CN108137149A - 喷射器和翼型构型 - Google Patents

喷射器和翼型构型 Download PDF

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CN108137149A
CN108137149A CN201680059194.XA CN201680059194A CN108137149A CN 108137149 A CN108137149 A CN 108137149A CN 201680059194 A CN201680059194 A CN 201680059194A CN 108137149 A CN108137149 A CN 108137149A
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aerofoil profile
aircraft
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injector
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A·埃弗莱特
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Jetoptera Inc
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    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
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    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C15/00—Attitude, flight direction, or altitude control by jet reaction
    • B64C15/14—Attitude, flight direction, or altitude control by jet reaction the jets being other than main propulsion jets
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    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
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    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
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    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
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    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
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    • B64D27/02—Aircraft characterised by the type or position of power plants
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    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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    • B64U50/15—Propulsion using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
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    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/36—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto having an ejector
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    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
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    • B64C2230/00—Boundary layer controls
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    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/06—Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/16—Boundary layer controls by blowing other fluids over the surface than air, e.g. He, H, O2 or exhaust gases
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    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0273—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for jet engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
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    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
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    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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    • F05D2220/00—Application
    • F05D2220/90—Application in vehicles adapted for vertical or short take off and landing (v/stol vehicles)
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Abstract

本发明涉及一种联接到飞行器的推进系统。该系统包括喷射器，所述喷射器具有出口结构，推进流体以预定的可调节的速度从所述出口结构流出。具有前缘的控制表面直接位于出口结构的下游，使得来自喷射器的推进流体流过控制表面。

Description

喷射器和翼型构型
版权声明
本公开受到美国和国际版权法的保护。2016Jetoptera。保留所有权利。本专利文献的公开的一部分包含有受版权保护的材料。版权所有者不反对任何人对本专利文献或专利公开进行传真复制，因为它出现在专利和商标局专利文件或记录中，但在其它方面保留所有版权。
优先权声明
本申请要求享有2015年9月2日提交的美国临时申请No.62/213,465的优先权，其全部公开内容通过参考包含于此，如同在此完全阐述一样。
背景技术
可以悬停、起飞和垂直着陆的飞机通常被称为垂直起飞和着陆(VTOL)飞机。该分类包括固定翼飞机以及直升机和带可倾斜的动力转子的飞机。某些VTOL飞机也可以在其它模式中操作，例如，短距起飞和着陆(STOL)。VTOL是V/STOL(垂直和/或短距起飞和着陆)的子集。
为了说明的目的，具有VTOL能力的当前飞机的示例是F-35Lightning。引导垂直升力气流的传统方法包括使用喷嘴连同使用两组扁平挡板叶片，所述喷嘴可以沿单个方向旋转，所述两组扁平挡板叶片彼此成90度布置并且位于外部喷嘴处。类似地，F-35Lightning的推进系统使用垂直取向的升力风扇和来自涡轮发动机的矢量推力的组合来提供垂直升力。升力风扇在带有上下双扇弧形门的机舱(bay)中位于驾驶舱后方。发动机通过三轴承旋转喷嘴排气，所述三轴承旋转喷嘴可以将推力从水平偏转至垂直正前方。侧倾控制管道从每个机翼中伸出，并且借助来自发动机风扇的空气被供应推力。俯仰控制受到升力风扇/发动机推力分裂影响。横摆控制是通过发动机旋转喷嘴的横摆运动。侧倾控制通过差动地打开和关闭在两个侧倾控制管道的端部处的孔来提供。升力风扇有可伸缩的“D”形喷嘴以沿前后方向提供推力偏转。D形喷嘴在出口孔处具有固定的叶片。
