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Deployment device and method of spatial mechanism

A space and time technology, applied to motor vehicles, transportation and packaging, space navigation equipment, etc., can solve problems such as loss of control, pollution of orbiting aircraft, attitude rollover, etc.

Inactive Publication Date: 2018-05-01
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] For the deployment mechanisms such as solar panels of long-term orbiters, the traditional deployment method is to deploy by means of explosive bolts, that is, to unlock the bolts through ignition artifacts, and then realize the deployment of the mechanism. This deployment method will produce a greater impact , produces a large attitude disturbance to the body of the on-orbit vehicle, especially for a micro-sized on-orbit vehicle, this disturbance appears to be relatively large, which may cause a large deflection of the attitude of the small vehicle, and even cause the attitude to roll over. Serious consequences of loss of control
In addition, when the explosive bolt is blasted, it will produce residues, which will cause a certain degree of pollution to the orbiting aircraft
For small on-orbit aircraft, due to the very limited volume, the use of pyrotechnic bolts is limited in space

Method used

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  • Deployment device and method of spatial mechanism

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Effect test

Embodiment

[0053] Such as figure 1 As shown, a 28V power supply is used to provide power, and two power resistors with a resistance value of 25 ohms are used in parallel on the fuse board. The diameter of the constantan wire is Φ0.25mm and the length is 10cm. The current of the constantan wire loop is about 2.2 A. After the ground test, the PE line was fused in about 4 seconds, and the sailboard was successfully deployed. If it is necessary to shorten the fuse time of the PE line, it can be realized by reducing the resistance value of the resistor on the fuse board and increasing the loop current.

[0054] A space mechanism deployment device, the device includes a constantan wire, two fishing lines (the first fishing line and the second fishing line), a fuse plate and a power supply;

[0055] One end of the constantan wire is welded at the punctual position of the fuse board, and the other end of the constantan wire is first wound one or two turns on the first fishing line, and then wou...

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Abstract

The invention relates to a deployment device and method of a spatial mechanism and belongs to the technical field of spatial mechanism deployment of in-orbit air vehicles. For an in-orbit air vehicleespecially a miniature air vehicle provided with a deployment mechanism such as a solar panel substrate, the solar panel substrate is deployed through traditional explosive bolts, multiple defects exist, in order to solve the problem, a mode for fixing the solar panel substrate through constantan wires and fish wires is proposed, power is supplied to the constantan wires through a fusing device, the constantan wires generate heat to fuse the fish wires, the deployment mechanism such as the solar panel substrate is released and deployed, and by the adoption of the novel deployment mode, an installation space is small, cost is relatively low, and impact on an air vehicle body is quite small.

Description

technical field [0001] The invention relates to a device and method for deploying a space mechanism, mainly referring to the on-orbit deployment of space mechanisms such as solar panels of space vehicles. Fundamentally, once space mechanisms such as solar panels cannot be deployed normally, it will be devastating for long-term on-orbit vehicles, and it belongs to the technical field of space mechanism deployment of on-orbit vehicles. Background technique [0002] For the deployment mechanisms such as solar panels of long-term orbiting vehicles, the traditional deployment method is to deploy by means of explosive bolts, that is, to unlock the bolts through ignition artifacts, and then realize the deployment of the mechanism. This deployment method will produce a greater impact , will cause a large attitude disturbance to the body of the on-orbit vehicle, especially for a micro-sized on-orbit vehicle, this kind of disturbance appears to be relatively large, which may cause a l...

Claims

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Application Information

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IPC IPC(8): B64G1/44
CPCB64G1/443
Inventor 卢伟张宏德刘巧珍岳梦云刘苑伊易航阎小涛李旷代苏小峰王之平杨自鹏卢頔白冰王芳韩阳
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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