Analysis of aircraft pitch axis stability augmentation system using sum of squares optimization
The aircraft pitch axis stability augmentation system was analyzed using sum of squares optimization. The nonlinear dynamics of the pitch axis of a fictitious Aircraft - the Robust Civil Aircraft Model (RCAM) was considered. A LTI dynamic inversion based control law for the short period dynamics of...
| Những tác giả chính: | , , , |
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| Định dạng: | Journal article |
| Ngôn ngữ: | English |
| Được phát hành: |
2005
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| Tóm tắt: | The aircraft pitch axis stability augmentation system was analyzed using sum of squares optimization. The nonlinear dynamics of the pitch axis of a fictitious Aircraft - the Robust Civil Aircraft Model (RCAM) was considered. A LTI dynamic inversion based control law for the short period dynamics of the AC pitch axis at a particular trim configuration which is given by a particular flight condition was designed. The stability region for the LTI controlled short period dynamics model of the A/C was determined. The stability regions of the LTI controlled short period + phugoid dynamics model of the A/C were determined. The stability regions were computed using SOSTOOLS which solves a Sum-of-Squares Optimization problem. |
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