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