公开(公告)号：US20140001275A1

公开(公告)日：2014-01-02

申请号：US14004166

申请日：2011-12-01

申请人： RuiQing Hong

发明人： RuiQing Hong

IPC分类号： B64C15/14

CPC分类号： B64C15/14 ,  B64C9/38

摘要： Disclosed is an ultra-high-pressure fluid injection dynamic orbit-transfer system and method to be used in aircraft. A collection of spray heads with nozzle holes are arranged symmetrically in effuser units placed on the flight surfaces or main body of an aircraft. These effusers allow more rapid and efficient changes of direction and motion.

摘要翻译： 公开了一种在飞机上使用的超高压流体注入动态轨道转移系统和方法。 具有喷嘴孔的喷头的集合对称地布置在放置在飞行器的飞行表面或主体上的喷射器单元中。 这些喷射器允许更快速和有效地改变方向和运动。

公开(公告)号：US08181903B2

公开(公告)日：2012-05-22

申请号：US12281445

申请日：2007-03-02

申请人： David Posva

发明人： David Posva

IPC分类号： B64C15/02 ,  B64C15/12 ,  B64C29/00 ,  B64C9/00

CPC分类号： B64C29/0025 ,  B64C15/14 ,  B64C27/28

摘要： Aircraft having two, preferably four or more, rotors (20) in wing hatches (10) which can be closed. The closure mechanism has, at the top, individually curved elements on a rollshutter (scroll/roller blind) (40) and, at the bottom, a set of longitudinal fins (30). One or more propeller/impeller drives are firmly connected to the stabilator (60), which can be pivoted over a wide extent. In hovering flight, the wing hatches (10) are opened and the impeller drives (60), together with the stabilator, are pivoted largely vertically downwards. During the transition to cruise flight, the large flaperons (100) are lowered, and the propeller/impeller drives (60), together with the stabilator, are slowly pivoted to the horizontal. When the forward speed is sufficient, the wing hatches (10) are closed, the rotors (20) are stopped, and the flaperons (100) are raised somewhat again. The pilot has unobstructed visibility through the gap between the wingtips (70).

摘要翻译： 具有可以关闭的翼形舱口（10）中的两个，优选四个或更多个转子（20）的飞行器。 闭合机构在顶部具有在卷绕器（滚动/卷帘）（40）上的单独弯曲的元件，并且在底部具有一组纵向翅片（30）。 一个或多个螺旋桨/叶轮驱动器牢固地连接到稳定器（60），稳定器可以在很大程度上枢转。 在悬停飞行中，翼舱（10）打开，叶轮驱动（60）与稳定器一起主要垂直向下枢转。 在向巡航飞行过渡期间，大的襟副翼（100）被降低，螺旋桨/叶轮驱动器（60）与稳定器一起缓慢地枢转到水平面。 当前进速度足够时，机翼舱口（10）关闭，转子（20）停止，并且襟副翼（100）再一次升高。 飞行员通过翼尖之间的间隙（70）无阻碍地看到。

公开(公告)号：US07988087B1

公开(公告)日：2011-08-02

申请号：US08634594

申请日：1996-04-25

申请人： Robert C Tonks ,  Philip A Mansfield ,  Leslie R Harper

发明人： Robert C Tonks ,  Philip A Mansfield ,  Leslie R Harper

IPC分类号： B64C29/00

CPC分类号： B64C29/0058 ,  B64C15/12 ,  B64C15/14 ,  B64D33/04 ,  F02K1/006 ,  F02K1/008 ,  F02K1/1207 ,  F02K3/068

摘要： A nozzle arrangement for a VTOL or STOVL aircraft having an airframe mounted lift system comprises a hinged deflector door pivotally mounted on the underside of the airframe for exhaust efflux deflection. The door is movable about its axis to vector impinging exhaust gases rearwards during the transition between vertical and horizontal flight, and in addition comprises a pair of lateral sidewalls which are movable in the plane of the door to direct the exhaust efflux sideways for improved aircraft yaw control.

