Missile steering device

Details Missile steering device Missile steering device

1991-03-20

1992-05-12

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

23926523, F42B 1066

Patent

active

051120070

ABSTRACT:
To improve the steering of autonomous missiles with respect to great thrusts and a large number of guide pulses, preferably in a caliber range of less than 100 mm, fluidic wall jet elements are provided in branching conduits which are connected to radially directed steering nozzles and which are disposed in a plurality, for example, four, of control discs arranged one behind the other within the missile. The respective fluidic wall jet elements permit a sudden change in direction in a respective branching conduit of a hot gas stream generated by a gas generator. This makes it possible to generate, for example, a change in the direction of the gas stream from one steering nozzle to an oppositely disposed steering nozzle. A plurality of miniature flame capsules or compressed gas cartridges are arranged in a space saving manner in at least one disc-shaped recess as the actuators for the fluidic wall jet elements. The actuators ensure individual or joint actuation of steering nozzles arranged, for example, at 90.degree. offsets on the missile circumference. Additionally, it becomes possible to perform variable time steering processes, particularly those with extremely short response times of less than 1 ms.

REFERENCES:
patent: 3740003 (1973-06-01), Ayre et al.
patent: 4408735 (1983-10-01), Metz
patent: 4413795 (1983-11-01), Ryan
patent: 4803925 (1989-02-01), Buchele-Buecher

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