A device and method for rapid disassembly of an aircraft tail cone

Abstract

The application discloses a device and method for quick dismounting of an aircraft tail cover, and belongs to the technical field of tooling, comprising a base body, a positioning surface, a mounting force applying surface, a compensation curved surface, a supporting curved surface and a working surface; the mounting force applying surface is opposite to the positioning surface, and the other end surface parallel to the mounting force applying surface is the positioning surface; the L-shaped groove part curved surface of the positioning surface matches the mounting end surface of the tail cover; the end surface of the base body in contact with the inner wall of the tail cover comprises the supporting curved surface and the compensation curved surface; the surface opposite to the supporting curved surface is the working surface of the dismounting device; the working surface is an inclined slope surface along the direction from the mounting front end to the rear end of the tail cover; and the starting end of the working surface is the end surface where the positioning surface is located. The device is convenient to operate, simple and reliable to position, and can be repeatedly used without limitation after installation, and has high working efficiency.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of tooling, in particular to a device and method for rapid disassembly of an aircraft tail cover. BACKGROUND

[0002] The tail cover of an aircraft is a device for transitioning between the aircraft fuselage structure and the engine nozzle, and is a thin-walled barrel-shaped structure in a horn shape, with a fixed end of the aircraft fuselage structure being an "L"-shaped groove structure, and the whole forming a front large and rear small horn-shaped barrel structure with an inner groove on the mounting end face.

[0003] The tail nozzle of a certain aircraft-mounted gas turbine fan engine is formed by a plurality of long strip-shaped elastic pieces, is also a horn-shaped structure with a front large and rear small horn shape, and the diameter of the horn-shaped front end of the engine nozzle is greater than the inner diameter of the inner groove of the tail cover; after the engine is mounted on the fuselage, during the process of sleeving the tail cover from the rear end of the engine nozzle, the inner side of the inner groove of the tail cover will force the elastic pieces of the engine nozzle to displace, thereby reducing the diameter of the horn-shaped front end of the engine nozzle, and after the tail cover passes through smoothly, the elastic pieces of the tail nozzle of the tail cover return to their original positions; however, when the aircraft tail cover is disassembled, the tail cover moves in the opposite direction to the installation direction, and the horn-shaped front end of the engine nozzle enters the inner groove of the tail cover, which results in the tail cover being unable to be disassembled.

[0004] Therefore, a disassembly auxiliary device is needed, which can force the horn-shaped front end elastic pieces to displace when the tail cover of a certain aircraft model is disassembled, so as to reduce the diameter to be less than the diameter of the inner side of the inner groove of the tail cover. SUMMARY

[0005] The present application aims to solve the problem that the elastic pieces of the tail nozzle of a certain turbofan engine slide into the "groove" of the tail cover when a certain aircraft model is disassembled, which results in the tail cover being unable to be disassembled, and proposes a device and method for rapid disassembly of an aircraft tail cover, which can improve the operation efficiency of disassembly of the tail cover of a certain aircraft model equipped with a certain turbofan engine.

[0006] In order to achieve the above-mentioned application purposes, the technical solutions of the present application are as follows:

[0007] The utility model provides a device for aircraft tail cover quick dismounting, characterized in that, comprising base body and setting on base body locating surface, installation force surface, compensation camber, support camber and working surface, installation force surface is opposite setting with locating surface, the locating surface with the vertical edge of the " L " shape groove of tail cover installation end face arc surface matching part, support camber and compensation camber are set in the end surface of base body and the inner wall of tail cover contact, and the opposite surface of support camber is the working surface of dismounting device, the working surface is with the locating surface as the starting point, and gradually approaches the inner wall tilt in the rear end direction of tail cover, and the locating groove for clamping into the flanging of vertical edge of " L " shape groove is set on the locating surface.

[0008] Further, a sign is arranged at the middle of the installation force surface.

