Aircraft structure corner filling glue injection head and glue injection method thereof

Abstract

The invention discloses a glue injection head for angle filling of an aircraft structure. The glue injection head is used for injecting glue to step edges between plates. The first wall surface is used for being laterally attached to the vertical surface of the step edge and forming sliding fit, and the second wall surface is used for being pressed to be attached to the upper plane of the step edge and forming sliding fit; and during glue injection, the first wall surface and the second wall surface can provide sliding support for the glue injection head. Aiming at the special requirements of system support angle filling, the angle filling stability of the aircraft structure is optimized, and the special size requirements of a sealant for angle filling and the structural support are met, so that the sealing performance of the aircraft is ensured, the problems of bubbles and needle holes easily caused by manual angle filling sealing are solved, the assembly efficiency of the aircraft is improved, and the working environment of an operation site is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aviation structure assembly, in particular to an aircraft structure corner filling glue injection head and a glue injection method thereof. Background Art

[0002] There is a large number of structural fillet seals on aircraft. The fillet sealant must overlap the structural support by 1.6mm, and the width of the fillet sealant must be ≥6.4mm. The fillet seal structure is shown in Figure 7 :

[0003] Traditionally, the filling nozzle is used to hold the part to be filled, so that force can be applied during filling to ensure that the injected glue is injected onto the part according to the shape of the nozzle, which cannot meet the filling sealing requirements of the CPS file for general sealing of passenger aircraft. Currently, only manual filling methods can be used: first apply protective tape to the aircraft structure, manually fill the reserved area with sealant, use a scraper to shape the sealant before the sealant solidifies, and finally remove the protective tape. This method wastes sealant, has a long production cycle, low work efficiency, and low glue adjustment quality.

[0004] The existing process method can only use the manual filling method: first stick protective tape on the aircraft structure, manually fill the reserved area with sealant, use a scraper to shape the sealant before the sealant cures, and finally remove the protective tape.

[0005] Disadvantages of existing process methods: This method wastes sealant, manual filling of corners is prone to bubbles, pinholes and other faults, long assembly cycle, low work efficiency and low glue adjustment quality. Summary of the invention

[0006] The purpose of the present invention is to design an aircraft structure filleting tool and method thereof, so as to make the aircraft structure filleting seal stable, achieve gapless assembly, reduce product failure rate, improve aircraft performance, improve the working environment at the operation site, solve the problems of bubbles and pinholes in filleting, and improve the assembly accuracy of aircraft products.

[0007] The technical solution of the present invention is:

[0008] Provided is a glue injection head for filling corners of an aircraft structure, the glue injection head is used for injecting glue on step edges between panels;

[0009] The front end of the glue injection head is a plane, and the plane is provided with a glue injection port, and the opening contour of the glue injection port is an irregular contour, and the irregular contour includes a long straight line L2, an inner fold line L1 and an arc line L3;

[0010] The long straight line L2, the inner fold line L1 and the arc line L3 are connected end to end in sequence to form the irregular contour;

[0011] The outer side wall of the injection port corresponding to the inner fold line L1 forms a right-angled indentation of the same shape, and the right-angled indentation continues from the injection port corresponding to the inner fold line L1 to form two mutually perpendicular wall surfaces, namely the first wall surface and the second wall surface; the inner fold line L1 is composed of two mutually perpendicular short straight lines, the first short straight line connects the long straight line L2 and corresponds to the first wall surface, and the second short straight line connects the arc line L3 and corresponds to the second wall surface;

[0012] The first wall surface is used to laterally abut against the vertical surface of the step edge and form a sliding fit, and the second wall surface is used to press against the upper plane of the step edge and form a sliding fit; when injecting glue, the first wall surface and the second wall surface can provide sliding support for the injection head.

[0013] Furthermore, the length of the long straight line L2 is greater than the length of the second short straight line.

[0014] Furthermore, the aircraft structure corner filling glue injection head is a stepped cylinder structure.

[0015] Furthermore, the length of the second short straight line is at least 1.6 mm.

[0016] Furthermore, the length of the long straight line L2 is at least 6.4 mm.

[0017] Furthermore, the length of the first short straight line is greater than 6.4 mm.

[0018] Furthermore, the first wall surface is parallel to or forms an acute angle with the axis of the glue injection head.

[0019] Furthermore, the second wall surface is parallel to or forms an acute angle with the axis of the glue injection head.

[0020] A method for injecting glue using the above-mentioned aircraft structure corner filling glue injection head is provided, wherein the first wall surface of the aircraft structure corner filling glue injection head is abutted against the vertical surface of the step edge, and the second wall surface is used to press against the upper plane of the step edge; while injecting glue, the aircraft structure corner filling glue injection head is slid along the step edge.

[0021] The advantages of the present invention are as follows: the present invention optimizes the stability of the fillet of the aircraft structure in view of the special requirements of the fillet of the system bracket, and achieves the special size requirements of the fillet sealant with the structural bracket (for example, a special requirement of 1.6mm overlap and a width of the fillet sealant ≥6.4mm), thereby ensuring the sealing of the aircraft, solving the problems of bubbles and pinholes that are easy to occur in manual fillet sealing, improving the efficiency of aircraft assembly, and improving the working environment at the operation site. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a structural schematic diagram of the present invention;

[0023] Figure 2 It is a schematic diagram of the use of the present invention;

[0024] Figure 3 It is a partial enlarged schematic diagram of the present invention in use;

[0025] Figure 4 It is a screenshot of the principle of the present invention in use;

[0026] Figure 5 It is a schematic diagram of the glue injection port of the present invention;

[0027] Figure 6 is a side view of the present invention;

[0028] Figure 7 It is a display diagram after glue injection of the present invention. DETAILED DESCRIPTION

[0029] The disclosed examples will be more fully described with reference to the accompanying drawings, in which some (but not all) of the disclosed examples are shown. In fact, many different examples may be described and these examples should not be construed as limited to the examples set forth herein. Instead, these examples are described so that this disclosure will be thorough and complete and will fully convey the scope of the disclosure to those skilled in the art.

