固体火箭发动机喷喉结构设计准则的研究

AN INVESTIGATION ON DESIGN CRITERIA FOR THROAT INSERT STRUCTURE OF SOLID ROCKET MOTORS

关键词:  固体推进剂火箭发动机  喷管衬套  设计规范

Key words:  Solid propellant rocket engine  Nozzle liner  Design criterion

摘要:

提出了固体火箭发动机喷管喉衬结构综合设计准则──间隙临界值δｋ的概念，详细介绍了该设计准则δｋ的计算公式推导过程及其应用。并通过某固体火箭发动机四种不同技术状态喷喉结构的地面试车得到试验验证。

Abstract:

This paper presents a comprehensive design criteria, a concept of clearance critical value 3k, for the throat insert structure of the solid rocket motor nozzles. The paper descibes in details that the deriving procedure and applications of the computational formular of the design criteria, which has pasted tests and verification in ground firing tests of the throat insert structure in four different technical status for a solid rocket motor.