Rigid heat dissipation device for medium-and-small-caliber space reflector
A mirror and small-caliber technology, applied in the field of space remote sensing, to achieve the effects of reducing thermal deformation, improving temperature stability, and ensuring rigidity
Active Publication Date: 2020-08-11
CHANGGUANG SATELLITE TECH CO LTD
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Problems solved by technology
[0004] In order to solve the problem of requiring a heat dissipation device that takes into account the thermal stability and rigidity requirements of the space mirror, the present invention provides a rigid heat dissipation device for small and medium-diameter space mirrors
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[0020] In order to understand the above-mentioned purpose, features and advantages of the present invention more clearly, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.
[0021] In the following description, many specific details are set forth in order to fully understand the present invention. However, the present invention can also be implemented in other ways different from those described here. Therefore, the protection scope of the present invention is not limited by the specific details disclosed below. EXAMPLE LIMITATIONS.
[0022] A rigid heat dissipating device for a small-to-medium-caliber space reflector includes a bushing 2 , a support cylinder 3 and a back plate 4 . structured as figure 1 and figure 2 shown. The bushing 2, the supporting cylinder 3 and the back plate 4 all adopt a rigid structure. The small and medium caliber space reflector is called the reflector body 1...
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The invention relates to the technical field of space remote sensing, in particular to a rigid heat dissipation device for a medium-small-caliber space reflector. The device solves the problems of lowsystem rigidity and large deformation. The device comprises a bushing, a support cylinder and a back plate. A bonding cylindrical hole is formed in the back surface of the reflector body. The liningand the supporting cylinder are each of a cylindrical structure with an opening in one end. The outer cylindrical surface of the bushing is bonded with the bonding cylindrical hole. A threaded throughhole I is formed in the bottom surface of the bushing. An unthreaded hole I corresponding to the threaded through hole I is formed in the bottom surface of the supporting cylinder. The supporting cylinder is connected with the lining through the first threaded through hole and the first unthreaded hole, a flange is arranged on the cylinder wall of an opening of the supporting cylinder, a second threaded through hole is formed in the flange, a second unthreaded hole corresponding to the second threaded through hole is formed in the back plate, the back plate is connected with the supporting cylinder through the second threaded through hole and the second unthreaded hole, and an external connection installation part is arranged on the back plate. The purpose of reducing thermal deformationof the mirror body is achieved, the requirements for thermal stability and rigidity of the space reflector are considered, and it is guaranteed that the remote sensor has good imaging quality.
Description
technical field [0001] The invention relates to the technical field of space remote sensing, in particular to a rigid heat dissipation device for a small and medium diameter space mirror. Background technique [0002] The temperature of the working environment of the remote sensor cannot be kept constant during the stage of ground installation and on-orbit operation. The changing temperature field will cause thermal deformation of the space mirror, which will affect the surface shape accuracy of the mirror and reduce the imaging of the remote sensor. Quality; in order to adapt to the changing ambient temperature, the space reflector in the remote sensor generally adopts the heat dissipation structure. At present, the common heat dissipating structures are all "flexible structures". The method is to process easily deformable structures such as flexible grooves and spring sheets on the supporting parts of the reflector, so as to introduce flexible links into the reflector asse...
Claims
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IPC IPC(8): G02B7/182
CPCG02B7/182
Inventor 袁健张雷姜启福霍占伟
Owner CHANGGUANG SATELLITE TECH CO LTD