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Slidable connecting structure

A technology of sliding connection and connection structure, which is applied in the direction of aircraft power plant, aircraft power plant components, pipes/pipe joints/pipe fittings, etc. It can solve problems such as thermal deformation mismatch, achieve reliable performance, simple form, and good application prospects Effect

Active Publication Date: 2019-01-04
BEIJING AEROSPACE TECH INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The invention provides a slidable connection structure, which can solve the technical problem of thermal deformation mismatch existing in the connection between the cabin body and the fairing in the prior art

Method used

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Embodiment Construction

[0023] 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 following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0024] It should be noted that the terminology used here is only for describing specific implementations, and is not intended to limit t...

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Abstract

The invention provides a slidable connecting structure which comprises a cabin, a rectifying cover and a plurality of connecting assemblies at intervals for slidable connection of the cabin and the rectifying cover. The body structure of the rectifying cover is approximately in a U shape. The upper edges of the two side walls of the U shape are both turned outwards. The turned edges are used for being connected with the cabin. Each connecting assembly comprises a thermal cushion, a thermal pressing strip and a plurality of connecting pieces, wherein the thermal cushion is arranged on the sideface, facing the cabin, of the corresponding turned edge, the thermal pressing strip is arranged on the side face, away from the cabin, of the corresponding turned edge, and the thermal cushion, the corresponding turned edge and the thermal pressing strip form a sandwich structure. Each connecting piece is used for pressing the corresponding sandwich structure to the cabin. In the connecting structure, the turned edges are slidable relative to the thermal cushions and the thermal pressing strips. The slidable connecting structure can solve the technical problem that thermal deformation is notmatched due to the connection of a cabin and a rectifying cover in the prior art.

Description

technical field [0001] The invention relates to a slidable connection structure, in particular to a slidable connection structure between cold and hot structural parts, especially suitable for the connection between a brittle material hot structure and a cold structural part. Background technique [0002] Hypersonic vehicles fly in the atmosphere at high speed for a long time, and the surface appears continuous high temperature during the flight. The fairing is a three-dimensional part outside the main body of the engine. It uses C / SiC material to withstand the high temperature of the cover. The cabin adopts the form of external heat protection and internal load-bearing. There is a thermal deformation mismatch between the cover and the cabin due to temperature differences. In addition, there are connection interfaces between the fairing, the engine nozzle, and the cabin. Due to the relative deformation of the engine nozzle and the cabin during flight, there is relative mech...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/00B64D29/06F16B1/02F16L59/02
CPCB64C1/00B64D29/06F16B1/02F16L59/028F16L59/029
Inventor 林旭斌袁豪杰陈雄斌宋锋李晶宋月娥
Owner BEIJING AEROSPACE TECH INST
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