火箭橇试验无扰动分离优化设计  

Undisturbed Separation Technique of Rocket Sled Test

作　　者：张晨辉 杨洋 杨珍 张喆昊 ZHANG Chenhui;YANG Yang;YANG Zhen;ZHANG Zhehao(Test and Measuring Academy of China Ordnance Industries,Shaanxi Huayin 714200,China;Xi’an Technological University,Xi’an 710072,China)

机构地区：[1]中国兵器工业试验测试研究院,陕西华阴714200 [2]西安工业大学,西安710072

出　　处：《弹箭与制导学报》2021年第2期47-50,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：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.

关 键 词：引战系统 终点效应 火箭橇试验 攻角 

分 类 号：TJ76[兵器科学与技术—武器系统与运用工程] V216[航空宇航科学与技术—航空宇航推进理论与工程]