大后翼装药固体发动机喷管收敛段绝热层烧蚀

推进技术 ›› 2009, Vol. 30 ›› Issue (1): 72-76.

大后翼装药固体发动机喷管收敛段绝热层烧蚀

刘中兵,汪亮,胡春波

西北工业大学航天工程学院;西北工业大学航天工程学院;西北工业大学航天工程学院

发布日期:2021-08-15

Ablation of nozzle convergent section insulation of solid rocket motors with long aft-finocyl grain

Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China;Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China;Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China

Published:2021-08-15

摘要/Abstract

摘要： 对具有大后翼装药结构的Φ315 mm发动机和全尺寸发动机进行了地面点火试验。试验后对喷管收敛段绝热层按照沟槽和非沟槽部位进行了解剖,得出了各个部位绝热层的烧蚀和炭化数据。结果表明,和药柱翼槽对应的喷管收敛段绝热层烧蚀严重,而非药柱翼槽对应部位的绝热层烧蚀较小。实测的最大烧蚀率可用于同类发动机的方案设计。

关键词: 固体推进剂火箭发动机;点火试验;烧蚀;装药;绝热层

Abstract: The ground firing tests of Φ315 mm motor and full-scale motor with long aft finocyl grain were performed.The nozzle convergent section insulation was dissected respectively according to groove section and non-groove section.The depth of ablation and charring layers was obtained.The results show that the ablation of the nozzle convergent section insulation corresponding grain fin-slots is high and the ablation corresponding grain non-fin-slots is low.The maximum ablation rate measured may be applied to design of the same kind of motors.

Key words: Solid propellant rocket engine;Ignition test;Ablation;Charge;Heat insulation layer

刘中兵,汪亮,胡春波. 大后翼装药固体发动机喷管收敛段绝热层烧蚀[J]. 推进技术, 2009, 30(1): 72-76.