助推滑翔飞行器复合控制系统线性化小偏差运动方程推导与控制系统设计  

Derivation of Linearization Small Deviation Equations and Design of Compound Control System for Aid-sliding Vehicles

作　　者：翟华[1] 谷志军[1] 刘娟 周伯昭[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073 [2]北京宇航系统工程研究所,北京100076

出　　处：《国防科技大学学报》2009年第3期37-42,共6页Journal of National University of Defense Technology

摘　　要：助推滑翔技术是制导武器实现增加射程、提高机动突防能力的关键技术之一,对飞行器姿态控制有较高的要求,需要设计复合控制方式的姿态控制系统。针对采用空气舵与燃气舵联动控制的飞行器,建立了动力学模型,详细推导了完整的三通道线性化小偏差运动方程,结合典型弹道数据给出了动力系数图像,分析了助推滑翔弹道各飞行段中飞行器的稳定性,在此基础上选取再入段低空飞行特征点进行了姿控系统设计,仿真结果验证了线性化小偏差运动方程的正确性和控制系统的有效性,为进行此类飞行器的稳定性分析与姿态控制系统设计提供了有益的参考。The aid-sliding technology is the one of key technologies for guided weapons to augment the range and enhance maneuver penetration ability. This technology has a high demand on vehicle＇ s attitude control and the compound control system. Aiming at vehicles controlled by the linkage mode with aerodynamic rudders and gas rudders, the integrated dynamic model is set up and the complete linearization small deviation equations on pitching, yawing and roll loops are elaborated in the derivation. Combined with typical trajectory data, figures of dynamic coefficients are presented, and according to these figures, the vehicle＇s stability in each phase of the boost gliding trajectory is analyzed. On the basis of the above work, the low altitude point 260s in reentry phase is picked as characteristic point and the attitude control system of this point is designed. Simulation results indicate the correctness of linearization small deviation equations and the validity of the control system. This research can provide helpful reference to stability analysis and designing attitude control system for this kind of vehicles.

关 键 词：助推滑翔 复合控制 线性化 小偏差 稳定性分析 控制系统设计 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]