Auxiliary airplane engine installing system

An aircraft engine and installation system technology, which is applied to aircraft parts, assembly machines, transportation and packaging, etc., can solve problems such as mutual friction and extrusion, low degree of automation, and no guarantee of safety

Inactive Publication Date: 2015-10-28
大连四达高技术发展有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This type of equipment mainly has the following shortcomings: 1. The attitude adjustment accuracy is low, and the engine and the installation cabin often rub against and squeeze each other during assembly; 2. There are few adjustable attitudes, and multi-axis attitude adjustment cannot be realized; 3. The load b...

Method used

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  • Auxiliary airplane engine installing system
  • Auxiliary airplane engine installing system
  • Auxiliary airplane engine installing system

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Embodiment Construction

[0015] The specific implementation manner of the present invention will be described below with reference to the accompanying drawings. Such as Figure 1 to Figure 5 Shown: an aircraft engine auxiliary installation system, which includes a car body 1, at least two pairs of outrigger assemblies 2 are evenly distributed on the car body 1, and lifting mechanisms 3 are symmetrically arranged at both ends of the car body 1 in the axial direction , the tops of these two sets of lifting mechanisms 3 jointly support the X-axis translation frame 4, X-axis slideways 5 are arranged on both sides of the X-axis translation frame 4, and a Y-axis slideway 5 is slidingly connected to the X-axis slideway 5. Axis translation frame 6, and matching with Y-axis translation frame 6 is provided with motor and ball screw transmission pair, on Y-axis translation frame 6, then is slidably connected with moving frame 8 driven by Y-axis electric push rod 7, in The moving frame 8 is provided with a C-axi...

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Abstract

The invention discloses an auxiliary airplane engine installing system which aims at overcoming the defects in the prior art. For installing operation of an airplane engine, a structure capable of meeting the bearing requirements for the heavy load eccentricity, high torque and high rotational inertia is designed. The adjustment on multi-shaft postures (X-axis and Y-axis movement, Z-axis lifting, A-axis and C-axis rotating and B-axis pitching) of the airplane engine can be achieved; meanwhile, the posture adjusting precision can be guaranteed. The device is commonly used with a control system developed in a matched mode, the track calculation can be carried out, the optimal installing track is established, and even the automatic installing of the airplane engine can be achieved. Thus, the auxiliary airplane engine installing system has multiple advantages as it were, and the auxiliary airplane engine installing system is particularly suitable for being applied and popularized in the field, and has wide market prospects.

Description

technical field [0001] The invention relates to a workpiece auxiliary installation system, in particular to an aircraft engine auxiliary installation system. Background technique [0002] As the core power component of the aircraft, the aircraft engine has the characteristics of complex structure, large volume, high quality, small assembly clearance, etc. It is difficult to load and unload the aircraft engine. When using traditional equipment to load and unload the aircraft engine in real time, it is often impossible to achieve accurate attitude adjustment. The loading and unloading quality of the engine will have an important impact on the dynamic performance of the aircraft. [0003] At present, when assembling aircraft engines, manual mechanical devices or hydraulic mechanisms are often used to adjust the various attitudes of the engines. This type of equipment mainly has the following shortcomings: 1. The attitude adjustment accuracy is low, and the engine and the insta...

Claims

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Application Information

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IPC IPC(8): B23P21/00
CPCB23P21/002B23P2700/01
Inventor 李东栓
Owner 大连四达高技术发展有限公司
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