固体火箭发动机喉径变化辨识

推进技术 ›› 1997, Vol. 18 ›› Issue (2): 27-30.

固体火箭发动机喉径变化辨识

方丁酉,张为华

国防科技大学航天技术系!长沙;410073;国防科技大学航天技术系!长沙;410073

发布日期:2021-08-15

IDENTIFICATION OF THROAT RADIUS VARIATION FOR SRM

Dept. of Aerospace Technology, National Univ. of Defense Technology, Changsha, 410073;Dept. of Aerospace Technology, National Univ. of Defense Technology, Changsha, 410073

Published:2021-08-15

摘要/Abstract

摘要： 根据发动机实验得到的燃烧室压强和发动机推力随时间变化数据，考虑了三氧化二铝沉积、消融和喉衬材料烧蚀，建立了喉径变化模型，并用辨识技术得到了喉径变化规律，为发动机性能计算提供了必要的数据，大大提高了性能计算的精度。

关键词: 固体推进剂火箭发动机;火箭发动机喷管;喉衬;喷管烧蚀计算

Abstract: A model of throat radius variation is presented by use of the experimental dataobtained from the SRM test, and the law of throat radius variation is identified by the least squaresmethods. The throat deposition and throat erosion are considered. The identification results are applitedto performance calculations of SRM and the perfermance computational accuracy is greatly improve.

Key words: Solid propellant rocket engine;Rocket engine nozzle;Throat insert;Nozzle erosion calcuation

方丁酉,张为华. 固体火箭发动机喉径变化辨识[J]. 推进技术, 1997, 18(2): 27-30.