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High stability multi-angle and multi-freedom satellite releasing and bearing apparatus of space remote sensing camera

A remote sensing camera, high-stability technology, applied in camera devices, cameras, camera bodies, etc., to ensure image quality and stability, strong flexibility and practicability, and reduce coupling effects.

Active Publication Date: 2013-06-19
北京航天创智科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002]At present, the three-point static support unloading and satellite installation technology of the camera uses three-point support to realize the static support through the distribution of degrees of freedom, which can realize the unloading and installation of the camera and satellite structure. However, the support rigidity of this structure is poor, and it is difficult to meet the rigidity requirements of the camera mounting star. It is often necessary to increase the auxiliary support method to increase the rigidity, and release the excess freedom constraints through the unlocking mechanism on the orbit. The reliability is low and the structural weight is heavy. The article" A review of connection methods between foreign high-resolution cameras and satellite platforms", "Space Return and Remote Sensing", Vol. 30, No. 4, pp. 36-41, which is the closest prior art to this application

Method used

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  • High stability multi-angle and multi-freedom satellite releasing and bearing apparatus of space remote sensing camera
  • High stability multi-angle and multi-freedom satellite releasing and bearing apparatus of space remote sensing camera
  • High stability multi-angle and multi-freedom satellite releasing and bearing apparatus of space remote sensing camera

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Embodiment 1

[0038] Such as figure 1 Shown is a schematic diagram of the installation positions of the four flexible support mechanisms, cameras and satellites of the present invention, in which the star installation device includes four flexible support mechanisms A, B, C, D, wherein the structure of the flexible support mechanism A is as follows figure 2 As shown, the structures of the flexible supporting mechanisms B and C are the same as Figure 4 As shown, the structure of the flexible support mechanism D is as follows Figure 6 As shown, the four flexible support mechanisms A, B, C, and D are all made of titanium alloy or aluminum alloy.

[0039] Such as figure 2 and Figure 3A As shown, the flexible support mechanism A is composed of an upper base plate 101, a lower base plate 102 and a flexible sheet, wherein the flexible sheet is composed of two mutually perpendicular flexible sheets 103, and the flexible sheet 103 is located between the upper base plate 101 and the lower ba...

Embodiment 2

[0048] Such as figure 1 Shown is a schematic diagram of the installation positions of the four flexible support mechanisms, cameras and satellites of the present invention. The star installation device in this embodiment includes four flexible support mechanisms A, B, C, and D, wherein the structure of the flexible support mechanism A is as follows figure 2 As shown, the structures of the flexible supporting mechanisms B, C, and D are the same as Figure 4 As shown, the four flexible support mechanisms A, B, C, and D are all made of titanium alloy or aluminum alloy materials.

[0049] The structures of the four flexible support mechanisms A, B, C, and D are as described in Example 1. In this embodiment, the four flexible support mechanisms A, B, C, and D are all designed in one piece, with strong structural rigidity. The height of the flexible sheets 103 and 203 is 10-40 mm, and the thickness is 0.5-3 mm.

[0050] Such as Figure 9 Shown is the schematic diagram of the in...

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Abstract

The present invention relates to a high stability multi-angle and multi-freedom satellite releasing and bearing apparatus of a space remote sensing camera. According to the present invention, a clamped connection point is arranged on an installation foot position for installing an optical remote sensing camera and a satellite, other connection points are provided with slice type flexible hinge structures according to line connecting directions of the connection points and the clamped connection point, such that a quasi-static clamped support manner of the remote sensing camera relative to a satellite installation plate is formed, the deformation and the uninstallation of the satellite installation plate by the remote sensing camera are realized, the slice type flexible hinge has high structure rigidity in the in-plane direction of the slice. With the present invention, the coupling effect of the camera structure and the thermal deformation of the satellite large base plate is effectively reduced, the sufficient whole support rigidity can be provided for the camera, such that the problem of imaging quality of the space remote sensing camera due to the thermal deformation of the satellite base plate is solved so as to ensure the imaging quality and the imaging stability of the space remote sensing camera after the space remote sensing camera enters the orbit; the method has characteristics of simple structure design, compact configuration, less connection steps and high reliability.

Description

technical field [0001] The invention relates to a high-stability release device with degrees of freedom, in particular to a high-stability multi-angle release star-mounting device for a space remote sensing camera. Background technique [0002] At present, the camera’s three-point static support unloading and satellite installation technology uses three-point support to realize static support by distributing degrees of freedom, which can realize the unloading and installation of the camera and satellite structure, but the support rigidity of this structure is poor, and it is difficult to meet the requirements of camera mounting and star mounting. Stiffness requirements, it is often necessary to increase the auxiliary support method to improve the stiffness, and release the redundant degree of freedom constraints through the unlocking mechanism on the orbit, the reliability is low, and the structural weight is heavy. Return and Remote Sensing", Volume 30, Issue 4, Pages 36-4...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C11/02G03B17/56
Inventor 蔡伟军范斌李庆林张凤芹王永辉李明雷文平马建华慈健
Owner 北京航天创智科技有限公司
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