It is very important to simulate reasonably the orbit external thermal flux of a space flying object and space optical remote sensor through thermal equilibrium experiment in order to investigate them for thermal effect

verify thermal design

and evaluate the capacity of their thermal-controlling system to adapt the space environment. A simulation and computation method for orbit external thermal flux is described

and especially the technique and the device for a space optical remote sensor are presented in connection with structure

surface property

distribution of external thermal flux and thermal equilibrium experiment requirement. And parameters of heating sheet are determined on the basis of computation and verification employing computer software. As a result

it provides an approach for simulating the orbit external thermal flux of a space flying object and space optical remote sensor.