摘要
针对高超声速飞行器调姿段姿态控制问题,将超燃冲压发动机不同工作状态对高超声速飞行器模型参数的影响看作是不确定对象鲁棒性问题的扩展,应用QFT设计了鲁棒控制器。通过将飞控系统的时域指标转化为频域指标,生成Nichols图上的复合频域边界,利用回路整形设计控制器和前置滤波器,使得闭环系统频率响应满足所有性能指标要求。仿真结果表明,所设计控制器能够满足高超声速飞行器调姿段控制需求,有效抑制输出端干扰,并且当模型参数具有较大范围的不确定性时,具有良好鲁棒性能,有较好的工程应用价值。
For the problem of attitude control during the attitude regulation phase, the influence of different working conditions of scramjet on the parameters of the hypersonic vehicle model was treated as an extension of the model uncertainty robustness problem. A robust longitudinal flight controller based on QFT was designed. To make the closed loop transfer function meet all the desired performance requirements, the composite bounds on the Nichols chart were generated with the frequency domain specifications converted from desired time domain specifications of flight control system and the design of the controller and pre-filter was performed by loop shaping. Simulation results show that the designed controller satisfies the performance specifications, rejects output disturbance effectively and is robust when the uncertain model parameters vary within large range. The proposed controller can be applied in engineering with favorable robust property.
出处
《系统仿真学报》
CAS
CSCD
北大核心
2010年第3期695-698,703,共5页
Journal of System Simulation
