An aircraft structure corner filling injection head and a method of injecting glue

Abstract

The application discloses an aircraft structure corner filling glue injection head, which is used for injecting glue to the step edge between plate pieces; the first wall surface is used for laterally abutting against the vertical surface of the step edge and forms a sliding fit, and the second wall surface is used for pressing against the upper surface of the step edge and forms a sliding fit; during glue injection, the first wall surface and the second wall surface can provide sliding support for the glue injection head. The application optimizes the aircraft structure corner filling stability according to the special requirements of the system support corner filling, achieves that the sealant for the corner filling meets the special size requirements of the structure support, thereby ensuring the aircraft sealing performance, solves the problems of air bubbles and pinholes which are prone to occurring in the manual corner filling sealing, improves the aircraft assembly efficiency, and improves the operation site working environment.

Description

Technical Field

[0001] This invention relates to the field of aerospace structural assembly technology, specifically to an aircraft structural filler glue injection head and its glue injection method. Background Technology

[0002] A type of structural filler seal is widely used on aircraft. The sealant in the filler must overlap the structural support with a 1.6mm gap, and the width of the filler sealant must be ≥6.4mm. See the example of the filler seal structure. Figure 7 :

[0003] Traditional corner filling involves holding the filler nozzle against the part to be filled, allowing for sufficient force and ensuring the sealant is applied according to the nozzle's shape. However, this method fails to meet the corner sealing requirements of the CPS (Common Sealing Specifications) for passenger aircraft. Currently, only manual corner filling is possible: protective tape is applied to the aircraft structural component, the remaining area is manually filled with sealant, and a scraper is used to reshape the sealant before it cures. Finally, the protective tape is removed. This method wastes sealant, has a long production cycle, low efficiency, and results in poor sealant mixing quality.

[0004] The existing process can only use a manual corner filling method: first, apply protective tape to the aircraft structural parts, then manually fill the left-out areas with sealant, use a scraper to shape the sealant before it cures, and finally remove the protective tape.

[0005] Disadvantages of existing processes: This method wastes sealant, and manual corner filling is prone to defects such as bubbles and pinholes. It also has a long assembly cycle, low work efficiency, and low adhesive mixing quality. Summary of the Invention

[0006] The purpose of this invention is to design an aircraft structure filler tool and method to ensure stable sealing of the aircraft structure filler, achieve gapless assembly, reduce product failure rate, improve aircraft performance, improve the working environment at the operation site, solve the problems of air bubbles and pinholes in the filler, and improve the assembly accuracy of aircraft products.

[0007] The technical solution of this invention is:

[0008] A filler glue injection head for aircraft structures is provided, the glue injection head being used to inject glue into the stepped edges between plates;

[0009] The front end of the dispensing head is a plane, and the plane has a dispensing port. The opening contour of the dispensing port is an irregular contour, which includes a long straight line L2, an inner fold line L1, and an arc L3.

[0010] The long straight line L2, the inner broken line L1 and the arc line L3 are connected end to end to form the irregular contour.

[0011] The outer wall of the glue injection port corresponding to the inner fold line L1 forms a right-angled concave shape. The right-angled concave extends from the glue injection port corresponding to the inner fold line L1 to form two mutually perpendicular walls, namely the first wall and the second wall. The inner fold line L1 is composed of two mutually perpendicular short straight lines. The first short straight line connects to the long straight line L2 and corresponds to the first wall. The second short straight line connects to the arc line L3 and corresponds to the second wall.

[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 surface of the step edge and form a sliding fit; during glue injection, the first wall surface and the second wall surface can provide sliding support for the glue 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 filling head of the aircraft structure 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 at an acute angle to the axis of the dispensing head.

[0019] Furthermore, the second wall surface is parallel to or at an acute angle to the axis of the dispensing head.

[0020] A method for applying adhesive using the aforementioned aircraft structure filler glue head is provided, wherein the first wall surface of the aircraft structure filler glue head is abutted against the vertical surface of the step edge, and the second wall surface is used to press against the upper surface of the step edge; while applying adhesive, the aircraft structure filler glue head is slid along the step edge.

[0021] The advantages of this invention are: This invention optimizes the stability of the corner filling of the aircraft structure in response to the special requirements of the corner filling of the system bracket, so that the sealant of the corner filling must meet the special dimensional requirements of the structural bracket (e.g., an overlap of 1.6mm and a width of ≥6.4mm for the corner filling sealant), thereby ensuring the airtightness of the aircraft, solving the problems of air bubbles and pinholes that are easy to occur in manual corner filling, improving the efficiency of aircraft assembly, and improving the working environment at the operation site. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the structure of the present invention;

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

[0024] Figure 3 This is a partially enlarged schematic diagram of the invention in use;

[0025] Figure 4 This is a screenshot illustrating the principle of the invention in use;

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

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

[0028] Figure 7 This is a diagram showing the effect of adhesive injection after the present invention is applied. Detailed Implementation

[0029] The disclosed examples will be described more fully 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 those set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete, and will fully convey the scope of this disclosure to those skilled in the art.

