A satellite power supply system

A technology of power supply system and satellite power supply, which is applied in the field of aerospace satellites, can solve problems such as failure to work normally, and achieve the effect of promoting standardized development and reducing the overall volume

Active Publication Date: 2022-04-26
北京微纳星空科技有限公司
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  • Abstract
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Problems solved by technology

[0004] The purpose of the embodiment of the present application is to provide a satellite power supply system, which is used to not supply power to the satellite before the separation of the satellite and the rocket, and to supply power to the satellite after the separation of the satellite and the rocket, so as to avoid the separation of the satellite and the rocket due to long-term power supply as much as possible Problems not working after

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  • A satellite power supply system
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Embodiment approach

[0090] As an implementation manner, the second travel switch (S2) may further include: a second static contact (4) of the second travel switch and a second movable contact (5) of the second travel switch. In this embodiment, the second static contact (4) of the first travel switch is grounded, and the second movable contact (5) of the first travel switch is connected to the second movable contact (5) of the second travel switch. The second static contact ( 4 ) is connected to the signal collection terminal (I / O) of the satellite load 102 .

[0091] Before the separation of the satellite and the rocket, the second moving contact (5) of the first travel switch is in contact with the second static contact (4) of the first travel switch, and the second moving contact (5) of the second travel switch is in contact with the second moving contact (5) of the second travel switch. The second static contact (4) of the switch contacts.

[0092] After the satellite and the rocket are sepa...

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Abstract

The application provides a satellite power supply system. The satellite power supply system includes: a satellite power supply module, a satellite load, a first travel switch and a power supply control circuit; The second terminal of the power supply control circuit is connected to the power input terminal of the satellite load, and the third terminal of the power supply control circuit is grounded; the first travel switch is set on the first terminal of the power supply control circuit. Between the terminal and the third terminal, the first travel switch is closed before the satellite and the rocket are separated, so that the first terminal and the second terminal of the power supply control circuit are disconnected, and after the satellite and the rocket are separated, the all The first end and the second end of the above-mentioned power supply control circuit are turned on, so as to realize the autonomous power supply of the satellite after the separation of the satellite and the rocket, and avoid the problem that the satellite cannot work normally after the separation of the satellite and the rocket due to long-term power supply before the separation of the satellite and the rocket. .

Description

technical field [0001] The present application relates to the field of aerospace satellites, in particular to a satellite power supply system. Background technique [0002] Satellites are brought from the ground to predetermined orbits by launch vehicles. When the satellite is in orbit, it converts solar energy into electrical energy and stores it in the battery to realize the autonomous power supply of the satellite. [0003] But satellites are typically stored in launch vehicles for several days before reaching orbit. During this period, if the satellite is always powered by the battery, the power of the battery will continue to decrease, and after the satellite is separated from the rocket, the satellite may not work properly due to the low power of the battery. Contents of the invention [0004] The purpose of the embodiment of the present application is to provide a satellite power supply system, which is used to not supply power to the satellite before the separati...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/42H02J7/00H02J7/35
CPCB64G1/428H02J7/007H02J7/35
Inventor 郭立业王亦楠孙树强苏帆刁占林高恩宇孔令波
Owner 北京微纳星空科技有限公司
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