具有脉冲姿控发动机的自旋导弹动态分析与控制设计  

Dynamic Analysis and Control Design for a Spinning Missile with Impulsive Attitude Control Motors

作　　者：王进[1] 陈万春[1] 殷兴良[2] 

机构地区：[1]北京航空航天大学宇航学院,北京100083 [2]中国航天科工集团公司,北京100830

出　　处：《宇航学报》2008年第4期1329-1335,共7页Journal of Astronautics

摘　　要：对脉冲姿控发动机阵列和自旋导弹进行建模,在导弹动力学模型中通过定义为矢量形式的力和力矩放大因子来描述喷流干扰效应,指出了这种定义的优点。在只考虑稳定气动力矩的情况下对低速自旋导弹进行了简单的动态分析,通过定义进动坐标系直观地表示了导弹的陀螺运动。动态分析的结论导致了导弹动力学方程的简化并应用到控制策略的设计中,最后设计了控制策略和点火逻辑。给出了采用不同喷流干扰效应数据情况下分别应用枚举算法和快速算法的点火逻辑的仿真结果,其验证了控制算法和快速点火逻辑的有效性,并显示出喷流干扰效应中的主向力矩因子的影响是主要的。Impulsive attitude control motor array mounted on missile and spinning missile models are built. Jet interaction is taken into account in dynamic model using force and moment amplification factors which are defined in the form of vector, The advantage of this definition is displayed. Missile which roils in a low rate is simply analyzed when only stabilization aerodynamic moment being considered. A new coordinate system is defined in which the gyro motion of missile can be conveniently depicted. Meaningful conclusion from dynamic analysis results in the simplification of missile dynamic equations which will be applied in the design of control strategy. Eventually, control strategy and ignition logic are designed. Simulation results are showed when several jet interaction data are set and ignition logic uses enumeration arithmetic and fast arithmetic respectively. The results show the effi- ciency of control strategy and ignition logic, and conclude that the influence of the main moment amplication factor is primary when jet interaction is considered.

关 键 词：导弹控制 脉冲姿控发动机 自旋导弹 喷流干扰效应 点火逻辑 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]