摘要
针对膨胀循环氢氧发动机多次点火需求,采用氢、氧推进剂吸热着火和火炬燃气降温放热的假设,用热力计算方法从理论上分析了推力室采用火炬点火的能量问题。在考虑火炬燃气与推力室内的氧补燃后,富燃低压火炬点火器的点火能量能够满足推力室点火需求。研制了2种低压火炬点火试验系统,对膨胀循环发动机进行了17次点火试验,试验结果与理论分析结果相符,验证了补燃点火假设。
In order to meet the requirement of multiple ignition of the expander cycle LOX/LH_(2) engine,considering the heat absorption of the propellant and the heat release of the igniter torch,the energy problem of torch ignition in the thrust chamber is theoretically analyzed by means of thermodynamic calculation method.Considering the re-combustion of torch gas and oxygen in the thrust chamber,the energy given by the fuel-rich low-pressure torch igniter can meet the demand of the thrust chamber.Then two low-pressure torch ignition systems for the expander cycle engine are designed and 17 ignition tests are carried out.The test results are in good agreement with the theoretical analysis results,and the re-combustion hypothesis is verified.
作者
李锦江
陈明航
崔荣军
张楠
LI Jinjiang;CHEN Minghang;CUI Rongjun;ZHANG Nan(Beijing Aerospace Propulsion Institute,Beijing 100076,China;Cryogenic Liquid Propulsion Technology Laboratory of China Aerospace Science and Technology Corporation,Beijing 100076,China)
出处
《宇航总体技术》
2024年第2期32-38,共7页
Astronautical Systems Engineering Technology
基金
载人航天预先研究项目(050101)。
