某型膨胀循环发动机高空模拟试验方案研究  

Research on altitude simulation test scheme for expand cycle engine

作　　者：黄仕启[1] 李锦江[1] 孙慧娟[1] 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2017年第5期39-44,共6页Journal of Rocket Propulsion

摘　　要：某型膨胀循环发动机在研制初期基于环境压力可能对膨胀循环发动机起动加速性有较大影响的考虑,采用了全程主动引射高空模拟试验方案,试验结果显示环境压力对发动机起动加速性的影响较小。发动机室压和喷管面积比是影响引射方式的主要参数,该型膨胀循环发动机与采用被动引射的某型燃气发生器循环发动机参数相当,这为该型膨胀循环发动机采用被动引射提供了可能,并对膨胀循环发动机采用被动引射高空模拟试验方案的可行性进行仿真研究。Based on the principal that the starting acceleration performance of an expand cycle engine was possibly affected by the ambient pressure in its developing beginning phase, a test scheme of the positive ejection altitude simulation was selected. The test results show that the ambient pressure affects the starting acceleration performance slightly, the chamber pressure and nozzle area ratio of the expand cycle engine are the main parameters affecting the ejection form, and the parameters of a cer- tain gas generator cycle engine with passive ejection are quite same as that of the expand cycle en- gine, which provide a possible selection for the expand cycle engine to adopt the passive ejection form. Therefore, the feasibility research on the passive ejection altitude simulation test scheme for the expand cycle engine is carried out in this paper.

关 键 词：膨胀循环发动机 高空模拟 主动引射 被动引射 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]