Spacecraft power supply double-bus system

Abstract

The invention provides a spacecraft power supply double-bus system. The spacecraft power supply double-bus system comprises a solar cell array module, a shunt module, a charging control module, a platform adjusting bus, a load non-adjusting bus, a platform load, a load and a storage battery pack module; the solar cell array module is controlled by the shunt module and then is output to the platform adjusting bus to supply power to the platform load; the solar battery array module is controlled by the charging control module and then is output to the storage battery pack module to charge the storage battery pack module; the first storage battery pack and the second storage battery pack are connected in series and then output to the load non-adjusting bus to supply power to the load; the first storage battery pack is output to the platform adjusting bus through a plurality of discharge adjusting modules to supply power to the platform load; and the second storage battery pack is connected to the platform adjusting bus through the plurality of discharge adjusting modules to supply power to the platform load. The system complexity can be reduced, and the system stability is improved.

Description

technical field [0001] The invention relates to the technical field of spacecraft power supply and distribution, in particular to a spacecraft power supply double busbar system, in particular to a spacecraft power supply double busbar solution based on battery pack modular reuse and reconfiguration design. Background technique [0002] With the development of the aerospace industry, there are more and more spacecraft loads, and there are more and more high-power loads, especially the power requirements of microwave remote sensing loads and optical remote sensing loads are increasing, resulting in a sharp increase in the power of the entire star, and the loads work in general. For high-power pulse or short-time work mode, the peak power exceeds several thousand watts, or even tens of kilowatts. Because the pulse or short-time work mode of the load has a serious reflection effect on the bus, generally speaking, spacecraft with high-power loads generally The dual-bus mode of th...

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Problems solved by technology

[0002] With the development of the aerospace industry, there are more and more spacecraft loads, and there are more and more high-power loads, especially the power requirements of microwave remote sensing loads and optical remote sensing loads are increasing, resulting in a sharp increase in the power of the entire star, and the loads work in general. For high-power pulse or short-time work mode, the peak power exceeds several thousand watts, or even tens of kilowatts. Because the pulse or short-time work mode of the load has a serious reflection effect on the bus, generally speaking, spacecraft with high-power loads generally The dual-bus mode of the platform-regulated bus and the load-unregulated bus is adopted. Usually, the supporting batteries for each bus are mostly two or more sets of battery packs. The battery packs cannot be interchanged and cannot be backed up with each other, resulting in a large number of battery assemblies. Many, the failure mode is complicated, and the failure of the entire battery pack usually results in failure, which cannot be redistributed, and the utilization rate of the battery pack is low; for the internal interface of the system, the corresponding control modules such as solar battery arrays, charging modules, discharging modules, and equalization modules are added. The system is complicated, the weight increases, the efficiency of the power supply system is low, and other unfavorable factors. At the same time, due to the inconsistent voltage of the double busbars, the design of the solar cell array corresponding to the two busbars is inconsistent, and the interconnection cannot be realized; for the external interface of the system, telemetry, remote control, thermal control , structure and other aspects increase, resulting in the waste of the whole star resources, reducing the loading capacity of the spacecraft load, which is not conducive to the utilization of the entire spacecraft resources; especially as the power demand of the spacecraft increases, this situation will be particularly serious protrude

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