多推力室的气动谐振点火器研究

推进技术 ›› 2002, Vol. 23 ›› Issue (5): 402-405.

多推力室的气动谐振点火器研究

童晓艳,张国舟,马彬,梁国柱,宋雅娜

北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083;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“八六三”基金资助项目(863 2 3 4 10);航天科技创新基金2000年资助项目

Research on gas dynamic resonance igniters of multi thruster

School of Astronautics, Beijing Univ of Aeronautics and Astronautics, Beijing 100083,China;School of Astronautics, Beijing Univ of Aeronautics and Astronautics, Beijing 100083,China;School of Astronautics, Beijing Univ of Aeronautics and Astronautics, Beijing 100083,China;School of Astronautics, Beijing Univ of Aeronautics and Astronautics, Beijing 100083,China;School of Astronautics, Beijing Univ of Aeronautics and Astronautics, Beijing 100083,China

Published:2021-08-15

摘要/Abstract

摘要： 为了满足多推力室多次同步点火的需要,通过大量的空气气动谐振加热实验和理论分析,研制了两种利用气动谐振点火技术的多推力室点火器,即多管点火器和小点火器,给出了这两种点火器的系统结构、试验参数以及部分试验结果。这两种点火器都能在1秒内提供不同流量的火焰燃气,分别适用于较小推力室和较大推力室的点火。在实验室中进行的多次点火试验结果表明,这两种点火器都可以可靠地进行海平面上多推力室的多次同步点火。

关键词: 塞式喷管火箭发动机;点火;点火系统;谐振管;气动加热

Abstract: To realize multi thruster ignition, two methods based on gas dynamic resonance heating technology were presented. Based on numerous air resonance heating experiments and analytical work, two kinds of igniters (multi tube igniter and small igniter) were developed and tested successfully. The system structure, experimental parameters and results were presented. The former can be fixed to smaller thruster easily, and the latter can provide larger flame gas flux and ignite normal thruster. Both were able to perform repetitious multi thruster ignition simultaneously and reliably in one second at sea level.

Key words: Plug nozzle rocket engine;Ignition;Ignition system;Resonance tube;Aerodynamic heating

童晓艳,张国舟,马彬,梁国柱,宋雅娜. 多推力室的气动谐振点火器研究[J]. 推进技术, 2002, 23(5): 402-405.