固体火箭冲压发动机设计计算一体化  

A design System for Solid Propellant Ramjet Rocket Motor under ACIS and Calculation

作　　者：付秀文[1] 鲍福廷[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《计算机仿真》2008年第9期62-65,85,共5页Computer Simulation

摘　　要：为了简化固体火箭冲压发动机的设计过程,减少工作量,基于AC IS几何造型平台开发了固体火箭冲压发动机的三维CAD软件,该软件能预估固冲发动机主要部件的结构尺寸和发动机性能并实现了图形的实时显示,使该系统可进行固体火箭冲压发动机总体方案论证。为了验证该软件设计结果的准确性,对某设计点的进气道和补燃室的流场进行了数值仿真。结果表明:数值仿真结果在一定程度上与设计值吻合较好,验证了设计方法的有效性。与国内相同类型软件相比较,该软件的性能计算准确性高,CAD图形处理能力强,实现了固体火箭冲压发动机的参数化设计、计算一体化。The paper presents a three-dimensional CAD system developed for solid propellant ramjet rocket motor design under ACIS for simplifying the design process and reducing the workload.The system can evaluate some system parameters and the theory structure of the solid propellant ramjet motor,graphics can be displayed at the same time.Numerical simulation results were obtained for the inlet and the secondary combustor at their design points to validate the precision.Important aspects of the study include： the numerical results agree to a certain extent with the design results,and it indicates that this design method is effective.Comparing with the similar internal software,this system has better precision,stronger ability to deal with graphics.The integration of parametric design and performance investigation is achieved.

关 键 词：固体火箭冲压发动机 计算机辅助设计 数值仿真 一体化 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]