飞机或无人驾驶飞机的设计更普遍地由其推进元件和将这些元件集成到其中的机体构成。常规地，飞机中的推进装置可以是涡轮喷气发动机、涡轮风扇发动机、涡轮螺旋桨发动机或涡轮轴发动机、活塞发动机或配备有螺旋桨的电动马达。小型无人机(UAV)中的推进系统(推进器)常规地是活塞发动机或经由轴向一个或若干个螺旋桨提供动力的电动马达。用于较大飞机的推进器，无论是有人还是无人，传统上都是喷气发动机或涡轮螺旋桨发动机。推进器通常经由塔架或支柱被附装到飞机的机身或本体或机翼，所述塔架或支柱能够将力传递到飞机并且维持载荷。出现的空气和气体的混合射流(射流外流(efflux))是沿与射流外流的流动方向相反的方向推进飞机的事物。
常规地，大型螺旋桨的气流外流在水平飞行中没有用于升力目的，并且因此大量的动能没有用于飞机的益处，除非其如同在今天现有的某些应用中旋转(即，Bell BoeingV-22Osprey)以外。当然，在大多数现有的飞机上的升力通过机翼和尾翼产生。此外，甚至在Osprey中发现的那些特定VTOL应用(例如，起飞通过过渡而达到水平飞行)中，由螺旋桨自身引起的升力在水平飞行期间最小，并且所述升力中的大部分仍然来自机翼。
用于在飞机上产生升力的当前技术状态是在机翼和机翼元件上方产生高速气流，所述机翼和机翼元件通常是翼型。翼型的特征在于主要沿轴向方向从翼型的前缘延伸到后缘的翼弦线。基于在入射气流与翼弦线之间所形成的迎角，并且根据翼型升力产生的原理，较低压力的空气流过吸力(上)侧，并且相反，通过伯努利定律以高于下侧(压力侧)的速度运动。飞机的空速越低，升力越低，并且需要更高的机翼表面积或更高的入射角度，包括起飞时在内。
大型UAV对此规则不例外。升力是通过设计具有适当的迎角、翼弦、翼展和中弧线的机翼翼型来产生的。襟翼、狭槽和许多其它装置是用于经由增大升力系数和机翼表面积来使升力最大化的其它常规工具，但是它将产生与飞机的空速相对应的升力。(增大面积(S)和升力系数(CL)允许根据公式L＝1/2ρV2SCL在较低飞机空速(V0)下产生类似的升力量，但是代价是较高的阻力和重量。)这些当前的技术也表现不佳，在具有较高侧风的条件下效率大幅下降。
尽管较小的UAV可能使用由螺旋桨产生的推力来提升飞行器，但是当前的技术严格地依赖于电动马达速度的控制，并且较小的UAV会具有或会不具有这样的能力，即，所述能力是旋转马达以产生推力和升力或通过倾斜螺旋桨过渡到水平飞行。此外，使用这些推进元件的较小UAV遭受到与电池、功率密度和大型螺旋桨有关的低效率，所述电池、功率密度和大型螺旋桨会在悬停中高效，但是在水平飞行中低效，并且由于叶片的快速运动的尖端而在操作时产生困难和危险。大多数当前的四轴飞机和其它电动飞行器仅能够有非常短的飞行时间，并且不能高效地提升或携带较大的有效载荷，如在飞行的任何时候电动马达系统和电池的重量会已经远远超过飞行器的重量的70％。使用喷气燃料或典型用在运输中的任何其它碳氢燃料的类似飞行器将携带多了至少一个数量级的可用燃料。这可以通过与电池系统相比明显更高的碳氢燃料的能量密度(高了至少一个数量级)以及更低的基于碳氢燃料的系统的重量与总飞行器重量之比来解释。
因此，在飞机中，尤其对于UAV和一些载人飞行器而言，需要提高的效率、改进的能力和其它技术进步。
附图说明
图1是本发明的一个实施例的剖视图，其示出喷射器的上半部分以及在内部流动内的速度和温度的分布；
图2示出根据实施例的入口结构的局部透视图；
图3示出根据实施例的、放置在控制表面前方的喷射器的侧平面图；
图4是根据实施例的、放置在与另一个控制表面组合的控制表面前方的喷射器的透视图；
图5是可替代的实施例的俯视局部剖视图；
图6是可替代的实施例的侧透视图；
图7是图6中所示的实施例的元件的侧视图；
图8至图9示出本发明的另一个可替代的实施例；以及
图10示出本发明的又一个可替代的实施例。
具体实施方式
本申请旨在描述本发明的一个或多个实施例。将应理解，诸如“必须”、“将要”和类似词语的绝对术语以及特定量的使用将应解释为可适用于一个或多个这样的实施例，但是不必适用于所有这样的实施例。照此，本发明的实施例可以省略或包括在这种绝对术语的上下文中描述的一个或多个特征或功能的修改。另外，本申请中的标题仅用于参考目的，并且应当不以任何方式影响本发明的含义或解释。
本发明的一个实施例包括推进器，所述推进器利用流体来夹带和加速环境空气并且递送高压气体(从气体发生器供应到推进器)和夹带的环境空气的混合物的高速射流外流。实质上，该目标是通过在凸面附近排放气体来实现的。该凸面是所谓的柯恩达表面，其得益于在1936年9月1日授予Henri Coanda的美国专利No.2,052,869中描述的柯恩达效应。原则上，柯恩达效应是射流喷射的气体或液体即使壁的弯曲方向远离射流的轴线也靠近壁轮廓行进的趋势。本文关于一个或多个实施例讨论的凸科恩达表面不必由任何特定的材料构成。
