Accession Number:

ADP003387

Title:

Multifunction Spacecraft Attitude Estimation and Navigation System,

Descriptive Note:

Corporate Author:

MARTRA S A VELIZY-VILLACOUBLAY (FRANCE)

Personal Author(s):

• Amieux,J. C.
• Claudinon,B.

Report Date:

1984-01-01

Pagination or Media Count:

17.0

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

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE