固体火箭冲压发动机燃烧室热防护层烧蚀计算

推进技术 ›› 2002, Vol. 23 ›› Issue (5): 375-378.

固体火箭冲压发动机燃烧室热防护层烧蚀计算

孙冰,刘小勇,林小树,蔡国飙

北京航空航天大学宇航学院北京100083;航天科工集团公司;北京100074;航天科工集团公司;北京100074;北京航空航天大学宇航学院北京100083

发布日期:2021-08-15
基金资助:
国家“九五”重点预研项目(26 4 1/A960031 02)。

Computation of ablation of thermal protection layer in solid rocket ramjet combustor

School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;The 31st Research Inst. , Beijing 100074, China;The 31st Research Inst. , Beijing 100074, China;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究冲压发动机燃烧室的热防护性能,用类比法计算了整体式固体火箭冲压发动机燃烧室壁面的烧蚀,其中考虑了热解气流对烧蚀的影响,并将国外有关固体火箭发动机喷管烧蚀计算时所用经验参数(指前因子)通过换算转换到冲压发动机燃烧室烧蚀计算中。计算结果符合物理规律,并与试验结果符合较好。该项研究为冲压发动机燃烧室热防护层的设计提供了有效的分析手段。

关键词: 类比法;烧蚀性能;热防护;冲压进气燃烧室;碳酚醛材料

Abstract: In order to study thermal protection function of ramjet combustion chamber, the ablation of the wall at the complete solid rocket ramjet combustion chamber was calculated using analogism. The pyrogenic flow factor was considered in the ablation computation. The experience coefficient used in the reference about solid rocket motor nozzle ablation conversion to the combustion chamber ablation computation. Calculated the result fits physics law, and it is better to fit with the test result. This research offered an effective analytical method for thermal protection layer design in the ramjet combustion chamber.

Key words: Analogism;Ablation property;Thermal protection;Ram air combustor;Carbon phenolic material

孙冰,刘小勇,林小树,蔡国飙. 固体火箭冲压发动机燃烧室热防护层烧蚀计算[J]. 推进技术, 2002, 23(5): 375-378.