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Flexible Support Structure for Large Circular Reflector of Space Optical Remote Sensor

A technology of space optical remote sensing and flexible support, which is applied in the field of space optical remote sensing to achieve precise installation and positioning, reduce stress concentration, and ensure the effect of surface shape accuracy

Active Publication Date: 2020-06-02
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a method that can solve the back support problem of the large circular reflector of the space optical remote sensor, eliminate the assembly profit and the influence of gravity deformation on the surface shape accuracy of the reflector generated during the assembly process of the reflector, and improve the temperature adaptability. Flexible support structure for large circular mirrors of space optical remote sensors that reduce the impact of positioning accuracy of traditional support structures on imaging quality

Method used

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  • Flexible Support Structure for Large Circular Reflector of Space Optical Remote Sensor
  • Flexible Support Structure for Large Circular Reflector of Space Optical Remote Sensor
  • Flexible Support Structure for Large Circular Reflector of Space Optical Remote Sensor

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Embodiment 1

[0052] see figure 2 As shown, the flexible support structure provided by Embodiment 1 of the present invention mainly includes:

[0053] flexible support unit 301;

[0054] Assembled and fixed with the flexible support unit 301, and sleeved on the upper part of the flexible support unit 301 Invar sleeve 2;

[0055] The flexible support unit 301 is formed with a plurality of flexible spring belt hinges arranged in the same section along its circumference, and a flexible curved groove 6 extending along the circumference of the flexible support unit 301 is opened between adjacent flexible spring belt hinges.

[0056] Specifically, the first embodiment mainly discloses a flexible support structure, which takes a flexible support unit 301 as the main body, and is provided with a set of Invar sleeves 2 on the upper end of the flexible support unit 301 in conjunction with the flexible support unit 301. , in order to be able to eliminate the stress well when an external force is ap...

Embodiment 2

[0066] see Figure 6 to Figure 8 As shown, the present invention discloses a large-scale circular reflector assembly for a space optical remote sensor. The reflector assembly includes a reflector body 1 and a substrate 4 formed on the back of the reflector body 1. The reflector body 1 and A plurality of flexible support structures as described above are assembled between the substrates 4 (see Figure 2 to Figure 5 shown). After the introduction of a pair of flexible supporting structures in the embodiment, the second embodiment takes the large circular mirror for space optical remote sensor using the flexible supporting structure as an example for further explanation.

[0067] Preferably, the back of the reflector mirror body 1 in the second embodiment is provided with three supporting blind holes 101 along its circumference, and each supporting blind hole 101 is embedded with one of the above-mentioned flexible supporting structures;

[0068] The lower end of the flexible s...

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Abstract

The invention discloses a flexible support structure for a large circular reflector of a space optical remote sensor. The flexible support unit provided with a flexible spring belt hinge and a flexible curved groove is used as a main stress-relief structure, which is integrated into the space optical remote sensor. On the large circular mirror assembly, it can transfer the force acting on the flexible support structure to the above-mentioned flexible curved groove, and use the deformation of the flexible curved groove as the main means to eliminate the stress, so as to avoid the force from continuing to be transmitted On the reflector body of the space optical remote sensor, the stress concentration of the reflector under the action of gravity is reduced, and the surface shape accuracy of the reflector does not exceed the tolerance value of the optical design.

Description

technical field [0001] The invention relates to the technical field of space optical remote sensing, in particular to a flexible support structure for a large circular mirror of a space optical remote sensor. Background technique [0002] Space optical remote sensor, as a sophisticated optical remote sensing system, has been widely used in earth topography surveying and mapping, earth resource survey, outer space astronomy and planetary observation, and national defense information census. As the core component of the space optical remote sensor, the mirror's installation positioning accuracy and support surface shape accuracy have a great influence on the imaging quality of the optical system. In order to reduce the weight of the mirror, reduce the cost of carrying and launching, and increase the first-order natural frequency of the mirror, the main mirror of the space optical remote sensor must be lightweight. However, the lightweight design of the mirror will reduce the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G02B7/182
CPCG02B7/182G02B7/1821G02B7/1822
Inventor 李宗轩李叶文金光王家骐徐伟徐明林
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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