公开(公告)号：US3830451A

公开(公告)日：1974-08-20

申请号：US37474473

申请日：1973-06-28

申请人： ROCKWELL INTERNATIONAL CORP

发明人： FOSNESS J

IPC分类号： F02K1/78 ,  B64C15/14 ,  B64C29/00 ,  B64C9/38 ,  B64C15/06

CPC分类号： B64C29/0091

摘要： Apparatus is disclosed for advantageously developing longitudinal, lateral, and directional attitude control and also lift control in improved manners in aircraft systems of the type capable of vertical, hovering, transitional, and conventional modes of flight operation. The aircraft system, having both a principal power plant which produces high-energy primary flow fluid and a fuselage which has attached, fixed aerodynamic liftproducing airfoils, is provided with fluid-reaction liftproducing ejector assemblies in the airfoils at locations symmetrically positioned relative to and laterally distant from the aircraft longitudinal axis and alternatively additionally at a location or locations laterally distant from such longitudinal axis and longitudinally distant from the system center of gravity. Each included airfoil lift ejector assembly is comprised of an airfoil-shaped after injector flap member, a forward ejector flap member which is spaced apart from but operated in combination with the after injector flap member in modes of flight operation other than conventional flight, a core injector essentially centered between the injector flap members, and a conduit conducting high-energy primary flow fluid from the principal power plant to a nozzle in the core injector and to Coanda-blowing slot devices in each system injector flap member during non-conventional modes of system flight. A pilot-operated control device is provided in the system for varying the divergence angles of the lift ejector diffuser sections defined by the flap members in each ejector by coordinated actuation and rotation to thereby vary the system longitudinal, lateral, and directional attitudes and also the system lift control selectively during vertical, hovering and transitional flight while perferably operating the principal power plant at substantially constant power.

摘要翻译： 公开了用于有利地显现纵向，横向和定向姿态控制的装置，并且还可以以能够垂直，悬停，过渡和常规飞行操作类型的飞机系统中的改进方式提升控制。 具有产生高能量一次流动流体的主要发电厂和附接有固定的气动提升机翼的机身的飞行器系统在对称定位的位置处在翼型件中设置流体反作用提升产生喷射器组件 相对于并且横向远离飞行器纵向轴线，或者另外在横向远离该纵向轴线并且远离系统重心的位置或位置处。 每个包括的翼型提升喷射器组件包括翼型的喷射器挡板构件之后的前喷射器挡板构件，其间隔开但是与除了常规飞行之外的飞行操作模式的后喷射器挡板构件结合操作， 喷射器基本上居中在喷射器挡板构件之间，以及导管从主动力装置到核心喷射器中的喷嘴的高能量一次流动流体的管道，以及在非常规模式下的每个系统喷射器挡板构件中的可伸缩槽装置 系统飞行 在该系统中设置一个先导操作的控制装置，用于通过协调的致动和旋转来改变由每个喷射器中的翼片构件限定的提升喷射器扩散器部分的发散角，从而改变系统纵向，横向和方向的姿态， 在垂直，悬停和过渡飞行期间选择性地进行系统升降，同时以基本恒定的功率优先操作主发电厂。

公开(公告)号：US3669386A

公开(公告)日：1972-06-13

申请号：US3669386D

申请日：1970-05-25

申请人： LOCKHEED AIRCRAFT CORP

发明人： JACOBS WILLI F ,  PLATZER MAXIMILIAN F

IPC分类号： B64C9/38 ,  B64B1/36 ,  B64C15/14

CPC分类号： B64C9/38

摘要： Controlled deflection of a jet flap emanating from an airfoil is accomplished by control fluid streams aligned at a substantial angle to the fluid jet which produces the jet flap. Disclosed embodiments show the use of the fluidically controlled jet flap to adjust the attitude and/or airfoil loading of an aircraft, to generate oscillatory lift forces for flight flutter testing of an aircraft, and to generate and control gusts in wind tunnels.

摘要翻译： 从翼型件发出的喷射翼片的受控偏转是通过与产生喷射翼片的流体射流成大致角度对准的控制流体流来实现的。 公开的实施例示出了使用流体控制的喷气翼片来调节飞行器的姿态和/或翼型载荷，以产生用于飞行器的飞行振动测试的振荡提升力，以及在风洞中产生和控制阵风。

