10.3.3 Space Segment Baseline Design (Photovoltaic Power Generation) Satellite General Architecture The proposed spacecraft architecture for the sun-synchronous orbit mission is presented in Figure 10.3.1 in stowed and deployed configurations. This configuration has been determined using the following constraints and guidelines: • Launcher capabilities: mass and volume offered by Energia • Symmetric configuration to minimize disturbance torque's • Minimize the air drag • Take into account sufficient allocation for solar array and antenna accommodation. The basic satellite configuration includes a 1000 m^ Silicon solar array for power generation (120 kW), a 100 m^ transmitting antenna, deployed from the platform which provides the basic services (power storage, attitude and orbit control, structure and thermal control, and data handling facilities). The satellite as presently designed is in the range 10 to 15 tons, and provides 150 kW at its output (solar array, batteries, antenna). Solar Array Sizing Considering the trade off between price, efficiency and mass, Silicon solar cells were chosen for the solar array SGD-1 subsystem (Space to Ground Demonstrator-1). Table 10.3.6 shows a quick comparison between Ga-As and Si solar cells. ______________ Table 10.3.6 Solar Cell Trade-Off Analysis______________
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