Preparation And Structure Analysis Of Carbon-based Form-stable Composite Energy Storage Material Used In Spacecraft Thermal Control

Phase change material can absorb a lot of heat and it's temperature can keep constant in the process of melting and solidification.Using phase change materials for spacecraft thermal control can ensure the electronic components always working at proper temperature.But majority of phase change materials have low thermal conductivity,so the heat cannot be quickly transmitted to other parts of the phase change material,which makes the heat accumulation in the heat source.To solve this problem,graphite foam prepared by template method with high thermal conductivity was used for the thermal conductivityenhancement of phase change material.Thermal conductivity is an important property of graphite foam,ANSYS software was used in this paper to simulate thermal conductivity of graphite foam,providing an effective method to predict thethermal conductivity of graphite foam.Carbon-based form-stable composite energy storage material was fabricated by vacuum impregnation method using graphite foam and phase change material.Composite phase change material musthave good thermal stability when used in spacecraft thermal control due to the cycle operation of spacecraft.Thermal cycling experiments have been carried out to analyze the thermophysicalproperties of composite phase change material changing with thermal cycling numbers.To analyze the influence of graphite foam and phase change material parameters on the thermal response of composite phase change material,local thermal non-equilibrium model was used to get the key factors affecting the thermal control.Thermal control of composite phase change material for satellite was simulated using FlUENT software,advantages of satellite thermal control using this method was abstained by comparison of multilayer insulation component thermal control.