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作 者:梁佳佳 马原[1] 周振君 厉彦忠[1] 王磊[1] LIANG Jiajia;MA Yuan;ZHOU Zhenjun;LI Yanzhong;WANG Lei(Xi’an Jiaotong University,Xi’an 710049,China;China Academy of Launch Vehicle Technology,Beijing 100076,China)
机构地区:[1]西安交通大学,西安710049 [2]中国运载火箭技术研究院,北京100076
出 处:《载人航天》2023年第6期720-727,共8页Manned Spaceflight
基 金:国家自然科学基金(51976151)。
摘 要:针对液氢贮箱在轨气液两相正推重定位过程,借助CFD手段研究了不同重力水平、充液率等条件下的微重力气液分布规律及其影响因素,分析了利用蒸发排气实现正推气液分离方案的可行性,提出了低温推进剂正推重定位时序管理的建议方案。研究表明:采用二维轴对称模型模拟重定位过程的方法可行,建立重定位所需的时间随重力水平增大和充液率增大而缩短,发动机再启动的特征时间是贮箱排气特征时间的2倍以上;在贮箱绝热良好的条件下(1~10 W/m~2),利用直接连续排气和TVS间歇排气作用力难以实现正推重定位;对于推进剂时序管理方案,待间歇泉向下运动,质心曲线稳定震荡前的极小值点增大推力为比较合理的推力时序。To study the liquid-vapor two-phase forward thrust reorientation process of liquid hydrogen storage tank on orbit,the CFD method was adopted to investigate the distribution law of gas-liquid in microgravity and its influencing factors under different gravity levels and liquid-filling ratio.The feasibility of the forward thrust gas-liquid separation scheme using evaporation and venting was analyzed,and a scheme for the time-series optimization of the forward thrust reorientation of cryogenic propellant was proposed.The results show that it is feasible to use two-dimensional axisymmetric model to simulate the reorientation process.The time required for reorientation decreases with the increase of the gravity level and the liquid-filling ratio,and the characteristic time of building reorientation is more than twice as long as the characteristic time of tank venting.When the tank is well insulated(1~10 W/m~2),it is difficult to achieve forward thrust reorientation by using direct continuous exhaust force or TVS intermittent exhaust force.For the time-series management scheme of propellant,the more reasonable thrust timing is the minimum point of the centroid curve before its stable oscillation when the geyser moves down.
分 类 号:V411[航空宇航科学与技术—航空宇航推进理论与工程]
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