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Topology structure and method of double-bus lunar exploration vehicle solar cell array sub-array

A technology of solar cell array and topological structure, which is applied to circuits, photovoltaic power generation, electrical components, etc., and can solve problems such as power waste of solar cell arrays

Active Publication Date: 2017-08-15
SHANGHAI AEROSPACE SYST ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0017] The problem solved by the present invention is the shortcoming of power waste in existing aircraft solar cell arrays; in order to solve the problem, the present invention provides a dual-bus lunar exploration aircraft solar cell array sub-array topology and method

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  • Topology structure and method of double-bus lunar exploration vehicle solar cell array sub-array
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  • Topology structure and method of double-bus lunar exploration vehicle solar cell array sub-array

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Embodiment Construction

[0038] Hereinafter, the present invention will be further described in conjunction with the drawings and embodiments.

[0039] According to the design characteristics of the lunar exploration vehicle, on the premise of ensuring the safety of energy supply, the power supply efficiency should be improved as much as possible. The dual-busbar lunar exploration aircraft solar cell array sub-array topology provided by the present invention adopts a dual-busbar power supply topology. According to the requirements of the equipment on the lunar exploration aircraft for the power supply voltage, the efficiency design of the power supply system is considered as a whole, and two types of busbar output voltages are set, respectively. In order not to adjust the bus voltage 23 ~ 29V, fully adjust the bus voltage 29V. According to the power demand of the load, select the busbar used by different loads, see figure 1 .

[0040] like figure 2 As shown, in order to adapt to the dual-bus outpu...

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Abstract

The invention discloses a solar battery array topology structure and method of a double-bus lunar exploration aircraft. The invention discloses a solar battery array topology structure of a double-bus lunar exploration aircraft. battery pack, charging circuit, BDR circuit; fully regulated busbar and non-regulated busbar; the power supply array supplies power to the fully regulated busbar through the shunt circuit; the charging array supplies power to the unregulated busbar through the charging circuit and charges the battery pack; the The charging array supplies power to the fully regulated bus through the BDR circuit. The invention can improve the power supply efficiency of the solar battery array of the lunar exploration vehicle.

Description

technical field [0001] The invention relates to the overall design technology of the power supply of the lunar probe, and in particular to a topological structure and method of a solar cell array of a double-bus lunar probe aircraft. Background technique [0002] Taking the third phase of the lunar exploration orbiter as an example, the typical tasks of this type of lunar exploration spacecraft are: to carry the sub-probe to complete the orbital transfer from the earth to the moon, to complete the capture of the orbit around the moon, to release the sub-probe in the orbit around the moon, And after a certain period of time, it will re-dock with the sub-probe, and then carry the lunar samples collected by the probe to complete the mission of returning to Earth. [0003] The flight stages of this lunar exploration vehicle are roughly divided into the following stages: [0004] Launch stage: The launch vehicle sends the lunar exploration vehicle and sub-probe assembly into the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H01L31/042
CPCY02E10/50
Inventor 赵晨张玉花侯建文胡震宇李天义曹彦魏然丁同才瞿水群朱智超
Owner SHANGHAI AEROSPACE SYST ENG INST