修正组件结构参数对旋转稳定弹道修正弹稳定性的影响研究

The influence of Correction Fuze's Structure Parameters on the Stability of Spin-stabilized Projectile

为提供修正组件优化与多种弹丸平台适配组件设计的参考与依据,结合弹-翼组合体气动特性理论简化模型与工程算法、复攻角理论及赫尔维兹稳定性原理,推导了与组件结构参数相关的弹道修正弹稳定性判据,并依此研究了修正组件结构参数(组件质量、质心位置、鸭翼翼展、舵偏角)对双旋式旋转稳定弹道修正弹飞行稳定性的影响规律。稳定性理论分析结果表明:相同组件外形(除鸭翼外)下,通过弹体配重或组件结构优化使组合体质心适当前移对弹丸飞行稳定性有利;为增大鸭翼修正力的同时减少对稳定性影响,增大舵偏角的方案相较于增大翼展更优。通过弹道仿真与飞行试验定性地验证了适当地前移质心可增强弹丸的飞行稳定性。

The stability criteria related to the structure parameters of correction fuze are derived based on the simplified model and engineering methods for the aerodynamic characteristics of wing-body combinations,Murphy’s complex variable method and the Hurwitz stability theory.The influence of structure parameters of correction fuze on the stability of spin-stabilized projectile is analyzed for the design and optimization of correction fuze.The stability analysis demonstrates that the forward movement of mass point of the combinations through the balance weight or the structure optimization of correction fuze is in favor of stability when the boundary dimensions of correction fuze(except for the canards)are the same;the increase in the deflection angles of canards is better than the extension of wingspan in order to increase the correction force while reducing the effect on stability.The simulations and experiments verify that the flight stability of projectile can be enhanced by moving the mass point of the combinations forward.