Accession Number : ADD008037

Title :   High Angle-of-Attack Missile Control System for Aerodynamically Controlled Missiles.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE NAVY WASHINGTON DC

Personal Author(s) : Yost,David J ; Arrow,Arthur ; Konigsberg,Robert L

Report Date : 18 Nov 1980

Pagination or Media Count : 14

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.

Descriptors :   *Patents, *Guided missiles, *Flight control systems, Pitch(Motion), Roll, Yaw, Aerodynamic forces, Coupling(Interaction), Feedback, Kinematics, Steering, Aerodynamic stability, Angle of attack

Subject Categories : Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE