关于弹性运载火箭姿态稳定性控制研究  

Research on Stability of Attitude Control of Elastic Launch Vehicles

作　　者：吴天驹 刘丽霞[1] 王欣[1] 

机构地区：[1]北京控制与电子技术研究所,北京100038

出　　处：《计算机仿真》2016年第4期71-75,共5页Computer Simulation

摘　　要：研究大长细比运载火箭的姿控系统的优化问题,对保障火箭的稳定飞行具有重要意义。在设计中,经常遇到弹性模态和控制系统交联严重的问题,应用传统的固定参数滤波器难以保证刚性和弹性箭体同时具有足够的稳定裕度。针对上述问题,设计了SMM自适应滤波器,具有计算量小、收敛迅速等优点。经仿真验证,上述方法可以对弹性噪声进行自适应估计与滤波,在保证弹性系统裕度的同时,显著提高了低频刚体的幅相稳定裕度,保障了弹性箭体的稳定控制,为火箭姿态稳定性研究提供科学依据。The attitude control system has important significance for ensuring the stability of launch vehicles with big length to diameter ratio. In its design, we often find the fact that the cross linking of the control system and the elastic modes is serious. It is difficult for the traditional fixed filter to guarantee the rigid and elastic launch vehicle with enough stability margin at the same time. In this paper, a SMM adaptive filter was designed, which has the advantages of small calculation, rapid convergence and so on. The simulation results show that the method can adaptively estimate and filter the elastic mode noise. Firstly, this method ensures the elastic system margin. Secondly, it also significantly increases the low -frequency rigid amplitude and phase stability margin, and guarantees the stabili- ty of the attitude control system.

关 键 词：弹性箭体 自适应滤波 斯坦利兹麦克莱德算法 

分 类 号：V448.153[航空宇航科学与技术—飞行器设计]