基于逆动力学的飞行器直接力控制系统及其稳定性分析

The Direct Force Flight Control Systems Based on the Inversed Dynamics and Their Stability Analysis

针对现代飞行器飞行动力学特性的非线性及耦合问题日益显著,传统线性系统设计方法已难以满足控制要求的现状,在非线性系统的逆系统解耦控制方法的基础上,提出了基于逆动力学的飞行器直接力控制技术。在翼面载荷可控的条件下,选取扰动较小的机体动力学部分建立逆系统模型进行解耦补偿,降低了逆系统模型的建模难度,提高了逆模型建模精度。稳定性分析证明了扰动条件下系统的稳定性,并求取了稳定条件。仿真结果验证了系统在不同负载条件下的稳定性,表现了良好的鲁棒性。

As the maneuverability of the modem aircraft is increasing day after day, the nonlinear effect and coupling character of the flight dynamics becone a big problem to the flight control systems. The nonlinear decoupled control system is needed for the aircraft controlling. Based on the inversed system mothods, the direct force flight control system based on the inversed dynamics is designed. With the help of the active load control technology for the aerodynamic surface, the influence of the aerodynamic disturbance and model uncertainty can be rejected, and the modelling precision of the inversed system can be improved. The stability of the disturbed system is analized and the stabilizing condition is given. The simulation results proved that the new flight control system has a good performance in the decoupled flight attitude control and the decoupled flying path control mode, it also shows a good anti-interference ability and strong rubustness in the simulation.