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

白治宁; 王明洲; 王 旅; 周景军; 王立文

doi:10.11993/j.issn.2096-3920.2018.02.004

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

doi: 10.11993/j.issn.2096-3920.2018.02.004

1.
中国船舶重工集团公司第705研究所, 陕西西安, 710077
2.
中国人民解放军91278部队, 辽宁大连, 116041

基金项目: 海军装备部预先研究项目(3020601030101)

详细信息

作者简介:
白治宁(1988-), 男, 工程师, 在读博士, 研究方向为空气动力学和多体动力学.

中图分类号: TJ630.1; TB301.2
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- 被引次数: 0
出版历程
- 收稿日期: 2018-01-02
- 修回日期: 2018-01-19
- 刊出日期: 2018-05-08

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

1.
The 705 Research Institute, China Shipbuilding Industry Corporation, Xi’an 710077, China
2.
91278th Unit, The People’s Liberation Army of China, Dalian 116041, China

摘要

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。
- 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
Abstract: 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.
- rocket-assisted torpedo /
- multi-body dynamics model /
- unsteady numerical simulation /
- torpedo-rocket separation /
- motion characteristics

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