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Off-orbit sail deployment method and device

A technology of de-orbiting and unfolding process, which is applied in the field of spacecraft de-orbiting, can solve problems such as the internal complexity of stars, and achieve the effects of preventing sudden damage, saving space, and ensuring support capacity

Active Publication Date: 2021-02-09
SPACETY CO LTD (CHANGSHA)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] Based on the interpretation of the prior art, the deorbiting device in the prior art has at least the following defects: it will be partially or completely installed inside the star, causing complications inside the star

Method used

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  • Off-orbit sail deployment method and device
  • Off-orbit sail deployment method and device
  • Off-orbit sail deployment method and device

Examples

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Effect test

Embodiment 1

[0046] This embodiment discloses an off-track sail deployment device.

[0047] Such as Figure 1-5 As shown, the off-track sail deployment device includes a non-folding sail 200 and a folding sail 300 . The non-folding sail 200 is rotatably connected with the folding sail 300 to form a deorbiting sail for driving the star 100 out of orbit. Preferably, the first side of the unfolded sail 200 is provided with a connecting plate 400 . The connecting plate 400 is provided with a hinge 400a capable of turning the folding sail 300 relative to the first side.

[0048] The folding sail 300 includes at least one first frame 300a capable of folding the sail body in a folded state and supporting the sail body in an unfolded state. Preferably, the first skeleton 300a is light alloy steel, for example, material. The use of lightweight alloy steel can reduce the weight of the folding sail 300 on the premise that the mechanical construction rigidity and strength meet the technical specif...

Embodiment 2

[0060] This embodiment can be further improved and / or supplemented to the folding sail 300 in Embodiment 1, and the repeated content will not be repeated. In the case of no conflict or contradiction, the whole and / or part of the content of the preferred implementations of other embodiments may serve as supplements to this embodiment.

[0061] This embodiment discloses a preferred folding sail 300 that can at least be used in the off-track sail deployment device of Embodiment 1. The folding sail includes at least one first frame 300a and a sail body. Preferably, it may also include a second skeleton 300b. The sail body can be an aluminum membrane sail. It can be sewn on each skeleton with cotton thread. The sail body can be an independent sail body, or a plurality of sail bodies assembled between two first frames 300a. When the folding sail 300 is folded, the sail body can be in a folded state based on the first frame 300a and the second frame 300b. When the folding sail 3...

Embodiment 3

[0067] This embodiment may be a further improvement and / or supplement to Embodiment 1, and repeated content will not be repeated here. In the case of no conflict or contradiction, the whole and / or part of the content of the preferred implementations of other embodiments may serve as supplements to this embodiment.

[0068] Such as Figure 1-5 As shown, the off-track sail deployment device includes a non-folding sail 200 and a folding sail 300 . The non-folding sail 200 and the folding sail 300 are connected by a connecting plate 400 . A hinge 400a is disposed on the connecting plate 400 . Used to rotate the folding sail 300 around the non-folding sail 200 . The non-folding sail 200 is provided with a fixing mechanism at the opposite end of the connecting plate 400 . For example, the fixing mechanism includes a connecting wire and a fuse resistor. One end of the connection line and the fuse resistor are in a fixed state before receiving the off-track command. The other en...

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Abstract

The invention relates to a method and device for deploying an off-orbit sail, comprising a non-folding sail and a folding sail, the non-folding sail and the folding sail are rotatably connected to form an off-orbiting sail for driving a star off-orbit; At least one first frame for folding the sail body in the state and for supporting the sail body in the unfolded state is rotated to a first clip of the folding sail and the non-folding sail at the first side of the folding sail relative to the non-folding sail When the angle is a first critical value, one or more of the at least one first frame begins to rotate around the folding sail in such a way that it can be parallel to the first side, and the first side of the folding sail relative to the non-folding sail Continue to rotate, so that the first included angle continues to increase to the second critical value that can make the folding sail and the non-folding sail form an off-track sail. Before launch, the folding sail can be folded to minimize the volume; the off-orbit sail has a large enough surface-to-mass ratio when it is unfolded.

Description

technical field [0001] The invention relates to the technical field of spacecraft off-orbit, in particular to a method and device for deploying an off-orbit sail. Background technique [0002] The de-orbit sail is a passive de-orbit device. Its purpose is to prevent the cube star from becoming long-term space junk after it fails. At the end of the cube star's life, a low-cost brake sail device is used to quickly de-orbit it. In addition to meeting the general design principles and technical indicators of mechanical components, the design of off-track sails also needs to meet the following principles: [0003] (1) Lightweight: After the off-orbit sail is deployed, the mass distribution changes, and more mass is far away from the inertial axis, which will put forward higher requirements for the capability of the attitude control components. Moreover, the mass of the satellite is also closely related to the launch cost. Therefore, the mass should be reduced as much as possible...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/00B64G1/22B64G1/24B64G1/62
CPCB64G1/24B64G1/62B64G1/2427B64G1/245B64G1/2228B64G1/2224B64G1/222B64G1/242B64G1/407
Inventor 李晓明王战辉邹宇任维佳杨峰
Owner SPACETY CO LTD (CHANGSHA)
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