摘要
飞航导弹的飞行主要是通过姿态稳定与调节来实现的。通过以小扰动模型为基础的导弹动力学特性分析,建立了导弹姿态控制回路的串级控制结构,并且以离散模型作为基于递推最小二乘法的自适应预测控制的被控对象,把原先响应较慢的质心控制转换为反应较快而且精度高的弹道角控制。根据导弹的特性,在姿态内回路采用广义预测控制,在弹道外回路采用一种积分形式的预测控制。在参考信号上,实现了质心指令到弹道指令的有效变换,为高精度小超调跟踪奠定了基础。这种方法实现了姿态参考信号与导引指令的统一,姿态控制与质心控制的统一,充分降低了对气动等数据的精度要求,参数选择简单。数值仿真结果说明了这种方法的有效性;提出了进一步的研究方向。
Cruise missile achieves good flight performance by means of stabilization and regulation of its attitudes. Based on analysis of the perturbation model of missile＇s dynamic characteristics, series control structures are constructed for attitude control loop, and their discrete models are served as controlled plant for recursive least square （RLS） based adaptive predictive control, thus the mass center control with slow response transforms into trajectory angle control with fast response and high precision. On the basis of missile＇s characteristics, generalized predictive control （GPC） is used in inner attitude loop, and an integral form of predictive control is adopted in outter trajectory loop. Effective transformation from mass center command to trajectory reference has achieved to realize high precision tracking. This method realizes the integration of attitude reference signal with guidance command, and that of attitude control with mass center control. It can reduce precision requirements on aerodynamic data and the control parameters can be easily selected. The numerical simulations demonstrate its effectiveness. Finally, ,some further academic directions are presented.
出处
《中国工程科学》
2005年第10期23-27,共5页
Strategic Study of CAE
基金
国家自然科学基金资助项目(60374037)
关键词
飞航导弹
自适应控制
模型预测控制
鲁棒性
cruise missile
adaptive control
model based predictive control
robustness
