固体火箭发动机方案集成设计方法研究

推进技术 ›› 1995, Vol. 16 ›› Issue (1): 13-19.

固体火箭发动机方案集成设计方法研究

刘金,常伯浚,沈铮铮,周济

北京精密机械总体设计部;华中理工大学;北京精密机械总体设计部;华中理工大学;北京精密机械总体设计部;华中理工大学;北京精密机械总体设计部;华中理工大学

发布日期:2021-08-15

AN INTEGRATED DESIGN OF THE CONCEPT OF SOLID ROCKET MOTOR

Huazhong Univ. of Science and Technology, Wuhan, 430074;Huazhong Univ. of Science and Technology, Wuhan, 430074;Huazhong Univ. of Science and Technology, Wuhan, 430074;Huazhong Univ. of Science and Technology, Wuhan, 430074

Published:2021-08-15

摘要/Abstract

摘要： 讨论了用基于知识的设计系统实现固体火箭发动机方案集成设计，论述了基于知识的设计系统的特点、结构。结合固体火箭发动机的方案设计特点，提出面向对象的知识表达方法和知识表达语言及其基于知识的设计系统的推理机制。

关键词: 固体推进剂火箭发动机;方案设计;知识表示;知识库;专家系统

Abstract: n integrated concept design of solid rocket motor usingthe knowledge-based design system is discussed. The characteristics andarchitecture of the knowledge-based design system are presented. Theobject-oriented knowledge expression, the language and the reasoningmechanism of the knowledge-based design system, applied to the concept design of solid rocket motor, are given.

Key words: Solid propellant rocket engine;Tentative design;Knowledge representation;Knowledge base;Expert system

刘金,常伯浚,沈铮铮,周济. 固体火箭发动机方案集成设计方法研究[J]. 推进技术, 1995, 16(1): 13-19.