Electric control box structure for space vehicle and assembly method thereof

A technology for electric control boxes and spacecraft, which is applied in the direction of support structure installation, clamping/extracting devices, etc., can solve the problems of complex structure of electric control boxes for spacecraft, and achieve the goals of avoiding insufficient structural space, compact structure, and improving utilization rate Effect

Pending Publication Date: 2018-11-27
INST OF HIGH ENERGY PHYSICS CHINESE ACADEMY OF SCI
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  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to address the deficiencies in the above-mentioned technologies, and propose a structure of an electric control box for a spacecraft and an assembly method thereof, aiming at solving the problem that the existing structure of an electric control box for a spacecraft is complicated

Method used

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  • Electric control box structure for space vehicle and assembly method thereof
  • Electric control box structure for space vehicle and assembly method thereof

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Embodiment Construction

[0025] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0026] Figure 1 to figure 2 As shown, the present invention provides an electric control box structure for a spacecraft, including a base and a cage; the cage includes an upper cage 3 and a lower cage 2; the base includes a bottom plate 1 and a side plate; the side plate includes a front Side plate 5, back side plate, left side plate 4 and right side plate; Front side plate 5, back side plate, left side plate 4 and right side plate are fixedly connected by assembly screw 12; And front side plate, back side plate, The left side plate and the right side plate are fixedly connected to the bottom plate 1 by screws, and are located around the bottom plate to form an assembled structure; electronic ...

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Abstract

The invention provides an electric control box structure for a space vehicle and an assembly method thereof. The structure comprises a base and a steamer machine case, wherein the steamer machine casecomprises an upper layer steamer machine case and lower layer steamer machine case; the base comprises a bottom plate and a side plate; the side plate is arranged around the bottom plate so as to form a splicing structure; an electronic element and PCBs are arranged in the splicing structure; a horizontal framework structure is arranged inside the splicing structure; the horizontal framework structure is used for installing the electronic device and the PCBs; the lower layer steamer machine case is arranged on the splicing structure in the horizontal direction; the upper layer steamer machinecase is arranged on the lower layer steamer machine case in the horizontal direction; the PCBs are respectively arranged in the lower layer steamer machine case and the upper layer steamer machine case. By using the scheme, the space utilization rate of the existing electric control box installation and design structure can be improved, so that the problem of space waste inside the machine case is solved. By using the technical scheme provided by the invention, the structure is compact and reasonable; the assembly and the dismounting are convenient; the shielding performance is good; the costis relatively low.

Description

technical field [0001] The invention belongs to the technical field of structure and assembly of an electric control box for a spacecraft, and in particular relates to a structure and an assembly method for an electric control box for a spacecraft. Background technique [0002] The lightweight design requirements of the existing spacecraft electric control box for spacecraft are getting higher and higher, which makes the internal space design requirements high or the internal space utilization rate is low; and the spacecraft electric control box needs to undergo strict mechanical environment simulation tests. The structural rigidity design of the electrical control box for aircraft has high requirements, especially the rigidity of the PCB installation structure inside the electrical control box. If the structural stiffness design of the electrical control box for spacecraft is insufficient, it will seriously damage the use of electronic components. In severe cases, the compon...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H05K7/14
CPCH05K7/1412
Inventor 杨生曹学蕾孟斌刘晓静杨家卫
Owner INST OF HIGH ENERGY PHYSICS CHINESE ACADEMY OF SCI
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