Abstract
According to the initial value solution procedures of the pseudo-inverse method, reach the conclusion that its solutions may have negative thrust or exceed the saturation constraints of the thruster of a drag-free spacecraft. Then we put forward the two-step optimization method and build up the relations between thrusters. If the output of one thruster is negative, we replace it with a coherent thruster to assure all its outputs are positive. If the saturation constraints of the thruster are exceeded, we determine the upper and lower boundaries of the saturation constraints to make sure all the outputs for the thruster are within the threshold. Finally, we simulate the interference tracking and the thrust output of the drag- free spacecraft. The simulation results show that our optimization method can satisfy the output requirements of the thruster and realize the real-time continuous thrust allocation of the drag-free spacecraft.
| Original language | English |
|---|---|
| Pages (from-to) | 948-953 |
| Number of pages | 6 |
| Journal | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| Volume | 35 |
| Issue number | 6 |
| State | Published - 1 Dec 2017 |
Keywords
- Actuators
- Aerodynamic drag
- Allocation
- Attitude control
- Coherent thruster
- Computational efficiency
- Computer simulation
- Constrained optimization
- Constraint theory
- Continuous thrust allocation
- Drag
- Drag-free spacecraft
- Initial value problems
- Initial value solution procedure
- Optimization
- Pseudo-inverse method
- Real time control
- Satellites
- Spacecraft
- Threshold
- Tracking(position)