小推力长时间工作固体火箭发动机初步试验研究  

Preliminary experimental investigation on small-thrust long-time working solid rocket motors

作　　者：熊文波[1] 刘宇[1] 任军学[1] 于泉 司学龙 

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]湖北航天技术研究院总体设计所,武汉430035

出　　处：《固体火箭技术》2009年第4期413-417,共5页Journal of Solid Rocket Technology

基　　金："863"国家高技术研究发展计划(2007AA702311;2008AA7020508)

摘　　要：为了实现小推力固体火箭发动机的长时间工作,对4种采用复合推进剂端燃药柱的发动机进行设计和试车,工作时间分别达到75、105、145、235 s。试验结果表明,该发动机设计方案合理,采用这种C/C喉衬的复合结构喷管实现长时间工作是完全可行的。其中,75 s发动机的地面比冲为2 217 N.s/kg;145 s发动机的地面比冲为2 236 N.s/kg;235 s发动机的地面比冲为2 147 N.s/kg,性能测试结果基本满足发动机总体指标要求。此外,在试验过程中,还获得了C/C喉衬的烧蚀和绝热层的烧蚀炭化规律,为后续开展长时间工作固体火箭发动机研究提供了重要参考。In order to achieve long-time working of small-thrust solid rocket motor（ SRM）, four motors with end-burning composite propellant grains were designed and tested. The working time reaches 75,105,145 and 235 s respectively. The experimental results show that it is appropriate and feasible to adopt the conceptual design of motor and C/C throat for long-time working. It also shows that 75 s-motor specific impulse reaches 2 217 N · s/kg, 145 s-motor specific impulse reaches 2 236 N ·s/kg and 235 s-mo- tor specific impulse reaches 2 147 N · s/kg, which are close to system requirements. Besides, the ablation-charring rules of C/C throat and insulation of motors were gained during these experiments, which may provide important design references for further longtime working solid rocket motors.

关 键 词：固体火箭发动机 长时间工作 复合推进剂 端燃药柱 发动机试验 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]