Method for precisely assembling space remote sensing camera body structure

An assembly method and remote sensing camera technology, applied in the direction of photographic devices, etc., can solve the problems of high stress and low assembly accuracy, and achieve the effects of low cost, high assembly accuracy, and simple and convenient operation

Inactive Publication Date: 2009-11-04
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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  • Abstract
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  • Application Information

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Problems solved by technology

[0014] The invention changes the traditional mechanical assembly method and overcomes the disadvantages of low assembly precision and large stress

Method used

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  • Method for precisely assembling space remote sensing camera body structure
  • Method for precisely assembling space remote sensing camera body structure
  • Method for precisely assembling space remote sensing camera body structure

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Embodiment Construction

[0030] combined with figure 2 , 3 , 4, take the space remote sensing camera as an example to further illustrate the specific method of the present invention:

[0031] First, align the relative position between the metal frames 1, and grind the flatness of the mating surfaces of the frame 1 and the transition piece 2; The fit gap between them should be determined according to the performance of the adhesive used. Then trim the width of the thin-walled metal gasket 6 to about 4 mm to 5 mm. If it is too narrow, it will affect the positioning accuracy, and if it is too wide, it will reduce the bonding area. Wrap the metal gasket 6 around the end of the transition piece 3 axis, the optimum winding thickness is 0.02mm-0.04mm in diameter of the metal gasket 6 less than the inner diameter of the hole, so as to facilitate assembly and the adhesive layer to absorb assembly stress. After the support rod 3 and the transition piece 2 are well matched, they are taken between the frame 1...

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Abstract

The invention provides a method for precisely assembling a space remote sensing camera body structure, belonging to the technical field of assembly connection of body equipment. The method is to use a glue film as the close loop size of body assembly, lead assembly precision and assembly stress to depend on the deflection of the glue film, cancel the pad which may generate larger error, change the assembly mode of a transition component from glue connection first and screwed connection second of mechanical connection method into screwed connection first and glue connection second, use the metal pad to be wound on the transition component to be closely matched with an inner hole of a strut, and better achieve the aims of small assembly stress, high assembly precision and steady and firm structure through a microstress glue connection method. The glue connection method reduces the stress of the body structure on sensitive orientation, namely on axial of the strut, and optimizes the stress status of the body. Meanwhile, the method has simple and convenient operation, short assembly period and low cost, and overcomes the defects of long period and high cost of the prior assembly method by finishing the pad.

Description

technical field [0001] The invention belongs to the technical field of precise assembly of body structure of space optical precision instruments, in particular to a method for assembling body structure of space remote sensing camera. Background technique [0002] The fuselage structure is a key component of a space remote sensing camera. The main function is to accurately ensure the relative position of each optical element, form an optical imaging system, and withstand the impact of the outside world. Therefore, the fuselage structure requires good structural rigidity and structural stability, which not only requires sufficient guarantees in the design, but also has a good implementation method in the assembly process. [0003] The assembly effect depends on the level of assembly accuracy and the size of assembly stress. Due to errors in measurement, processing and assembly, assembly stress will inevitably occur. If the assembly stress is large, the fuselage will undergo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C11/02
Inventor 张凯何欣谭进国
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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