Aerodynamic flail for a spinning projectile

Details Aerodynamic flail for a spinning projectile Aerodynamic flail for a spinning projectile

1989-02-06

1990-05-01

Brown, David H.

Ammunition and explosives

Shells

Practice

102387, 102388, 102529, F42B 800, F42B 1320, F42B 1510

Patent

active

H00007765

ABSTRACT:
A flail is provided which reduces the spin of a projectile in a recovery system which includes a parachute, a cable connected to the parachute, a swivel, and means for connecting the swivel to the projectile. The flail includes a plurality of flexible filaments and a rotor for attaching the filaments to the front end of the projectile. The rotor is located radially with respect to the spinning axis of the projectile. In one embodiment, the projectile includes a first nose cone section housing a deployable spin damping assembly; a second nose cone section, housing a deployable parachute assembly; a shell section, supporting the first and second nose cone sections during flight of the projectile; a mechanism for releasing the first nose cone section from the second cone section; and a mechanism for releasing the second nose cone section from the shell section. In operation of this embodiment, the deployable spin damping assembly deploys during flight of the projectile when the mechanism for releasing the first nose cone section from the second nose cone section are actuated. Then, upon actuation of the mechanism for releasing the second nose cone section from the shell section, two things happen: the spin damping assembly separates from the projectile; and the deployable parachute assembly is deployed.

REFERENCES:
W. Pepper et al., "Parachute System To Recover Spinning (250 RPS 155-mm Shell Subjected To 20,000 g's Launch Conditions", Sandia Report SC-R-68-1806, Sep. 1968 (also No. 68-937, AIAA 2nd Aerodynamic Deceleration Systems Conference, El Centro, CA, Sep. 23-25, 1968.

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