Integrated missile fin deployment system

Details Integrated missile fin deployment system Integrated missile fin deployment system

1998-05-18

2000-06-13

Poon, Peter M.

Aeronautics and astronautics

Missile stabilization or trajectory control

Externally mounted stabilizing appendage

244 324, 244 49, 244 46, F42B 1014

Patent

active

060738804

ABSTRACT:
Pairs of aerofins used for stabilization and control of missile flight are deployed through shared longitudinal slots provided in the missile body. Before launch, the pairs of aerofins, each pair comprised of a canard and a deflector, are retained in a folded position by a releasable latch mechanism within the missile body. The deflectors are mounted in a laterally displaced position from the longitudinal slots and are constrained from sliding into alignment with the slots by the presence of the folded canards. When the canards are released by the latch mechanism and permitted to extend outward to their deployed positions, the deflectors are able to laterally shift, effectively displacing the canards in the alignment position and subsequently deploying. The latch mechanism is designed to simultaneously release all the canards following missile launch, with biasing torsional springs operating to urge the canards outward through the associated slots to the extended position upon release. The deflectors are also provided with biasing springs, with these springs providing not only torsional force for urging the deflectors outward, but also compressional force to effect the lateral shifting of the deflectors. The latch mechanism is activated by an actuation mechanism when the missile has cleared the launch tube or other launch facility.

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patent: 4667899 (1987-05-01), Wedertz
patent: 4709877 (1987-12-01), Goulding
patent: 5240203 (1993-08-01), Myers
patent: 5950963 (1999-09-01), Speicher et al.
patent: 5975461 (1999-11-01), Ulrich

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