固体火箭发动机总冲精度预示与分析

推进技术 ›› 1996, Vol. 17 ›› Issue (2): 27-31.

固体火箭发动机总冲精度预示与分析

蔡淑芬,张玉成,胡克娴,方蜀州

北京理工大学飞行器工程系;北京理工大学飞行器工程系;北京理工大学飞行器工程系;北京理工大学飞行器工程系

发布日期:2021-08-15

ACCURACY PREDICTION AND ANALYSIS OF TOTAL IMPULSE FOR SOLID ROCKET MOTOR

Dept. Flight Vehicle Engineering, Beijing Inst. of Technology, Beijing, 100081;Dept. Flight Vehicle Engineering, Beijing Inst. of Technology, Beijing, 100081;Dept. Flight Vehicle Engineering, Beijing Inst. of Technology, Beijing, 100081;Dept. Flight Vehicle Engineering, Beijing Inst. of Technology, Beijing, 100081

Published:2021-08-15

摘要/Abstract

摘要： 介绍一种发动机总冲精度预示的工程方法。利用编制的计算机软件，调整影响总冲精度的各参量公差范围，可控制固体火箭发动机的总冲相对偏差达到技术指标要求。通过几个实例，表明该方法有较好的实用性。同时还分析了控制发动机总冲偏差的有效措施，为设计者合理地制定发动机主要性能参数和结构尺寸的公差与技术条件提供了依据。

关键词: 固体推进剂火箭发动机;比冲;精度分析;性能预测

Abstract: An engineering method of the accuracy prediction of the total impulse for Solid RocketMotor (SRM) is presented in this paper. Using the compufer software, the relative deviation of thetotal impulse can be controled by adjusting the tolerance zone of those parameters having influence onthe total impulse accuracy. And it can reach the technical specification. Some examples show that themethod is available. This paper also analyses suitable actions to obtain good accuracy of the totalimpulse. The tolerances and technical conditions of major performance parameters and structuraldimensions for SRM can be made in reason based on the total impulse accuracy prediction.

Key words: Solid propellant rocket engine;Specific impulse;Accuracy analysis;Performance prediction

蔡淑芬,张玉成,胡克娴,方蜀州. 固体火箭发动机总冲精度预示与分析[J]. 推进技术, 1996, 17(2): 27-31.