A method for replacing aircraft ring-type reinforced bulkheads

Abstract

A method for replacing an aircraft ring-type reinforced bulkhead includes the following steps: a) fabricating an inner template; b) assembling the inner template with the original bulkhead; c) creating positioning reference holes on the inner template; d) disassembling the original bulkhead; e) positioning the new bulkhead; f) creating assembly holes on the new bulkhead; and g) fixing the new bulkhead to the fuselage. This invention achieves the conversion of the positioning reference by using an inner template to locate the original bulkhead, avoiding adverse effects on other components during bulkhead replacement, and thus ensuring the stability of the overall aircraft structure and improving the quality of maintenance work.

Description

Technical Field

[0001] This invention relates to a replacement process for aircraft parts, and more particularly to a replacement process for ring-type reinforced bulkhead components suitable for aircraft maintenance. Background Technology

[0002] Aircraft bulkheads are lateral load-bearing components on the fuselage. Their function is to maintain the aircraft's shape, support the skin, and facilitate the fuselage's ability to withstand localized aerodynamic loads. (See attached image) Figure 1 , Figure 2 The aircraft ring-type reinforced bulkhead shown has flanges on both the inner and outer edges of its web to ensure the strength of the bulkhead 1. In addition, its web is provided with assembly holes 1-1 for cooperating with other components.

[0003] If the bulkhead becomes damaged after a certain flight time, it needs to be replaced entirely during aircraft maintenance. To avoid adverse effects on other components during bulkhead replacement and to ensure the overall structural stability of the aircraft, it is necessary to optimize the design of a replacement process for the aircraft's ring-type reinforced bulkhead. Summary of the Invention

[0004] This invention provides a process for replacing aircraft ring-type reinforced bulkheads to avoid adverse effects on other components during the replacement process, thereby ensuring the stability of the overall aircraft structure and improving the quality of maintenance work.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A method for replacing an aircraft ring-type reinforcing bulkhead includes the following steps:

[0007] a. Make an inner template. Make an annular inner template with an inner flange according to the shape of the original machine frame web plate, and make a notch that runs through the inside and outside in the radial direction on the inner template.

[0008] b. Assembly of the inner template with the original aircraft frame: The inner template is assembled with the original aircraft frame. The plastic deformation of the notch on the inner template makes the inner flange structure fit with the inner edge flange of the original aircraft frame. Then the inner template is fixed together with the connecting parts on the aircraft fuselage.

[0009] c. Make positioning reference holes on the inner template, taking the assembly holes on the original machine frame as reference, and make positioning reference holes at the corresponding positions on the inner template.

[0010] d. Disassemble the original aircraft bulkhead and remove it from the aircraft fuselage structure.

[0011] e. Positioning the new partition frame: Pre-install the new partition frame onto the inner template using a snap-fit ​​method;

[0012] f. Make assembly holes on the new partition frame, and make assembly holes at positions corresponding to the positioning reference holes on the inner template.

[0013] g. The new bulkhead is fixed to the fuselage. The inner template is removed, and the new bulkhead is fixed to the aircraft fuselage by matching the assembly holes opened on the new bulkhead with the assembly parts, thus completing the bulkhead replacement operation.

[0014] In the above-mentioned aircraft ring-type reinforced bulkhead replacement process, in step a, the inner template is made of aluminum alloy or other rigid metal alloy materials.

[0015] In the above-mentioned aircraft ring-type reinforced bulkhead replacement process, in step d, cutting equipment and pneumatic drills are used to disassemble the original bulkhead to maintain the stability of the original bulkhead's assembly position with the fuselage.

[0016] In the above-mentioned aircraft ring-type reinforced bulkhead replacement process, in step e, the relative position of the new bulkhead is adjusted by using an inner template.

[0017] In the above-mentioned aircraft ring-type reinforced bulkhead replacement process, in step f, the positioning reference holes on the inner template are reverse-drawn onto the new bulkhead by scribing or template reverse-drawing.

[0018] This invention provides a process for replacing an aircraft ring-shaped reinforced bulkhead. By creating an internal template to locate the original bulkhead position, the positioning reference is converted, avoiding adverse effects on other components during the bulkhead replacement process. This achieves the goal of ensuring the stability of the overall aircraft structure and improving the quality of maintenance work. Attached Figure Description

[0019] Figure 1 This is a diagram of an aircraft ring-type reinforced bulkhead structure;

[0020] Figure 2 yes Figure 1 Schematic diagram of the cross-sectional structure of the middle AA section;

[0021] Figure 3 This is a schematic diagram of the internal template structure;

[0022] Figure 4 yes Figure 3 Schematic diagram of the cross-sectional structure of the middle BB section;

[0023] Figure 5 This is a schematic diagram showing the positioning reference holes opened at the corresponding positions on the inner template, based on the assembly holes on the original machine frame.

[0024] Figure 6 yes Figure 5 Schematic diagram of the CC cross-section structure.

