Flight Attitude Controller Using Dynamic Inversion Theory with Stability Margin Guarantee
Journal Title: International Journal of engineering Research and Applications - Year 2018, Vol 8, Issue 12
Abstract
In order to realize reusable launch vehicle, flight attitude control system is important. Dynamic inversion (DI) theory is known well as nonlinear control theory. DI theory can cancel the nonlinear dynamics and linearize the input and output maps. Therefore, closed loop analysis through flight trajectory becomes easier than other control systems, e.g. gain tuning method. When we use DI theory, we must know certain dynamics models. However, since modeling errors necessarily arise, ensuring robustness is important. Even using DI theory, stability margins cannot be uniquely determined because the loop is opened when we calculate stability margins. In this paper, the authors propose the stability margin guaranteeing method for flight control system using DI theory.In this article the authors propose the new evaluation function for guaranteeing required stability margin. By onboard design variable tuning, all stability margins become larger than required ones.
Authors and Affiliations
Kento Shirakata, Koichi Yonemoto, Takahiro Fujikawa
Keywords
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- EP ID EP431555
- DOI 10.9790/9622-0812031627.
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