Abstract: The working environment of missile-borne computer is extremely harsh, the mechanical environment with large vibration and strong shock and the high temperature environment with closed small space exist at the same time, and the installation location is usually near the engine combustion chamber. Therefore, the key and difficult point of the missile-borne computer design is the design of vibration reduction and thermal insulation. This paper studies the thermal insulation design of rubber damper for a missile-borne computer and proposes two thermal insulation design schemes of heat insulation pad and adapter plate. Based on the measured temperature change curve of the computer mounting base, the applicabilities of the two schemes are verified by simulation analysis. The results in this paper can provide some reference for the vibration reduction and thermal insulation design of missile-borne computer.