The SGD-1 basic thermal control design will be based on: • Thermal space environment as shown in Figure 10.3.6 • Thermal balance of external surface in space • Internal heat transfer by radiation • Internal heat transfer by conduction • Eventually internal heat transfer by evaporation or melting Figure 10.3.6 Thermal Space Environment The thermal space environment of SGD-1 is shown in Table 10.3.7 and the environmental fluxes are indicated in Table 10.3.8. Table 10.3.7 SGD-1 Orbit Tab e 10.3.8 Environmental Fluxes In order to calculate the heat balance of the spacecraft three kind of data are needed: INTERNAL DISSIPATION + ABSORBED FLUXES = RE-RADIATED HEAT TO SPACE The Thermal Control Subsystem (TCS) of the SGD-1 will not be designed in detail but globally described because of the high level spacecraft design. Two kinds of internal dissipation can occur in the spacecraft: radiative and conductive. The first one can be controlled quite reliably when modeling and computing data. However, the conductive heat transfer is difficult to estimate because of the high uncertainties. Two kinds of Thermal Control Methods can be use in the SGD-1: Passive and Active. Passive systems These kind of systems are the basis for all thermal control subsystems. No mechanical moving parts and no power consumption are required. The characteristics of these systems are the low mass, low
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