空间自燃推进剂发动机起动点火问题与研究进展  

A review of starting and ignition issues in space hypergolic propellant engines

作　　者：谭永华[1,2] 刘晓伟 汪广旭[2,3] 杨宝娥 谭松林 周军[2,3] TAN Yonghua;LIU Xiaowei;WANG Guangxu;YANG Baoe;TAN Songlin;ZHOU Jun(Academy of Aerospace Propulsion Technology,Xi'an 710100,China;National Key Laboratory of Aerospace Liquid Propulsion,Xi'an 710100,China;Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)

机构地区：[1]航天推进技术研究院,陕西西安710100 [2]航天液体动力全国重点实验室,陕西西安710100 [3]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2025年第1期1-16,共16页Journal of Rocket Propulsion

摘　　要：空间自燃推进剂发动机起动点火过程涉及复杂的非定常湍流两相流动和燃烧,过程中容易出现起动超压现象,不仅会造成发动机烧蚀爆炸等严重后果,还可能诱发高频燃烧不稳定问题。国内外已围绕此类发动机起动点火过程涉及的推进剂空间闪蒸、液相反应、化学点火延迟等现象开展了大量的基础研究,并在实际发动机起动超压控制方面积累了丰富的工程应用经验。对上述工作进行整理,重点梳理了诱发起动超压的关键机理及影响因素,系统总结了国内外相关经验,归纳了现有研究存在的不足,提出了后续研究方向,为我国空间自燃推进剂发动机的研制提供参考。The starting and ignition process of a space hypergolic propellant engines involves complex unsteady turbulent two-phase flow and combustion,which can lead to the occurrence of starting overpressure.This phenomenon not only causes serious consequences such as engine ablation explosion,but also induces high frequency combustion instability.Therefore,numerous fundamental research has been conducted on propellant space flash,liquid phase reaction,chemical ignition delay,and other phenomena related to the ignition process of this type of engine.Substantial engineering application experience has been accumulated for controlling starting overpressure in actual engines.This paper summarizes the aforementioned work,focuses on the key mechanisms and influencing factors of induced starting overpressure,systematically reviews relevant domestic and international experiences,identifies shortcomings in existing research,and proposes future research directions to provide reference for the development of space hypergolic propellant engines in China.

关 键 词：空间发动机 自燃推进剂 起动超压 空间闪蒸 液相反应 点火延迟 

分 类 号：V434.24[航空宇航科学与技术—航空宇航推进理论与工程]