变质心控制策略分析  

Moving-Mass-Center Control of Missile

作　　者：易 彦[1] 周凤歧[1] 周 军[1] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《西北工业大学学报》2002年第1期117-120,共4页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(69784002);高等学校优秀青年教师教学和科研奖励基金资助

摘　　要：导弹高速飞行时，气动舵控制方案存在着舵面烧蚀及控制效率降低等弊端。本文研究了一种新颖的适用于再入飞行器的控制方法──变质心控制，从根本上克服了气动舵控制方法的不足。建立了完整的变质心控制导弹六自由度非线性动力学方程，深入分析由于导弹质心移动引起弹体姿态角变化的两个重要因素，分别给出针对弹体自旋转角频率高、低不同情况时相应的控制策略，为进一步设计导弹控制系统奠定了坚实的基础。Abstract: The disadvantages of traditional pneumatic rudder control for missiles flying at high speeds include rudder surface ablation and decreased control efficiency. We propose using moving-mass-center control for reentry vehicles to overcome such disadvantages. Failing to find detailed information in the open literature, we establish complete nonlinear dynamic equations for missile controlled by moving mass center. We analyze two important factors that cause the changes of the airframe attitude due to the movement of the mass center. What these two factors are are apparent from the conclusions that we can draw from the simulation results shown in Fig. 2. These conclusions are: when the roll rate of the airframe is below the critical roll rate, the aerodynamic forces dominate; when the roll rate is above the critical roll rate, the inertia forces dominate.

关 键 词：变质心控制 非线性动力学方程 自动驾驶仪 自旋转角频率 控制策略 导弹 飞行器 飞行控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计] TJ765.2[兵器科学与技术—武器系统与运用工程]