极端载弹下直升机载火箭发射燃气冲击效应研究  

Research on Gas Impact Effect of Helicopter Airborne Rocket Launching Under Extreme Missile Loading

作　　者：纪元 卓长飞[1] 孙皓天[2] 蒋显松 蔡雨娇 Ji Yuan;Zhuo Changfei;Sun Haotian;Jiang Xiansong;Cai Yujiao(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China;China Helicopter Research and Development Institute,Jingdezhen 333001,China;Institute of Precision Equipment,Chongqing Chang’an Industry(Group)Co.,Ltd.,Chongqing 401120,China)

机构地区：[1]南京理工大学机械工程学院,南京210094 [2]中国直升机设计研究所,江西景德镇333001 [3]重庆长安工业(集团)有限公司精密装备研究所,重庆401120

出　　处：《兵工自动化》2023年第2期75-82,共8页Ordnance Industry Automation

摘　　要：针对机载火箭发射过程中对机体造成的动力冲击效应,对直升机机载火箭系统发射全过程的燃气射流冲击流场进行计算。通过3维非定常的数值模拟方法,结合动网格方法及分块混合网格模型,对比不同载弹状态下的火箭巢结构对冲击效应的影响。计算结果表明:机身表面受到的最大冲击超压在10 kPa量级,不同载弹状态下起始冲击波流场发展过程相似,超压分布均为单峰函数,但火箭离管时空载状态发射的冲击流场变化更为复杂,机身最大超压分布规律为双峰曲线。Aiming at the dynamic impact effect of airborne rocket during launching,the gas jet flow field of helicopter airborne rocket system in the whole launching process was calculated.Through the 3D unsteady numerical simulation method,combined with the dynamic grid method and the block hybrid grid model,the influence of the rocket nest structure on the impact effect under different missile loading conditions was compared.The results show that the maximum shock overpressure on the fuselage surface is about 10 kPa,the initial shock wave flow field development process is similar under different missile loading conditions,and the overpressure distribution is a single-peak function,but the shock flow field change is more complex when the rocket is launched from the tube under no-load condition,and the maximum overpressure distribution law of the fuselage is a double-peak curve.

关 键 词：机载火箭 燃气射流 冲击效应 超压 武装直升机 

分 类 号：TJ71[兵器科学与技术—武器系统与运用工程]