[0009] Further, the surface of the support camber is higher than that of the compensation camber, and the shape and the curvature of the support camber are adapted to the inner wall of the tail cover; and the compensation camber is perpendicular to the locating surface and adapted to the arc surface on the side of the inner wall of the tail cover.

[0010] Further, the space of the locating groove is large at the outside and small at the inside, and the cross section of the locating groove is in the shape of an inverted triangle when cut along the direction perpendicular to the length of the locating groove.

[0011] Further, the base body is made of high-strength resin material and is 3D printed.

[0012] According to the device, the utility model also provides a method for quick dismounting of the aircraft tail cover, comprising the following steps:

[0013] Firstly, the aircraft tail cover is moved to a position where the dismounting device can be accommodated into the " L " shape groove space of the tail cover.

[0014] Secondly, the base body posture and the installation posture of the dismounting device are adjusted by hand, and the locating surface of the dismounting device is confirmed to face the vertical edge of the " L " shape groove of the tail cover.

[0015] Thirdly, the dismounting device is put between the elastic sheet of the tail cover and the engine tail nozzle by hand, so that the support camber is tightly attached to the inner arc surface of the tail cover, and the compensation camber is tightly attached to the arc surface on the side of the inner wall of the tail cover.

[0016] Fourthly, force is applied to the dismounting device, so that the dismounting device is moved in the direction of the " groove " of the tail cover and tightly attached to the inner arc surface of the tail cover, until the locating surface of the dismounting device is inserted into the " L " shape groove of the tail cover.

[0017] Fifthly, the dismounting device is loosened, and is installed and evenly distributed in sequence at the required positions.

[0018] Step 6, pull the tail cover to the disassembly direction, the elastic sheet on the tail nozzle is pressed to be displaced by the working surface of the disassembly device, so that the diameter of the horn-shaped front end of the engine tail nozzle is reduced to accommodate the installation front end of the tail cover;

[0019] Step 7, the disassembly device is taken out from the inside of the L-shaped groove of the tail cover.

[0020] In summary, the present application has the following advantages:

[0021] 1, the device improves the operation efficiency of disassembling the tail cover of the certain type of aircraft equipped with a certain type of turbofan engine, realizes the quick disassembly operation of the tail cover in the daily maintenance process of the aircraft, solves the problem that the elastic sheet of the engine tail nozzle slides into the tail cover groove during the disassembly of the tail cover of the certain type of aircraft, and the aircraft tail cover disassembly device is convenient to operate, the positioning on the tail cover is simple and reliable, and after installation, the tail cover can be adaptively positioned according to the stress condition during disassembly, without human intervention;

[0022] 2, the device has strong practicability, and the arc surface working area characteristics of the device can be changed according to the different arc surface sizes of the tail cover of the certain type of aircraft, and has strong reference and promotion value in the daily tail maintenance work of the certain type of aircraft;

[0023] 3, the device is made of high-strength resin material 3D, and can be repeatedly used without limitation, and has high working efficiency;

[0024] 4, in the device, the supporting arc surface is the main force bearing part during work, and can assist the positioning groove to be reliably positioned; the positioning groove is located on one side of the positioning surface, and is large inside and small outside, and is a reverse triangular groove, which can ensure normal use of the tail cover of the certain type of aircraft under the condition that there is shape error. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 is a use state diagram of the present application;

[0026] Figure 2 is an assembly position diagram of the tail cover and the tail nozzle;

[0027] Figure 3 is a whole structure diagram of the device;

[0028] Figure 4 is a side view of the device;

[0029] Figure 5 is a diagram of the positioning surface;

[0030] Figure 6 is an enlarged diagram of the positioning groove;

[0031] Figure 7 (a), (b), (c), (d) show the operation process of disassembling device;

[0032] In the figure:

[0033] 1, base, 2, tail cover, 3, tail nozzle, 4, elastic sheet, 5, positioning surface, 6, installation force surface, 7, compensation arc surface, 8, support arc surface, 9, working surface, 10, positioning groove, 11, "L" shaped groove, 12, label. DETAILED DESCRIPTION