图1示出可以附装到飞行器(未示出)的喷射器200的上半部分的剖视图，所述飞行器例如对于非限制性的示例而言是UAV或载人飞行器，例如，固定翼飞机。从例如可以被飞行器采用的基于燃烧的发动机向增压室211供应比环境更热的空气(即，加压的运动气体流)。由箭头600指示的该加压的运动气体流经由至少一个导管引导到喷射器200的内部，所述导管例如是初级喷嘴203。更具体地，初级喷嘴203构造成将运动流体流600作为壁射流直接在凸科恩达表面204上方加速到可变的预定期望速度。另外地，初级喷嘴203提供可调节的体积的流体流600。该壁射流继而用于通过入口结构206夹带次级流体，例如由箭头1指示的环境空气，其可以静止或从由箭头1指示的方向以非零的速度逼近喷射器200。在各种实施例中，喷嘴203可以沿弯曲取向、螺旋取向和/或之字形取向布置在阵列中。
流600和空气1的混合物可以在喷射器200的喉部225处纯粹地轴向运动。通过在诸如扩散器210的扩散结构中扩散，混合和平滑处理持续进行，所以沿喷射器200的轴向方向的温度(800)和速度(700)的分布不再具有存在于喉部225处的高值和低值，而是在扩散器210的末端101处变得更为均匀。随着流600和空气1的混合物逼近末端101的出口平面，温度和速度分布几乎是均匀的。尤其，混合物的温度低到足以被朝向翼型指引，所述翼型例如是机翼或控制表面。
在实施例中，入口结构206和/或末端101可以具有圆形的构型。然而，在不同的实施例中，并且如在图2中最好示出，入口结构206以及末端101可以是非圆形的，并且实际上是非对称的(即，在将入口结构平分的至少一个或可替代地任何给定的平面的两侧上是不相同的)。例如，如图2所示，入口结构206可以包括第一横向相对边缘401和第二横向相对边缘402，其中第一横向相对边缘具有比第二横向相对边缘更大的曲率半径。末端101可以被类似地构造。
图3示出推进器/喷射器200，所述推进器/喷射器200被放置在控制表面前方，所述控制表面例如是具有前缘302并且产生升力400的翼型100。如图所示，翼型100被直接定位在喷射器的出口结构后方(即，下游)，使得来自喷射器200的推进流体流过翼型，所述出口结构例如是扩散器210的末端101。实际上，在实施例中，翼型100可以被定位成足够靠近末端101，使得排除其它环境空气之外仅来自喷射器200的推进流体流过翼型。如本文所使用的，术语“直接后方”可以被解释为意指前缘302的至少一部分位于如下平面之一内或与其对准，所述平面是(a)由与前缘平行的末端101的表面占据和(b)沿轴向方向(即，沿下面讨论的箭头300的方向)延伸到喷射器200的平面。
由于与由箭头500指示的飞机空速相比由箭头300指示的喷射器200退离射流外流的速度更高，所以在机翼100之上的局部流动具有比飞机的速度高的速度。喷射器200以较高的夹带速率将较热的运动流600(图1)与进入的较冷环境空气流激烈地混合。额外的控制表面可以在翼面100上实施，例如，升降机表面150。在实施例中，任何这种控制表面的整体可围绕与前缘302平行取向的轴线转动。通过改变这样的表面100和/或150的角度，考虑到射流外流300的较高局部速度，飞机的姿态可以在较小的努力下迅速地改变。混合物是足够均质的，以将喷射器的热运动流600的温度减小到将没有机械地或结构上对翼型100或150产生负面影响的混合物温度分布800。离开推进器的射流外流的速度分布700使得其由于较高的局部速度而允许由翼型100产生更多的升力400。
图4示出推进器/喷射器200也可以被放置在与另一个翼型1000组合的且处于与图3中所示的控制表面的构型不同的构型中的控制表面1500前方。在所示的实施例中，控制表面1500的前缘1501相对于翼型1000的前缘1001以约90度的角度布置。喷射器200可以是非轴对称的形状，并且控制表面可以被确切地放置在所述喷射器200的尾迹中。喷射器200以较高的夹带速率将较热的运动流600(图1)与进入的较冷环境空气流激烈地混合。类似地，混合物是足够均质的，以将喷射器的热运动流600的温度减小到将没有机械地或结构上对控制表面1500产生负面影响的混合物温度分布。在该实施例中，可以通过改变控制表面1500的取向来控制横摆。在类似的方式中，并且通过改变控制表面1500相对于诸如飞机机身的飞行器主体的取向，同样可以控制俯仰和侧倾。喷射器200的功能是产生推力，但是它也可以提供升力或姿态控制。在该实施例中，横摆控制是沿着方向151，从而产生围绕飞机轴线10的转动。
