Electric power supply system of sun-synchronous satellite

Results are presented of designing the photoelectric supply system for Earth remote sounding on solar-synchronous orbit. A system is developed on a principle of direct energy transport from generator to a load. Main design characteristics of the system are evaluated. Its weight is less than 20% of a satellite weight, specific energy output is 190 kWh/kg, operation life is 3-5 years. In choice of orientation lay-out of solar battery, a characteristic property of solar-synchronous orbits is taken into account; for these orbits a constancy of local time T 0 when satellite passes a node of the orbit is a typical characteristic. Calculations have showed that due to this, an angle between a normal to an orbital plane and direction to the Sum during satellite flight, changes negligibly (maximum by 30°). It made possible to increase an efficiency of the single - axis lay-out of the solar battery orientation by means of angle optimization of its installation relative to an axis of rotation. A criterion of optimization is a maximum energy output during one turn of the satellite around the Earth at average value of the angle n during active existence Calculation results of optimal angle of solar battery installation are given for any T 0 and also distribution histograms of daily average power of the system intensity and number of charging-discharging cycles of the storage battery are given.