Abstract
Reliable and cost-effective control of spacecraft should account for modeling uncertainties, unexpected disturbances, subsystem failures, and limited resources simultaneously. This paper presents an indirect (nonregressor-based) approach to attitude tracking control of spacecraft. It is shown that the control algorithms developed are not only robust against external disturbances and adaptive to unknown and time-varying mass/inertia properties, but also able to accommodate actuator failures under limited thrusts. All are achieved with inexpensive online computations (a feature of practical importance in reducing the usage of onboard resources in terms of computing power and memory size). Furthermore, this method is user/designer friendly in that it does not involve a time-consuming design procedure and demands little redesigning or reprogramming during vehicle operation. The benefits of the proposed control method are analytically authenticated and also validated via simulation study.
| Original language | English |
|---|---|
| Pages (from-to) | 1456-1463 |
| Number of pages | 8 |
| Journal | Journal of Guidance, Control, and Dynamics |
| Volume | 31 |
| Issue number | 5 |
| DOIs | |
| Publication status | Published - Aug 2008 |
| Externally published | Yes |
Bibliographical note
The authors would like to thank the associate editor for his variable comments, which substantially improved the quality of the paper.Funding
This work was sponsored by the NASA Constellation University Institutes Project under grant NCC3-989 with Claudia Meyer as the project manager.
Keywords
- Attitude Tracking
- Rigid Spacecraft
- Actuators
- Control Algorithm
- Onboard Computing
- Attitude Dynamics
- Adaptive Control Algorithm
- Variable Structure Control
- Quaternions
- Numerical Simulation