Aircraft built-in engine installation structure and its moving assembly method

Abstract

The invention discloses a mounting structure for an aircraft built-in type engine and a shifting assembly method for the mounting structure. The mounting structure comprises a protective cover and an engine which is fixedly mounted in an inner cavity of the protective cover; an end surface mounting frame is arranged on the front part of the protective cover; an end surface connecting frame is arranged on the head of the engine; the two end surface connecting frames are connected in a tightly-fit mode through a first bolt assembly, so that the head of the engine is fixedly arranged in a front inner cavity of the protective cover; and a shaft section supporting frame is arranged on the rear part of the protective cover, the tail part of the engine is seated on the shaft section supporting frame, and a fastening hoop is arranged above the shaft section supporting frame, so that the tail part of the engine is tightly hooped in a rear inner cavity of the protective cover. The invention further provides a shifting assembly method for the mounting structure for the aircraft built-in type engine. According to the practice, the mounting structure is simple in structure, is convenient to operate and is high in reliability; and the shifting assembly method for the mounting structure can effectively realize quick, precise and stable assembly, under common facility conditions, of the aircraft built-in type engine.

Description

technical field [0001] The invention relates to the technical field of link design and rapid assembly of an aircraft built-in power system, in particular to an aircraft built-in engine installation structure and a step-by-step assembly method thereof. Background technique [0002] At present, the existing aircraft built-in engine installation structure usually adopts the following two methods: one is an open installation structure, that is, a relevant window is reserved on the aircraft shell, and the engine enters / exits the internal space of the aircraft through the window. After installation, the window is closed with a cover plate. Although the installation steps of this method are relatively simple, the error of the aerodynamic shape of the closed window is relatively large, and the gap between the window and the cover plate is difficult to fill, especially in a high-speed flight environment, which may easily lead to damage to the aircraft shell. The other is a closed ve...

AI Technical Summary

Problems solved by technology

Although this method can guarantee the shape and protective performance of the aircraft shell, its vertical hoisting involves complex conversion of product stations, and must rely on the guarantee of large facilities

It can be seen that the above two methods cannot meet the requirements of coordination and unity in terms of the convenience, safety, speed, and accuracy of the installation of aircraft built-in engines.

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