Fixed covering cap structure capable of adjusting outer edge step difference of airplane and mounting method of fixed covering cap structure

Abstract

The invention belongs to the technical field of aviation structure design, and particularly relates to a fixed covering cap structure with an adjustable outer edge step difference for an airplane and a mounting method thereof. The structure comprises a covering cap skin; the first covering cap supporting plate is provided with a turned-over edge, the first covering cap supporting plate is connected with an on-machine fixing structure through the turned-over edge, and a first mounting hole is formed in the first covering cap supporting plate; a flange is arranged on the second covering cap supporting plate, the second covering cap supporting plate is connected with an on-machine fixing structure through the flange, a second mounting hole is formed in the second covering cap supporting plate, and the second mounting hole is an oblong hole; one end of the main connecting angle sheet is connected with the covering cap skin, and the other end is connected with a second mounting hole of the second covering cap supporting plate; one end of the auxiliary connecting angle sheet is connected with the covering cap skin, and the other end is connected with the first mounting hole of the first covering cap supporting plate. The pneumatic outer edge tolerance requirements of gaps, step differences and the like between the covering cap and the peripheral structure can be met through rapid adjustment in the fixed covering cap installation process.

Description

Technical Field

[0001] The present application belongs to the technical field of aviation structure design, and in particular relates to a fixed cover structure with adjustable outer edge step difference for an aircraft and an installation method thereof. Background Art

[0002] Due to maintenance requirements or aerodynamic shape continuity requirements, there are many fixed covers on the aircraft. It is difficult to adjust the tolerance between these fixed covers and the outer edges of the surrounding structures.

[0003] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0004] The purpose of the present application is to provide a fixed cover structure with adjustable outer edge step difference for an aircraft and an installation method thereof, so as to solve at least one problem existing in the prior art.

[0005] The technical solution of this application is:

[0006] The first aspect of the present application provides a fixed cover structure with adjustable outer edge step difference for an aircraft, comprising:

[0007] Mouth cover skin;

[0008] A first cover support plate, wherein a flange is provided on the first cover support plate, the first cover support plate is connected to the fixed structure on the machine through the flange, and a first mounting hole is opened on the first cover support plate;

[0009] A second cover support plate, wherein a flange is provided on the second cover support plate, the second cover support plate is connected to the fixed structure on the machine through the flange, and a second mounting hole is opened on the second cover support plate, and the second mounting hole is an oblong hole;

[0010] A main connecting angle piece, one end of which is connected to the mouth cover skin, and the other end of which is connected to the second mounting hole of the second mouth cover support plate;

[0011] An auxiliary connecting angle piece, one end of which is connected to the aperture cover skin, and the other end of which is connected to the first mounting hole of the first aperture cover support plate.

[0012] In at least one embodiment of the present application, the flap skin is rectangular.

[0013] In at least one embodiment of the present application, the first cover support plates include two.

[0014] In at least one embodiment of the present application, the flange on the first cover support plate is a non-flat structure with a predetermined curvature.

[0015] In at least one embodiment of the present application, the flange on the first cover support plate is connected to the on-machine fixing structure through multiple sets of bolts, nuts and gaskets.

[0016] In at least one embodiment of the present application, the second flap support plate includes one, and the second flap support plate is located between the two first flap support plates.

[0017] In at least one embodiment of the present application, the flange on the second cover support plate is a non-flat structure with a predetermined curvature.

[0018] In at least one embodiment of the present application, the flange on the second cover support plate is connected to the on-machine fixing structure through multiple sets of bolts, nuts and gaskets.

[0019] In at least one embodiment of the present application, the major axis direction of the oblong hole on the second aperture cover support plate is perpendicular to the aperture cover skin.

[0020] In at least one embodiment of the present application, the cross-sections of the main connecting angle piece and the auxiliary connecting angle piece are L-shaped.

[0021] In at least one embodiment of the present application, the main connecting angle piece and the mouth cover skin are connected by a plurality of blind rivets.

[0022] In at least one embodiment of the present application, the main connecting angle piece and the second cover support plate are connected by multiple sets of bolts, nuts and gaskets.

[0023] In at least one embodiment of the present application, the auxiliary connecting angle piece is connected to the mouth cover skin by a plurality of blind rivets.

[0024] In at least one embodiment of the present application, the auxiliary connecting angle piece and the first cover support plate are connected by multiple sets of bolts, nuts and gaskets.

[0025] A second aspect of the present application provides a method for installing a fixed port cover structure with an adjustable outer edge step difference of an aircraft, based on the fixed port cover structure with an adjustable outer edge step difference of an aircraft as described above, comprising:

[0026] Step 1: Connect the flanges on the first cover support plate and the second cover support plate to the fixed structure on the machine;

[0027] Step 2: Connect the main connecting angle piece and the auxiliary connecting angle piece to the cover skin respectively by means of blind rivets;

[0028] Step 3: pre-connect the second cover support plate and the main connection angle piece with bolts, nuts and gaskets, and do not tighten the nuts; adjust the step difference between the cover skin and the surrounding structure by moving the cover skin up and down until the step difference meets the requirements;

[0029] Step 4: Tighten the nuts between the second cover support plate and the main connecting angle piece to fix the cover skin;

[0030] Step 5: Drill holes in the first cover support plate and the auxiliary connecting angle piece, and connect them with bolts, nuts and gaskets.

