Accession Number : ADP003387

Title :   Multifunction Spacecraft Attitude Estimation and Navigation System,

Corporate Author : MARTRA S A VELIZY-VILLACOUBLAY (FRANCE)

Personal Author(s) : Amieux,J. C. ; Claudinon,B.

Report Date : JAN 1984

Pagination or Media Count : 17

Abstract : The primary function of a spacecraft attitude control subsystem is the attitude determination and, more generally, the state estimation (attitude of the main body, appendages and flexible modes). The so-called optical-inertial concept is first described with application to a number of modern spacecraft; an example of implementation using space-qualified microprocessors is given in detail; the state estimation of a flexible spacecraft is then considered, a technique which can be readily implemented on existing hardware. The extension of this concept to autonomous orbit control of an orbiting spacecraft is then considered for future development. (Author)

Descriptors :   *Attitude control systems, *Satellite attitude, *Space navigation, *Space systems, Orbits, Gyro stabilizers, Stabilization systems, Autonomous navigation, Angular motion, Algorithms, Kalman filtering

Distribution Statement : APPROVED FOR PUBLIC RELEASE