变结构近空间飞行器大飞行包络控制特性研究

Variable Structure Near Space Vehicle Control Characteristics of Large Flight Envelope

针对近空间飞行器大包络、多任务模式飞行运动,结合通用高超声速飞行器确立了近空间飞行器不同飞行阶段的机体结构,详细建立了气动参数由攻角、马赫数与控制舵面偏转量表示的12状态动力学方程,绘制了不同飞行阶段气动参数随攻角、马赫数的变化曲线,建立了近空间飞行器的大包络运动控制模型,而后研究了不同机体结构与飞行状态下的控制特性和各通道耦合性质,表明该系统可以有效用于全程强鲁棒稳定飞行控制系统的设计与仿真测试,充分体现了近空间飞行器非线性、时变、耦合等飞行运动特点,仿真验证表明了研究结果符合现有分析结果。

The variable structure near space vehicle is confirmed in different flight stages for large envelop and multiple mission mode based on generic hypersonic vehicle. Twelve states dynamic system is developed with aerodynamic coefficients which are denoted by angle of attack, roach number and deflection of control surface. Diagrams of aerodynamic coefficient are exhibited in different flight processes. The large envelop dynamic model is established and demonstrates the charaeteristies of nonlinear, fast time-varying and tight coupling by researching control and coupling characteristics in different flight conditions. The model can be effectively applied in designing and testing large envelop robust stable flight control system. Simulation results indicate that this model is rational and accord with existing reference.