Abstract
A novel matched sliding mode attitude control method is proposed for near-space hypersonic vehicle with mismatched uncertainties. Firstly, a model with matched uncertainties is derived from matching transformation, and the derivative of system output is compensated by the estimated uncertainties from an extended disturbance observer. Secondly, a compound derivator with asymptotic stability is designed based on the disturbance observer and the frequency domain filter to obtain the derivative of system output. A novel matched sliding mode attitude control method is proposed based on variable structure control theory. Finally, the performances are assessed through a numerical simulation, and the proposed attitude control system has faster tracking performance and better robustness compared with the backstepping control system.
| Original language | English |
|---|---|
| Pages (from-to) | 2081-2086 |
| Number of pages | 6 |
| Journal | Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics |
| Volume | 39 |
| Issue number | 9 |
| DOIs | |
| State | Published - 1 Sep 2017 |
Keywords
- Derivator
- Extended disturbance observer
- Mismatched uncertainties
- Near-space hypersonic vehicle
- Sliding mode
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