A Quick Response Power System for Small Satellites

Abstract

The present invention provides a power supply system for a small satellite with fast response, comprising: a solar cell array, used to convert solar energy into electric energy to supply power to the small satellite or to charge a battery pack; a battery pack, connected in parallel with the solar cell array, for storing The electric energy converted by the solar cell array or the output electric energy is given to the small satellite; the power controller is used for the energy management of the small satellite; the battery pack is electrically connected to the power controller, and the solar cell array is arranged on the small satellite through a fixed connection device On the outer wall of the cabin plate, there is a gap with the outer wall of the cabin plate; the battery pack is arranged in the cabin plate of the small satellite. With such an arrangement, on the one hand, the solar cell array does not need to be deployed after the small satellite enters orbit, and realizes the function of the small satellite entering orbit immediately; The decoupling between designs makes it possible to do thermal design for the small satellite body separately.

Description

technical field [0001] The invention belongs to the technical field of power supply, and in particular relates to a power supply system for fast response small satellites. Background technique [0002] Traditional small satellites generally use an unfolded solar cell array or an integrated solar cell array as the power generation device in the small satellite power system. For the deployable solar cell array method, after the small satellite enters orbit, it needs to be unlocked and deployed. The deployment process takes a certain amount of time, so that the small satellite cannot perform tasks immediately after entering orbit, and the deployment process is likely to cause vibration of the battery array structure. As a result, the attitude of the small satellite body shakes, which is not conducive to the realization of the small satellite's work after entering orbit; [0003] For the integrated solar cell array method, the power generation devices and solar cells on the sol...

AI Technical Summary

Problems solved by technology

For the deployable solar cell array method, after the small satellite enters orbit, it needs to be unlocked and deployed. The deployment process takes a certain amount of time, so that the small satellite cannot perform tasks immediately after entering orbit, and the deployment process is likely to cause vibration of the battery array structure. As a result, the attitude of the small satellite body shakes, which is not conducive to the realization of the small satellite's work after entering orbit;

[0003] For the integrated solar cell array method, the power generation devices and solar cells on the solar cell array are usually directly mounted on the surface of the cabin of the small satellite. This method does not require the related actions of on-orbit deployment, but this The method will cause a certain coupling between the installation of the solar cell array and the implementation of the thermal control means of the small satellite whole star, that is to say, there is coupling between the thermal design of the small satellite whole star structure and the design of the solar cell array, resulting in a Interaction between thermal design and structural development

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