The purpose of this paper is to design helicopter H∞ flight control system to improve its stability, maneuverability, and agility. Firstly, the linear mathematical model of a helicopter is established from the nonlinear six degree-of-freedom dynamic equations. Then, linear H ∞ control theory is applied to the linearized model to design the H∞ controller, which, in turn, is integrated in the nonlinear model of a helicopter to simulate nonlinear dynamic response, and to evaluate flying quality. Two helicopter flying quality indices, quickness index and phase delay margin, are adopted to test the robustness of H ∞ controller, and the results show that while the forward velocity of helicopter changes, the H∞ controller can maintain the specifications in level-1 standard.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering