鸭式布局双旋弹飞行动力学建模与仿真

Modeling and Simulation of Flight Dynamics for Dual-spin Stabilized Projectile Equipped With Canards

为发展具有精确打击能力的有控旋转稳定弹,研究了一类采用双旋结构的鸭式布局旋转稳定弹。分析了该类有控弹的飞行原理,补充了其飞行动力学建模所需的坐标系;根据牛顿第二定律和动量矩定理,建立了七自由度刚体质心运动方程和绕质心运动方程;讨论了作用在弹体上的诸力和力矩。编制计算程序对鸭式布局双旋弹的弹道特性进行了仿真分析,揭示了无控条件下双旋弹前、后体的转速和全弹攻角、偏流的变化规律,得到了控制力和控制力矩作用下双旋弹体的攻角响应。仿真结果与其飞行原理吻合,符合外弹道规律,验证了所建模型的合理性,为后续研究该类有控旋转弹提供了理论基础。

To develop the guided spin-stabilized projectiles with high hit-precision,a class of dual- spin stabilized projectiles equipped with canards was studied. The flight principle of canard-control dual-spin projectile was briefly analyzed. The reference frames for flight dynamics modeling were complemented. According to Newton＇s second law and the moment of momentum theorem, the seven-degree-of-freedom rigid-body flight-dynamic-model was established as well as the forces and moments acting on the projectile. The flight properties of dual-spin projectiles equipped with canards was analyzed and simulated through computer programming. The variation law of spin rates for two bodies, attack angle, and ballistic drift without action of control was revealed. The response of attack angle with the action of canard force and moment was also obtained. The simulation results are in accordance with the flight principle and exterior ballistic theory, which verifies the reasonableness of the established flight-dynamic-model. The results provide theoretical basis for further research on this type of guided projectiles.