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.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2008年第4期1329-1335,共7页
Journal of Astronautics
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
Missile control
Impulsive attitude control motor
Spinning missile
Jet interaction
Ignition logic
