末修弹脉冲控制参数约束条件研究  

Research on Constraint Condition of Impulse Control Parameters for Terminal Correction Projectiles

作　　者：曹小兵[1] 徐伊岑[1] 常思江[2] 姚晓宁[1] 

机构地区：[1]无锡职业技术学院控制技术学院,江苏无锡214121 [2]南京理工大学能源与动力工程学院,南京210094

出　　处：《弹箭与制导学报》2015年第6期101-105,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：中国博士后科学基金(2013M541676)资助

摘　　要：针对低旋尾翼式脉冲末修弹脉冲冲量及其距质心距离参数的设计问题,建立了脉冲控制力及力矩作用下的六自由度弹道模型,推导了脉冲引起的速度偏角及弹轴摆动角速度的变化量,对脉冲扰动后的复攻角方程进行了解析求解,分析了脉冲对攻角运动的影响,并提出了脉冲冲量及其距质心作用距离约束条件。仿真结果表明:脉冲冲量及其距质心距离取值不当会造成飞行失稳,而根据建立的约束条件来取值,能有效控制最大攻角,保证飞行的稳定。As for design of impulse magnitude and the distance from the mass center to individual thruster for low-spinning fin-stabilized ter- minal correction projectiles, 6-DOF model for the trajectory was established. The impulse induced changes of velocity deflection angle and oscillating angular velocity of body axis were derived. An analytic solution to the equation of complex angle of attack （AoA） after thruster operation was obtained. The effect of an impulse on the angular motion of AoA was analyzed. Then, a constraint condition of the impulse magnitude and the distance from the mass center to individual thruster was proposed. Simulation results show that the flight of projectiles may become unstable if the two parameters are chosen incorrectly. Using the constraint condition to determine the two parameters, the max- imum value of AoA can be controlled under an allowed value, and the flight stability of projectiles can also be assured.

关 键 词：尾翼弹 弹道修正 脉冲发动机 飞行稳定性 

分 类 号：TJ765.1[兵器科学与技术—武器系统与运用工程]