Accession Number : ADD011970
Title : SSICM (Spin Stabilized Impulsively Controlled Missile) Guidance and Control Concept.
Descriptive Note : Patent,
Corporate Author : DEPARTMENT OF THE ARMY WASHINGTON DC
Personal Author(s) : Howell,W Max
Report Date : 24 Sep 1985
Pagination or Media Count : 8
Abstract : This patent presents the guidance scheme utilizing wide beam width semiactive RF sensors, a precision roll attitude reference, and a controlled grade pitch, yaw and roll rate gyros to deliver high quality homing guidance information to a spin stabilized controlled missile. A filtering system is utilized to eliminate errors caused by body roll signals generated due to the spin of the missiles. The nutational motion is used to calibrate the sensors. Impulsive maneuvers are utilized to intercept incoming ballistic targets.
Descriptors : *PATENTS, *GUIDANCE, *ATTITUDE CONTROL SYSTEMS, SPIN STABILIZATION, GYROSCOPES, GATES(CIRCUITS), NAVIGATION REFERENCE, ROLL, PITCH(MOTION), YAW, FLIGHT MANEUVERS, PULSES, INTERCEPTORS, SURFACE TO AIR MISSILES
Subject Categories : Surface-launched Guided Missiles
Distribution Statement : APPROVED FOR PUBLIC RELEASE