Thin-wall sleeve-type space development mechanism

A technology of space deployment and thin-walled sleeves, applied in the direction of aerospace vehicle guides, etc., can solve problems such as mass, high power consumption, low power consumption and low quality of small satellites, and achieve the effect of improving stiffness and carrying capacity

Inactive Publication Date: 2009-12-23
BEIHANG UNIV
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  • Abstract
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Problems solved by technology

[0005] Most of the existing general space deployment mechanisms are large-scale mechanisms, used for large satellites, space stations, etc. Such mechanisms generally adopt large-scale truss structures, which often have high rigidity and strength, and can carry large task loads, but It is also quite large in terms of quality and power consumption, which is not suitable for the needs of small satellites with low power consumption and low quality

Method used

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  • Thin-wall sleeve-type space development mechanism
  • Thin-wall sleeve-type space development mechanism
  • Thin-wall sleeve-type space development mechanism

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Embodiment Construction

[0028] The present invention is a thin-walled sleeve-type space deployment mechanism, which includes a support part 1 and a transmission part 2 .

[0029] Such as figure 1 , figure 2 As shown, the support part 1 includes an upper support plate 101 , a lower support plate 102 , a front support plate 105 , a rear support plate 106 , a left support plate 103 , a right support plate 104 , and a motor frame 107 .

[0030] The left support plate 103, the right support plate 104, the front support plate 105 and the rear support plate 106 are fixed between the upper support plate 101 and the lower support plate 102 by screws to support the whole mechanism. The motor frame 107 is fixed on the lower support plate 102 by screws. Both the lower support plate 102 and the upper support plate 101 have positioning grooves to help the left support plate 103 and the right support plate 104 to be installed and positioned. The upper support plate 101 is wider than the lower support plate 102,...

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Abstract

The invention discloses a thin-wall sleeve-type space development mechanism, which is a device used for sending apparatuses on a spacecraft to a position certain distance away from the spacecraft to perform function operations. The mechanism is driven by a motor and drives the sleeve for development by gradually developing a thin-wall pipe from a coiled state. The magnification ratio of the mechanism is big due to coiling, the quality of the mechanism is reduced by means of a thin-wall structure, and a component made from nonferromagnetic metal materials can prevent the mechanism from ferromagnetic interference. By using a sleeve design, the mechanism has higher stiffness and stability, and linear development ensures the stationarity of the development process. Synchronously, the position accuracy of the development and the reliability of the development result are ensured by the design of a caging device.

Description

technical field [0001] The invention relates to the field of space utilization, in particular to a thin-walled sleeve-type space deployment mechanism. technical background [0002] The space deployment structure is the application expansion of the traditional deployment mechanism in the space field. It is one of the main mechanisms to realize functions such as solar sails, antenna deployment, and detector support. With the continuous development of technology and needs, a variety of different space deployment mechanisms have emerged. Concept and Application. There are many types of space deployment mechanisms, among which the rod-shaped frame type deployment mechanism is widely used and developed rapidly. [0003] Space scientific exploration requires the stretching mechanism to have the characteristics of small mass and large expansion ratio. At the same time, the use of precision instruments also requires the mechanism to have a high degree of magnetic cleanliness. [00...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
Inventor 赵国伟卫巍张展智
Owner BEIHANG UNIV
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