子母弹侧向气囊分离数值模拟与试验研究  

Numerical simulation and experimental study on lateral gasbag separation of submunition missile

作　　者：李宝星 孟豪龙 邢鹏涛[1] 梅开 许云志[1] 舒慧明[1] 赵凤起[1] LI Baoxing;MENG Haolong;XING Pengtao;MEI Kai;XU Yunzhi;SHU Huiming;ZHAO Fengqi(Xi’an Modern Chemistry Research Institute,Xi’an 710065,China)

机构地区：[1]西安近代化学研究所,西安710065

出　　处：《航空动力学报》2023年第8期2024-2033,共10页Journal of Aerospace Power

摘　　要：为了研究子母弹侧向气囊分离特性,采用低燃温高燃速固体推进剂作为能量源,建立了燃气囊式分离数学模型,利用4阶龙格库塔法进行求解,获得了燃气发生器内弹道、气囊膨胀以及子弹模拟载荷分离运动等分离参数变化规律,并搭建了子母弹侧向气囊分离模拟试验系统进行分离试验验证。计算结果表明:在分离过程中,气囊内压力呈现先增加后缓慢降低,再缓慢上升的变化趋势,子弹模拟载荷的加速度则呈现出先增加后减小,最大加速度峰值为15.1g,分离速度逐渐增加后趋于平缓,分离末速度为6.17 m/s;试验验证了子母侧向气囊分离的可行性,并获得子弹模拟载荷分离的加速、速度等参数的变化特性,计算结果与试验结果趋势基本一致,参数误差均在5.5%以内,表明该分离模型能够较好描述子母弹侧向气囊分离过程,可为子母弹短距离低过载分离技术提供一定基础支撑。In order to study the lateral gasbag separation characteristics of the submunition missile,the low burning temperature and high burning rate solid propellant was used as energy source,a mathematical model of gasbag separation was established and solved by fourth-order Runge-Kutta method.The variation laws of separation parameters such as gas generator interior ballistics,gasbag expansion and bullet simulated load separation motion were obtained.A simulation experimental system for lateral gasbag separation of submunition missile was set up for separation test verification simultaneously.The calculation results indicate that during the separation process,the pressure in the gasbag presents a variation trend that it increases first,and then decreases slowly,and then increases slowly.The acceleration of the bullet simulated load increases first and then decreases,with the maximum acceleration peak value of 15.1g.Its separation speed tends to be flat after gradual increase with the final separation speed at 6.17 m/s.Besides,the feasibility of the lateral gasbag separation of the submunition missile is verified by the experiment,and the variation characteristics of the separation parameters such as acceleration and velocity of the bullet simulated load are obtained.The calculation results are basically consistent with the experimental results,and the parameter errors are within 5.5%,showing that this separation model can better describe the lateral gasbag separation process of the submunition missile,and can provide some basic support for the short-range low-overload separation technology of the submunition missile.

关 键 词：子母弹 侧向气囊分离 数学模型 模拟试验系统 分离参数 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]