Method for machining bolt holes in hanging subassembly of aircraft engine by using numerical control equipment

An aircraft engine and numerical control equipment technology, which is applied in the field of numerical control machining method preparation, can solve the problems of difficult drilling of connecting bolt holes, high labor intensity, low assembly efficiency, etc. The effect of improving the degree of assembly automation

Inactive Publication Date: 2014-05-14
AVIC SAC COMML AIRCRAFT
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Problems solved by technology

These characteristics make it extremely difficult to drill connecting bolt holes during the assembly process. Usually, it takes 20

Method used

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Effect test

Embodiment

[0037] It is applied to the IPS engine suspension of C919 large passenger aircraft.

[0038] The method of the invention is adopted for the engine suspension of the C919 large passenger aircraft, so that the engine duct has better aerodynamic characteristics, can effectively reduce the fuel consumption of the engine, and serves as the biggest bright spot of the C919 aircraft. But also because of this feature, the central box section integrates the engine nacelle anti-thrust slide rail, which makes the box section structure more complex, and the part size is thicker. The average thickness is 25mm, and the local position reaches 45mm. It is difficult to process with traditional assembly methods, and the assembly cycle is long, which cannot meet the delivery needs of customers.

[0039] After adopting this method on the first IPS box section test piece, the cycle of hole making is shortened by half, and the processing quality is stable and reliable.

[0040] This method is also ...

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PUM

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Abstract

The invention belongs to the field of numerical control machining methods, and particularly relates to a method for machining bolt holes in a hanging subassembly of an aircraft engine by using mechanical control equipment. The method comprises the following steps of preassembling the hanging subassembly by using an assembling tool; positioning the hanging subassembly on a special machining supporting clamp; performing measurement and reverse analysis and adjusting numerical control machining programs; positioning the subassembly and the clamp on a machine tool in an integrated manner; automatically forming holes by using the machine tool and examining a machining result; preassembling the hanging subassembly by using a small number of bolts; establishing a measuring benchmark on the product under aircraft axes; positioning the product on the special machining supporting clamp and then examining the appearance error and the location degree of the product; performing reverse modeling and analysis by using CATIA (computer-graphics aided three-dimensional interactive application) software; adjusting a normal tolerance point of a curved surface of the subassembly; correcting a hole-forming machining program; and positioning the whole pre-assembled hanging subassembly by using the benchmark of the special machining clamp on the machine tool as a tool setting benchmark and using the measuring benchmark established on the subassembly as an examination point, and then forming the holes on the subassembly in a machining manner.

Description

technical field [0001] The invention belongs to the field of numerical control machining method preparation, and in particular relates to a method for machining bolt holes of aircraft engine suspension components by using numerical control equipment. Background technique [0002] The main materials of civil aircraft engine suspension are titanium alloy and steel, and the main load-bearing box section is mostly machine-added parts. The thickness of the assembly interlayer is from 20mm to 45mm, and the selected fasteners are mainly from Φ7.94mm to Φ21mm. These characteristics make it extremely difficult to drill connecting bolt holes during the assembly process. Usually, it takes 20 to 40 minutes to drill a hole by hand, resulting in high labor intensity, labor-intensive assembly, and low assembly efficiency. Contents of the invention [0003] In view of the above-mentioned deficiencies in the prior art, the technical problem to be solved by the present invention is to provi...

Claims

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Application Information

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IPC IPC(8): B23B35/00
CPCB23B35/00
Inventor 贾晓亮刘润玲刘振山辛宏光魏志强
Owner AVIC SAC COMML AIRCRAFT
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