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Inter-satellite power supplying device

A technology of power supply device and main star, which is applied in the direction of coupling device, two-part connection device, parts of connection device, etc. It can solve problems such as failure and affecting the working life of the battery, and achieve reliable connection, reliability, and continuous power supply.

Active Publication Date: 2013-12-25
AEROSPACE DONGFANGHONG SATELLITE
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  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

However, for satellites with a long flight time in the active segment (such as micro-satellites carried by geostationary orbit satellites), if the on-board battery of the micro-satellite is used for power supply at this time, due to the long discharge time (generally about 7 days), the battery discharge depth If it is too large, it will affect the working life of the battery or even cause failure

Method used

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  • Inter-satellite power supplying device

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Embodiment Construction

[0013] Such as figure 1 Shown is the structural diagram of the star power supply device of the present invention, which mainly includes the target star terminal fixed support 1, the target star terminal power supply electrode 2, the target star terminal compression spring 3, the target star terminal dielectric layer 4, and the target star terminal Top block 5, main star terminal fixed support 6, main star terminal power supply electrode 7, main star terminal compression spring 8, main star terminal dielectric layer 9, main star terminal top block 10. The target star terminal fixed support 1, the target star terminal power supply electrode 2, the target star terminal compression spring 3, the target star terminal dielectric layer 4, and the target star terminal top block 5 are installed on the target star, and the target star terminal power supply electrode 2 is embedded Inside the target star-terminal dielectric layer 4 , the bonding force between the target star-terminal powe...

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Abstract

An inter-satellite power supplying device comprises a target satellite side fixing and connecting support (1), a target satellite side conductive electrode (2), a target satellite side pressure spring (3), a target satellite side medium layer (4), a target satellite side top block (5), a main satellite side fixing and connecting support (6), a main satellite side conductive electrode (7), a main satellite side pressure spring (8), a main satellite side medium layer (9) and a main satellite side top block (10). The inter-satellite power supplying device replaces conventional power supplying connection methods which relate to umbilical cables or shed electric connectors, is simple and reliable, and can not influence separation safety. When a powered phase of a carrier rocket flies, a main satellite provides power for an auxiliary satellite through the inter-satellite power supplying device, therefore, power supply capacity in a long-term powered phase flying period (about seven days) is guaranteed, the depth of discharge of a storage battery of the auxiliary satellite can be effectively decreased, and the service life of the storage battery is prolonged.

Description

technical field [0001] The invention relates to a star power supply device used in the power supply path between a main star and a small satellite (secondary star) during the active flight of the satellite. Background technique [0002] Microsatellites generally refer to satellites with a weight of less than 100 kilograms. Considering factors such as launch costs, microsatellites generally adopt launch methods such as piggyback launch and multiple satellites with one arrow. For low-earth orbits, microsatellites are generally installed on launch vehicles using star-rocket adapters, and the flight time of the active segment is relatively short. At this time, the communication between the launch vehicle and the microsatellites can be ensured by using the method of disconnecting electrical connectors or umbilical cables. (such as sending out electrical separation signals), the satellite mainly relies on the battery pack installed in the star to realize the power supply to the wh...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01R24/00H01R13/04H01R13/10H01R13/502B64G1/10
Inventor 常新亚包锦忠
Owner AEROSPACE DONGFANGHONG SATELLITE
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