固体火箭发动机技术发展综述  

Review on technology development of solid rocket motor

作　　者：马帅 郭健鑫 周磊[1] 朱子环[1] MA Shuai;GUO Jianxin;ZHOU Lei;ZHU Zihuan(Beijing Institute of Aerospace Testing Technology,Beijing 100074,China)

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《火箭推进》2023年第2期1-14,共14页Journal of Rocket Propulsion

基　　金：国家自然科学基金资助项目(51605026)。

摘　　要：火箭发动机的研制始终是推进航天技术和探索未知空间的重要支柱,固体火箭发动机以成本低、可靠性高等特点,常被选作推进系统,针对航天工程中火箭运载、在轨维修和精确制导等技术的需求,重点梳理了多年来美国、俄国、日本、欧洲和中国固体火箭发动机的研究进展与成果。以火箭运载和精确制导为临界点,将固体火箭发动机进行大小型区分,基于整体式和分段式的特点,列表对比了大型固体火箭发动机的长度、直径、推力等重要技术参数。沿着时间的发展主线,概述了小型单/双脉冲固体火箭发动机的工作原理、结构参数、飞行测试结果等。通过对比国内外的研究成果,揭示了国内固体火箭发动机发展的技术差距,提出了固体火箭发动机发展的关键技术。The development of rocket motor has always been an important pillar to promote aerospace technology and explore unknown space.Solid rocket motor is often selected as the propulsion system because of its low cost and high reliability.In view of the requirements of rocket launch,on-orbit maintenance and precision guidance in aerospace engineering,the research progress and achievements of solid rocket motor including the United States,Russia,Japan,Europe and China over the years have been emphatically summarized.Taking the rocket launch and precise guidance as the critical point,solid rocket motor is divided into large and small.Based on the characteristics of integral and segmented,the important technical parameters such as length,diameter and thrust of large solid rocket motor are listed and compared.Along the main line of time development,the working principle,structural parameters and flight test results of small single/dual pulse solid rocket motor are summarized.Through the comparison of this research,the technical gap in the development of domestic solid rocket motor is revealed,and the key technologies are put forward.

关 键 词：固体火箭发动机 助推器 导弹 单脉冲 双脉冲 推进剂 姿态控制 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]