气动谐振管点火技术研究

推进技术 ›› 2001, Vol. 22 ›› Issue (4): 286-289.

气动谐振管点火技术研究

梁国柱,马彬,张国舟,程显辰,张振鹏

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 (86 3 2 3 4 7)

Investigation on gas dynamic resonance tube ignition method

School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083

Published:2021-08-15

摘要/Abstract

摘要： 为了发展液体火箭发动机的气动谐振管非电点火新技术 ,提出了一种新颖的组合喷嘴混气谐振加热方案 ,并介绍了所研制的氦气谐振热表面点火器和同轴氢氧谐振火炬点火器 ,给出了气动谐振管点火器工程设计的一般原则和相关参数的选择

关键词: 液体推进剂火箭发动机;点火;点火系统;气动加热

Abstract: To develop the new technology of gas dynamic resonance tube non electric ignition for liquid rocket engines,a new conceptual scheme of combined nozzle mixing gas resonance heating was proposed. The gaseous helium resonance surface heating igniter and the co axial gaseous oxygen hydrogen resonance torch igniter were described. And the general engineering design criteria for the resonance tube igniter were proposed.

Key words: Liquid propellant rocket engine;Ignition;Ignition system;Aerodynamic heating

梁国柱,马彬,张国舟,程显辰,张振鹏. 气动谐振管点火技术研究[J]. 推进技术, 2001, 22(4): 286-289.