雷箭分离时运载器-分离舱组合体运动特性非定常数值仿真  

Unsteady Numerical Simulation on Motion Characteristics of Combination of Rocket and Separating-Capsules during Torpedo-Rocket Separation

作　　者：白治宁 王明洲[1] 王旅[2] 周景军[1] 王立文[1] BAI Zhi-ning;WANG Ming-zhou;WANG Lu;ZHOU Jing-jun;WANG Li-wen(The 705 Research Institute, China Shipbuilding Industry Corporation, Xi＇an 710077, China;91278%th Unit, The People＇ s Liberation Army of China, Dalian 116041, China)

机构地区：[1]中国船舶重工集团公司第705研究所 [2]中国人民解放军91278部队

出　　处：《水下无人系统学报》2018年第2期122-128,共7页Journal of Unmanned Undersea Systems

基　　金：海军装备部预先研究项目(3020601030101)

摘　　要：为了研究助飞鱼雷雷箭分离时运载器-分离舱组合体运动特性,建立雷箭分离多体动力学模型并嵌入流场求解器,采用重叠网格方法对雷箭分离过程进行非定常数值仿真,并通过火箭橇试验验证了该仿真方法的合理性。采用该仿真方法对不同分离条件下运载器-分离舱组合体的运动特性进行分析。分析结果表明,雷箭分离时运载器姿态变化对上、下分离舱张开的同步性影响较大,同时运载器气动特性对其姿态变化有重要影响:在气动力作用下,分离攻角为1.5°和0°时,运载器"抬头"而引起上、下分离舱张开过程严重不同步;分离攻角为-1.5°时,运载器俯仰姿态变化不大,上、下分离舱张开同步性较好。因此,设计雷箭分离方案时应综合考虑运载器气动特性和分离条件,以提高雷箭分离安全性。To study the motion characteristics of the combination of rocket and separating-capsules, a multi-body dynamics model during torpedo-rocket separation is established based on Lagrange method and is embedded into the flow field solver. Unsteady numerical simulation on the torpedo-rocket separation is performed using the overset mesh method. The validity of the numerical method is proved through comparison with the experimental results of rocket sled. The motion characteristics of the combination of rocket and separating-capsules under different separating conditions are analyzed through simulation. It is shown that the attitude of the rocket has significant effect on the open synchronism of the upper and lower separating-capsules＇ during separation. And the aerodynamic characteristics of the rocket significantly influence its attitude change, i.e. when the separation attack angle is 1.5° or 0°, the rocket pitches up under the action of aerodynamic force, resulting in asynchronism of the separating-capsules. When the separation attack angle is –1.5°, the attitude of the rocket remains stable and the open synchronization of the separating-capsules keeps well. Thus the aerodynamics of the rocket as well as the interaction between the rocket and the separating capsules should be fully taken into account in design of torpedo-rocket separation scheme, and the separating condition should also be considered to improve the safety of separation.

关 键 词：火箭助飞鱼雷 多体动力学模型 非定常数值仿真 雷箭分离 运动特性 

分 类 号：TJ630.1[兵器科学与技术—武器系统与运用工程] TB301.2[一般工业技术—材料科学与工程]