摘要
对某型号低温液体火箭一二级级间分离过程中二级贮箱推进剂晃动情况进行研究。在流体仿真计算中采用VOF两相流模型对自由液面进行捕捉,得到了冷分离变过载条件下刚性贮箱模型中液面运动历程。计算结果显示在一级关机段内箭体轴向过载快速减小导致液面晃幅增大、晃动周期延长;失重段内液体倾向维持原有运动状态,晃动波浪到达壁面后不反向传播,液体在壁面附近积聚;新的晃动波浪在二级开机过载产生后不久重新形成。通过研究不同计算条件对于级间分离过程液体运动的影响,发现一级开始关机时刻的液体晃动相位对于分离过程液体运动特性影响较大。
The 2^(nd)-stage propellant sloshing in a cryogenic liquid rocket during stage separation was investigated.The dynamic behavior of liquid free surface under time-varying acceleration in a rigid tank model during cold separation process was obtained using the CFD-VOF method.The results revealed that the rapid decrease in axial acceleration during the 1^(st)-stage engine shutdown led to sloshing amplification in the 2^(nd)-stage tanks and increase in sloshing period.In the zero-gravity period,the liquid tended to keep the original velocity,and the sloshing wave did not reflect after reaching the tank wall but swelled near the wall.The returning sloshing wave did not occur until the firing of the 2^(nd)-stage engine.The influential factors for sloshing dynamics during stage separation were studied and it was found that the initial phase position had a strong effect on computing results.
作者
张凯强
秦春云
何奕为
ZHANG Kaiqiang;QIN Chunyun;HE Yiwei(Land Space Technology Corporation Ltd.,Beijing 100176,China)
出处
《载人航天》
CSCD
北大核心
2022年第4期480-486,共7页
Manned Spaceflight
关键词
低温推进剂
级间分离
晃动
两相流
cryogenic liquid propellants
stage separation
sloshing
VOF
作者简介
第一作者:张凯强,男,博士,工程师,研究方向为火箭晃动及热环境研究。E-mail:zhangkaiqiang@landspace.com。