图5示出这样的实施例，即，所述实施例提供将喷气发动机放置在飞机的机翼上以产生推力的传统方法的可替代方案。在图5中，气体发生器501产生运动空气流，用于为嵌入诸如机翼503的初级翼型中的一系列喷射器502提供动力，用于通过从初级翼型的后缘直接喷射气体流来向前推进。在该实施例中，气体发生器501被嵌入飞行器的主体机身504中，经由导管505流体地联通到喷射器502，并且是推进飞机的唯一手段。喷射器502可以如同图2中所示的实施例是圆形的或非圆形的，具有与末端101类似的相对应成形的出口结构，并且从发生器501和导管505以预定的可调节的速度提供气体流。另外地，喷射器502可以是以与襟翼或副翼类似的方式运动的，可转动通过180°的角，并且可以被致动以除了提供所需的推力以外还控制飞机的姿态。具有前缘507的次级翼型506与机翼503串联地直接放置在喷射器502后方，使得来自喷射器502的气体流流过次级翼型506。因此，次级翼型506接收比飞机的空速明显更高的速度，并且照此产生较高的升力，如所述升力是与空速的平方成正比的。次级翼型506的整体可以是可围绕与前缘507平行取向的轴线转动的。
在本发明的该实施例中，由于由气体发生器501产生的运动流体(也被称为初级流体)与次级流体混合，次级翼型506将看到适度更高的温度，所述次级流体是由运动流体以每份初级流体有介于5份至25份之间的二次流体的速率夹带的环境空气。照此，根据以下公式，由次级翼型506看到的温度略高于环境温度，但是明显低于运动流体，从而允许次级机翼的材料支撑和维持升力载荷：T混合＝(T运动+ER*T环境)/(1+ER)，其中T混合是从喷射器502出现的射流外流的最终流体混合物温度，ER是每份运动空气夹带的环境空气份数的夹带速率，T运动是运动流体或初级流体的较热温度，并且T环境是逼近的环境空气温度。
图6示出根据可替代的实施例的用于飞行器700的推进系统。第一增强翼型702联接到飞行器700并且定位在流过飞行器的初级翼型701的流体的下游。翼型702构造成围绕轴线707转动并且由致动器708控制。如在图7中最好示出，第一增强翼型702包括：第一输出结构，例如，相对的喷嘴表面705、706；以及与由喷嘴表面限定的末端703流体连通的至少一个导管，例如，增压室704。喷嘴表面705、706可以包括或可以不包括与上面参照图1讨论的喷嘴203类似的喷嘴。另外地，喷嘴表面705、706中的一个或多个可以包括凸面，所述凸面因此可以促进柯恩达效应并且可以具有没有尖锐或突变拐角的连续圆润的表面。从例如可以被飞行器700采用的基于燃烧的发动机向增压室704供应比环境更热的空气(即，加压的运动气体流)。增压室704构造成将该气体流引导到末端703，所述末端703构造成为流向初级翼型701和从第一增强翼型702流出的气体流提供出口。
参照图8至图9，实施例可以包括与翼型702类似的第二增强翼型902，每个翼型都具有从另一个后缘发散的相应的后缘714、914。更具体地，第二增强翼型902联接到飞行器700并且定位在流过飞行器的初级翼型701的流体的下游。翼型902构造成以与上面参照翼型702讨论的方式类似的方式转动。翼型902包括：第一输出结构，例如，相对的喷嘴表面905、906；以及与由喷嘴表面限定的末端903流体连通的至少一个导管，例如，增压室904。喷嘴表面905、906可以包括或可以不包括与上面参照图1讨论的喷嘴203类似的喷嘴。另外地，喷嘴表面905、906中的一个或多个可以包括凸面，所述凸面因此可以促进柯恩达效应。从例如可以被飞行器700采用的基于燃烧的发动机向增压室904供应比环境更热的空气(即，加压的运动气体流)。增压室904构造成将该气体流引导到末端903，所述末端903构造成为流向初级翼型701和从第二增强翼型902流出的气体流提供出口。
第一增强翼型702和第二增强翼型902中的每个都具有朝向初级翼型布置的前缘716、916，其中第一增强翼型与第二增强翼型相对。在操作中，第一增强翼型702和第二增强翼型902在它们之间并且沿着它们的长度限定扩散区域802，其在功能上与上文讨论的扩散器210类似。前缘716、916限定入口区域804，所述入口区域804构造成接收来自增压室704、904的气体流和流过初级翼型701的流体并且将其引导到扩散区域802。扩散区域802包括初级末端806，所述初级末端806构造成为所引导的气体流和流过初级翼型701的流体从扩散区域提供出口。
图10示出以串联式机翼为特征的本发明的可替代的实施例。在所示的实施例中，次级翼型1010被直接放置在增强翼型702、902的下游，使得流过初级翼型701的流体和来自增强翼型的气体流流过次级翼型。两个较短机翼701、1010的组合比缺乏增强翼型702、902的明显更大跨距的机翼产生更大的升力，所述明显更大跨距的机翼依赖于附装到较大机翼以产生推力的喷气发动机。
虽然前述文本阐述了许多不同的实施例的详细描述，但是将应理解，保护范围由遵循的权利要求书的词语限定。详细的描述仅被解释为示例性的，并且没有描述每个可能的实施例，这是因为描述每个可能的实施例即使不是不可能的也是不切实际的。可以使用当前技术或在本专利申请日之后开发的技术来实现许多可替代的实施例，这些实施例将仍然落入权利要求书的范围内。
因此，可以在不脱离本权利要求书的精神和范围的情况下对在此描述和示出的技术和结构进行许多修改和变化。因此，将应理解，本文描述的方法和设备仅是说明性的，并且不限制权利要求书的范围。

