Abstract
This paper studies a nonlinear discrete-time state observer design problem for rigid spacecraft, particularly for spacecraft attitude estimation. The observer is a partial state observer, and it is constructed based on a numerical algorithm that preserves the orthogonality of a matrix function. Orthogonality preservation is important as the attitude matrix to be estimated is orthogonal, whereas in general orthogonality is destroyed under sampling. We prove that the proposed construction yields a semiglobal practical asymptotic observer. We also show that the separation principle holds for our problem, and hence stabilization using output feedback is possible. Two examples are provided to illustrate the usefulness of our results in a sampled-data implementation
| Original language | English |
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| DOIs | |
| Publication status | Published - 7 May 2007 |
| Event | IEEE Conference on Decision and Control - California, San Diego, United States Duration: 13 Dec 2006 → 15 Dec 2006 |
Conference
| Conference | IEEE Conference on Decision and Control |
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| Country/Territory | United States |
| City | San Diego |
| Period | 13/12/06 → 15/12/06 |
Bibliographical note
The full text is currently unavailable on the repository.Keywords
- Space vehicles
- Position measurement
- Observers
- Sun
- Algorithm design and analysis
- Attitude control
- State estimation
- Output feedback
- Earth
- USA Councils
- space vehicles
- attitude control
- discrete time systems
- nonlinear control systems
- observers
- sampled data systems
- semiglobal practical asymptotic observer
- nonlinear sampled-data systems
- orthogonality preservation
- output feedback
- numerical algorithm
- spacecraft attitude determination
- nonlinear discrete-time state observer design problem
- rigid spacecraft
- spacecraft attitude estimation
- partial state observer
- Spacecraft
- discrete-time observer