基于WEB的固体火箭发动机集成设计平台

Web-based integrated design platform for solid rocket motor

为满足固体火箭发动机设计过程对集成的需求,开发了一个基于WEB的发动机集成设计平台,提出了采用J2EE技术构建基于WEB的集成设计平台方案,建立了集成设计平台体系结构,分析了体系结构中每一层内涵,重点对集成平台功能框架层进行了详细分析,给出了基于J2EE的平台软件实现方案。平台实现了发动机设计过程中应用集成、信息集成和过程集成,能够支持优化设计和分布式设计人员的协同工作。通过在某翼柱型装药固体火箭发动机设计中的应用实例表明,该平台能够有效提高设计效率和质量,显著缩短设计周期。

A web-based integrated design platform for solid rocket motor was developed to meet the integration requirement of solid rocket motor design process. A scheme for web-based solid rocket motor integrated design platform using J2EE was proposed. The four layer architecture of the platform was built. The content of each layer was analyzed. The functional framework layer was discussed in detail and software realization based on J2EE was presented. The platform realizes the application, information and process integration of design process, and can support design optimization and collaborative design of distributed engineers. An example for the design of solid rocket motor with Finocyl grain based on the platform demonstrates that the platform can effectively improve design efficiency and quality as well as dramatically reduce design cycle time.