在轨激励作用下低温推进剂动力学行为仿真研究  

Simulation Study on Dynamic Behavior of Low Temperature Propellant During On-orbit Excitation

作　　者：严天 王磊[1,2] 王娇娇 黄晓宁[1] 马原 厉彦忠[1,2] YAN Tian;WANG Lei;WANG Jiaojiao;HUANG Xiaoning;MAYuan;LI Yanzhong(Institute of Refrigeration&Cryogenic Engineering,Xi’an Jiaotong University,Xi’an 710049,China;State Key Laboratory of Technologies in Space Cryogenic Propellants,Beijing 100028,China)

机构地区：[1]西安交通大学制冷与低温工程系,西安710049 [2]航天低温推进剂技术国家重点实验室,北京100028

出　　处：《真空与低温》2021年第3期239-248,共10页Vacuum and Cryogenics

基　　金：国家自然科学基金(51406142);航天低温推进剂技术国家重点实验室基金(SKLTSCP1810)。

摘　　要：针对全尺寸低温在轨贮箱,建立了可描述两相流体运动的数值模型,分别就10-3g0过载下初始液位倾斜、侧向正弦波、慢旋等激励作用下流体的运动特性开展了瞬态仿真,并讨论了防晃挡板的作用效果。研究发现:(1)当经历变过载时,初始倾斜液面达到新的平衡,耗时不超过80 s;当倾角较大时,挡板可对液面恢复稳定起加速作用。(2)对侧向激励,当液位处于挡板附近及以下时,无论重力高低,挡板总能起防晃作用。此外,作用效果随液位升高呈线性下降,在同一激励下,2.6 m液位工况时挡板抑制液面晃动幅度约2.6 cm,而3.2 m液位工况时仅为0.3 cm。(3)侧向激励作用时,氢、氧的响应不同。氢的晃动振幅可达6.5 cm,占最大允许值的43.3%,而氧振幅为4.0 cm,仅占16.0%。而液位倾斜与慢旋激励时推进剂类型不同不造成流体行为的明显差异。(4)侧向激励与慢旋均可能使贮箱底部暴露于气枕,应在推进剂管理中加以考虑并进行限制,合理设计角速度。本文工作有助于理解低温推进剂贮箱在多种空间激励下的流动运动规律,为流体控制方案及火箭时序的设置提供理论指导。For a full-size low-temperature on-orbit tank,a numerical model describing the movement of microgravity two-phase fluid was established.The transient simulation was carried out to discuss the fluid movement characteristics under the excitation of initial liquid level tilt,lateral sine wave,and slow rotation under 10-3g0 overload,and the effect of the antislosh baffle was discussed.The study found that:(1)When experiencing variable overloads,the time for initial inclined liquid surface reaching a new equilibrium takes less than 80 s.When the inclination angle is large,the baffle can accelerate the recovery process of liquid surface;(2)For lateral excitation,when the liquid level is near and below the baffle,the baffle can always exert the anti-sloshing effect regardless of gravity.In addition,the effect has a linear drop relationship with the liquid level.Under the same excitation,the sloshing range of the 2.6 m liquid level can be suppressed by about 2.6 cm,while that of 3.2 m is only 0.3 cm.(3)The response of hydrogen and oxygen is different during lateral excitation.The sloshing amplitude of hydrogen can reach 6.5 cm,accounting for 43.3%of the maximum allowable value,while that of oxygen is 4.0 cm,accounting for only 16.0%.However,the different types of propellant when the liquid surface is inclined and the slow rotation excitation do not cause obvious differences in fluid behavior.(4)Both lateral excitation and slow rotation may expose the bottom of the tank to the ullage,which should be considered and limited in the propellant management,and the angular velocity should be reasonably designed.The work of this paper helped to understand the law of cryogenic propellant flow motion during variable excitations in space,and provides theoretical guidance for the fluid control scheme and aircraft timing.

关 键 词：低温推进剂 微重力 防晃板 数值模拟 推进剂管理 

分 类 号：V511.6[航空宇航科学与技术—航空宇航推进理论与工程]