Blended missile autopilot

Details Blended missile autopilot Blended missile autopilot

1995-06-05

1997-01-07

Carone, Michael J.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

244 321, F42B 1501

Patent

active

055908500

ABSTRACT:
Blended missile autopilots for a missile employing direct lift and tail controlled autopilots coupled by way of a blending filter. The blended missile autopilots have movable tails aft of the center of gravity of the missile and side force thrusters or movable canards mounted forward of the center of gravity, and that are controlled using the direct lift and tail-controlled autopilots. Lift is generated from the tails and side force is generated by the thrusters or canards, such that the body of the missile maintains zero angle of attack and generates no lift. The present invention thus combines the fast response of a direct lift autopilot with the high acceleration capability of a body lift autopilot, and blends the two using the blending filter to achieve improved performance.

REFERENCES:
patent: 4171115 (1979-10-01), Osder
patent: 4589594 (1986-05-01), Kranz
patent: 4624424 (1986-11-01), Pinson
patent: 4830311 (1989-05-01), Pritchard et al.
patent: 4883239 (1989-11-01), Lachmann et al.
patent: 5058836 (1991-11-01), Nobel
patent: 5088658 (1992-02-01), Forsmo
patent: 5439188 (1995-08-01), Depew, Jr. et al.
Blakelock, John H., Automatic Control of Aircraft and Missile, Second Edition. John WIley & sons, Inc.: New York, pp. 233-251 1991.

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