Analysis Of Cryogenic Propellant On-orbit Evaporation In Storage

Liquid hydrogen and oxygen is one of clean energy in the world,Compared with other flues,It has a great advantage in terms of specific impulse,that make it to get developing in the satellites and manned space explorations,However,The temperature is extremely low,very easy to evaporate,Storage difficult is the main cause of has plagued its development,In this paper,We refer to the research status at overseas and domestic,A general knowledge of the change of the basic properties of storage in the cryogenic liquid fuel,the analysis of the external environment,storage in the cryogenic liquid fuel spacecraft in orbit state run and according to the existing liquid hydrogen oxygen fuel storage protection technology at home and abroad,Combining the influence of spacecraft in orbit under the heat radiation,Simulation analysis of internal fuel tank external heat flux density distribution and its pressure field,temperature field and other physical fields,corresponding change rule and evaporation,etc.Firstly,This article calculation and analysis distribution of on-orbit tank external heat used the business software-SINDA/FLUINTt ? We analyzed the different heat insulation coating material conditions,layer number of variable density,different attitude spacecraft heat flux distribution,Compared the various working conditions is the external heat flow and the heat flux distribution,Indicates the minimum working condition of external heat flux distribution for 6,mean for posture,With the method of aluminized amide aluminized,interlining for 20 layer variable density materials.In order to control the evaporation,require smaller external heat flux,Show that the coefficient of thermal conductivity is small,the absorption rate is low,the emissivity of material is more advantageous to impede heat transfer,and lay the foundations for the later evaporation tank internal calculations.Secondly,This article simulated horizontal tank cryogenic propellant thermal stratification by used Fluent software.Simulating horizontal tank cryogenic propellant thermal stratification.With C+ + compiler and plugins in Fluent software to calculate.through the comparison of two kinds of models to choose the right model-The VOF model.And proved the validity of the model.Finally,Using the already verified scheme and UDF phase transformation model,simulation analysis was carried out on the storage tank in orbit,the fixed heat flux,heat flux and spin three states were analyzed,and the internal physical parameters such as pressure,temperature and velocity distribution is analyzed,and the evaporation capacity of three different working condition of the state of the comparative analysis.The research results show that the spacecraft orbit space by solar radiation from outside,In the day stance in aluminized layer under variable density material protection,20 can better to isolate external radiation protection,at the same time does not spin state is more advantageous to the evaporation of internal propellant have the effect of controlling.The research results show that the spacecraft orbit space by solar radiation from outside,in the day stance in aluminized layer under variable density material protection,20 can better to isolate external radiation protection,at the same time does not spin state is more advantageous to the evaporation of internal propellant have the effect of controlling.