| 摘要 |
The deployable wing (1) of the present invention comprises an internal struc ture having diverging leading edge spars (7) attached to a keel spar (11) and cross spats (9) to form a delta wing configuration. Th is internal structure is enclosed within a volume define d by a fabric sail having an upper section (3a), a lower section (3b), and fabric r ibs (5) disposed therebetween. This fabric sail volume is internally pressurized through a ram air intake (15) at the nose stagnation point. Thi s deployable wing can be folded and deployed in the air.
|
