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The thermal analysis of a fictitious, but representative, comet rendezvous mission was undertaken in order to investigate and validate some previously untried analysis techniques. The two major features of the investigation were the highly non-isothermal property of the body around which the orbit is made and the need to fully model the transient thermal effect of a temperature dependant shutter. The analysis was undertaken using the software tools ESATAN and ESARAD. A method was developed, using a sub-model approach, which successfully demonstrated one possible solution to these types of problems.