公开(公告)号：US3507465A

公开(公告)日：1970-04-21

申请号：US3507465D

申请日：1968-05-28

申请人： ENTWICKLUNGSRING SUED GMBH

发明人： WEIGMANN ERICH W

IPC分类号： B64C29/00 ,  B64C15/14

CPC分类号： B64C29/0075

公开(公告)号：US2719683A

公开(公告)日：1955-10-04

申请号：US44771854

申请日：1954-08-04

申请人： PAUL JONES

发明人： PAUL JONES

IPC分类号： B64C15/14 ,  B64D27/14 ,  B64D39/00

CPC分类号： B64D27/14 ,  B64C15/14

公开(公告)号：US2451008A

公开(公告)日：1948-10-12

申请号：US58492345

申请日：1945-03-26

申请人： BELL AIRCRAFT CORP

发明人： WILLIAMS WILLIAM W

IPC分类号： B64C15/14 ,  B64D39/00

CPC分类号： B64C15/14

公开(公告)号：US20240336350A1

公开(公告)日：2024-10-10

申请号：US18681875

申请日：2022-08-17

申请人： NORAERO AS

发明人： Kim Schlunke

IPC分类号： B64C15/14 ,  B64C9/04 ,  B64C21/04

CPC分类号： B64C15/14 ,  B64C9/04 ,  B64C21/04

摘要： A system for providing lift, propulsion and control for an aircraft vehicle that facilitates vertical take-off and landing/short take-off and landing operations is described. The system is configured to provide an airfoil that has a leading and a trailing edge, a cross flow fan partially embedded in the airfoil and mounted adjacent to the trailing edge of the airfoil and an exit duct for the cross flow fan to provide distributed flow along the trailing edge of the system to achieve high propulsive efficiency in forward flight and a substantially vertical jet for vertical take-off and landing.

公开(公告)号：US20240246689A1

公开(公告)日：2024-07-25

申请号：US18243049

申请日：2023-09-06

申请人： JETOPTERA, INC.

发明人： Andrei Evulet

IPC分类号： B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C39/02 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  B64U30/00 ,  B64U30/10 ,  F02C3/04 ,  F02C6/04 ,  F02K1/00 ,  F02K1/36

CPC分类号： B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C23/005 ,  B64C39/024 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  F02C3/04 ,  F02C6/04 ,  F02K1/002 ,  F02K1/36 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/16 ,  B64D2033/0273 ,  B64U30/00 ,  B64U30/10 ,  F05D2220/90 ,  Y02T50/10 ,  Y02T50/30 ,  Y02T50/40

摘要： A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

公开(公告)号：US20230150654A1

公开(公告)日：2023-05-18

申请号：US17624358

申请日：2021-01-12

申请人： Sun Yat-sen University

发明人： Rui DENG ,  Fugiang LUO ,  Tiecheng WU ,  Pengnan SUN ,  Wanzhen LUO ,  Zezhen ZHANG ,  Siyuan CHEN

IPC分类号： B64C15/14 ,  B64D45/00 ,  B64C35/00 ,  G05D1/08

CPC分类号： B64C15/14 ,  B64C35/008 ,  B64D45/00 ,  G05D1/0816

摘要： Disclosed is a novel jet-propelled lift-increasing and stability-increasing amphibious aircraft and an application method thereof. An air intake fan connects and communicates with an air intake end of a pressurized air storage tank, an air outlet end of the pressurized air storage tank connects and communicates with a shunting pipeline, the shunting pipeline respectively connects and communicates with a plurality of air chambers, each connection of the plurality of air chambers and the shunting pipeline is provided with an adjusting valve, and the plurality of air chambers are distributed in a plurality of positions of the bottom of the aircraft, and are configured to jet air outwards. A navigation state sensing device is configured to detect navigation data of the aircraft and send the navigation data to an intelligent analysis device. The intelligent analysis device is configured to analyze the navigation data, obtain a control scheme and send to a jet control device. The jet control device controls open and closed states of the adjusting valves according to the control scheme to adjust a jet state of the plurality of air chambers. By adjusting the jet quantity of each position of the bottom of the aircraft from various positions, the aircraft is assisted to stably fly. The problems in the prior art are practically solved.

公开(公告)号：US20220371723A1

公开(公告)日：2022-11-24

申请号：US17749053

申请日：2022-05-19

申请人： JETOPTERA, INC.

发明人： ANDREI EVULET

IPC分类号： B64C15/14 ,  F02K1/36 ,  F02K1/46 ,  B64D37/00

摘要： A propulsion system includes at least one compressor, multiple conduits, a multiple-way valve, and at least one thrust augmentation device. A series of flaps can be retracted, tilted and operated in conjunction with the at least one thrust augmentation device. A converging channel in fluid communication with the valve is configured to allow expansion to ambient of a compressed air stream in a preferred single direction. The at least one thrust augmentation device each contains a mixing section, a throat section and a diffusor. Each said augmentation device receives compressed air from the at least one compressor via at least one of the conduits and valve and uses pressurized air as motive gas to generate thrust by fluidically entraining ambient air, mixing it with the motive gas and ejecting the motive gas at high velocities via the diffusor.

公开(公告)号：US20220315208A1

公开(公告)日：2022-10-06

申请号：US17635574

申请日：2020-09-03

申请人： BAE Systems plc

发明人： Clyde Warsop ,  Ian Lunnon ,  William James Crowther

IPC分类号： B64C19/00 ,  G05D1/10 ,  B64C39/02 ,  B64C21/08 ,  B64C15/14 ,  B64C21/04 ,  G05D7/06

摘要： The present disclosure relates to a control system for a vehicle, comprising: at least one compressor arranged to generate compressed fluid having a massflow rate; at least one fluidic control effector in fluidic communication with the at least one compressor and arranged to change the direction of travel of the vehicle when the compressed fluid is incident on the at least one fluidic control effector; a dump duct for expelling excess compressed fluid not delivered to the at least one fluidic control effector out of the vehicle; a dump valve for controlling the massflow rate of compressed fluid delivered to the dump duct; and a controller electrically coupled to the dump valve and configured to adjust the dump valve. The present disclosure also relates to an aircraft having the control system and a method of controlling a vehicle.