固体火箭发动机点火系统一体化设计及仿真  

Solid rocket motor igniter integration design and numerical simulation

作　　者：胡海峰[1] 鲍福廷[1] 丁林[1] 蔡强[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2009年第6期606-610,共5页Journal of Solid Rocket Technology

摘　　要：基于ACIS几何造型平台结合HOOPS图形显示,开展了固体火箭发动机点火器一体化设计及性能仿真的研究。实现了快速预估点火器的主要结构尺寸、预示点火器的性能及三维模型的实时显示和交互。提出了一种计算点火器质量流量和压强时间关系的模型,通过比较证明了模型的有效性。采用流场数值模拟软件对点火过程进行分析,得到的结果和理论计算结果吻合较好。Integrated igniter design based on the ACIS 3D geometric modeler and HOOPS display modeler is presented. The main dimension of the structure of the igniter was estimated, the performance of the igniter was indicated and time graphics was displayed. A new mathematics model was developed to calculate mass flux and the pressure time history relationship. In order to validate the new model, an example was given. The numerical simulation method was used to analyze the ignition transient. The result is in agreement with the outcome by using the method of this paper.

关 键 词：固体火箭发动机 点火器 计算机辅助设计 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]