[0025] Explanation of each label in the diagram:

[0026] 1 is the partition frame, and 1-1 is the assembly hole;

[0027] 2 is the inner template, 2-1 is the notch, 2-2 is the inner flange, and 2-3 is the positioning reference hole. Detailed Implementation

[0028] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0029] See Figure 1. Figure 2 A ring-shaped reinforced bulkhead for aircraft is described. To ensure the strength of the bulkhead 1, flanges are provided on both the inner and outer edges of its web. In addition, mounting holes 1-1 are provided on its web for mates with other components. If the bulkhead 1 is damaged after a certain flight time, it needs to be replaced entirely during aircraft maintenance.

[0030] See Figures 1 to 6 To avoid adverse effects on other aircraft components during the replacement of bulkhead 1 and to ensure the overall structural stability of the aircraft, this invention provides a method for replacing an aircraft ring-type reinforced bulkhead, the specific steps of which are as follows:

[0031] a. Make an inner template. Make an annular inner template 2 with an inner flange 2-2 according to the shape of the web of the original machine frame 1. The inner template 2 is preferably made of aluminum alloy or other rigid metal alloy materials, with a certain thickness and width, and a flat surface. A notch 2-1 is opened on the inner template 2 that runs through the inside and outside in the radial direction.

[0032] b. Assemble the inner template with the original aircraft frame. Assemble the inner template 2 with the original aircraft frame 1. The shape of the inner template 2 is finely adjusted by the plastic deformation of the notch 2-1 on the inner template 2, so that the inner flange 2-2 structure of the inner template 2 fits with the inner edge flange of the original aircraft frame. Then, fix the inner template 2 with the connecting parts on the aircraft fuselage.

[0033] c. Make positioning reference holes on the inner template. Taking the assembly hole 1-1 on the original machine frame 1 as the reference, make positioning reference holes 2-3 at the corresponding positions on the inner template 2.

[0034] d. Disassemble the original aircraft bulkhead. After disassembling the original aircraft bulkhead 1 using cutting equipment and pneumatic drills, remove it from the aircraft fuselage structure to maintain the stability of the original aircraft bulkhead 1's assembly position with the fuselage.

[0035] e. Positioning of the new partition frame: The new partition frame is pre-installed on the inner template 2 by snap-fit, and the relative position of the new partition frame is adjusted by the inner template 2 so that the web and inner edge flange of the new partition frame are completely fitted with the web and inner edge flange 2-2 of the inner template 2.

[0036] f. Make assembly holes on the new partition frame. Use the scribing method or template reverse tracing method to reverse trace the positioning reference holes 2-3 on the inner template 2 onto the new partition frame. Then make assembly holes at the positions corresponding to the positioning reference holes 2-3 on the inner template 2.

[0037] g. The new bulkhead is fixedly assembled with the fuselage. The inner template 2 is removed. The new bulkhead is fixed to the fuselage of the aircraft by matching the mounting holes opened on the new bulkhead with the mounting parts on the fuselage, thus completing the bulkhead replacement operation.

Claims

1. A method for replacing an aircraft ring-type reinforcing bulkhead, characterized in that: It includes the following steps: a. Make an inner template. Make an annular inner template (2) with an inner flange (2-2) according to the shape of the web of the original machine frame (1). Make a notch (2-1) that runs through the inner template (2) radially. b. Assemble the inner template with the original frame. Assemble the inner template (2) with the original frame (1). Through the plastic deformation of the notch (2-1) on the inner template (2), make the inner flange (2-2) structure fit with the inner edge flange of the original frame. Then fix the inner template (2) with the connecting parts on the aircraft fuselage. c. Make positioning reference holes on the inner template. Using the assembly hole (1-1) on the original machine frame (1) as the reference, make positioning reference holes (2-3) at the corresponding positions on the inner template (2). d. Disassemble the original aircraft bulkhead and remove it from the aircraft fuselage structure after disassembling the original aircraft bulkhead (1); e. Positioning of the new partition frame: Pre-install the new partition frame on the inner template (2) using a snap-fit ​​method; f. Make assembly holes on the new partition frame, and make assembly holes at the positions corresponding to the positioning reference holes (2-3) on the inner template (2); g. The new bulkhead is fixedly assembled with the fuselage. The inner template (2) is removed. The new bulkhead is fixed to the fuselage of the aircraft by matching the mounting holes opened on the new bulkhead with the mounting parts on the fuselage, thus completing the bulkhead replacement operation.

2. The aircraft ring-type reinforcing bulkhead replacement process method according to claim 1, characterized in that: In step a, the inner template (2) is made of aluminum alloy or other rigid metal alloy materials.

3. The aircraft ring-type reinforcing bulkhead replacement process method according to claim 2, characterized in that: In step d, cutting equipment and pneumatic drills are used to disassemble the original machine frame (1) to maintain the stability of the original machine frame (1) and the machine body assembly position.

4. The aircraft ring-type reinforcing bulkhead replacement process method according to claim 3, characterized in that: In step e, the relative position of the new partition is adjusted by using the inner template (2).

5. The aircraft ring-type reinforcing bulkhead replacement process method according to claim 4, characterized in that: In step f, the positioning reference holes (2-3) on the inner template (2) are reverse-drawn onto the new partition frame by scribing or template reverse-drawing.

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