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公开(公告)号：EP3402718A1
公开(公告)日：2018-11-21
申请号：EP17701961.9
申请日：2017-01-12
发明人： GIANNINI, Francesco , GOMEZ, Martin , COTTRELL, Dan , LEDE, Jean-Charles , ROBERTS, Tom , SCHAEFER, Carl, Jr. , COLAS, Dorian , WHIPPLE, Brian , NUHFER, Tim , HUNTER, Herb , GROHS, Jonathon , PETULLO, Steve
CPC分类号： B64C29/0033 , B64C3/385 , B64C5/04 , B64C5/16 , B64C39/024 , B64C39/12 , B64C2201/021 , B64C2201/042 , B64C2201/048 , B64D27/24 , B64D29/02 , B64D2027/026 , Y02T50/14 , Y02T50/44 , Y02T50/64
摘要： A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.
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13.发明授权Aircraft lifting surface with variable sweep distribution along the span 有权Flugzeugtragflächemit variabler Pfeilungsverteilung entlang der Spannweite
公开(公告)号：EP2687437B1
公开(公告)日：2017-01-18
申请号：EP12382282.7
申请日：2012-07-16
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14.发明公开Aircraft lifting surface with variable sweep distribution along the span 有权飞机机翼沿翼展变量Pfeilungsverteilung
公开(公告)号：EP2687437A1
公开(公告)日：2014-01-22
申请号：EP12382282.7
申请日：2012-07-16
摘要： An aircraft lifting surface (43, 73) attached to the rear or frontal end (11, 10) of the aircraft fuselage with a variable sweep angle α in an inboard part (45, 75) and with a constant sweep angle α 1 in an outboard part (47, 77) is provided. The aircraft lifting surface can be for example a horizontal tail plane (43) or a vertical tail plane attached to the rear end fuselage (11) or a canard (73) attached to the frontal end fuselage (10).
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15.发明公开Super Agile aircraft and method of flying it in supernormal flight 失效超吸收剂Flugzeug und Methodefürsupernormalen Flug。
公开(公告)号：EP0202020A1
公开(公告)日：1986-11-20
申请号：EP86302638.1
申请日：1986-04-09
发明人： Strom, Thomas H.
摘要： A superagile tactical fighter aircraft has articulatable air inlets (13), articulatable exhaust nozzles (14), highly deflectable canard surfaces (19), and control thruster jets (22) located around the nose (11) of the fuselage, on the top and bottom surfaces of the propulsion system near the exhaust nozzles, and on both sides of at least one vertical tail (20). The superagile aircraft attains supernormal flight by articulating the air inlets and exhaust nozzles, deflecting the canard surfaces, and vectoring the thruster jets. Supernormal flight may be defined as flight at which the superagile aircraft operates at an angle of attack much greater than the angle of attack which produces maximum lift. In supernormal flight, the superagile aircraft is capable of almost vertical ascents, sharp turns, and very steep descents without losing control.
摘要翻译： 超级战术战斗机具有可铰接的空气入口（13），铰接式排气喷嘴（14），高度可偏转的鸭舌面（19）和位于机身的鼻部（11）周围的控制推进器射流（22） 靠近排气喷嘴的推进系统的底面，以及至少一个垂直尾部（20）的两侧。 超级飞机通过铰接空气入口和排气喷嘴，使鸭子表面偏转并对推进器射流进行矢量化而达到超常飞行。 超正常飞行可以被定义为超级飞机飞行器的飞行距离大于产生最大升程的迎角的攻角。 在超级飞行中，超级飞行器能够几乎垂直上升，急转弯和非常陡峭的下降，而不会失去控制。
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