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

Abstract

The invention discloses an aircraft built-in engine installation structure and a step-by-step assembly method thereof. The installation structure includes a protective cover and an engine fixedly installed in the inner cavity of the protective cover. The front part of the protective cover is provided with an end face mounting frame, and the head of the engine is provided with an end face connection frame. The two are closely connected through the first screw assembly. Connected to fix the head of the engine in the inner cavity of the front of the protective cover; a shaft segment support frame is provided at the rear of the protective cover; the tail of the engine is seated on the shaft segment support frame; a fastening clip is provided above the shaft segment support frame hoop, thereby tightly hooping the rear end of the engine in the rear inner cavity of the guard. The invention also provides a step-by-step assembly method of the aircraft built-in engine installation structure. Practice has proven that this installation structure is simple in structure, easy to operate, and highly reliable. Its step-by-step assembly method can effectively realize the rapid, accurate, and stable assembly of the aircraft's built-in moving engine under general facility conditions.

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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