翼身融合体导弹火箭橇试验平台气动外形设计  

Pneumatic shape design of a rocket sled test platform for wing-body fusion missiles

作　　者：张晨辉 贺祥锋 付良 解珍珍 ZHANG Chenhui;HE Xiangfeng;FU Liang;XIE Zhenzhen(China Ordnance Industry Testing Institute,Huayin 714200,China)

机构地区：[1]中国兵器工业试验测试研究院,陕西华阴714200

出　　处：《兵器装备工程学报》2022年第S02期100-104,共5页Journal of Ordnance Equipment Engineering

基　　金：国防科技创新特区项目(20-163-16-ZD-005-007-01)。

摘　　要：为了满足翼身融合体导弹地面考核试验需求,实现高动态环境下翼身和弹体平稳分离,开展超声速双轨火箭橇试验气动流场布局研究,提出3种双轨火箭橇试验平台设计方案,通过三维外流场数值仿真计算,对比分析高空状态下与3种橇型影响下翼身融合体飞行器气动压心分布情况并模拟翼身与弹体动态分离过程。研究表明,大动压条件下大斜面塔式火箭橇试验平台可为试验件提供纵向压心偏离不大于5%的力学环境,攻克了翼身融合体导弹地面分离试验中“易滚转”的技术难题。In order to meet the needs of the ground assessment test of a wing-body fusion missile and realize a smooth separation of the wing and the projectile main part in a high dynamic environment,this paper carries out researches on the aerodynamic flow field layout of the supersonic two-track rocket sled test,and puts forward three design schemes of the two-track rocket sled test platform,which are calculated through the numerical simulation of the three-dimensional outflow field.The pneumatic pressure center distribution of wing-body fusion aircrafts under the influence of three hazel types at high altitude is compared and analyzed,and the dynamic separation progress between the wing and the projectile is simulated.The research shows that the large inclined tower rocket sled test platform can provide the mechanical environment with a longitudinal pressure deviation of less than 5%under the condition of a high dynamic pressure,which solves the technical problem of“being easy to roll”in the ground separation test of the fusion missile.

关 键 词：翼身融合体 火箭橇试验 数值分析 气动压心 龙格库塔法 

分 类 号：TJ011.3[兵器科学与技术—兵器发射理论与技术]