Accession Number:

ADP003387

Title:

Multifunction Spacecraft Attitude Estimation and Navigation System,

Descriptive Note:

Corporate Author:

MARTRA S A VELIZY-VILLACOUBLAY (FRANCE)

Personal Author(s):

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

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE