A high-power and high-efficiency satellite power supply system based on high-voltage and low-voltage dual buses

Abstract

The invention discloses a high-power high-efficiency satellite power supply system based on high voltage and low voltage double buses. The system comprises a solar battery array, an energy storage battery pack, a power supply controller, a power supply lower computer and a power distribution part. All-adjusting bus design is employed for a 28 V bus. Semi-adjusting bus design is employed for a 42 V bus. Power for signal collection and control of the two buses is supplied by the 28 V bus. Functions such as parameter collection, remote control instruction output, battery pack management and satellite service host communication are finished by sharing the same power supply lower computer. According to a high voltage and low voltage bus system related to the system, a new type topological structure with independent power circuits and a shared control circuit is employed. Moreover, an energy management strategy is improved; long-term load and short-term load of partial load are configured on the all-adjusting low-voltage bus. The short-term load of the rest load is configured on the semi-adjusting low-voltage bus. The current density of the system is effectively reduced. The power level of the system is improved. The high-efficiency, light-weight and high-power satellite power supply system is realized.

Description

technical field [0001] The invention relates to a high-power and high-efficiency satellite power supply system based on high-voltage and low-voltage double buses. The invention is suitable for small satellites with large long-term power consumption and short-term high-power load work requirements, and can realize a compact power supply system with high specific power and high efficiency. Background technique [0002] The satellite power system is composed of a power controller, a battery pack and a solar cell array, which are always in working condition during the entire life of the satellite to meet the power requirements of the satellite in various working modes during the entire life. When there is a demand for high power output on the planet, it is usually necessary to jointly discharge the solar cell array and the battery pack. For satellites with high long-term power and short-term high-power load, the battery pack is mainly used to supply power for the load. The exi...

AI Technical Summary

Problems solved by technology

The existing small satellite power system mainly adopts single-bus technology, that is, the satellite primary power bus is a single 28.5V voltage, and the current passing through the bus is relatively large, which puts forward higher requirements for battery capacity and cable derating.

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