新型非壅塞式固体火箭冲压发动机试验研究

推进技术 ›› 1999, Vol. 20 ›› Issue (1): 16-18.

新型非壅塞式固体火箭冲压发动机试验研究

张炜,夏智勋,姜春林,方丁酉,张为华,朱慧,万章吉,曹金亮

国防科技大学航天技术系;国防科技大学航天技术系;国防科技大学航天技术系;国防科技大学航天技术系;国防科技大学航天技术系;国防科技大学航天技术系;国防科技大学航天技术系;国防科技大学航天技术系

发布日期:2021-08-15

EXPERIMENTAL STUDY ON A NEW UNCHODED SOLID ROCKET RAMJET SYSTEM

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

Published:2021-08-15

摘要/Abstract

摘要： 建立了一种新型非壅塞燃气发生器固体火箭冲压发动机系统。一系列直连式实验证实，验证的镁铝中能贫氧推进剂在低压（≥０．５ＭＰａ）范围内可以稳定燃烧，燃气发生器的工作压强可以随冲压补燃室压强的改变而变化，因此贫氧推进剂燃速随之进行自适应调节，最终达到富燃烧气流量自主调节的目的。

关键词: 冲压火箭发动机;整体式火箭冲压发动机;地面实验;自主控制

Abstract: A new type of unchoked solid rocket ramjet system was established.The test results show that a magnesium aluminum fuel rich propellant can burn steady at the pressure as low as 0 5MPa,and the pressure of gas generator can be adjusted according to the variation of ram combustor pressure.Therefore,the burning rate of fuel rich propellant can adjust adaptively with the variation of ram combustor pressure.

Key words: Ducted rocket engine;Integral rocket ramjet;Ground test;Autonomous control adjust adaptively

张炜,夏智勋,姜春林,方丁酉,张为华,朱慧,万章吉,曹金亮. 新型非壅塞式固体火箭冲压发动机试验研究[J]. 推进技术, 1999, 20(1): 16-18.