Abstract
A three-dimensional rest-to-rest attitude maneuver of flexible spacecraft equipped by on-off reaction jets is studied. Equations of motion of the spacecraft is developed by employing a hybrid system of coordinates and Lagrangian formulation. The finite element method is used to examine discrete elastic deformations of a particular model of satellite carrying flexible solar panels by modelling the panels as flat plate structures in bending. Results indicate that, under an unshaped input, the maneuvers induce undesirable attitude angle motions of the satellite as well as vibration of the solar panels. An input shaper is then applied to reduce the residual oscillation of its motion at several natural frequencies in order to get an expected pointing precision of the satellite. Once the shaped input is given to the satellite, the performance improves significantly.
Highlights
Precise orientation of spacecraft during its operation in space requires frequent corrections of its attitude
Flexible spacecraft equipped with on-off reaction jets cannot produce the variable-amplitude actuation force that is usually required with input shaping; the spacecraft must be moved with constant amplitude force pulses
For the system with a large number of flexible modes such as the finite element model of satellite with flexible solar panels studied by Koguchi and Parman [4,5,6], when the satellite is subjected to a shaped input suppressing residual vibration at the frequency with largest vibration amplitude, other frequencies can amplify the resulted residual vibration so that the satellite attitude oscillation after maneuver is still greater than the permissible attitude error
Summary
Precise orientation of spacecraft during its operation in space requires frequent corrections of its attitude. For the system with a large number of flexible modes such as the finite element model of satellite with flexible solar panels studied by Koguchi and Parman [4,5,6], when the satellite is subjected to a shaped input suppressing residual vibration at the frequency with largest vibration amplitude, other frequencies can amplify the resulted residual vibration so that the satellite attitude oscillation after maneuver is still greater than the permissible attitude error. The maximum deflections of solar panels during the attitude maneuver are studied qualitatively in order to find the strategy in choosing an input shaper with small deflection of flexible members
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