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Satellite

A technology for satellites and solar panels, applied in the fields of spacecraft and satellites, can solve problems such as limitations, difficulty in obtaining a large area for solar cells, and restricting the practical level of the use capability of microsatellites, and achieve the effect of improving power supply.

Inactive Publication Date: 2012-12-19
SHANGHAI ENG CENT FOR MICROSATELLITES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Limited by the size of tiny satellites and other devices such as a stand-alone satellite installed on the sky, it is difficult to obtain a large area of ​​solar cells pasted on the sky of the main body of the satellite.
thus limiting the power it can provide to satellites
However, the limitation of providing electric energy greatly restricts the ability of micro-satellites to support loads and the practical level of satellites.

Method used

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Examples

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Effect test

no. 1 example

[0024] Figure 1-2 A satellite 1 according to a first embodiment of the invention is shown in a folded and unfolded state, respectively. figure 1 is a schematic perspective view of a satellite according to a first embodiment of the present invention, wherein the solar device is in a folded state. figure 2 is a schematic perspective view of a satellite according to a first embodiment of the present invention, wherein the solar device is in a deployed state.

[0025] Such as Figure 1-2 As shown, the satellite 1 includes a satellite main body 2 and a solar device 3 installed on the satellite main body 2 . The satellite main body 2 is a rectangular frame structure, and includes various functional modules accommodated in the space inside it, for example, a communication module and the like. The solar device 3 includes a first solar sail panel 31 and a second solar sail panel 32 .

[0026] Further, as figure 1 and 2 As shown, the first solar panel 31 has a first side 311 and...

no. 2 example

[0041] Refer below Figure 3-4 , to describe a second embodiment according to the present invention. image 3 is a schematic perspective view of a satellite 10 according to a second embodiment of the present invention, wherein the solar device is in a folded state. Figure 4 is a schematic perspective view of a satellite 10 according to a second embodiment of the present invention, wherein the solar installation is deployed. Components of the satellite 10 according to the second embodiment of the invention that are identical to the satellite 1 of the first embodiment of the invention are given the same references in the figures.

[0042] refer to image 3 and 4 , it can be seen that, unlike the satellite 1 according to the first embodiment of the present invention, in the satellite 10 according to the second embodiment of the present invention, solar energy is provided on the side 23 of the satellite main body 2 and the surface 21 facing the sky. Battery board7. The light...

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PUM

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Abstract

The invention provides a satellite comprising a satellite main body and a solar device arranged on the satellite main body. The solar device comprises a first solar array and a second solar array. The first solar array comprises a first side and a second side, wherein the first side and the second side are adjacent; and the first solar array is rotationally hinged to the side surface of the satellite main body by the first side. One side of the second solar array is rotationally hinged to the second side of the first solar array. The solar device has a folding state and an expanding state. According to the satellite provided by the invention, the expansion of effective irradiated area of the satellite solar arrays in simple modes of folding and expanding of the solar arrays is realized, and the power supply of the solar device to the satellite is well prompted.

Description

technical field [0001] The invention relates to a spacecraft, in particular to a satellite, in particular to a low-orbit tiny satellite. Background technique [0002] Microsatellites generally refer to small satellites with a mass of less than 100kg that are lightweight, miniaturized, and have high functional density. Due to their low cost, short development cycle, and technological innovation, they have been highly valued by the international aerospace community in the past decade. Developed and launched dozens or even hundreds of tiny satellites. [0003] Microsatellites need electric energy as a driving force to work in orbit, and most of the current generation of spacecraft electric energy relies on solar panels with photocells to obtain electric energy. Limited by the size and complexity of microsatellites, microsatellites of this magnitude cannot be equipped with rotating sailboards with rotating drive mechanisms and conductive slip rings. Most of them directly adopt ...

Claims

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Application Information

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IPC IPC(8): B64G1/10
Inventor 陈宏宇陈有梅付碧红
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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