[0031] The invention has at least the following beneficial technical effects:

[0032] The fixed cover structure with adjustable outer edge step of the aircraft in the present application has strong applicability and can meet the aerodynamic outer edge tolerance requirements such as the gap and step between the cover and the surrounding structure through rapid adjustment during the installation of the fixed cover. At the same time, it can also effectively reduce the assembly stress generated during the installation process. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a perspective schematic diagram of a fixed cover structure with adjustable outer edge step difference for an aircraft according to an embodiment of the present application;

[0034] Figure 2 This is a schematic diagram from another perspective of a fixed cover structure with an adjustable outer edge step difference for an aircraft according to an embodiment of the present application.

[0035] in:

[0036] 1- flap skin; 2- first flap support plate; 3- second flap support plate; 4- main connecting angle piece; 5- auxiliary connecting angle piece. DETAILED DESCRIPTION

[0037] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0038] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0039] The following is combined with Figure 1 to Figure 2 This application is described in further detail.

[0040] A first aspect of the present application provides a fixed flap structure with an adjustable outer edge step difference for an aircraft, comprising: a flap skin 1, a first flap support plate 2, a second flap support plate 3, a main connecting angle piece 4 and an auxiliary connecting angle piece 5.

[0041] like Figure 1-2 As shown, the first cover support plate 2 is provided with a flange, the first cover support plate 2 is connected to the fixed structure on the machine through the flange, and a plurality of first mounting holes are provided on the first cover support plate 2; the second cover support plate 3 is provided with a flange, the second cover support plate 3 is connected to the fixed structure on the machine through the flange, and a plurality of second mounting holes are provided on the second cover support plate 3, and the second mounting holes are oblong holes; one end of the main connecting angle piece 4 is connected to the cover skin 1, and the other end is connected to the second mounting hole of the second cover support plate 3; one end of the auxiliary connecting angle piece 5 is connected to the cover skin 1, and the other end is connected to the first mounting hole of the first cover support plate 2.

[0042] In the preferred embodiment of the present application, the flap skin 1 may adopt a rectangular structure. It is understandable that the specific structural form of the flap skin 1 may be determined according to the installation requirements of the actual installation position on the aircraft, such as round, square, etc.

[0043] In a preferred embodiment of the present application, the number and layout of the first flap support plates 2 and the second flap support plates 3 are arranged according to the structural form and size of the flap skin 1 .

[0044] In one embodiment of the present application, the first cover support plate 2 may include two; the flange on the first cover support plate 2 is a non-flat structure with a predetermined curvature; the flange on the first cover support plate 2 is connected to the on-machine fixed structure through multiple sets of bolts, nuts and gaskets.

[0045] In one embodiment of the present application, the second cover support plate 3 includes one, and the second cover support plate 3 is located between the two first cover support plates 2; the flange on the second cover support plate 3 is a non-flat structure with a predetermined curvature; the flange on the second cover support plate 3 is connected to the fixed structure on the machine through multiple sets of bolts, nuts and gaskets. In this embodiment, it is preferred that the long axis direction of the oblong hole on the second cover support plate 3 is perpendicular to the cover skin 1.

[0046] In the aircraft fixed cover structure with adjustable outer edge step difference of the present application, the main connecting angle piece 4 and the auxiliary connecting angle piece 5 are L-shaped angle materials, and their cross sections are L-shaped. Among them, the main connecting angle piece 4 is connected to the cover skin 1 by multiple blind rivets; the main connecting angle piece 4 is connected to the second cover support plate 3 by multiple sets of bolts, nuts and gaskets. The auxiliary connecting angle piece 5 is connected to the cover skin 1 by multiple blind rivets; the auxiliary connecting angle piece 5 is connected to the first cover support plate 2 by multiple sets of bolts, nuts and gaskets.

[0047] The fixed flap structure of the aircraft with adjustable outer edge step difference of the present application provides a specific structural form, which is composed of a flap skin 1, three flap support plates, and three connecting angle pieces. The first flap support plate 2 and the second flap support plate 3 have flanges, which are connected to the fixed structure on the aircraft near the flap through the flanges. The flap skin 1 is connected to the first flap support plate 2 through an auxiliary connecting angle piece 5, and the flap skin 1 is connected to the second flap support plate 3 through a main connecting angle piece 4.

