A thermal protection device based on aircraft compartment docking

Abstract

The invention discloses a thermal protection device based on aircraft cabin docking. The thermal protection device based on aircraft cabin docking comprises a first cabin shell, a second cabin shell and a lapping cover plate, wherein a first cabin protection layer externally covers the first cabin shell; the second cabin shell is connected with the first cabin shell; a second cabin protection layer connected with the first cabin protection layer externally covers the second cabin shell; and the lapping cover plate is adapted to the interior of a double-edge step-shaped cavity formed by the first cabin protection layer and the second cabin protection layer and abuts against the first cabin shell. According to the thermal protection device based on aircraft cabin docking, as the cabin shells, the cabin protection layer, the cabin protection layer and the lapping cover plate are independently mounted, the lapping cover plate enables the first cabin protection layer and the second cabin protection layer to be independent of each other, and therefore, the first cabin protection layer and the second cabin protection layer are effectively prevented from being affected by sliding at high temperature and high pressure; and through adoption of the step-shaped structure of the lapping cover plate, high speed hot flow is effectively stopped from heating the cabin shells or entering into the cabin.

Description

technical field [0001] The invention relates to the technical field of heat protection for a docking structure of a cabin section of a high-speed aircraft, in particular to a thermal protection device based on a docking section of an aircraft cabin. Background technique [0002] The cabins of the aircraft are generally connected by "U"-shaped frames, "L"-shaped frames, and double "L-shaped" frames. These types of connections occupy a large space in the cabin; after the cabins are docked or connected, a A gap, if the gap is not treated, high-speed heat flow will enter the cabin and affect the work of a single machine in the cabin, especially for aircraft with harsh flying environments, the cabin protection layer, that is, the cabin heat protection layer, will slip or deform, resulting in The butt joint gap gradually becomes larger, and the high-speed heat flow directly heats the metal shell of the cabin, causing the failure of the cabin and affecting the success of the flight...

AI Technical Summary

Problems solved by technology

[0004] For the aircraft flying in the atmosphere at high Mach for a long time, especially the aircraft with a small-diameter cabin, the cabin space is limited, the cabin filling ratio coefficient is high, the design of the radial connection thermal protection structure is difficult, and the design reliability is difficult to guarantee. To ensure the convenience of installation after the cabins are docked, the overlapping structure of the protective layer needs to be installed independently

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