发明名称 RING-WING AIRCRAFT
摘要 This invention relates to ring-wing aircraft and is suited particularly, although not exclusively, to use in micro-unmanned air vehicles (UAV's) with ring-wings. An aircraft (10) according to the invention comprises a ring-win g (11) defining a duct (16) with a longitudinally-extending central axis (31), propulsion means (15) located within the duct and moveable aerofoils (13, 18 ) for controlling the aircraft in flight, the ring-wing being truncated obliquely at one end, that end being the rear (11b) when in horizontal fligh t, to form a ring-wing with opposed sides of unequal length. This arrangement produces centre of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its centre o f mass will always be at the lowest height possible when the aircraft is airborne. Therefore the aircraft has a preferred orientation, and the contro l surfaces can be oriented with respect to this preferred orientation. In addition, the oblique truncation at the rear keeps the centre of mass toward s the front of the aircraft thereby giving improved stability in all three axe s.
申请公布号 CA2410308(A1) 申请公布日期 2001.12.20
申请号 CA20012410308 申请日期 2001.04.20
申请人 BAE SYSTEMS PLC 发明人 LOCK, GARY;HENDERSON, JAMES;WOODS, MIKE;WARSOP, CLYDE
分类号 B64C39/02;B64C39/06;(IPC1-7):B64C39/02 主分类号 B64C39/02
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