【作者】 郭大庆；

【导师】 鲍福廷；

【作者基本信息】 西北工业大学 ， 航空宇航推进理论与工程， 2005， 硕士

【摘要】 本文系统地研究了固体火箭发动机喷管热结构CAD系统的组成,应用面向对象技术和大型有限元分析软件ANSYS的二次开发技术,开发了固体火箭发动机喷管热结构设计、计算与分析系统,较为成功地解决了如下几个关键问题: 1.为固体火箭发动机喷管热结构设计提供了一个界面友好、交互性强、通用性好的设计工具与集成化的设计环境,用户可以在该设计环境中完成喷管结构形式的选择、流动的计算及温度场、热应力场的分析等喷管设计流程。与以往的手工设计和其它设计方法相比,大大提高了设计的效率,而且整个设计结果以单个文件的形式保存,易于管理和查看。 2.该系统集成了目前工程上常用的喷管热结构设计与计算方法,提供了多种喷管结构形式,具有很强的实用性。 3.利用图形技术对喷管结构进行了二维绘图显示,对喷管结构的构造采用参数化的方法,通过一系列几何参数值来确定结构的具体形式,参数改变后可以立即显示生成新的设计示意图形。 4.对ANSYS进行二次开发,利用ANSYS提供的参数化设计语言(APDL)及其批处理模式对ANSYS进行封装,编制该CAD软件与ANSYS的接口程序,用户可以在该CAD软件中从后台调用ANSYS核心计算程序进行喷管定边界温度场、烧蚀温度场和热应力分析。 整个系统采用C++Builder 5.0作为主要开发环境,运用面向对象的思想将喷管分成不同的结构组件,然后通过组合可以构成不同的喷管结构,这样使得本系统的通用性得到很好的体现,并进一步保证了系统的可扩展性,新结构类型的喷管只需要添加没有的组件形式就可以了。软件模块的独立性、动态链接性和可维护性都得到很好的体现。更多还原

【Abstract】 Abstract This thesis fully discusses the Solid Rocket Motor (SRM) Nozzle Thermal Structure CAD system. A SRM nozzle design, calculation and analysis system is developed by use of Object-Oriented Programming (OOP) technique and the powerful finite element analysis software ANSYS. Several key techniques have been solved successfully. The details are as follows:1. This software provides a user friendly, interactive, general tool and an integration environment for the design of SRM nozzle thermal structure, which has overcome the deficiency of handwork and other methods. By use of this software, the whole design process, such as selecting the design scheme, confirming the performance, designing each part, calculating and analyzing the performance can be fulfilled. The whole design results can be saved as a single file, which is easily managed.2. The engineering design methods of nozzle have been integrated. Many structure configurations of nozzle have been provided. And this software is very practical.3. 2-D graphics are plotted by use of graphics technique, which makes this software well visualized. The computation of mass properties adopts the discrete integration combined with the graphic construction of the SRM structure, assuring the internal data coherence. The parameter technique is adopted to plot nozzle structure, the graphics is decided by a series of geometric parameters, and new graphics can be repainted immediately.4. Encapsulate ANSYS to this software by use of the ANSYS batch mode and ANSYS Parametric Design Language (APDL). and develop the interface with this software. Users can transfer the kernel calculation program in the background to do thermal analysis of the designed nozzle, and the thermal stress distribution with fixed and erosive boundary can be calculated.The whole system adopts C++Builder5.0 as the main developing environment. The system divides nozzle into some basic components by use of OOP. and then comprises different type of nozzle by different combination, which demonstrates the flexibility of this system, also guarantees the extensibility of system. Here only new components are needed for a new type of nozzle structure. This module has good independence, dynamic linking and maintainability.更多还原