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A passive thermal control system is provided for the temperature control of the panchromatic camera of IRS-1C spacecraft. The camera with a spatial resolution of better than 10m and a revisiting capability requires a stringent thermal control system. The thermal design is based on mathematical models. This paper gives the details of the model and the predicted temperature distribution of the camera.

A numerical solution is attempted for the steady state temperature distribution in a two dimensional rectangular radiating fin with single heated footprint. The solution is presented for problems similar to spacecraft doubler plate with single heated footprint. The spacecraft thermal doublers are used to spread the localized heat dissipation by some electronic packages over large area and thus ensure the operating temperature of the package within the specified maximum temperature. The results of this analysis are presented as the design charts for the design of doubler plates in a spacecraft environment. Basically, design of doubler plate is meant to find out the required radiator area and the thickness of the plate for given heat dissipation and the maximum operating temperature of the electronic package.

“Tinned Copper Braid” is planned to be used in IRS-1C spacecraft for the thermal control of the detector of the “Middle Infra Red” (MIR) band of LISS III Camera. The thermal conductance of the braid was evaluated experimentally in the temperature range of -65°C to +35°C by employing the calorimetric technique. The measured thermal conductance of the 215mm long copper braid varies from 0.051 to 0.056 W/°C at different temperatures in the specified range. An error estimation has been performed which shows a maximum uncertainty of better than ± 5% on the conductance value measured.