Mechanism for thrust vector control using multiple nozzles and o

Details Mechanism for thrust vector control using multiple nozzles and o Mechanism for thrust vector control using multiple nozzles and o

1997-05-21

1999-03-30

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft, steering propulsion

Fluid

244 327, 23926535, 60232, B64C 1502

Patent

active

058878211

ABSTRACT:
In a missile thrust vector control (TVC) system, two yoke plates are used which surround a pair of pivotably-mounted rocket nozzles. The rocket nozzles pass through corresponding elongated slots disposed on each yoke plate, the elongate slots engaging said rocket nozzles and operating to actuate the movement of the rocket nozzles in accordance with command signals issued by the missile autopilot. The actuator yoke plates are mounted for movement in orthogonal directions, and for rotation in unison. The orthogonal movement of the yoke plates effects corresponding movement of the rocket nozzles in the yaw and pitch directions. Simultaneous rotation of the yoke plates produces a relative twisting of the pivotably-mounted rocket nozzles causing thrust angles to deviate from the missile central axis in opposite directions but equal degree, thereby imparting a roll moment to the missile. In this fashion, any combination of movements of the missile during flight is made possible.

REFERENCES:
patent: 3200586 (1965-08-01), Ernest
patent: 3200587 (1965-08-01), Tolson
patent: 3786993 (1974-01-01), Burgess et al.
patent: 3986683 (1976-10-01), Ellison
patent: 4163534 (1979-08-01), Seeger
patent: 4432512 (1984-02-01), Young
patent: 4892253 (1990-01-01), Speicher et al.
patent: 5505408 (1996-04-01), Speicher et al.

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