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A kind of architecture that supports ultra-high power consumption for small satellites

A satellite and ultra-high technology, applied in the field of architecture supporting ultra-high power consumption, can solve problems that hinder the launch of small satellites, large launch space, and the inability to realize rapid assembly and mass production of small satellites, so as to achieve rapid assembly and mass production , the effect of small volume

Active Publication Date: 2022-07-08
HARBIN INST OF TECH
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Problems solved by technology

however, the larger cube volume requires a correspondingly larger launch space in the launch vehicle, thus preventing the launch of small satellites in a "multiple satellites with one rocket" approach
The cube-shaped structure is also not conducive to the simultaneous operation of multiple people in the process of small satellite assembly, which makes it impossible to realize the rapid assembly and mass production of small satellites

Method used

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  • A kind of architecture that supports ultra-high power consumption for small satellites
  • A kind of architecture that supports ultra-high power consumption for small satellites
  • A kind of architecture that supports ultra-high power consumption for small satellites

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Embodiment Construction

[0013] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0014] see Figure 1 to Figure 2 , the embodiment of the present invention provides an architecture 100 supporting ultra-high power consumption of a small satellite S, the architecture 100 may include:

[0015] Main structure 110, see specifically figure 2 , the main structure 110 is formed with a plurality of cabin sections 111 for installing the satellite unit U of the small satellite S, and the plurality of cabin sections 111 are distributed in the same distribution plane P, wherein figure 2 A grid-like main structure 110 is exemplarily shown in FIG. figure 2 As shown, these cabin sections 111 are distributed in the main structure 110 in the form of a two-dimensional matrix, in other words, these cabin sections 111 do not have any form of "superposition" in th...

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Abstract

An embodiment of the present invention discloses an architecture for a small satellite that supports ultra-high power consumption. The architecture includes: a main structure, where the main structure is formed with a plurality of cabin sections for installing a single satellite of the small satellite, the A plurality of cabin sections are distributed in the same distribution plane; an attitude control cabin, the attitude control cabin is arranged in the distribution plane in which the plurality of cabin sections are distributed, so that the main structure and the attitude control cabin are formed as a whole as a board a solar panel configured to be capable of being in a deployed state extending from the main structure to convert solar energy into electrical energy for use by the small satellite.

Description

technical field [0001] The invention relates to the field of overall configuration design of small satellites, in particular to a small satellite architecture supporting ultra-high power consumption. Background technique [0002] With the continuous development of small satellite technology, the satellite load in the small satellite requires higher and higher total power to achieve higher satellite performance. At the same time, the high power of the load will cause the small satellite to generate more heat. Take communication type small satellites as an example. The weight of such small satellites is usually about 200kg, and the long-term power consumption in orbit will reach the kilowatt level. Due to the high long-term power consumption in orbit, a large amount of heat will be generated. [0003] The overall structure of the current small satellite is usually in the shape of a cube. In order to dissipate more heat generated by the small satellite, it is usually necessary ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/17G06F119/08
CPCG06F30/17G06F2119/08Y02E10/50
Inventor 郭金生李化义曹喜滨张冀鹞
Owner HARBIN INST OF TECH
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