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