火箭橇试验无扰动分离优化设计

Undisturbed Separation Technique of Rocket Sled Test

为解决弹箭引战系统终点效应火箭橇试验攻角精确模拟与控制难题,采用火箭橇试验战斗部攻角动态数值计算方法,通过开展火箭橇弹橇分离装置结构及分离时空位置优化设计研究,实现了火箭橇试验弹橇间无扰动分离,并达到了攻角控制偏差≤±0.5°的指标要求。该研究结果可用于精确、高效战斗部火箭橇试验攻角设计与控制,为相关技术研究提供一定参考和技术支持。

In order to solve the problem of attack angle accurate simulation and control in the projectile and fuze-warhead system terminal effect rocket sled tests,this paper uses the dynamic numerical method of attack angle of warhead in rocket sled tests,and develops the research for the optimization of rocket sled separation device structure and the design of the separation spatiotemporal position.The study achieves undisturbed separation between warhead and rocket sled and the index requirement of the attack angle control deviation which is no greater than±0.5°.The research can be used in precise and efficient warhead rocket sled test to attack angle design and control,and it provides a certain reference and technical support for the related technology research.