气动偏心角对非对称翼末敏弹扫描运动的影响规律研究

针对非对称尾翼末敏弹的结构特点,建立适合力学分析的坐标系,分析考虑气动偏心角和大攻角非线性时的力和力矩模型,推导出六自由度运动微分方程组。以某非对称末敏弹结构为例进行数值仿真计算,计算结果与实验数据相吻合,表明:与非对称翼展开方向一致的气动偏心角能够诱导弹体产生稳定螺旋扫描运动,且扫描角必定与气动偏心角共面,扫描转速随气动偏心角的增大而减小,扫描角随气动偏心角的增大而增大,且大致成线性关系,为非对称翼末敏弹的结构设计和气动设计提供了理论参考。

Research on the Effect of Pneumatic Eccentric Angle on Scanning Motion of Asymmetric-fin Terminal Sensitive Ammunition

A coordinate system for mechanics analysis is established based on the structural features of the asymmetric-fin terminal sensitive ammunition. The force and moment models are analyzed with consideration of pneumatic eccentric angle and large angle of attack asymmetries, and the 6D differential equation set of motion is deduced. The simulation calculation is performed according to the structure of a certain asymmetric terminal sensitive projectile. The calculated result shows that the pneumatic eccentric angle which is in the same plane as the wingspan direction can induce stable spiral scanning motion, and the scanning angle must be in the same plane as the pneumatic eccentric angle. The result also shows that the scanning rolling speed decreases but the scanning angle increases linearly as the pneumatic eccentric angle increases.