Aircraft adjustable outer rim step fixed cowl structure and installation method thereof

Abstract

The application belongs to the technical field of aviation structure design, and particularly relates to a fixed cover structure with adjustable outer edge step difference of an airplane and a mounting method thereof. The structure comprises a cover skin, a first cover support plate provided with a flange, the first cover support plate being connected with an on-machine fixed structure through the flange, and the first cover support plate being provided with a first mounting hole; a second cover support plate provided with a flange, the second cover support plate being connected with the on-machine fixed structure through the flange, and the second cover support plate being provided with a second mounting hole, the second mounting hole being an oblong hole; a main connecting angle piece having one end connected with the cover skin and the other end connected with the second mounting hole of the second cover support plate; and an auxiliary connecting angle piece having one end connected with the cover skin and the other end connected with the first mounting hole of the first cover support plate. The application can meet the requirements of the gap between the cover and the surrounding structure and the step difference and other aerodynamic outer edge tolerance requirements by quick adjustment during the mounting process of the fixed cover.

Description

Technical Field

[0001] This application belongs to the field of aerospace structural design technology, and specifically relates to a fixed cover structure with adjustable outer edge step of an aircraft and its installation method. Background Technology

[0002] Due to maintenance requirements or the need for aerodynamic continuity, aircraft have many fixed openings and covers. Adjusting the tolerances of these fixed openings and covers relative to the outer edges of the surrounding structures is difficult.

[0003] Therefore, it is desirable to have a technical solution to overcome or at least mitigate one of the aforementioned defects of the prior art. Summary of the Invention

[0004] The purpose of this application is to provide a fixed cover structure with adjustable outer edge step for aircraft and its installation method, 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 this application provides a fixed hatch structure with adjustable outer edge step for an aircraft, comprising:

[0007] Mouth flap skin;

[0008] A first cover support plate is provided with a flange. The first cover support plate is connected to the machine fixing structure through the flange. A first mounting hole is provided on the first cover support plate.

[0009] The second cover support plate is provided with a flange. The second cover support plate is connected to the fixed structure on the machine through the flange. The second cover support plate is provided with a second mounting hole, which is an oblong hole.

[0010] The main connecting corner piece has one end connected to the cover skin and the other end connected to the second mounting hole of the second cover support plate;

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

[0012] In at least one embodiment of this application, the mouth cover skin is rectangular.

[0013] In at least one embodiment of this application, the first cover support plate comprises two.

[0014] In at least one embodiment of this 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 this application, the flange on the first cover support plate is connected to the machine fixing structure by multiple sets of bolts, nuts and washers.

[0016] In at least one embodiment of this application, the second cap support plate includes one plate, which is located between the two first cap support plates.

[0017] In at least one embodiment of this 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 this application, the flange on the second cover support plate is connected to the machine fixing structure by multiple sets of bolts, nuts and washers.

[0019] In at least one embodiment of this application, the long axis of the elongated hole on the second cap support plate is perpendicular to the cap skin.

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

[0021] In at least one embodiment of this application, the main connecting corner piece and the cover skin are connected by a plurality of pop rivets.

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

[0023] In at least one embodiment of this application, the auxiliary connecting corner piece is connected to the cover skin by a plurality of pop rivets.

[0024] In at least one embodiment of this application, the auxiliary connecting corner piece is connected to the first cover support plate by multiple sets of bolts, nuts and washers.

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

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

[0027] Step 2: Connect the main connecting corner piece and the auxiliary connecting corner piece to the cover skin using pop rivets;

[0028] Step 3: Pre-connect the second cover support plate to the main connecting corner piece using bolts, nuts, and washers. 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 corner piece to secure the cover skin;

[0030] Step 5: Drill holes in the first cover support plate and the auxiliary connecting corner piece using a matching drill, and connect them with bolts, nuts and washers.

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

[0032] The fixed cover structure with adjustable outer edge step of the aircraft proposed in this application has strong applicability. It can meet the aerodynamic outer edge tolerance requirements such as the gap and step difference between the cover and the surrounding structure by quick 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. Attached Figure Description

[0033] Figure 1 This is a schematic diagram from one perspective of an aircraft adjustable outer edge step fixed cover structure according to one embodiment of this application.

[0034] Figure 2 This is another schematic diagram of a fixed cover structure with adjustable outer edge step of an aircraft according to one embodiment of this application.

[0035] in:

[0036] 1-Cover skin; 2-First cover support plate; 3-Second cover support plate; 4-Main connecting corner piece; 5-Auxiliary connecting corner piece. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0038] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0039] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0040] The first aspect of this application provides a fixed hatch structure with adjustable outer edge step for an aircraft, including: hatch skin 1, first hatch support plate 2, second hatch support plate 3, main connecting corner piece 4, and auxiliary connecting corner piece 5.

[0041] like Figure 1-2 As shown, the first cover support plate 2 is provided with a flange, and the first cover support plate 2 is connected to the fixed structure on the machine through the flange. The first cover support plate 2 has multiple first mounting holes. The second cover support plate 3 is provided with a flange, and the second cover support plate 3 is connected to the fixed structure on the machine through the flange. The second cover support plate 3 has multiple second mounting holes, which are oblong holes. One end of the main connecting corner 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 corner 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 a preferred embodiment of this application, the cover skin 1 may adopt a rectangular structure. It is understood that the specific structural form of the cover skin 1 can be determined according to the installation requirements of the actual installation location on the aircraft, such as circular, square, etc.

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

[0044] In one embodiment of this 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 machine fixing structure by multiple sets of bolts, nuts and washers.