[0030] A filler glue injection head for aircraft structures is provided, the glue injection head being used to inject glue into the stepped edges between plates;

[0031] The front end of the dispensing head is a plane, and the plane has a dispensing port. The opening contour of the dispensing port is an irregular contour, which includes a long straight line L2, an inner fold line L1, and an arc L3.

[0032] The long straight line L2, the inner broken line L1 and the arc line L3 are connected end to end to form the irregular contour.

[0033] The outer wall of the glue injection port corresponding to the inner fold line L1 forms a right-angled concave shape. The right-angled concave extends from the glue injection port corresponding to the inner fold line L1 to form two mutually perpendicular walls, namely the first wall and the second wall. The inner fold line L1 is composed of two mutually perpendicular short straight lines. The first short straight line connects to the long straight line L2 and corresponds to the first wall. The second short straight line connects to the arc line L3 and corresponds to the second wall.

[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 surface of the step edge and form a sliding fit; during glue injection, the first wall surface and the second wall surface can provide sliding support for the glue 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 filler 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 at an acute angle to the axis of the dispensing head.

[0041] The second wall surface is parallel to or at an acute angle to the axis of the dispensing head.

[0042] A method for applying adhesive using the aforementioned aircraft structure filler glue head is provided, wherein the first wall surface of the aircraft structure filler glue head is abutted against the vertical surface of the step edge, and the second wall surface is used to press against the upper surface of the step edge; while applying adhesive, the aircraft structure filler glue head is slid along the step edge.

[0043] Descriptions of various advantageous arrangements have been shown for illustrative and descriptive purposes, but such descriptions are not intended to be exclusive or limited to the disclosed forms. Many modifications and variations will be apparent to those skilled in the art. Furthermore, different advantageous examples may describe different advantages compared to other advantageous examples. One or more examples have been selected and described in order to best illustrate the principles and practical application of the examples, and to enable those skilled in the art to understand that this disclosure contains various examples with various modifications suitable for the particular intended use.

Claims

1. A filler glue injection head for aircraft structures, the injection head being used for injecting glue onto the stepped edges between plates; characterized in that: The front end of the dispensing head is a plane, and the plane has a dispensing port. The opening contour of the dispensing port is an irregular contour, which includes a long straight line L2, an inner fold line L1, and an arc L3. The long straight line L2, the inner broken line L1 and the arc line L3 are connected end to end to form the irregular contour. The outer wall of the glue injection port corresponding to the inner fold line L1 forms a right-angled concave shape. The right-angled concave extends from the glue injection port corresponding to the inner fold line L1 to form two mutually perpendicular walls, namely the first wall and the second wall. The inner fold line L1 is composed of two mutually perpendicular short straight lines. The first short straight line connects to the long straight line L2 and corresponds to the first wall. The second short straight line connects to the arc line L3 and corresponds to the second wall. 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 surface of the step edge and form a sliding fit; during glue injection, the first wall surface and the second wall surface can provide sliding support for the glue injection head.

2. The aircraft structural filler injection head as described in 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 structural filler injection head as described in claim 1, characterized in that: The aircraft structure filler injection head is a stepped cylinder structure.

4. The aircraft structural filler injection head as described in claim 1, characterized in that: The length of the second short straight line is at least 1.6 mm.

5. The aircraft structural filler injection head as described in claim 1, characterized in that: The length of the long straight line L2 is at least 6.4 mm.

6. The aircraft structural filler injection head as described in claim 1, characterized in that: The length of the first short straight line is greater than 6.4 mm.

7. The aircraft structural filler injection head as described in claim 1, characterized in that: The first wall surface is parallel to or at an acute angle to the axis of the dispensing head.

8. The aircraft structural filler injection head as described in claim 1, characterized in that: The second wall surface is parallel to or at an acute angle to the axis of the dispensing head.

9. A method for applying adhesive using the aircraft structure filler glue applicator according to any one of claims 1-7, wherein the first wall surface of the aircraft structure filler glue applicator is abutted against the vertical surface of the step edge, and the second wall surface is used to press against the upper surface of the step edge; while applying adhesive, the aircraft structure filler glue applicator is slid along the step edge.

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