基于动态逆控制的高超声速飞行器飞 / 发一体化控制方法研究

In order to reduce the influence of the coupling characteristics between the aircraft and engine of hyper⁃ sonic vehicle, an integrated aircraft⁃engine control method of hypersonic vehicle is studied in this paper. Firstly, the control⁃oriented aircraft⁃engine integrated mathematical model of the hypersonic vehicle is established. Then, by using the nonlinear dynamic inversion (NDI) and the incremental nonlinear dynamic inversion (INDI), the outer loop control algorithm with slow attitude change and the inner loop control algorithm with fast angular rate change are respectively designed. Moreover, based on the online ontology model including aircraft⁃engine coupling charac⁃ teristics of the hypersonic vehicle, the coupling control scheme of flight posture and engine of the hypersonic vehicle is designed in the form of control linkage. Finally, the reference model, error control, online estimation and other modules are introduced into the NDI controller to ensure the flight quality and robustness requirements of the hyper⁃ sonic vehicle. The simulation results show that the aircraft⁃engine coupling control scheme based on the NDI achieves the expected control performance.