High angle-of-attack missile control system for aerodynamically

Details High angle-of-attack missile control system for aerodynamically High angle-of-attack missile control system for aerodynamically

1978-06-08

1980-11-18

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

318585, 318586, 364434, F41G 700, G05D 108

Patent

active

042341426

ABSTRACT:
A missile control system can avoid instability at high angles of attack by cross-coupling roll and steering sensor signals between the steering and roll channels. The control law for the system is derived by use of the Model-in-the-Performance Index Technique which makes the system respond at high angles as it does at low angles with desired response times, bandwidths, and stability.

REFERENCES:
patent: 2924401 (1960-02-01), Goss et al.
patent: 3945593 (1976-03-01), Schanzer
patent: 3946968 (1976-03-01), Stallard
patent: 4033525 (1977-07-01), Leonard
patent: 4037806 (1977-07-01), Hirsch et al.
patent: 4044237 (1977-08-01), Cowgill
Kalman, et al., "Fundamental Study of Adaptive Control Systems", ASD-TR-67, vol. II, Oct. 1964.
AF Manual 52-31, Guided Missile Fundamentals, Sep. 20, 1957, UG 630u491, 1957, e.z. pp. 379-387.
Tyler, Jr., J. S. "The Characteristics of Model-Following Systems as Synthesized by Optimal Control", IEE Trans. on Automatic Control, 10, 1964, p. 485.

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