一种航天器火工冲击源建模和分析方法  

A Feasible Method for Modeling and Analyzing the Pyroshock Source of Spacecraft

作　　者：赵欣[1] 韩增尧[2] 邹元杰[1] 郑世贵[1] 丁继锋[1] 

机构地区：[1]中国空间技术研究院总体设计部,北京100094 [2]中国空间技术研究院研发部,北京100094

出　　处：《宇航学报》2015年第10期1210-1218,共9页Journal of Astronautics

基　　金：国防973项目(6131333)

摘　　要：为解决航天器火工冲击力学环境预示中无法确定载荷力函数的问题,提出一种基于流体编程软件(Hydrocodes)的"振源系统-近场结构"一体化建模和分析方法,分析由火工品触发的航天器星箭分离机构及其他解锁释放机构的冲击过程,从中提取力函数,实现对振源与主结构的解耦分析。以包带式星箭分离结构为例,对该方法的可行性进行研究和论证。通过对模型进行爆炸冲击直接加载和力函数的解耦加载这两轮计算结果的对比分析,初步校验了该方法的可行性。通过对模型的耦合性分析和对其简化模型的分析,进一步校验了局部建模的合理性和解耦分析的准确性。该方法是一种能够确定航天器火工冲击源函数的可行方法,为从工程上解决航天器火工冲击的响应预示问题奠定了基础。To solve the problem of acquiring the load force function description in the process of spacecraft pyroshock environment prediction,a ‘source system-near field structures ’integrated modeling and analyzing method based on Hydrocodes is proposed to analyze the shock processes of the spacecraft-launch vehicle separation mechanisms and other release mechanisms triggered by pyrotechnicsin spacecraft. By using this method,the force time history can be computed,so that the decoupled analysis of the shock can be realized. The analysis of a clamp-band separation structure is taken as an example to illustrate the feasibility of the method. Both the integrated（ coupled） model and the decoupled model are constructed and computed,and both comparison and analysis of the computational results preliminarily illustrate the feasibility of the method. Further studies including a series of coupled studies and a simplified model study are also implemented to prove the accuracy and the rationality of partially modeling of the method. In conclusion,this method is a feasible way to acquire the exact function of the pyroshock load force in spacecraft,and provides a basis for the prediction of the spacecraft pyroshock environment.

关 键 词：火工冲击 火工品 航天器 流体编码 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程] V416