固体火箭发动机总体设计集成系统的研究与开发

Research and Development of Integrated System for Solid Rocket Motor Overall Design

关键词:  固体火箭发动机  总体设计  算法模块  数据字典  算法集成

Key words:  Solid rocket motor  Overall design  Algorithm module  Data dictionary  Algorithm integration

摘要:

固体火箭发动机性能与结构方案总体设计是发动机设计工作的第一步，对发动机研制的技术路线有深远影响。为了解决现有集成设计系统“软件功能难定制、算法模块少协作、数据结构扁平化”三大问题，本文使用算法模块动态组合思想设计开放的算法模块接口规范体系，在此基础上，以“功能解耦，模块独立，算法重用”为原则，根据固体火箭发动机设计理论，开发包括热力计算、总体参数优化、设计指标分配、装药设计在内的30个算法模块和2个对外接口。使用并行轮循计算方法实现算法模块的集成与协作，在算法模块并行解耦的基础上显著提高了计算速度。并基于算法层、应用层、用户界面层和表现层的四层系统架构开发出适于工程应用的集成设计软件系统SRM-PASCOD。使用该系统复现“长征一号”第三级FG-02固体火箭发动机的设计过程，梳理出含有四百余条数据的全系统数据字典。将设计结果与实际对比，性能偏差和尺寸偏差在10%以内，满足工程需要。通过对算法模块的灵活组合，又完成了某战术导弹双推力长尾喷管发动机的设计，体现了软件的实用性、可定制性和可扩展性。本文建立的设计方法、开发的算法库和集成规范可以灵活支撑固体火箭发动机性能与结构方案总体设计，所形成的层次化的发动机数据字典为工程应用提供了数据支持。

Abstract:

Performance and structure conceptual overall design of solid rocket motor is the first stage in the design work. It has a deep influence on the designing roadmap. However， the existing integrated systems face problems that function of software is hard to customize， algorithm modules lacks of collaboration and data structure remains non-hierarchical. To solve these problems， first of all， using the idea of the dynamic combination of algorithm modules， an open algorithm module interface specification system was designed. Secondly， following the principle of decoupled functions， independent modules and reusable algorithms， 30 algorithm modules and 2 external interfaces were developed， including thermodynamic calculation， system parameter optimization， design target allocation and grain design， etc. based on the solid rocket motor design theories. Thirdly， the integration and collaboration of the algorithm modules were realized using the parallel round-robin calculation method. The decoupling of algorithm modules significantly accelerated the computation. Finally， based on a four-layer system architecture consisting of the algorithm layer， application layer， user interface layer and presentation layer， the integration design software system SRM-PASCOD applicable to the engineering field was constructed. The system was used to replicate the design process of the third stage FG-02 solid rocket motor of Long March 1， where a data dictionary containing over 400 pieces of data was extracted. Comparing the results with the actual ones， the performance and size deviation are less than 10% and meet the engineering needs. The flexible combination of algorithm modules enables the software to be applied to design a tactical missile dual-thrust long-tail nozzle motor which verifies the practicality， customizability and extensibility of the software. The design method， algorithms library and integration specifications developed can flexibly support the performance and structure conceptual overall design of solid rocket motors. The hierarchical data dictionary of the motor formed during the design process provides data support for engineering applications.