摘要翻译： 用于具有机身安装的升降系统的VTOL或STOVL飞机的喷嘴装置包括枢转地安装在机身的下侧上的用于排气流出偏转的铰接偏转器门。 门可以围绕其轴线移动，以在垂直和水平飞行之间的过渡期间向后冲击排气，并且还包括一对侧壁，其可在门的平面中移动以引导排气流向侧向以改善飞行器偏航 控制。

公开(公告)号：US20100127115A1

公开(公告)日：2010-05-27

申请号：US11582046

申请日：2007-05-08

申请人： Yigal Adir

发明人： Yigal Adir

IPC分类号： B64B1/36 ,  B64D17/80

CPC分类号： B64C25/56 ,  B64C15/14 ,  B64D17/80 ,  F02K1/78

摘要： It illustrated in FIG. 1 and FIG. 2. A controlled reservoir with at least 2 Adjustable holes. In our example 6 adjustable holes will able an aircraft to maneuver in 3 dimensions vectors. It will give more control to the pilot to make better and quicker maneuvers. And it can help to avoid accidents. Also it will give advantage to pilot in air to air combat.

摘要翻译： 如图所示。 如图1和图2所示。 2.具有至少2个可调孔的受控储存器。 在我们的例子中，6个可调节的孔能使飞机在3维向量机动。 它将给飞行员更多的控制力，使飞机更好，更快捷。 它可以帮助避免事故。 这也将有利于空中和空中的飞行员。

公开(公告)号：US20070252032A1

公开(公告)日：2007-11-01

申请号：US11224404

申请日：2005-09-12

申请人： Edward Lawson ,  David Boyer

发明人： Edward Lawson ,  David Boyer

IPC分类号： B64C15/02 ,  B64C29/00

CPC分类号： B64C29/0016 ,  B64C15/02 ,  B64C15/14 ,  B64C29/0066 ,  B64D27/20 ,  B64D33/02 ,  B64D33/04 ,  F02C6/00 ,  F02K3/077

摘要： A method of generating lift for a vehicle including a gas turbine engine having a combustor, a core flow heated by the combustor, and a bypass flow which bypasses the combustor. The method includes segregating at least a portion of the core flow from the bypass flow, directing the segregated portion of the core flow in a first direction to generate lift for the vehicle, segregating at least a portion of the bypass flow from the core flow, and directing the segregated a portion of the bypass flow in a second direction to generate lift for the vehicle.

摘要翻译： 一种产生用于车辆的升降机的方法，包括具有燃烧器的燃气涡轮发动机，由燃烧器加热的芯流，以及绕过燃烧器的旁路。 该方法包括将来自旁路流的核心流的至少一部分分离，将核心流的分离部分沿第一方向引导以产生用于车辆的升力，将旁路流的至少一部分与核心流隔离， 并且将旁路流的一部分分离在第二方向上以产生用于车辆的升力。

公开(公告)号：US20070095970A1

公开(公告)日：2007-05-03

申请号：US11265655

申请日：2005-11-02

申请人： Steven Richardson

发明人： Steven Richardson

IPC分类号： B64C27/24 ,  B64C15/12

CPC分类号： B64C3/385 ,  B64C15/02 ,  B64C15/14 ,  B64C27/18 ,  B64C27/24 ,  B64C27/26 ,  Y02T50/14

摘要： Aircraft including an airframe having a fuselage extending between a forward end and an aft end and a fixed wing extending laterally from the fuselage. The aircraft includes a power plant mounted on the airframe producing exhaust during operation. The aircraft includes a rotor/wing rotatably mounted on the airframe including a plurality of blades and an adjustable nozzle mounted on the airframe downstream from the power plant exhaust for selectively directing the power plant exhaust to exit the aircraft at a pre-selected angle with respect to the airframe within a range of angles extending from about horizontally rearward to about vertically downward.

摘要翻译： 飞机包括具有在前端和后端之间延伸的机身的机身和从机身横向延伸的固定翼。 飞机包括安装在机身上的发电厂，在运行期间产生排气。 飞行器包括可旋转地安装在机身上的转子/机翼，其包括多个叶片和安装在发电厂排气下游的机身上的可调节喷嘴，用于选择性地引导发电厂排气以相对于预定角度离开飞行器 在从大约水平向后延伸到大约垂直向下的角度范围内的机身上。

公开(公告)号：US07104499B1

公开(公告)日：2006-09-12

申请号：US10255766

申请日：2002-09-25

申请人： Allen A. Arata

发明人： Allen A. Arata

IPC分类号： B64D41/00

CPC分类号： B64D27/02 ,  B64C9/38 ,  B64C15/02 ,  B64C15/14 ,  B64C2027/8245

摘要： A system for providing aircraft thrust includes a compressor, operable to take in a quantity of air, reduce the volume of the air to generate compressed air, and to deliver the compressed air to a tank. The tank is coupled to the compressor and is operable to receive the compressed air, store the compressed air, and deliver the compressed air to a nozzle mounted externally to the aircraft. The nozzle is operable to receive the compressed air and discharge the compressed air to provide thrust for the aircraft.

