CONTROLLING THE ATTITUDE MANEUVERS OF FLEXIBLE SPACECRAFT BY USING TIME-OPTIMAL/FUEL-EFFICIENT SHAPED INPUTS
✍ Scribed by S. Parman; H. Koguchi
- Publisher
- Elsevier Science
- Year
- 1999
- Tongue
- English
- Weight
- 272 KB
- Volume
- 221
- Category
- Article
- ISSN
- 0022-460X
No coin nor oath required. For personal study only.
✦ Synopsis
A three-dimensional rest-to-rest attitude maneuver of ¯exible spacecraft equipped with on±o reaction jets is studied. Equations of motion of the spacecraft are developed by using Lagrangian formulation. The ®nite element method is used to discretize elastic deformations of a particular model of satellite with ¯exible solar panels by modelling the panels as ¯at plate structures in bending. Under unshaped inputs, the maneuvers induce an undesirable motion of the satellite as well as vibration of the solar panels. Time-optimal and fuel-ecient input shapers are 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 inputs are given to the satellite, the performance improves signi®cantly. Results indicate that, the fuel-ecient shaped inputs give smaller maximum de¯ections of ¯exible members compared with the time-optimal ones.