远程火箭弹实现本体减速方案的研究

Research on the Body Deceleration Scheme of Long-range Rocket

为满足远程火箭子母类弹药后续流程对降低飞行速度的要求,对采用本体实现减速的方案进行了研究。首先选取一种实现本体减速方案的典型结构,计算主要气动参数,并分析了气动特性。然后采用四元数方法建立了弹道模型,通过弹道数值仿真,分析了弹道特性。最后对本体减速方案的机理进行了研究,提出了优化设计的方法:对于典型结构的本体减速方案,将质心位置设计在速度200 m/s,攻角90°或270°处的压心位置,减速效果最好。

In order to meet the requirements for reducing flight speed in the subsequent process of some long-rang rocker subcarrier ammunition,a study is conducted on the scheme of using body to achieve deceleration.A typical structure for implementing body deceleration scheme is selected in the articl,and the main aerodynamic parameters were calculated,and the aerodynamic characteristics were analyzed.Ballistic model is established using quaternion method,and through ballistic numerical simulation,ballistic characteristics is analyzed.Finally,the mechanism fo the body deceleration scheme is studied,and a method for optimizing design was proposed.For typical main body deceleration schemes,the deceleration effect is best achieved by designing the center of mass position at the pressure center position at a speed of 200 m/s and an angle of attack of 90°or 270°.