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