Attitude Dynamics of a Satellite During Deployment of Large Plate-Type Structures

The paper analyzes the attitude dynamics of a spacecraft while deploying large plate-like structures. Equations governing the rotational dynamics of the system and the lateral vibrations of the panels are obtained using a Lagrangian formulation. Even the linearized equations are unusually lengthy and involve time-varying coefficients. Hence they are integrated numerically for given length histories. Two types of axial extension—uniform and exponential—are considered. The system parameters are varied for the two procedures and their influence on the attitude dynamics is noted.