Aircraft inner flap lifting method and lifting appliance

Abstract

The invention relates to the technical field of aircraft wing assembly, and provides an aircraft inner flap hoisting method and sling.The hoisting method comprises the steps that firstly, pulley yoke trolleys, located on two sliding rails respectively, on an inner flap are adjusted to the working position, then the positions of an outer flap and a ground spoiler are adjusted, so that the hindering influence caused by installation of the inner flap is reduced, and the hoisting efficiency is improved. The center-of-gravity position of the inner flap on the aircraft body in the working state is analyzed, and the lifting appliance is adjusted according to parameters obtained through analysis and is assembled; a travelling crane is used for hoisting the inner flap and transferring the inner flap to a mounting position of a machine body, then a torque tube is connected with a connecting lug piece of one pulley yoke trolley, and a connecting lug piece of the other pulley yoke trolley is connected with a connecting lug piece of the machine body, so that mounting of the inner flap is completed, and therefore the inner flap can be kept in an ideal mounting posture in the hoisting process; the inner flap can be conveniently installed, meanwhile, the influence of a peripheral structure in the inner flap hoisting process can be avoided, and therefore the inner flap can be accurately and efficiently installed.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft wing assembly, and in particular to an aircraft inner flap hoisting method and a hoisting device. Background Art

[0002] In order to increase lift during takeoff and increase resistance and deceleration during landing, a certain civil aircraft usually arranges a variable airfoil flap on the trailing edge of the aircraft wing. The flap is connected to the pulley frame on the aircraft, and provides guidance and support functions with the help of the slide rail. The slide rail retreats linearly and deflects to create a certain gap with the fixed trailing edge of the wing, guiding the high-pressure airflow to flow to the upper wing surface at high speed, delaying the separation of the airflow while also changing the curvature of the wing, further achieving the effect of increasing lift. The retraction and extension of the flap is realized through the slide rail motion mechanism to achieve four states: takeoff, cruise, go-around, and landing, corresponding to four card positions respectively, to meet the lift requirements of the aircraft under different working conditions, thereby improving the takeoff and landing performance of the aircraft.

[0003] Usually, the inner flap is hoisted by using a rope on a horizontal boom, which is connected to a reserved hoisting point on the flap, and then the horizontal boom is hoisted by a crane to finally realize the flap hoisting operation. In the existing aircraft assembly technology, it is necessary to set a reserved hoisting point on the flap, which is not conducive to the optimization of the aircraft flap structure design. In addition, in order to ensure the smooth assembly of the aircraft flap hoisting as much as possible, a boom with a length close to the flap is used. Therefore, when the flap is hoisted to the installation position, there is a risk that the overly long boom will touch the fuselage.

[0004] In addition to considering the safety of the operation, the lifting process did not take into account the theoretical center of gravity of the flap installation in the 4-position (take-off, landing) posture. After the flap was lifted, it was not in the installation posture and the stability of the lifting posture was not high. After the flap was lifted to the installation position in any posture, it could not accurately dock with the mechanical connection position on the flap slide trolley. In the end, multiple people were still needed to assist in the installation, which increased the labor cost and reduced the efficiency of on-site aircraft assembly.

[0005] Therefore, there is an urgent need for a method and a lifting device for lifting an inner flap of an aircraft to solve the above-mentioned technical problems. Summary of the invention

[0006] The purpose of the present invention is to provide an aircraft inner flap hoisting method and a hoisting device, which can accurately and efficiently install the inner flap.

[0007] To achieve this object, the present invention adopts the following technical solutions:

[0008] Aircraft inner flap hoisting method, including:

[0009] S1. Using the flap support tooling, the pulley frame trolley on the first slide rail and the pulley frame trolley on the second slide rail of the inner flap are both synchronized in the working position and maintained in a synchronized docking posture with the inner flap, while the outer flap is retracted to the zero position and the ground spoiler is supported to the maximum opening;

[0010] S2. Analyze the posture and center of gravity position of the inner flap when it is in working state on the fuselage;

[0011] S3, installing a sling joint on the inner flap, and selecting a sling rope of corresponding length to connect the sling joint and the sling rod according to the parameters obtained in S2;

[0012] S4, the crane lifts the inner flap via the suspension rod and transports it to the installation location;

[0013] S5, connecting the force transmission torque tube installed on the above-mentioned body to the first connecting ear piece of the above-mentioned pulley frame trolley on the above-mentioned first slide rail;

[0014] S6. By lowering the above-mentioned crane, the second connecting ear piece of the above-mentioned pulley frame trolley on the above-mentioned second slide rail is aligned and connected with the third connecting ear piece fixed on the above-mentioned body.

