提高卷弧翼火箭弹圆锥运动渐近稳定性的几个方法  

Several methods for improving asymptotic stability of coning motion of wrap-around-fin rockets

作　　者：赵良玉[1] 杨树兴[2] 焦清介[1] 

机构地区：[1]北京理工大学机电学院,北京100081 [2]北京理工大学宇航学院,北京100081

出　　处：《固体火箭技术》2010年第4期369-372,共4页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(10972034);中国博士后基金(20090460216);国防基础科研基金(B222006060)

摘　　要：定量分析了火箭弹外弹道参数、标志量和几何参数对平衡转速及临界转速的影响趋势,指出在降低火箭弹飞行速度、将火箭弹质心位置前移、保持尾翼等效面积不变的情况下,减小尾翼展长、增大其弦长及减小尾翼安装角等均有利于提高其圆锥运动的渐近稳定性。探讨了圆锥运动稳定性判别与弹道仿真一体化的分析方法,指出只需判断速度最大点的圆锥运动稳定性态即可评估整个飞行过程中的圆锥运动稳定性态;最后,说明了该分析方法的不足,并讨论了进一步研究的方向。The effects of the exterior ballistic,the mass characteristics and the geometry parameters on the equilibrium spinning rate and the critical spinning rate were analyzed quantitatively.Four feasible methods for improving the asymptotic stability of the conning motion,namely reducing the flight speed,bringing forward the mass center to the nose,reducing the span and increasing the chord at the same time in keeping the reference area of the tail fin constant and reducing the mounting angle of the tail fin,were concluded.The way for integrating the stability of the coning motion into the ballistic simulation was also discussed,and the stability of the coning motion during the whole ballistic can be evaluated by judging the stability at the max point of the velocity only.Finally,the limitations of this paper and future research directions were described.

关 键 词：卷弧翼火箭弹 圆锥运动 渐近稳定性 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]