摘要翻译： 用于提供飞机推力的系统包括可操作地吸入大量空气的压缩机，减少空气的体积以产生压缩空气，并将压缩空气输送到罐。 罐与压缩机相连，可操作以接收压缩空气，储存压缩空气，并将压缩空气输送到安装在飞机外部的喷嘴。 喷嘴可操作以接收压缩空气并排出压缩空气以为飞机提供推力。

公开(公告)号：US20010020665A1

公开(公告)日：2001-09-13

申请号：US09800659

申请日：2001-03-08

发明人： James C. Hayes

IPC分类号： B64C015/00

CPC分类号： B64C5/00 ,  B64C5/08 ,  B64C15/00 ,  B64C15/14

摘要： Disclosed is a fluid vehicle having one or more vertical wings in contact with the fluid for generating a forward motion. This fluid vehicle also has a stabilizing torque system for generating jets transverse to the forward motion for the purpose of counterbalancing any capsizing effect. Preferably, the system is devised to generate up and down jets to the opposite ends of at least one horizontal wing.

摘要翻译： 公开了一种流体车辆，其具有与流体接触的一个或多个垂直翼片，用于产生向前运动。 该流体车辆还具有用于产生横向于向前运动的喷气的稳定扭矩系统，以平衡任何倾覆效果。 优选地，该系统被设计成向至少一个水平翼的相对端产生上下喷射。

公开(公告)号：US5481868A

公开(公告)日：1996-01-09

申请号：US225943

申请日：1994-04-11

申请人： Guy E. Davies ,  David R. Tucker

发明人： Guy E. Davies ,  David R. Tucker

IPC分类号： B64C15/14 ,  F02K1/06 ,  F02K3/02 ,  F02K1/30

CPC分类号： B64C15/14 ,  F02K1/06 ,  F02K3/025 ,  F05D2250/292 ,  F05D2250/323 ,  F05D2250/324 ,  Y02T50/671

摘要： A variable area convergent-divergent nozzle for use as an attitude control thruster on a VTOL aircraft is formed by a curved wall forming a chamber a convergent section a throat section and a divergent section and a pair of parallel side plates, one of the side plates being movable to alter the area of the nozzle.

摘要翻译： 在VTOL飞机上用作姿态控制推进器的可变区域会聚 - 发散喷嘴由弯曲壁形成，该弯曲壁形成一个收敛部分，该部分具有一个收敛部分，一个喉部和一个平行的侧板，一个侧板 可移动以改变喷嘴的面积。

公开(公告)号：US5273237A

公开(公告)日：1993-12-28

申请号：US970747

申请日：1992-11-02

申请人： Robert W. Guyton ,  Jon A. Tinapple ,  Kenneth C. Cornelius

发明人： Robert W. Guyton ,  Jon A. Tinapple ,  Kenneth C. Cornelius

IPC分类号： B64C15/14 ,  F41G7/00 ,  F42B10/60

CPC分类号： F42B10/663 ,  B64C15/14

摘要： A system for augmenting yaw control in an aircraft is described which comprises first and second thrust nozzles disposed on the upper surface of the aircraft forebody aft of the forebody nose apex a distance of about 0.5 times the forebody diameter at about 45.degree. to either side of the symmetry plane of the forebody, each thrust nozzle oriented to direct a fluid jet at an angle of about 10.degree. from the surface of the forebody and generally rearwardly toward the symmetry plane at about 60.degree. .+-.10.degree. to the symmetry plane, and a source of pressurized fluid operatively connected to the thrust nozzles for generating the jets.

摘要翻译： 描述了一种用于增加飞行器中的偏航控制的系统，其包括设置在飞行器的上表面上的第一和第二推力喷嘴的前身前部顶点的后部约为前体直径的约0.5倍的距离， 前体的对称平面，每个推力喷嘴定向成以与前体表面大约10°的角度引导流体射流，大致向对称平面向对称平面向对称面约60°+/- 10°， 以及可操作地连接到推力喷嘴以产生射流的加压流体源。