Integrated Thermal Control System for Space Platform and Fractionated Payload

With the development of space exploration, combined spacecraft which can implement more complicated targets through fractionated payload or part of the spacecraft separated from the space platform have been in urgent need. Space platform provides carriage service for the fractionated payload or part of the spacecraft before separation. Under the hypothetical space platform and fractionated payload conditions, the paper proposed an integrated thermal control system for it, simultaneously, simulations of several cases such as thermal control efficacy for the payload during storage stage, the thermal impact between the space platform and the fractionated payload, and the temperature variation of the platform during separation were carried out. Moreover, the steady-state simulations and thermal mathematic model were verified through thermal vacuum test. Thermal simulations and thermal vacuum tests generate the scheme characters of the temperature and thermal fluxes between the platform and fractioned payload. The whole figures of the simulations and test results proved the rationality and effectiveness of the system, meanwhile, verified the feasibility of the thermal vacuum test method for the thermal coupled space platform and fractioned payload while would be independent during thermal vacuum test, which can be as a reference of such spacecraft cases.