[0034] In order to more clearly illustrate the present application, the present application is further described below in conjunction with preferred embodiments and drawings. Those skilled in the art should understand that the specific description below is illustrative rather than limiting, and the protection scope of the present application should not be limited thereby. The description, claims and above drawings of the present application belong to "first", "second" and the like are used to distinguish different objects, rather than to describe a specific order. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product or equipment including a series of steps or units is not limited to the listed steps or units, but optionally also includes steps or units not listed, or optionally also includes other steps or units inherent to these processes, methods or equipment.

[0035] Example 1

[0036] The tail cover 2 is a trumpet-shaped thin-walled structure, and the fixed end of the aircraft fuselage structure is an "L" shaped groove 11 structure, and the whole forms a front large and rear small trumpet-shaped barrel structure with an inner groove on the installation end surface. As shown in Figure 1 .

[0037] As shown in Figure 2 , the engine tail nozzle 3 is also trumpet-shaped with a front large and rear small trumpet, and the diameter of the trumpet-shaped front end of the engine tail nozzle 3 is larger than the inner diameter size of the inner groove of the tail cover 2. After completing the installation of the engine on the fuselage, during the process of sleeving the tail cover 2 from the rear end of the engine tail nozzle 3, because the diameter of the trumpet-shaped front end of the engine tail nozzle 3 is larger than the inner diameter size of the inner groove of the tail cover 2, the inner side of the inner groove of the tail cover 2 will force the elastic sheet 4 of the engine tail nozzle 3 to shift, thereby reducing the diameter of the trumpet-shaped front end of the engine tail nozzle 3, and after the tail cover 2 passes through smoothly, the elastic sheet 4 of the tail nozzle 3 of the tail cover 2 returns to the original position. However, when the aircraft tail cover 2 is disassembled, the tail cover 2 moves in the opposite direction to the installation direction, and the trumpet-shaped front end of the engine tail nozzle 3 enters the inner groove of the tail cover 2, resulting in that the tail cover 2 cannot be disassembled.

[0038] In order to solve the above problems, the embodiment provides a device for quickly disassembling the tail cover 2 of an airplane, which can improve the operation efficiency of disassembling the tail cover 2 of the airplane equipped with a certain type of turbofan engine, realize the quick disassembling operation of the tail cover 2 in the daily maintenance process of the airplane, and solve the problem that the elastic sheet 4 of the engine tail nozzle 3 slides into the “groove” of the tail cover 2, so that the tail cover 2 cannot be disassembled.

[0039] As shown in Figure 3 , the disassembling device is in the shape of a wedge block, which comprises a base body 1 and a positioning groove 10, a positioning surface 5, an installation force surface 6, a compensation curved surface 7, a supporting curved surface 8 and a working surface 9 arranged on the base body 1.

[0040] Among them, the installation force surface 6 is located at the end face of the thinner side of the overall thickness of the wedge block, and a sign 12 is arranged at the middle position of the installation force surface 6, which is convenient for management.

[0041] As shown in Figure 5 , the other end face opposite to the installation force surface 6 is the positioning surface 5, which matches the part of the curved surface of the vertical edge of the “L”-shaped groove 11 of the installation end face of the tail cover 2. The vertical edge is perpendicular to one side of the inner wall of the tail cover 2, and the edge of the vertical edge is also provided with a flange extending towards the inside of the tail cover 2. Since the “L”-shaped groove 11 is arranged on the installation end face of the tail cover 2, it forms a step with the inner wall of the tail cover 2, so that the supporting curved surface 8 and the compensation curved surface 7 are arranged at the end of the disassembling device in contact with the inner wall of the tail cover 2, respectively. Among them, the supporting curved surface 8 is higher than the compensation curved surface 7, the shape and curvature of the supporting curved surface 8 are matched with the inner wall of the tail cover 2, and the compensation curved surface 7 is perpendicular to the positioning surface 5 and matched with the curved surface on the side of the inner wall of the tail cover 2.

