Connecting structure integrating thermal protection with finished component mounting

A connection structure and component technology, applied in the field of aircraft component installation and connection structure, can solve the problems of difficulty in machining process and assembly process, inconvenient repair, and lengthening product development cycle, etc.

Active Publication Date: 2018-02-23
JIANGXI HONGDU AVIATION IND GRP
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AI Technical Summary

Problems solved by technology

But the disadvantage of this heat insulation method is that it is not easy to replace the heat insulation layer after it is pasted or brushed, and it is inconvenient to repair the damage of the heat insulation layer caused by the repeated disassembly and assembly of the component equipment.
[0003] For the small and medium-sized aircraft, the cabin needs internal heat insulation. Because the cabin is equipped with a heat insulation layer and various electronic co

Method used

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  • Connecting structure integrating thermal protection with finished component mounting

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Embodiment Construction

[0017] The connection structure of the present invention will be described in detail below with reference to the drawings and embodiments.

[0018] Such as figure 1 As shown, the connection structure of the integrated heat protection and component installation includes cabin body 1; heat insulation layer 2; hexagonal thin nut 3; heat insulation sealing gasket 4; component equipment 5; threaded bush 6; Bolt 7; heat insulation sealing putty 8. Among them, the cabin body 1 is made with mounting bosses, and the number of bosses arranged in the circumferential direction and the course direction depends on the load and the weight of the finished equipment 5, and the bosses are provided with internal thread holes, and the forming material of the cabin body 1 needs to be similar to titanium. Alloy light-weight high-temperature-resistant materials to meet the requirements of weight loss and high-temperature-resistant environment; the heat insulation layer 2 is an integral plate, and t...

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Abstract

The invention relates to a connecting structure for mounting a finished component of an aircraft and discloses the connecting structure integrating thermal protection with finished component mounting.The connecting structure comprises a cabin (1), a heat-insulating layer (2), a hexagon thin nut (3), a heat-insulating sealing gasket (4), a finished component device (5), a threaded bush (6) and a snap-head bolt (7). The connecting structure is adopted for effectively reducing the complex degree of the cabin structure, increasing the mounting reliability of the heat-insulating layer and repeatedly detaching, replacing and repairing the heat-insulating layer; besides, the connecting structure is designed in a sinking form; the refractory sealant is filled in a sinking area of the structure, so that the heat-insulating effect is obvious, and meanwhile, the connecting structure is suitable for the conical structure of the elastic element and is capable of achieving the effect of reducing aerodynamic resistance, effectively reducing the processing precision of the technology and meeting the requirement of central high-precision mounting of the finished component device along the radial direction of the cabin.

Description

technical field [0001] The invention relates to an aircraft component installation and connection structure, in particular to a connection structure integrating heat collection protection and component installation. Background technique [0002] When the aircraft flies at hypersonic speed, due to shock wave compression, viscous friction and other effects, it will cause strong aerodynamic heating near the wall. In order to ensure that the component equipment inside the aircraft can work normally within the allowable temperature range, effective structural thermal protection design must be carried out. At present, the internal heat insulation of the aircraft is usually brushed, sprayed with silicone heat-insulating sealant on the inner surface of the cabin, or pasted with a sealed heat-insulating plate, so that the heat introduced into the structure is small enough to cause the structure and internal component equipment to be in contact with the air in the cabin. The temperat...

Claims

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Application Information

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IPC IPC(8): B64C1/40
CPCB64C1/403
Inventor 周晓华刘慧慧欧阳金栋梁可人易龙王克强龚仔华陈龙董皓葳张维陈逸云
Owner JIANGXI HONGDU AVIATION IND GRP
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