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)
Multifunction Spacecraft Attitude Estimation and Navigation System
1984
17 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Navigation & Guidance System Components , Unmanned Spacecraft , Attitude control systems , Satellite attitude , Space navigation , Space systems , Orbits , Gyro stabilizers , Stabilization systems , Autonomous navigation , Angular motion , Algorithms , Kalman filtering , Foreign technology , Component Reports , NATO furnished , Optico-inertial concept
Spacecraft large attitude estimation using a navigation sensor
Tema Archive | 2010
|Spacecraft Large Attitude Estimation Using a Navigation Sensor
Online Contents | 2010
|Kalman Filtering for Spacecraft Attitude Estimation
AIAA | 1982
|Unscented Filtering for Spacecraft Attitude Estimation
Online Contents | 2003
|