[0045] In one embodiment of this application, the second cover support plate 3 is one, located between 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 machine fixing structure by multiple sets of bolts, nuts and washers. In this embodiment, preferably, the long axis of the elongated hole on the second cover support plate 3 is perpendicular to the cover skin 1.

[0046] The fixed hatch structure with adjustable outer edge step of the aircraft disclosed in this application uses L-shaped angle members 4 and 5 as the main connecting angle members, with an L-shaped cross-section. The main connecting angle member 4 is connected to the hatch skin 1 by multiple blind rivets; the main connecting angle member 4 is connected to the second hatch support plate 3 by multiple sets of bolts, nuts, and washers. The auxiliary connecting angle member 5 is connected to the hatch skin 1 by multiple blind rivets; the auxiliary connecting angle member 5 is connected to the first hatch support plate 2 by multiple sets of bolts, nuts, and washers.

[0047] This application discloses a fixed hatch structure with adjustable outer edge step for aircraft, which comprises a hatch skin 1, three hatch support plates, and three connecting corner pieces. The first hatch support plate 2 and the second hatch support plate 3 have flanges, which connect to the onboard fixed structure near the hatch. The hatch skin 1 is connected to the first hatch support plate 2 via auxiliary connecting corner pieces 5, and the hatch skin 1 is connected to the second hatch support plate 3 via main connecting corner pieces 4.

[0048] Based on the aforementioned fixed cover structure with adjustable outer edge step for aircraft, a second aspect of this application provides a method for installing such a fixed cover structure, comprising the following steps:

[0049] Step 1: Connect 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: Connect the main connecting corner piece 4 and the auxiliary connecting corner piece 5 to the cover skin 1 using pop rivets;

[0051] Step 3: Pre-connect the second cover support plate 3 and the main connecting corner piece 4 with bolts, nuts and washers, but 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 corner piece 4 to fix the cover skin 1;

[0053] Step 5: Drill holes in the first cover support plate 2 and the auxiliary connecting corner piece 5 using a matching drill, and connect them with bolts, nuts and washers.

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

[0055] The fixed cover structure and installation method of the aircraft with adjustable outer edge step of this application have strong applicability. It can meet the aerodynamic outer edge tolerance requirements such as the gap and step difference between the cover and the surrounding structure by quick adjustment during the installation process, and can also effectively reduce the assembly stress generated during the installation process.

[0056] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aircraft adjustable-blade-threshold fixed cowl structure, characterized by, include: Mouth flap skin (1); The first cover support plate (2) is provided with a flange. The first cover support plate (2) is connected to the machine fixing structure through the flange. The first cover support plate (2) is provided with a first mounting hole. The second cover support plate (3) has a flange on it. The second cover support plate (3) is connected to the machine fixing structure through the flange. The second cover support plate (3) has a second mounting hole, which is an elongated hole. The long axis of the elongated hole on the second cover support plate (3) is perpendicular to the cover skin (1). The main connecting corner piece (4) has one end connected to the cover skin (1) and the other end connected to the second mounting hole of the second cover support plate (3); Auxiliary connecting corner piece (5), one end of which 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); The installation method for a fixed cover structure with adjustable outer edge step on an aircraft includes: Step 1: Connect 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: Connect the main connecting corner piece (4) and the auxiliary connecting corner piece (5) to the cover skin (1) using pop rivets; Step 3: Pre-connect the second cover support plate (3) and the main connecting corner piece (4) with bolts, nuts and washers, but 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; Step 4: Tighten the nuts between the second cover support plate (3) and the main connecting corner piece (4) to fix the cover skin (1); Step 5: Drill holes in the first cover support plate (2) and the auxiliary connecting corner piece (5) using a matching drill, and connect them with bolts, nuts and washers.

2. The aircraft adjustable-bleed fixed cowl structure of Claim 1, wherein, The mouth cover skin (1) is rectangular.

3. The aircraft adjustable-bleed fixed cowl structure of Claim 1, wherein, The first cover support plate (2) comprises two.

4. The aircraft adjustable-bleed fixed cowl structure of Claim 3, wherein, The flange on the first cover support plate (2) is a non-flat structure with a predetermined curvature.

5. The aircraft adjustable-bleed fixed cowl structure of Claim 4, wherein, The flange on the first cover support plate (2) is connected to the machine fixing structure by multiple sets of bolts, nuts and washers.

6. The aircraft adjustable-bleed fixed cowl structure of Claim 5, wherein, 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).

7. The aircraft adjustable-bleed fixed cowl structure of Claim 6, wherein, The flange on the second cover support plate (3) is a non-flat structure with a predetermined curvature.

8. The aircraft adjustable-bleed fixed cowl structure of Claim 7, wherein, The flange on the second cover support plate (3) is connected to the machine fixing structure by multiple sets of bolts, nuts and washers.

9. The aircraft adjustable-bleed fixed cowl structure of Claim 1, wherein, The cross-sections of the main connecting corner piece (4) and the auxiliary connecting corner piece (5) are L-shaped.

10. The aircraft adjustable-bleed fixed cowl structure of Claim 9, wherein, The main connecting corner piece (4) and the cover skin (1) are connected by multiple pull rivets.

11. The aircraft adjustable-bleed fixed cowl structure of Claim 10, wherein, The main connecting corner piece (4) is connected to the second cover support plate (3) by multiple sets of bolts, nuts and washers.

12. The aircraft adjustable-bleed fixed cowl structure of Claim 11, wherein, The auxiliary connecting corner piece (5) is connected to the cover skin (1) by a plurality of pop rivets.

13. The aircraft adjustable-bleed fixed cowl structure of Claim 12, wherein, The auxiliary connecting corner piece (5) is connected to the first cover support plate (2) by multiple sets of bolts, nuts and washers.

Images