[0042] As shown in Figure 4 , the face opposite to the supporting curved surface 8 is the working surface 9 of the disassembling device, which starts from the intersection edge of the positioning surface 5 and gradually approaches the inner wall in the direction of the rear end of the tail cover 2, and is an inclined slope surface, the slope of the slope surface (the angle with the inner wall of the tail cover 2) is controlled to be 15-30°, and the starting end of the working surface 9 is the end face of the positioning surface 5.

[0043] Further, as shown in Figure 4 , the positioning groove 10 is arranged at the intersection of the starting end of the working surface 9 and the positioning surface 5, and the opening of the positioning groove 10 is located on the positioning surface 5. Figure 6As shown, the positioning groove 10 is designed to be able to just make the "L" shaped groove 11 stand edge on the flange card. Further, the space of the positioning groove 10 is large outside and small inside, and after cutting open in the direction perpendicular to the length of the positioning groove 10, the cutting surface is a reverse triangular groove, which can ensure that the tail cover 2 of the certain type of aircraft is normally used in the case of shape error, so that the positioning groove 10 can be tightly buckled with the flange of the "L" shaped groove 11.

[0044] Through the positioning groove 10 and the supporting arc surface 8, self-adaptive and reliable positioning can be realized. When the tail cover 2 is moved in the disassembly direction, the working surface 9 of the invention device will force the elastic sheet 4 of the engine tail nozzle 3 to shift, the diameter of the horn-shaped front end of the engine tail nozzle 3 is reduced, and finally the tail cover 2 is smoothly disassembled.

[0045] Embodiment 2

[0046] Based on the above disassembly device, the application also provides a method for quickly disassembling the tail cover 2 of the aircraft, as shown in Figure 7 As shown, the method specifically comprises the following steps:

[0047] Firstly, the tail cover 2 of the aircraft is moved to a position where the disassembly device can be accommodated into the "L" shaped groove space of the tail cover 2 in the disassembly direction; as shown in Figure 7 (a);

[0048] Secondly, the posture and installation posture of the disassembly device are adjusted by hand, and it is confirmed that the positioning surface 5 of the disassembly device faces the stand edge of the "L" shaped groove of the tail cover 2 (that is, the side perpendicular to the inner wall of the tail cover 2);

[0049] Thirdly, the disassembly device is put between the tail cover 2 and the elastic sheet 4 of the engine tail nozzle 3 by hand, so that the supporting arc surface 8 tightly abuts against the inner side arc surface of the tail cover 2, and the arc surface 7 tightly abuts against the arc surface of the "L" shaped groove 11 on the side of the inner wall of the tail cover 2.

[0050] Fourthly, force is applied to the disassembly device, so that the disassembly device tightly abuts against the inner side arc surface of the tail cover 2 and moves in the direction of the "L" shaped groove of the tail cover 2, until the positioning surface 5 of the disassembly device is inserted into the "L" shaped groove 11 of the tail cover 2; as shown in Figure 7 (b);

[0051] Fifthly, the disassembly device is loosened and is installed one by one at the required positions, and generally 6 to 8 disassembly devices are installed uniformly at the front end of the tail cover 2.

[0052] Sixthly, the tail cover 2 is pulled to move in the disassembly direction, and the elastic sheet 4 on the tail nozzle 3 is shifted by being extruded by the working surfaces 9 of the plurality of disassembly devices, so that the diameter of the horn-shaped front end of the engine tail nozzle 3 is reduced to be able to accommodate the installation front end of the tail cover 2 to pass; as shown in Figure 7(c) shown;

[0053] The seventh step, the dismounting device is taken out from the "L" shaped groove 11 inside the tail cover 2 one by one. As Figure 7 (d) shown.

