Stochastic control of pitch motion of satellites using stabilizing flaps
Abstract
The modelling analysis and synthesis of an attitude control system for low orbit artificial satellites, using stabilizing flaps are presented. The function of the system is to maintain the satellite aligned with the local vertical. The aerodynamic forces on the satellite are modelled assuming free molecular flow using the kinetic theory of gases. The control system development is considered through the application of stochastic control concepts. The satellite motion is described by the equations of motion based on Newtonian formulation. Starting from the separation principle, a sequential procedure is developed in which the state estimation and control problems are handled simultaneously. State estimate is provided by Kalman filter using the information about the position of the satellite and of the flaps. The controller acts on satellite in real time, and the stabilizing flaps are the only control elements.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 August 1984
 Bibcode:
 1984STIN...8434458F
 Keywords:

 Artificial Satellites;
 Attitude Control;
 Earth Orbits;
 Flaps (Control Surfaces);
 Pitch (Inclination);
 Stochastic Processes;
 Aerodynamic Forces;
 Equations Of Motion;
 Kalman Filters;
 Stabilization;
 State Estimation;
 Launch Vehicles and Space Vehicles