A Simulation Method of Spray Blending in Cryogenic Propellant Tank

A low-temperature propellant and simulation method technology, applied in design optimization/simulation, instrumentation, calculation, etc., can solve the problems of lack of tank pressure, air pillow temperature, fluid form and spray form simulation methods, and achieve accurate pressure change trends , reasonable temperature distribution, and good results

Active Publication Date: 2021-07-13
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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  • Application Information

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Problems solved by technology

Scholars at home and abroad have done some research on the prediction of evaporation of low-temperature propellants under passive control schemes under ground conditions. However, for the simulation of active control schemes, especially the simulation of spray blending, there is still a lack of effective prediction of tank pressure and gas pressure. Simulation method of pillow temperature, fluid form and spray form

Method used

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  • A Simulation Method of Spray Blending in Cryogenic Propellant Tank
  • A Simulation Method of Spray Blending in Cryogenic Propellant Tank
  • A Simulation Method of Spray Blending in Cryogenic Propellant Tank

Examples

Experimental program
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Effect test

Embodiment

[0111] (1) Establish a grid for spray mixing in a large liquid hydrogen storage tank under microgravity;

[0112] (2) Program the evaporation / condensation model, the heat and mass transfer model between the droplet and the continuous phase, and the conversion model between the droplet and the continuous phase into the FLUENT software, define the physical properties of liquid hydrogen and oxygen, and open the energy and composition Divide the model, add the discrete phase, and set the physical property of the discrete phase to liquid hydrogen, open the VOF model, check the implicit body force, and complete the setting of the discrete phase and VOF method;

[0113] (3) Define the nozzle type, position, speed as 0.1m / s, injection temperature as 20K, flow rate as 3.9×10 -5 kg / s. Initialize the process, start the simulation calculation, and obtain the fluid behavior characteristics (including tank pressure, temperature distribution and other parameters) in the tank under this grou...

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Abstract

The invention relates to a simulation calculation method for spray blending in a low-temperature propellant storage tank, which belongs to the field of overall design of aerospace transportation. A simulation method for pressure control of long-term on-orbit tanks. The present invention adopts discrete phase combined with VOF method for the calculation of spray and two-phase flow, and establishes a computational fluid dynamics simulation model for spray mixing in the low-temperature propellant storage tank. The results obtained by this method are in good agreement with the test results, compared with The simple lumped parameter model can realize the prediction of the fluid form, temperature change and heat transfer trend in the storage tank; through the method of the present invention, the simulation design and optimization of the mixing under different flow rates, flow rates and injection temperatures can be carried out. The ability of the spray blending scheme to control the pressure of the long-term on-orbit low-temperature propellant tank has contributed to the realization of the long-term on-orbit evaporation control technology.

Description

technical field [0001] The invention relates to a simulation method for spray mixing in a low-temperature propellant storage tank, and belongs to the technical field of overall design of aerospace vehicles. Background technique [0002] Cryogenic propellants refer to liquid propellants with a boiling point lower than 112K at atmospheric pressure, such as liquid hydrogen, liquid oxygen, methane, etc. Cryogenic propellants have the advantages of high specific impulse performance, non-toxic and non-polluting, but low-temperature propellants have a low boiling point, are easily vaporized by heat, and are difficult to store. Urgent needs. The third sub-stage of my country's future heavy rockets uses liquid hydrogen and liquid oxygen propellants. The long-term on-orbit time requirement for low-temperature propellants is 5 days, in which the evaporation of liquid oxygen is required to be less than 0.17% per day, and the evaporation of liquid hydrogen is required to be less than 2....

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20G06F119/14G06F119/08
CPCG06F30/20G06F2119/06G06F2119/08
Inventor 王夕罗庶陈士强容易王珏王楠黄辉尕永婧朱平平魏一邵业涛汤波
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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