| 引用本文: | 万军,李道奎,刘林,等.运载器牵制释放结构动力响应数值模拟方法研究.[J].国防科技大学学报,2008,30(3):37-42.[点击复制] |
| WAN Jun,LI Daokui,LIU Lin,et al.A New Numerical Simulation Method for the Launch Vehicle's Structure Transient Response in the Phases of Hold-down and Release[J].Journal of National University of Defense Technology,2008,30(3):37-42[点击复制] |
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| 运载器牵制释放结构动力响应数值模拟方法研究 |
| 万军, 李道奎, 刘林, 唐国金 |
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(国防科技大学 航天与材料工程学院，湖南 长沙 410073)
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| 摘要: |
| 将运载器牵制释放垂直发射的过程依次分为静态、牵制、释放三个阶段。利用MSC.Patran/Nastran的场功能和分组分析功能，将前一个阶段的计算结果场向后一个阶段的初始条件场传递，提出了一种分析运载器牵制释放全过程结构动力响应的分阶段计算新方法。解决了牵制释放过程中由于出现运载器-发射台分离面给结构动力响应计算带来的困难。采用该方法计算了几个运载器牵制释放的算例，分析了牵制阶段牵制力的变化、释放阶段运载器结构动力响应的特点、不同释放时间对结构动力响应的影响。算例表明：该方法实施简便、精度较高，还可拓展用于不同时刻释放、释放不同步、施加缓释力等条件下运载器结构动力响应的分析，为牵制释放系统的研制提供参考。 |
| 关键词: 运载器 牵制释放 瞬态响应 |
| DOI： |
| 投稿日期：2007-10-29 |
| 基金项目: |
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| A New Numerical Simulation Method for the Launch Vehicle's Structure Transient Response in the Phases of Hold-down and Release |
| WAN Jun, LI Daokui, LIU Lin, TANG Guojin |
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(College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China)
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| Abstract: |
| The vertical take-off event of launch vehicle was divided into static phase, hold-down phase and release phase, and the computational result fields of the previous phase provided the initial condition fields of the next phase. A new analysis method to compute the launch vehicle's structure transient response during the hold-down and release phase was proposed in this paper, using the field transferring function and group analysis function of the MSC.Patran/Nastran software. This analysis method solved the difficulty brought about by the changed boundary condition (the separate face between the launch vehicle and the launch pad) during the structure transient response computation course. Several examples of launch vehicle's structure transient response during the hold-down and release phase were analyzed by the proposed method. The variety characteristics of hold-down force during hold-down phase and the vehicle's structure transient response during the release phase were obtained. The computational results indicated that the analysis method is both simple and convenient, and the computational result was quite accurate. The method can be used to make efficient analysis of the influence of the different release time, the disappearing characteristics of the hold-down force, the dispersion of the release time, the restrain force of soft release mechanism to the vehicle's structure transient response. It can provide reference for the design of the hold-down and release mechanism. |
| Keywords: launch vehicle hold-down and release transient response |
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