Thermal equilibrium experiment is an important experiment item in developing space optical remote sensors. It is essential to create a ground simulative environment which is required to be equivalent with that of actual space high vacuum and ultra-lower temperature. In term of experiment requirements of space optical remote sensors

the thermal equilibrium experiment will be implemented under the condition of simulation in connection with space vacuum

orbit external thermal flux

and thermal boundary. It is concerned with orbit parameters

structures

properties of material and its surface

calculation of orbit external thermal flux

simulation of orbit external thermal flux

space vacuum

thermal boundary status

thermal computation

and thermal design

etc. On the basis of research on above factors

a sort of device of thermal equilibrium experiment of space optical remote sensors is schemed out and presented

meanwhile

its structure design is made employing software AutoCAD. Consequently

the conformation

characteristics and design method of this device are described.