Modeling radiative heat fluxes on a satellite

I need to model radiative heat fluxes on a satellite orbiting the Earth along different trajectories. Could you suggest the best way to model these heat fluxes? I need to take into account that the angles between the surface and the radiation rays change over time as the satellite orbits the Earth. Would it be possible to control the variation of parameters, such as trajectory angles, the time for one full rotation, and satellite orientation, for example from a Python script?