Ensuring Dimensional Stability of Space Platform Panels by Using Electric Heaters

In orbital flight, the temperature state of spacecraft and their constituent space platforms complexly changes in time and space. The inhomogeneous temperature field of the space platform can cause shape distortion, which negatively affects the performance of targets. To equalize the temperature field of the space platform, it is proposed to use electric heaters with differentiated power distributions. The purpose of this work is to improve the thermal stability of spacecraft platforms through the use of differentiated electric heaters, as well as to reduce the time spent on designing, as part of the methodology for determining the specific power of heaters, necessary to equalize the temperature field on the outer side of the spacecraft panel. The formulation of the boundary inverse heat conduction problem is presented and the specific power of the heaters necessary for uniform distribution of the temperature field of a panel of composite material is determined. The results of thermal condition modeling of the satellite bus composite structure were presented.