Integrated thrust vector aerodynamic control surface

Details Integrated thrust vector aerodynamic control surface Integrated thrust vector aerodynamic control surface

1975-08-08

1977-08-30

Pendegrass, Verlin R.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

F42B 1518

Patent

active

040449700

ABSTRACT:
A missile is disclosed on which constant burning thrust reaction motors are provided integral with the tail panels of the missile to enhance the effect thereof, particularly during the boost phase of flight. The motors provide thrust along the chord of the tail panel and are moved about the axis of rotation of the tail panel by the servo motor associated therewith. The servo motors are activated by central missile control circuitry.

REFERENCES:
patent: 3013494 (1961-12-01), Chanut
patent: 3164338 (1965-01-01), Cooper et al.
patent: 3276376 (1966-10-01), Cubbison et al.
patent: 3286956 (1966-11-01), Nitikman

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