[0048] Based on the above-mentioned fixed port cover structure with adjustable outer edge step difference of an aircraft, a second aspect of the present application provides a method for installing the fixed port cover structure with adjustable outer edge step difference of an aircraft, comprising the following process:

[0049] Step 1, connecting the flanges on the first cover support plate 2 and the second cover support plate 3 to the fixed structure on the machine;

[0050] Step 2, respectively connect the main connecting angle piece 4 and the auxiliary connecting angle piece 5 to the cover skin 1 by means of blind rivets;

[0051] Step 3: pre-connect the second cover support plate 3 and the main connection angle plate 4 by bolts, nuts and gaskets, and do not tighten the nuts; adjust the step difference between the cover skin 1 and the surrounding structure by moving the cover skin 1 up and down until the step difference meets the requirements;

[0052] Step 4, tighten the nuts between the second cover support plate 3 and the main connecting angle piece 4 to fix the cover skin 1;

[0053] Step 5: Drill holes in the first cover support plate 2 and the auxiliary connecting angle plate 5 by means of a drill, and connect them by means of bolts, nuts and gaskets.

[0054] The present application discloses a method for installing a fixed flap structure with an adjustable outer edge step difference for an aircraft. During the installation process, the flap support plate is first connected to the fixed structure on the aircraft. Then, the flap skin is adjusted in a direction perpendicular to the surface through the oblong hole on the middle flap support plate. After adjusting the gap between the flap skin and the surrounding structure, the other two connecting angle pieces are installed and fixed by drilling and punching.

[0055] The fixed cover structure with adjustable outer edge step difference of the aircraft and the installation method thereof of the present application have strong applicability and can meet the aerodynamic outer edge tolerance requirements such as the gap and step difference between the cover and the surrounding structure through rapid adjustment during the installation of the fixed cover, while also effectively reducing the assembly stress generated during the installation process.

[0056] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A fixed cover structure with adjustable outer edge step difference for an aircraft, characterized in that: include: Mouth cover skin (1); A first cover support plate (2), the first cover support plate (2) being provided with a flange, the first cover support plate (2) being connected to an on-machine fixed structure via the flange, and the first cover support plate (2) being provided with a first mounting hole; A second cover support plate (3), the second cover support plate (3) being provided with a flange, the second cover support plate (3) being connected to the fixed structure on the machine via the flange, the second cover support plate (3) being provided with a second mounting hole, the second mounting hole being an oblong hole; A main connecting angle piece (4), one end of the main connecting angle piece (4) is connected to the mouth cover skin (1), and the other end is connected to the second mounting hole of the second mouth cover support plate (3); An auxiliary connecting corner piece (5), one end of the auxiliary connecting corner piece (5) is connected to the mouth cover skin (1), and the other end is connected to the first mounting hole of the first mouth cover support plate (2).

2. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 1, characterized in that: The mouth cover skin (1) is rectangular.

3. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 1, characterized in that: The first cover support plates (2) include two.

4. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 3, characterized in that: The flange on the first cover support plate (2) is a non-flat structure and has a predetermined curvature.

5. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 4, characterized in that: The flange on the first cover support plate (2) is connected to the fixed structure on the machine through multiple sets of bolts, nuts and gaskets.

6. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 5, characterized in that: The second cover support plate (3) comprises one, and the second cover support plate (3) is located between the two first cover support plates (2).

7. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 6, characterized in that: The flange on the second cover support plate (3) is a non-flat structure and has a predetermined curvature.

8. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 7, characterized in that: The flange on the second cover support plate (3) is connected to the fixed structure on the machine via multiple sets of bolts, nuts and gaskets.

9. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 8, characterized in that: The long axis direction of the oblong hole on the second mouth cover support plate (3) is perpendicular to the mouth cover skin (1).

10. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 1, characterized in that: The cross sections of the main connecting angle piece (4) and the auxiliary connecting angle piece (5) are L-shaped.

11. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 10, characterized in that: The main connecting angle piece (4) and the mouth cover skin (1) are connected via a plurality of blind rivets.

12. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 11, characterized in that: The main connecting angle piece (4) and the second cover support plate (3) are connected via multiple sets of bolts, nuts and gaskets.

13. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 12, characterized in that: The auxiliary connecting angle piece (5) is connected to the mouth cover skin (1) via a plurality of blind rivets.

14. The fixed cover structure with adjustable outer edge step of an aircraft according to claim 13, characterized in that: The auxiliary connection angle piece (5) is connected to the first cover support plate (2) via multiple sets of bolts, nuts and washers.

15. A method for installing a fixed port cover structure with an adjustable outer edge step difference of an aircraft, based on the fixed port cover structure with an adjustable outer edge step difference of an aircraft according to any one of claims 1 to 14, characterized in that: include: Step 1, connecting the flanges on the first cover support plate (2) and the second cover support plate (3) to the fixed structure on the machine; Step 2, connecting the main connecting angle piece (4) and the auxiliary connecting angle piece (5) to the mouth cover skin (1) respectively by means of blind rivets; Step 3: pre-connect the second cover support plate (3) and the main connection angle plate (4) by means of bolts, nuts and washers, and do not tighten the nuts; adjust the step difference between the cover skin (1) and the surrounding structure by moving the cover skin (1) up and down until the step difference meets the requirement; Step 4, tighten the nuts between the second cover support plate (3) and the main connecting angle piece (4) to fix the cover skin (1); Step 5: Drill holes in the first cover support plate (2) and the auxiliary connecting angle plate (5) by means of a drill, and connect them by means of bolts, nuts and gaskets.

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