a free-fall. And when the mother-ship reclaims the sub-aircraft，the belly of the spacecraft-carrier holds the saucer-shaped spacecraft with a manipulator，then turn it into a vertical posture, and then retract it inside the airframe.

母舰在恒星系内的内太空中飞行时，携带的核燃料和推进介质较少。而在恒星系之间远距离航行时，则将在机体外部携带额外的核燃料和推进介质（使用圆筒形储存箱）。从常识来看，飞船的离子电推进器如果用更大质量的推进介质电离加速后喷射而出，将得到同等的推力但更小的“比冲量”，则飞船的能源消耗相对会更少。当飞船实现恒星际远航后到达目的地时，有助于仍保留足够的剩余反物质核能燃料（一半以上）用于中途再加速、终点的减速和恒星系的建设及其他用途。太空母舰在长期的太空航行中难以避免会碰上较大的太空尘埃，所以在机体前方布置有较多的阻拦设施，包括激光束和粒子束发射装置及产生旋转磁场的通电超导螺线管，甚至向前喷射磁性纳米颗粒气凝胶阻拦网等。由于物理学的“动量定理”，飞船在航行数光年的距离后，会因长期的与太空的粒子相撞而减速，则可以开动主要发动机（反物质诱导核聚变堆）进行重新加速，而长期以物理惯性在太空中航行时，飞船会一直采用核裂变堆供电供热。可以预计银河系中每一个原生的恒星系，都存在一个类似的“奥尔特云”，当母舰到达我们的太阳系的“奥尔特云”之前，就必须预先派出“碟形飞行器”加速飞行到“奥尔特云”内部，再减速后搬运无数的大大小小的慧星和陨石，通过高温熔解和粉尘化的物理方式产生等离子体流和纳米颗粒流，在母舰将要经过的路径上撒开成为一个流体星云，让母舰用磁场和减速伞吸收得以减速。当母舰在“奥尔特云”内从原来10%光速以上的速度经过长时间的减速达到1%光速后，再进入太阳系的柯伊伯带以内航行。在到达太阳之前开始利用太阳风和太阳大气层进行最后的减速，可以最大程度的节约反物质核燃料。从母舰的三大类核燃料（核裂变燃料、核聚变燃料、反物质核燃料）的携带量和消耗速率及必要剩余量来看，用母舰进行外恒星系的开拓一般单次航行距离不超过十光年，那么母舰经过近一百年时间的航行并减速到达新的恒星系后，将用另外的一千年由机器人和剩余的反物质核燃料进行全面开发新恒星系成为太空机器人生产基地，再生产得到足够的反物质核燃料后，母舰将重新出发, 或用更多的新造母舰向各个方向（包括各种预先派遣的微型纳米芯片探测器）去开发下一个新的恒星系。那么初步地开拓整个银河系的总的时间将会最多用去两千万年（如果还有机会的话）。而只有实现大量生产反物质核燃料的技术创新和开发恒星的巨大规模工程，才能让“雪茄型太空母舰”和“碟形飞行器”得以有预期的足够强大的飞行能力和武装力量,去守卫遍布银河系的星际文明和太空基地。

