Analysis of aircraft pitch axis stability augmentation system using sum of squares optimization
The region of attraction of a trim point for the pitch axis of a nonlinear modeled aircraft modulated via linear dynamic inversion based controller was determined numerically. The model incorporates uncertainty in the position of center of gravity along the X-body axis. The stability regions are computed using SOSTOOLS, which converts the required sum of squares conditions to an appropriate semi definite program that is then solved using SeDuMi.
© 2005 AACC. Issue Date: 8-10 June 2005. Date of Current Version: 01 August 2005.
Published - KRIacc05a.pdf