Claims (20)

1.一种联接到飞行器的推进系统，所述系统包括：
喷射器，所述喷射器包括出口结构，推进流体以预定的能调节的速度从所述出口结构流出；和
第一控制表面，所述第一控制表面具有前缘，并且直接位于所述出口结构的下游，使得来自所述喷射器的推进流体流过所述第一控制表面。
2.根据权利要求1所述的系统，其中，在所述系统的操作期间，仅来自所述喷射器的推进流体流过所述控制表面。
3.根据权利要求1所述的系统，其中，所述喷射器还包括：
扩散结构；
至少一个导管，所述至少一个导管联接到所述扩散结构并且构造成将由所述飞行器产生的初级流体引导到所述扩散结构；和
入口结构，所述入口结构联接到所述扩散结构并且构造成将能接近所述飞行器的次级流体引导到所述扩散结构，其中，所述扩散结构包括所述出口结构，并且所述推进流体包括所述初级流体和次级流体。
4.根据权利要求3所述的系统，其中，所述喷射器还包括凸面，所述扩散结构联接到所述凸面，并且所述至少一个导管联接到所述凸面并且构造成将所述初级流体引导到所述凸面。
5.根据权利要求1所述的系统，其中，所述控制表面的整体能围绕与所述前缘平行取向的轴线转动。
6.根据权利要求1所述的系统，其中，所述出口结构是非对称的。
7.根据权利要求6所述的系统，其中，所述出口结构包括第一横向相对边缘和第二横向相对边缘，并且所述第一横向相对边缘具有比所述第二横向相对边缘更大的曲率半径。
8.根据权利要求1所述的系统，还包括第二控制表面，所述第二控制表面具有前缘并且直接联接到所述飞行器，其中，所述第一控制表面联接到所述第二控制表面，使得所述第一控制表面的所述前缘相对于所述第二控制表面的所述前缘成非零的角度。
9.一种飞行器，其包括：
主体；
初级翼型，所述初级翼型联接到所述主体；
气体发生器，所述气体发生器联接到所述主体并且产生气体流；
导管，所述导管流体地联接到所述发生器；
喷射器，所述喷射器流体地联接到所述导管并且嵌入所述初级翼型中，所述喷射器包括出口结构，所述气体流以预定的能调节的速度从所述出口结构流出；以及
次级翼型，所述次级翼型具有前缘并且直接位于所述出口结构的下游，使得来自所述喷射器的气体流流过所述次级翼型的前缘。
10.根据权利要求9所述的飞行器，其中，所述气体发生器被布置在所述主体中。
11.根据权利要求9所述的飞行器，其中，所述初级翼型包括后缘，并且所述至少一个喷射器直接从所述初级翼型的所述后缘喷射所述气体流。
12.根据权利要求9所述的飞行器，其中，由所述发生器产生的所述气体流是推进所述飞行器的唯一手段。
13.根据权利要求9所述的飞行器，其中，所述次级翼型的整体能围绕与所述前缘平行取向的轴线转动。
14.根据权利要求9所述的飞行器，其中，所述喷射器能转动通过180°的角。
15.根据权利要求9所述的飞行器，其中，所述出口结构是非圆形的。
16.一种用于飞行器的推进系统，所述系统包括：
初级翼型，所述初级翼型联接到所述飞行器；
第一增强翼型，所述第一增强翼型联接到所述飞行器并且被定位在流过所述初级翼型的流体的下游，所述第一增强翼型包括第一输出结构和联接到所述第一输出结构的至少一个第一导管，所述至少一个第一导管构造成将由所述飞行器产生的初级流体引导到所述第一输出结构，所述第一输出结构包括第一末端，所述第一末端构造成为朝向所述初级翼型引导和从所述第一增强翼型引导出的初级流体提供出口；以及
次级翼型，所述次级翼型直接位于所述第一增强翼型的下游，使得流过所述初级翼型的流体和来自所述第一增强翼型的所述初级流体流过所述次级翼型。
17.根据权利要求16所述的系统，还包括第二增强翼型，所述第二增强翼型联接到所述飞行器并且定位在流过所述初级翼型的流体的下游，所述第一增强翼型和所述第二增强翼型中的每个都具有朝向所述初级翼型布置的前缘，所述第一增强翼型与所述第二增强翼型相对，由此：
所述第一增强翼型和所述第二增强翼型限定扩散区域；并且
所述前缘限定入口区域，所述入口区域构造成接收所述初级流体和流过所述初级翼型的流体并且将其引导到所述扩散区域，所述扩散区域包括初级末端，所述初级末端构造成将所引导的初级流体和流过所述初级翼型的流体混合和提供到所述次级翼型。
18.根据权利要求17所述的系统，其中，所述第二增强翼型包括第二输出结构和联接到所述第二输出结构的至少一个第二导管，所述至少一个第二导管构造成将由所述飞行器产生的初级流体引导到所述第二输出结构，所述第二输出结构包括第二末端，所述第二末端构造成为朝向所述初级翼型引导和从所述第二增强翼型引导出的初级流体提供出口。
19.根据权利要求16所述的系统，还包括第一致动器，所述第一致动器构造成相对于所述飞行器转动所述第一增强翼型。
20.根据权利要求17所述的系统，还包括第二致动器，所述第二致动器构造成相对于所述飞行器转动所述第二增强翼型。
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