Gapped flap for a missile

Details Gapped flap for a missile Gapped flap for a missile

1992-06-22

1994-02-01

Brown, David H.

Aeronautics and astronautics

Missile stabilization or trajectory control

Externally mounted stabilizing appendage

244 327, F42B 1014, F42B 1062

Patent

active

052825884

ABSTRACT:
A missile (20) comprises a missile body (22) and a plurality of (typically four) body flaps (28) located around the circumference of the missile body (22). Each body flap (28) is independently pivotable to an extended position wherein the body flap (28) is pivoted outwardly from a pivot axis along the leading edge (34) of the body flap (28). The forward edge (34) of the body flap (28) is displaced outwardly from the body (22) of the missile (20) by a distance no less than a boundary layer thickness of the body (22) of the missile (22) at the maximum operating speed and altitude of the missile (20), and preferably about the boundary layer thickness, which thickness typically is about 1-3 inches for a high-velocity missile.

REFERENCES:
patent: H854 (1990-12-01), Madderra
patent: 3313499 (1967-04-01), hman
patent: 4411398 (1983-10-01), Wedertz et al.
patent: 5125344 (1992-06-01), Kline et al.

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