组合动力验证机助推段纵向控制器设计

Longitudinal Control Law Design for Boost Phase of Hypersonic Vehicle

针对飞行器的飞行特点和自身的气动结构,建立复杂的非线性数学模型,给出静稳定性和模态特性的分析。为解决高超声速飞行器在助推段因纵向静不稳度大而导致的常规控制律鲁棒性不足的问题,设计基于角速率指令内回路的纵向控制律,并从时域、频域、鲁棒性三方面进行分析,得出指令内回路适用于助推段纵向控制的结论。

According to the flight characteristics and aerodynamic structure of aircraft,a complex non-linear mathematical model is established,and the static stability and modal characteristics are analyzed.In order to solve the problem of insufficient robustness of conventional control law caused by the large longitudinal static instability of hypersonic vehicle in boost phase,a longitudinal control law based on the inner loop of angular rate command is designed.From the three aspects of time domain,frequency domain and robustness,the designed control law is analyzed,with the conclusion that the inner loop of command fits the longitudinal control of boost phase well.