可重复使用运载火箭返回段低温流体行为特性

doi:10.7527/S1000-6893.2023.29563

Abstract

Abstract:

Under the complex interference of the return stage of the reusable launch vehicle， the cryogenic propellant in the tank and the high-temperature ullage are violently mixed， resulting in a series of problems， such as tank pressure drop and propellant temperature rise. In this paper， the propellant mixing and reorientation process of Vertical Take-off and Vertical Landing （VTVL） launch vehicle is studied. A simulation model of the behavior of liquid oxygen mixing is established for the first time and verified by the accelerated drop tower test. The model was used to study the behavior characteristics of cryogenic propellant under the complex interference in the return stage of a VTVL launch vehicle， and the variation laws of propellant morphology， tank pressure， propellant temperature and evaporation were obtained， which provided support for the design of propellant management system and supplementary pressure scheme.

Key words: reusable, return stage, liquid oxygen, heat and mass transfer, propellant behavior characteristics

CLC Number:

V475.1

Yi RONG, Hui LIU, Ziwen YU, Pingping ZHU, Yue PENG, Jiahui YU. Behavior of cryogenic propellant in return stage of reusable launch vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 629563-629563.

Figures/Tables 25

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Table 1

Comparison between simulation results and test results

重定位时间	$t 1$	$t 2$	$t 3$	$t 4$	$t 5$
测量值/s	0.46	0.58	0.71	1.04	2.68
仿真值/s	0.46	0.62	0.74	1.06	2.74
仿真误差/%	≈0	6.90	4.23	1.92	2.24

Table 1

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Table 2

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References 18

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参数	数值
参数	掺混前	掺混后
无量纲气枕平均温度	1	0.74
无量纲氧箱压力	1	0.569
降温引起的无量纲压降		0.257
冷凝引起的无量纲压降		0.174

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Behavior of cryogenic propellant in return stage of reusable launch vehicle

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