[0030] Provided is a glue injection head for filling corners of an aircraft structure, the glue injection head is used for injecting glue on step edges between panels;

[0031] The front end of the glue injection head is a plane, and the plane is provided with a glue injection port, and the opening contour of the glue injection port is an irregular contour, and the irregular contour includes a long straight line L2, an inner fold line L1 and an arc line L3;

[0032] The long straight line L2, the inner fold line L1 and the arc line L3 are connected end to end in sequence to form the irregular contour;

[0033] The outer side wall of the injection port corresponding to the inner fold line L1 forms a right-angled indentation of the same shape, and the right-angled indentation continues from the injection port corresponding to the inner fold line L1 to form two mutually perpendicular wall surfaces, namely the first wall surface and the second wall surface; the inner fold line L1 is composed of two mutually perpendicular short straight lines, the first short straight line connects the long straight line L2 and corresponds to the first wall surface, and the second short straight line connects the arc line L3 and corresponds to the second wall surface;

[0034] The first wall surface is used to laterally abut against the vertical surface of the step edge and form a sliding fit, and the second wall surface is used to press against the upper plane of the step edge and form a sliding fit; when injecting glue, the first wall surface and the second wall surface can provide sliding support for the injection head.

[0035] Furthermore, the length of the long straight line L2 is greater than the length of the second short straight line.

[0036] The aircraft structure corner filling glue injection head is a stepped cylinder structure.

[0037] The length of the second short straight line is 1.6 mm.

[0038] The length of the long straight line L2 is at least 6.4 mm.

[0039] The length of the first short straight line is greater than 6.4 mm.

[0040] The first wall surface is parallel to or forms an acute angle with the axis of the glue injection head.

[0041] The second wall surface is parallel to or forms an acute angle with the axis of the glue injection head.

[0042] A method for injecting glue using the above-mentioned aircraft structure corner filling glue injection head is provided, wherein the first wall surface of the aircraft structure corner filling glue injection head is abutted against the vertical surface of the step edge, and the second wall surface is used to press against the upper plane of the step edge; while injecting glue, the aircraft structure corner filling glue injection head is slid along the step edge.

[0043] The description of different advantageous arrangements has been presented for purposes of illustration and description, but the description is not intended to be exclusive or limited to examples of the disclosed form. Many modifications and variations will be apparent to those of ordinary skill in the art. Additionally, different advantageous examples may describe different advantages over other advantageous examples. The selected example or examples are chosen and described in order to best illustrate the principles of the examples, the practical application, and to enable those of ordinary skill in the art to understand the disclosure with various examples with various modifications suitable for the particular use contemplated.

Claims

1. A glue injection head for filling corners of aircraft structures, the glue injection head is used to inject glue on the step edges between panels; it is characterized by: The front end of the glue injection head is a plane, and the plane is provided with a glue injection port, and the opening contour of the glue injection port is an irregular contour, and the irregular contour includes a long straight line L2, an inner fold line L1 and an arc line L3; The long straight line L2, the inner fold line L1 and the arc line L3 are connected end to end in sequence to form the irregular contour; The outer side wall of the injection port corresponding to the inner fold line L1 forms a right-angled indentation of the same shape, and the right-angled indentation continues from the injection port corresponding to the inner fold line L1 to form two mutually perpendicular wall surfaces, namely the first wall surface and the second wall surface; the inner fold line L1 is composed of two mutually perpendicular short straight lines, the first short straight line connects the long straight line L2 and corresponds to the first wall surface, and the second short straight line connects the arc line L3 and corresponds to the second wall surface; The first wall surface is used to laterally abut against the vertical surface of the step edge and form a sliding fit, and the second wall surface is used to press against the upper plane of the step edge and form a sliding fit; when injecting glue, the first wall surface and the second wall surface can provide sliding support for the injection head.

2. The aircraft structure fillet glue injection head according to claim 1, characterized in that: The length of the long straight line L2 is greater than the length of the second short straight line.

3. The aircraft structure fillet glue injection head according to claim 1, characterized in that: The aircraft structure corner filling glue injection head is a stepped cylinder structure.

4. The aircraft structure fillet glue injection head according to claim 1, characterized in that: The length of the second short straight line is at least 1.6 mm.

5. The aircraft structure fillet glue injection head according to claim 1, characterized in that: The length of the long straight line L2 is at least 6.4 mm.

6. The aircraft structure fillet glue injection head according to claim 1, characterized in that: The length of the first short straight line is greater than 6.4 mm.

7. The aircraft structure fillet glue injection head according to claim 1, characterized in that: The first wall surface is parallel to or forms an acute angle with the axis of the glue injection head.

8. The aircraft structure fillet glue injection head according to claim 1, characterized in that: The second wall surface is parallel to or forms an acute angle with the axis of the glue injection head.

9. A method for injecting glue using the aircraft structure corner filling glue injection head described in any one of claims 1 to 7, wherein the first wall surface of the aircraft structure corner filling glue injection head is abutted against the vertical surface of the step edge, and the second wall surface is used to press against the upper plane of the step edge; while injecting glue, the aircraft structure corner filling glue injection head is slid along the step edge.

Images