When the spacecraft-carrier is flying in inner space within a stellar-system, it carries less nuclear fuel and propulsion medium. And when it is traveling long distances between stellar-system, additional nuclear fuel and propulsion medium will be carried outside the airframe (using many of cylindrical storage-boxes).By common sense,if the ion electric thruster of the spacecraft have ionized and accelerated the larger mass of propulsion medium before it be ejected,it will get the same thrust but smaller 'specific impulse',and the energy consumption of the spacecraft will be relatively less. And when the spacecraft reaches its destination after interstellar voyage，it helps to retain enough remaining antimatter-nuclear-fuel (more than half) for midway re-acceleration, terminal deceleration, star-system construction and other purposes.The spacecraft-carrier will inevitably encounter large space-dust during long-term space navigation,then more blocking facilities are arranged in front of the airframe,including the laser-beam and particle-beam launcher, and the electric superconducting solenoid which generating a rotating magnetic field, and even forward magnetic nanoparticle-aerogel blocking-net, etc.Due to the 'momentum theorem' of physics, the spacecraft will be slowed down by long-term collision with particles in space after sailing a distance of several light-years,then the main engine (antimatter-induced-fusion-reactor) will be started for re-acceleration.When the spacecraft navigates in space with physical inertia for a long time, the spacecraft will always use nuclear-fission-reactor for power supply and heating.It will be predicted that there is a similar 'Oort cloud' in every primary star-system in the Milky-way.Before the spacecraft-carrier reaches the 'Oort cloud' of our solar-system, it must send a 'the saucer-shaped spacecraft' to accelerate its flight to the inside of the 'Oort cloud' in advance,and decelerate and carry countless of large and small comets and meteorites.Then the plasma-current and nanoparticle-current are generated by physical means of high temperature melting and dusting,and will be spreaded out into a fluid Nebula on the path of the spacecraft-carrier, so that the spacecraft-carrier will be slowed down with the magnetic-field and deceleration-umbrella absorpting.After the spacecraft-carrier decelerates for a long time from the original speed of more than 10% light-speed to 1% light-speed in the 'Oort cloud',then will sail into the 'Kuiper belt' of the solar-system.Before it reaching the sun,the spacecraft-carrier will use the solar-wind and solar-atmosphere for final deceleration, which will save antimatter-nuclear-fuel to the greatest extent. From the carrying capacity, consumption rate and necessary surplus of the three categories of nuclear fuel (nuclear fission fuel, nuclear fusion fuel and antimatter nuclear fuel) of the spacecraft-carrier, in general, using the the spacecraft-carrier to develop outer galaxy, the distance of a single voyage is no more than ten light-years. Well, after nearly a hundred years of sailing and slowing down to reach the new star-system, the spacecraft-carrier will be fully developed by robots and remaining antimatter-nuclear-fuel in another thousand years, and become a production-base of space-robots. After sufficient antimatter nuclear fuel is obtained for reproduction, the spacecraft-carrier will start sailing again. Or use more new spacecraft-carriers to develop the next new star-system in all directions (including various micro-nano-chip-detectors dispatched in advance). Then the total time for the initial exploration of the whole Milky Way will take 20 million years (if there is still a chance). Only by realizing the technological innovation of mass production of antimatter-nuclear-fuel and the huge scale project of developing stars,then the cigar-shaped spacecraft-carrier and the saucer-shaped spacecraft will have the expected strong enough flight-ability and armed-force to guard interstellar-civilizations and space-bases throughout Milky Way.

地球全力

5.1.“雪茄型太空母舰”和“碟形飞行器”在太空中防御性作战。
Fig.5.1.The defensive-warfare-spectacle about the cigar-shaped spacecraft-carrier and the saucer-shaped spacecraft in the space.

地球全力

5.2.“雪茄型太空母舰”和“碟形飞行器”在大气层内进攻性作战。
Fig.5.2.The offensive-warfare-spectacle about the cigar-shaped spacecraft-carrier and the saucer-shaped spacecraft in the atmosphere.

地球全力

5.3.“雪茄型太空母舰”和“碟形飞行器”在海面下的超空泡航行。
Fig.5.3.The supercavity-navigating-spectacle about the cigar-shaped spacecraft-carrier and the saucer-shaped spacecraft under the sea-surface.

地球全力

5.4.“雪茄型太空母舰”机体内部的结构。
Fig.5.4.The airframe-interior-structures of the cigar-shaped spacecraft-carrier.

地球全力

5.5.“雪茄型太空母舰”机体内部的拆分。
Fig.5.5.The spliting up the airframe's interior of the cigar-shaped spacecraft-carrier.

地球全力

5.6.“雪茄型太空母舰”在不同航行状态下的机体外部设备的拆分组合。
Fig.5.6. The separation and combination of airframe-exterior-equipment under the different navigational states of the cigar-shaped spacecraft-carrier.