Carbon fiber thin-wall cylinder type main supporting structure of large-aperture space camera
A space camera and thin-walled cylinder technology, applied in the field of space optical remote sensing, can solve problems such as difficulty in satisfying self-weight deformation and vibration response, low specific stiffness, and difficulty in controlling the size and weight of the whole machine, so as to reduce product quality and meet shading requirements , reducing the effect of the product envelope
A space camera and thin-walled cylinder technology, applied in the field of space optical remote sensing, can solve problems such as difficulty in satisfying self-weight deformation and vibration response, low specific stiffness, and difficulty in controlling the size and weight of the whole machine, so as to reduce product quality and meet shading requirements , reducing the effect of the product envelope
CN112485955AActive Publication Date: 2021-03-12CHANGGUANG SATELLITE TECH CO LTD
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[0026] It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.
[0027] The present invention will be described in detail below with reference to the accompanying drawings and examples.
[0028] like Figure 1-Figure 3 As shown, a carbon fiber thin-walled cylindrical main support structure for a large-caliber space camera includes a secondary mirror truss assembly 1 and a front cylinder assembly 2, and the secondary mirror truss assembly 1 includes a secondary mirror joint 3, three secondary mirror truss rods 4, Several truss bar left clips 5 and some truss bar right clips 6 are provided with a secondary mirror assembly interface 17 on the lower surface of the secondary mirror joint 3, and three adhesive mounting surfaces are uniformly arranged on the side wall of the secondary mirror joint 3, and equipped with There are corresponding threaded holes for connecting with t...
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The invention provides a carbon fiber thin-wall cylinder type main supporting structure of a large-aperture space camera, which comprises a secondary mirror truss assembly and a front cylinder assembly, wherein the secondary mirror truss assembly comprises a secondary mirror connector, three secondary mirror truss rods, a plurality of truss rod left clamping blocks and a plurality of truss rod right clamping blocks, the lower surface of the secondary mirror connector is provided with a secondary mirror assembly interface, the front cylinder assembly comprises a cylinder body, longitudinal bars, a longitudinal bar upper connector and a longitudinal bar lower connector, an upper flange is arranged at the upper end of the cylinder body, and a lower flange is arranged at the lower end of the cylinder body; the three longitudinal bars are evenly arranged on the outer wall of the cylinder body, the side wall of one end of each secondary mirror truss rod is bonded with the corresponding bonding installation face of the side wall of the secondary mirror connector, the other end of each secondary mirror truss rod is connected with the top surface of the upper flange through the truss rod left clamping block and the truss rod right clamping block, and the connecting positions of the three longitudinal bars and the upper flange and the connecting positions of the three secondary mirror truss rods and the upper flange are arranged in an up-down one-to-one correspondence mode. The invention provides a main supporting structure considering shading and force transmission paths. The structure is small in outer envelope, high in specific stiffness and light in weight.
Description
technical field [0001] The invention belongs to the technical field of space optical remote sensing, and in particular relates to a carbon fiber thin-wall cylindrical main support structure for a large-diameter space camera. Background technique [0002] Large aperture and long focal length coaxial optical system space camera generally refers to a camera with an aperture of more than 1m. The secondary mirror and its supporting structure are located at the light entrance. There are strict requirements for blocking ratio, self-weight deformation, temperature rise deformation and vibration response. The traditional truss structure has a large outer envelope and requires an additional light-shielding structure, making it difficult to control the size and weight of the whole machine; the A-type truss rod structure has low specific stiffness and is greatly affected by the weight of the secondary mirror. Requirements such as vibration response. In view of the above shortcomings, ...
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Patent Timeline
12 Mar 2021
Publication
CN112485955A
- IPC
- G03B17/56
- CPC
- G03B17/561
- Inventors
- 宋训鹏; 张雷