[0054] Although the specific embodiments of the present application are described in detail with reference to the accompanying drawings, it should not be understood as limiting the scope of protection of the patent. Various modifications and variations made by those skilled in the art within the scope described in the claims are still within the scope of protection of the patent.

[0055] The above is only the preferred embodiment of the present application, not any form of the present application, any simple modification, equivalent change made according to the technical essence of the present application to the above embodiment, falls within the scope of protection of the present application.

Claims

1. A device for rapid disassembly of an aircraft tail cone, characterized in that, The device comprises a base (1) and a positioning surface (5), an installation force surface (6), a compensation arc surface (7), a support arc surface (8) and a working surface (9) arranged on the base (1); the installation force surface (6) is arranged opposite to the positioning surface (5), the positioning surface (5) is matched with the arc surface of the vertical edge of the "L" shaped groove (11) of the installation end surface of the tail cover (2); the support arc surface (8) and the compensation arc surface (7) are arranged on the end surface of the base (1) in contact with the inner wall of the tail cover (2); the surface opposite to the support arc surface (8) is the working surface (9) of the dismounting device, the working surface (9) is inclined to the inner wall in the direction of the rear end of the tail cover (2) from the intersection edge of the positioning surface (5); the positioning groove (10) for clamping the turn-up edge of the vertical edge of the "L" shaped groove (11) is arranged on the positioning surface (5).

2. A device for rapid removal of an aircraft tail cone according to claim 1, wherein, A label (12) is arranged at the middle position of the installation force surface (6).

3. A device for quick removal of an aircraft tail cone according to claim 1, characterized in that, The surface of the support arc surface (8) is higher than that of the compensation arc surface (7), the shape and the arc of the support arc surface (8) are matched with the inner wall of the tail cover (2); the compensation arc surface (7) is perpendicular to the positioning surface (5) and matched with the arc surface of the inner wall of the tail cover (2) on one side of the "L" shaped groove (11).

4. A device for quick removal of an aircraft tail cone according to claim 1, characterized in that, The space of the positioning groove (10) is large at the outside and small at the inside, the cross section of the positioning groove (10) is inverted triangle when it is cut along the direction perpendicular to the length of the positioning groove (10).

5. A device for quick removal of an aircraft tail cone according to claim 1, characterized in that, The base (1) is made of high-strength resin material by 3D printing.

6. A method for quick release of an aircraft tail cone, according to any one of claims 1-5, characterized in that, The device comprises the following steps: Firstly, the tail cover (2) is moved to the position where the dismounting device can be accommodated into the space of the "L" shaped groove (11) of the tail cover (2) in the dismounting direction; Secondly, the posture and the installation posture of the base (1) are adjusted by hand, and it is confirmed that the positioning surface (5) of the dismounting device faces the vertical edge of the "L" shaped groove (11) of the tail cover (2); Thirdly, the dismounting device is put between the tail cover (2) and the elastic sheet (4) of the engine tail nozzle (3) by hand, so that the support arc surface (8) is tightly attached to the inner arc surface of the tail cover (2), and the compensation arc surface (7) is tightly attached to the arc surface of the "L" shaped groove (11) on one side of the inner wall of the tail cover (2); Fourthly, force is applied to the dismounting device, so that the dismounting device is moved in the direction of the "groove" of the tail cover (2) and tightly attached to the inner arc surface of the tail cover (2), until the positioning surface (5) of the dismounting device is inserted into the "L" shaped groove (11) of the tail cover (2); Fifthly, the dismounting device is loosened, and then it is installed and distributed evenly at the required positions in sequence; Sixthly, the tail cover (2) is moved in the dismounting direction, the elastic sheet (4) on the tail nozzle (3) is displaced by the extrusion of the working surface (9) of the dismounting device, so that the diameter of the horn-shaped front end of the engine tail nozzle (3) is reduced to the diameter that can accommodate the installation front end of the tail cover (2); Seventhly, the dismounting device is taken out from the inner side of the "L" shaped groove (11) of the tail cover (2) in sequence.

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