A connection structure integrating heat collection protection and component installation

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...

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 components, the structure of the cabin is compact and complex, and some component equipment has a great impact on the installation accuracy (along the cabin) The accuracy in the radial direction) has very high requirements. If the installation and fit accuracy requirements are met only through design tolerances, it will bring great difficulty to the machining process and assembly process, lengthen the product development cycle, and increase the development cost.

Images