Established procedures of linear, quadratic Gaussian optimal estimation and control are developed and interpreted for their application to spacecraft with dynamically significant elastic appendages. Comparisons are made between alternative coordinate systems, and a realistic range of design parameters is considered. For single axis control system evaluation is accomplished by simulation of a fifteenth-order spacecraft plant with alternative second-order, fourth-order, and sixth-order constant gain estimators. Results point out the importance of modeling errors.
Optimal estimation and attitude control of a solar electric propulsion spacecraft
Optimalwertbestimmung und Stellungsregelung eines Sonnenenergie-getriebenen Raumfahrzeuges
IEEE Transactions on Aerospace and Electronic Systems ; AES-13 , 1 ; 35-47
1977
13 Seiten, 15 Quellen
Article (Journal)
English
Three-axis attitude control for solar-powered electric propulsion spacecraft
Tema Archive | 1974
|Three-Axis Attitude Control for Solar-Powered Electric Propulsion Spacecraft
SAE Technical Papers | 1974
|