火箭推进
火箭推進
화전추진
JOURNAL OF ROCKET PROPULSION
2012年
6期
20-23,51
,共5页
张银勇%吴剑%李向党
張銀勇%吳劍%李嚮黨
장은용%오검%리향당
减压阀%系统仿真%压力稳定性
減壓閥%繫統倣真%壓力穩定性
감압벌%계통방진%압력은정성
relief valve%system simulation%pressure stability
为研究某推进系统气路启动特性,找到造成影响减压阀建压稳定性的原因,获得稳定的减压阀出口压力建压过程,依据系统仿真方法及相关试验,对该推进系统气路启动特性进行了研究。结果表明,减压阀阀后压力稳定性与阀后的管径及阀内的N_M~L存在关系。
為研究某推進繫統氣路啟動特性,找到造成影響減壓閥建壓穩定性的原因,穫得穩定的減壓閥齣口壓力建壓過程,依據繫統倣真方法及相關試驗,對該推進繫統氣路啟動特性進行瞭研究。結果錶明,減壓閥閥後壓力穩定性與閥後的管徑及閥內的N_M~L存在關繫。
위연구모추진계통기로계동특성,조도조성영향감압벌건압은정성적원인,획득은정적감압벌출구압력건압과정,의거계통방진방법급상관시험,대해추진계통기로계동특성진행료연구。결과표명,감압벌벌후압력은정성여벌후적관경급벌내적N_M~L존재관계。
In order to find the reason which affects the pressure-establishment stability of the re- lief valve and obtain the stable pressure-establishment process at outlet of the relief valve, the starting characteristics of a pneumatic system used in some propulsion system were researched by means of system simulation method and relevant tests. The result shows that the pressure stability behind the re- lief valve depends on the diameter of the pipe behind this valve and damping area inside this valve.