CN-115806055-B - Aircraft ring type reinforced bulkhead replacement process method

Abstract

A process for replacing the ring-type reinforced bulkhead of airplane includes such steps as preparing internal template, assembling it with original bulkhead, arranging locating reference holes on internal template, decomposing original bulkhead, locating new bulkhead, arranging assembling holes on new bulkhead, and fixing the new bulkhead to airplane body. The invention realizes the conversion of the positioning reference by manufacturing the internal template to position the former bulkhead, avoids the adverse effect on other parts in the process of replacing the bulkhead, and achieves the aims of ensuring the stability of the whole structure of the aircraft and improving the overhaul working quality.

Inventors

• ZHANG JIANZHAO
• LI YUNFENG
• CHENG KE
• ZHU ZIHONG
• LUO WENBING
• REN FEI
• Ning tengfei
• ZHANG HAO
• ZHANG QIANG
• KANG JIANZHONG
• GUO TIECHENG

Assignees

• 中国人民解放军第五七二一工厂

Dates

Publication Date

20260505

Application Date

20221123

Claims (5)

1. 1. The aircraft ring type reinforced bulkhead replacement process method is characterized by comprising the following working steps of: a. Manufacturing an inner template, manufacturing an annular inner template (2) with an inner flanging (2-2) according to the web shape of an original machine bulkhead (1), and forming a notch (2-1) which is penetrated inwards and outwards along the radial direction on the inner template (2); b. assembling the inner template and the original machine bulkhead, assembling the inner template (2) and the original machine bulkhead (1), enabling the inner flange (2-2) structure to be attached to the inner edge flange of the original machine bulkhead through plastic deformation of the notch (2-1) on the inner template (2), and then fixing the inner template (2) and a connecting piece on an airplane body together; c. A positioning reference hole is formed in the inner template, and a positioning reference hole (2-3) is formed in a corresponding position of the inner template (2) by taking an assembly hole (1-1) on the former bulkhead (1) as a reference; d. the original machine bulkhead is decomposed, and the original machine bulkhead (1) is removed from the structure of the aircraft body after being decomposed; e. positioning a new bulkhead, and preassembling the new bulkhead on the inner template (2) in a clamping manner; f. the new bulkhead is provided with an assembly hole, and the position corresponding to the positioning reference hole (2-3) on the inner template (2) is provided with an assembly hole; g. the new bulkhead is fixedly assembled with the aircraft body, the inner template (2) is removed, and the new bulkhead is fixed on the aircraft body of the aircraft through the matching of the assembly holes formed in the new bulkhead and the assembly parts on the aircraft body, so that the bulkhead replacement operation is completed.
2. 2. The aircraft ring type reinforcing bulkhead replacement process according to claim 1, wherein in the step a, the inner template (2) is made of aluminum alloy or other rigid metal alloy materials.
3. 3. The method for replacing and assembling the annular reinforced bulkhead of the aircraft according to claim 2, wherein in the step d, the original bulkhead (1) is decomposed by cutting equipment and an air drill tool, and the stability of the assembling position of the original bulkhead (1) and the aircraft body is maintained.
4. 4. The method for replacing an annular reinforcing bulkhead of an aircraft according to claim 3, wherein in the step e, the relative position of the new bulkhead is adjusted by an inner template (2).
5. 5. The aircraft ring type reinforcing bulkhead replacement process according to claim 4, wherein in the step f, the positioning reference holes (2-3) on the inner template (2) are reversely led to the new bulkhead by a scribing method or a template reverse extension method.

Description

Aircraft ring type reinforced bulkhead replacement process method Technical Field The invention relates to a process method for replacing parts of an aircraft, in particular to a process method for replacing ring-type reinforced bulkhead parts in the process of overhauling the aircraft. Background The aircraft bulkhead is a transverse stress member on the aircraft body, and has the functions of keeping the appearance of the aircraft and supporting the skin so as to be beneficial to bearing local aerodynamic load on the aircraft body. In order to ensure the strength of the bulkhead 1, flanges are arranged at the inner and outer edges of the web plate of the bulkhead, and in addition, the web plate of the bulkhead is also provided with assembly holes 1-1 matched with other parts. After a certain flight time, if the bulkhead is damaged, the bulkhead needs to be replaced integrally when the aircraft is overhauled. In order to avoid adverse effects on other parts in the process of replacing the bulkhead and ensure the stability of the whole structure of the aircraft, an aircraft ring type reinforcing bulkhead replacement process method is required to be optimally designed. Disclosure of Invention The invention provides a process method for replacing an annular reinforced bulkhead of an aircraft, which aims to avoid adverse effects on other parts in the process of replacing the bulkhead, ensure the stability of the whole structure of the aircraft and improve the overhaul working quality. In order to achieve the above purpose, the invention adopts the following technical scheme: An aircraft ring type reinforced bulkhead replacement process method comprises the following working steps: a. manufacturing an inner template, manufacturing an annular inner template with an inner flanging according to the shape of a web plate of an original machine partition frame, and forming a gap which is penetrated inwards and outwards along the radial direction on the inner template; b. Assembling the inner template and the original machine bulkhead, enabling the inner flanging structure to be attached to the inner edge flanging of the original machine bulkhead through plastic deformation of the notch on the inner template, and then fixing the inner template and the connecting piece on the aircraft body together; c. A positioning reference hole is formed in the inner template, and the positioning reference hole is formed in a corresponding position of the inner template by taking the assembly hole on the former bulkhead as a reference; d. The original machine bulkhead is decomposed, and the original machine bulkhead is removed from the structure of the aircraft body after being decomposed; e. Positioning a new bulkhead, and preassembling the new bulkhead on the inner template in a clamping manner; f. the new bulkhead is provided with an assembly hole, and the position corresponding to the positioning reference hole on the inner template is provided with an assembly hole; g. The new bulkhead is fixedly assembled with the aircraft body, the inner template is removed, and the new bulkhead is fixed on the aircraft body through the matching of the assembly holes formed in the new bulkhead and the assembly parts, so that the bulkhead replacement operation is completed. In the above-mentioned aircraft ring type reinforcing bulkhead replacement process, in the step a, the inner template is made of aluminum alloy or other rigid metal alloy materials. In the step d, the original frame spacer is decomposed by adopting cutting equipment and an air drill tool, so that the stability of the assembly position of the original frame spacer and the machine body is maintained. In the above-mentioned aircraft ring type reinforcement bulkhead replacement process method, in the step e, the relative position of the new bulkhead is adjusted by the internal template. In the above-mentioned aircraft ring type reinforcement bulkhead replacement process method, in the step f, the positioning reference hole on the inner template is reversely led to the new bulkhead by a scribing method or a template reverse extension method. The invention provides a process method for replacing an annular reinforced bulkhead of an aircraft, which realizes the conversion of a positioning reference by manufacturing an inner template to position the bulkhead of the original aircraft, avoids the adverse effect on other parts in the process of replacing the bulkhead, and achieves the aims of ensuring the stability of the integral structure of the aircraft and improving the overhaul working quality. Drawings FIG. 1 is a block diagram of an aircraft ring reinforcement bulkhead; FIG. 2 is a schematic view of the cross-sectional structure A-A of FIG. 1; FIG. 3 is a schematic diagram of an internal template structure; FIG. 4 is a schematic view of the cross-sectional structure B-B in FIG. 3; FIG. 5 is a schematic diagram of a positioning reference hole formed in a corresponding position o