Leading edge flap system for aircraft control augmentation

Details Leading edge flap system for aircraft control augmentation Leading edge flap system for aircraft control augmentation

1983-08-12

1984-12-04

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft control

Rudders and empennage

244214, B64C 900

Patent

active

044859929

ABSTRACT:
Traditional roll control systems such as ailerons, elevons or spoilers are least effective at high angles of attack due to boundary layer separation over the wing. This invention uses independently deployed leading edge flaps 16 and 18 on the upper surfaces of vortex stabilized wings 12 and 14, respectively, to shift the center of lift outboard. A rolling moment is created that is used to control roll in flight at high angles of attack. The effectiveness of the rolling moment increases linearly with angle of attack. No adverse yaw effects are induced. In an alternate mode of operation, both leading edge flaps 16 and 18 are deployed together at cruise speeds to create a very effective airbrake without appreciable modification in pitching moment. Little trim change is required.

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patent: 2768801 (1956-10-01), Bitner et al.
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patent: 4182503 (1980-01-01), Muscatell
patent: 4267990 (1981-05-01), Staudacher
patent: 4293110 (1981-10-01), Middleton et al.

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