-
公开(公告)号：EP3691967B1
公开(公告)日：2024-08-07
申请号：EP18864524.6
申请日：2018-10-02
CPC分类号： B64C15/02 , B64C27/56 , B64C29/0025 , B64C29/0033 , Y02T50/10 , B64U20/70 , B64U30/26 , B64U30/295
-
公开(公告)号：EP2903895A4
公开(公告)日：2016-06-01
申请号：EP13843351
申请日：2013-10-04
申请人： SKYKAR INC , LENG MARCUS
发明人： LENG MARCUS
CPC分类号： B64C27/26 , B60L11/1805 , B60L11/1859 , B60L11/1861 , B64C1/26 , B64C11/46 , B64C15/02 , B64C29/00 , B64C29/0025 , B64C29/02 , B64C39/026 , B64D17/00 , B64D27/24 , B64D31/12 , B64D33/08
摘要： An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control.
-
公开(公告)号：EP2903895A1
公开(公告)日：2015-08-12
申请号：EP13843351.1
申请日：2013-10-04
申请人： Skykar Inc. , Leng, Marcus
发明人： LENG, Marcus
CPC分类号： B64C27/26 , B60L50/52 , B60L58/12 , B60L58/14 , B64C1/26 , B64C11/46 , B64C15/02 , B64C29/00 , B64C29/0025 , B64C29/02 , B64C39/026 , B64D17/00 , B64D27/24 , B64D31/12 , B64D33/08
摘要： An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control.
-
公开(公告)号：EP2452873B1
公开(公告)日：2015-04-01
申请号：EP11187906.0
申请日：2011-11-04
摘要： A system and method to control flight of an aircraft. The aircraft (101; 1001) having an engine (111; 1017) with a rotatably nozzle assembly (401) configured to create forward propulsion and yaw control of the aircraft (101; 1001). The engine exhaust (129c) passing through the nozzle (401) is redirected with a valve (419) disposed within the nozzle (401). Lift is created with a lift system (1009) carried by the wing (1007) of the aircraft (1001). Additional lift is created during flight with a retractable wing extension (1015) disposed within the wing (1007) of the aircraft (1001).
-
公开(公告)号：EP2116714B1
公开(公告)日：2011-10-26
申请号：EP07806238.7
申请日：2007-08-29
发明人： HORINOUCHI, Shigeru
CPC分类号： B64D33/04 , B64C15/02 , B64D33/06 , F02K1/006 , F02K1/1207 , F02K1/44 , F02K1/60 , F02K1/763 , F05D2260/96 , Y02T50/671
摘要： A low noise air craft which can reduce engine noise on the ground sharply at the time of take-off and landing by utilizing a well-known mechanism. By utilizing a thrust deflection means constituted of a well-known mechanism for making the direction of thrust variable, exhaust direction of an engine is deflected to the upper side (upward) of the course direction (flight direction) of the aircraft so that the maximum propagation direction of the engine jet exhaust noise is kept away from the ground, thus reducing the engine noise level on the ground at the time of aircraft take-off and landing. In particular, when the thrust deflection type exhaust nozzle (20) is constituted of an upper deflection nozzle (21) and a lower deflection nozzle (22), the engine can generate reverse thrust during a landing run.
-
6.发明授权Extremely short takeoff and landing of aircraft using multi-axis thrust vectoring 失效通过使用多轴推力矢量极短的起飞和飞机的着陆距离
公开(公告)号：EP0882647B1
公开(公告)日：2005-07-27
申请号：EP98109745.4
申请日：1998-05-28
CPC分类号： F02K1/002 , B64C15/02 , B64C25/001 , B64C2025/005 , Y02T50/671
-
公开(公告)号：EP1364872A3
公开(公告)日：2004-01-07
申请号：EP03012874.8
申请日：2001-02-07
申请人： Aerovironment Inc.
CPC分类号： B64D27/24 , B64C15/02 , B64C39/10 , B64D31/06 , B64D2211/00 , G05D1/0808 , Y02T50/12 , Y02T50/55 , Y02T50/62
摘要： An aircraft (10) has a plurality of motors (14) mounted on its wing (12), the wing being configured to produce a dihedral during flight, wherein the dihedral causes at least one of the motors (14) to produce thrust above the center of drag (202) and at least one motor (14) to produce thrust below the center of drag (202), such that control of the relative thrusts can control the pitch of the aircraft (10).
-
8.发明授权
公开(公告)号：EP0385834B1
公开(公告)日：1993-05-05
申请号：EP90400502.2
申请日：1990-02-23
CPC分类号： F02K1/006 , B64C15/02 , Y02T50/671
-
公开(公告)号：EP0322775A3
公开(公告)日：1989-11-08
申请号：EP88121541.2
申请日：1988-12-23
CPC分类号： B64C29/0075 , B64C15/02
摘要： Two tail control surfaces operable doubly as thrust-deflectng vanes are rotatably supported on respective lateral sides of a jet engine of a V/STOL aircraft. Each tail surface (8) can be actuated to rotate about an axis parallel to the engine axis (9) and also to rotate about an axis perpendicular to the engine axis. The tail surfaces can be placed in outer positions on respective lateral sides of the engine for high-speed flight to function as stabilizer surfaces and to be placed within the engine exhaust gas stream and, moreover, to be placed in an inclined state relative thereto thereby to deflect the stream downward for slow-speed or hovering flight.
-
公开(公告)号：EP0120008A1
公开(公告)日：1984-10-03
申请号：EP83900087.0
申请日：1982-09-29
申请人： THE BOEING COMPANY
CPC分类号： B64C29/0075 , B64C3/385 , B64C15/02
摘要： Avion à décollage et atterrissage courts (10) et avion à décollage et atterrissage verticaux/courts (10) possédant des moteurs soufflants (12, 14) sur une surface supérieure sur des ailes en forme d'ailes de mouettes (24, 26) qui peuvent être inclinées et subir un mouvement de translation au moyen d'un dispositif de translation à incidence variable (52). Les moyens de translation (80, 62, 64) sont adaptés pour assurer une compensation du déplacement du centre de gravité et une compensation du moment critique des moteurs. La poussée vectorisée des moteurs soufflants de la surface supérieure s'effectue par une combinaison de l'inclinaison de l'aile et de la soufflante de la surface supérieure, et la vectorisation des moteurs inférieurs de sustentation/accélération (124, 126) s'effectue à l'aide de tuyères orientables (138, 140). La compensation latérale critique du moteur s'effectue par une combinaison de l'inclinaison de l'avion et d'une vectorisation différentielle à l'aide des moteurs inférieurs de sustentation/accélération (124, 126).
摘要翻译： 在鸥翼翼（24,26）的上表面上具有鼓风机马达（12,14）的短距起飞和降落飞机（10）和垂直/短距起降飞机（10）， 可以借助可变入射平移装置（52）倾斜和平移。 平移装置（80,62,64）适于补偿重心的位移和电机的临界力矩的补偿。 上表面的鼓风机马达的矢量推力是由翼的和上表面的送风机的倾斜度的组合，和较低的马达升降/加速度的矢量（124，126）s'的实现 通过可转向喷嘴（138,140）实现。 发动机的临界横向补偿通过使用较低悬浮/加速电机（124,126）的飞机倾斜和差异矢量化的组合来实现。
-
-
-
-
-
-
-
-
-
搜索结果
88 条记录 (耗时 0.014 秒)
