弹性高超声速飞行器建模及精细姿态控制  

The Modeling and Fine Attitude Control for Aeroelastic Hypersonic Vehicle

作　　者：孟中杰[1] 闫杰[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《宇航学报》2011年第8期1683-1687,共5页Journal of Astronautics

基　　金：国家自然科学基金(90816027);航天支撑基金(2010-HT-XGD);西工大基础研究基金(JC20100203)

摘　　要：为保证超燃冲压发动机的良好进气,需要对高超声速飞行器进行精细姿态控制,但弹性振动问题极大影响其精细姿态控制精度。以高超声速飞行器的纵向通道为例,分析弹性振动问题对飞行控制系统的影响,建立面向控制的弹性高超声速飞行器数学模型,考虑气动参数和模态参数的大范围摄动,采用主动控制策略,基于鲁棒H∞理论和LQR理论设计精细姿态控制系统。大量仿真表明:在考虑测量噪声、舵机非线性、参数大范围摄动的情况下,控制系统能够很好地跟踪刚体攻角,抑制弹性攻角,并保证进气口当地攻角±0.4度的控制精度,满足高超声速飞行器精细姿态控制的要求。To ensure a good scramjet inlet environment,a hypersonic vehicle should be controlled as a fine attitude control.But the elastic vibration greatly influences the accuracy of attitude control.Taking the longitudinal channel of hypersonic vehicle for example,the impact of elastic problem on the flight control system is analyzed and a elastic aerodynamic model is established in this paper.Considering the large-scale perturbation of model parameters caused by body/engine coupling and aerodynamic heating,the fine attitude control system is designed base on robust H∞ theory and LQR theory under a active control strategy.Simulation results show that,under the condition of measurement noise,nonlinear actuator and large-scale perturbation of model parameters,the rigid body angle of attack is tracked exactly and the flexible angle of attack is well suppressed.The Control accuracy of local angle of attack of inlet is within ± 0.4 degrees,and can meet the requirements for fine attitude control.

关 键 词：高超声速飞行器 振动建模 精细姿态控制 主动控制 鲁棒控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]