[0015] As a preferred technical solution of the above-mentioned aircraft inner flap hoisting method, four mounting holes are opened on the circumferential side of the above-mentioned inner flap.

[0016] As a preferred technical solution of the above-mentioned aircraft inner flap hoisting method, each of the above-mentioned mounting holes is provided with a blocking piece, the above-mentioned blocking piece is plugged into the above-mentioned mounting hole, and the axial end face of the above-mentioned blocking piece is flush with the end face of the above-mentioned inner flap.

[0017] A hoist is also provided, which is applied to the above-mentioned aircraft inner flap hoisting method. The above-mentioned hoist includes a process joint, one end of which is threadedly connected to the above-mentioned mounting hole, and the above-mentioned process joint corresponds to the above-mentioned mounting hole one by one.

[0018] As a preferred technical solution of the above-mentioned sling, a gasket is arranged between the above-mentioned process joint and the above-mentioned inner flap.

[0019] As a preferred technical solution of the above-mentioned sling, it also includes a sling joint and a pin, one of the above-mentioned process joint and the above-mentioned sling joint is provided with a slot, and the other is provided with a plug plugged into the above-mentioned slot, the above-mentioned sling joint and the above-mentioned process joint are fixed by the above-mentioned pin, and the plugging direction of the above-mentioned plug and the above-mentioned slot is perpendicular to the plugging direction of the above-mentioned pin and the above-mentioned process joint.

[0020] As a preferred technical solution of the above-mentioned sling, it also includes a safety pin, which is plugged into the above-mentioned plug pin along the radial direction of the above-mentioned plug pin to maintain a fixed relationship between the above-mentioned plug pin and the above-mentioned process joint and the above-mentioned sling joint.

[0021] As a preferred technical solution of the above-mentioned sling, it also includes a sling rod and a sling rope, wherein both ends of the above-mentioned sling rod are respectively provided with sling rings, the above-mentioned sling rope corresponds one-to-one with the above-mentioned sling joint, one end of the above-mentioned sling rope is connected to the above-mentioned sling joint, and the other end is connected to the above-mentioned sling ring.

[0022] As a preferred technical solution of the above-mentioned sling, a shackle is fixed to one end of the above-mentioned sling rope, and the above-mentioned shackle is connected to the above-mentioned sling joint.

[0023] As a preferred technical solution of the above-mentioned sling, a multi-hole eye plate is installed in the middle of the above-mentioned sling, and the multi-hole eye plate is sequentially provided with a plurality of connecting holes along the axial direction of the above-mentioned sling, and the above-mentioned crane can be connected to one of the above-mentioned connecting holes.

[0024] Beneficial effects of the present invention:

[0025] Provided is a method and a lifting device for lifting an inner flap of an aircraft. The lifting method comprises S1, using a flap supporting tool to synchronize a pulley frame trolley located on a first slide rail and a pulley frame trolley located on a second slide rail in the inner flap in a working position and maintain a synchronous docking posture with the inner flap, while receiving the outer flap to a zero position and supporting a ground spoiler to a maximum opening; S2, analyzing the posture and center of gravity position of the inner flap when in a working state on a fuselage; S3, installing a lifting device joint on the inner flap, and selecting a lifting rope of corresponding length to connect the lifting device joint and a lifting rod according to the parameters obtained in S2; S4, a crane lifting the inner flap through the lifting rod and transporting it to an installation position; S5, connecting a force transmission torque tube installed on the fuselage with a first connecting ear of the pulley frame trolley on the first slide rail; S6, aligning and connecting the second connecting ear of the pulley frame trolley on the second slide rail with a third connecting ear fixed on the fuselage by lowering the crane.

[0026] The aircraft inner flap hoisting method of the present invention calculates the center of gravity of the inner flap and optimizes the design of the matching hoisting rope length, so that the inner flap can maintain an ideal installation posture during hoisting, and the inner flap can be easily installed while avoiding the influence of the surrounding structure during the inner flap hoisting, so that the inner flap can be installed accurately and efficiently. And through the hoist, the connection between the inner flap and the crane can be more conveniently achieved. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without paying any creative work.

[0028] Figure 1 is a flow chart of a method for hoisting an aircraft inner flap provided by an embodiment of the present invention;

[0029] Figure 2 The embodiment of the present invention provides an assembly method of the inner flap and the fuselage. Figure 1 ;

[0030] Figure 3 The embodiment of the present invention provides an assembly method of the inner flap and the fuselage. Figure 2 ;

[0031] Figure 4 is an assembly diagram of a hanger and an inner flap provided by an embodiment of the present invention;

[0032] Figure 5 This is an enlarged view of point A in Figure 4;

[0033] Figure 6 is a schematic structural diagram of a sling provided by an embodiment of the present invention;

[0034] Figure 7 It is an enlarged view of point B in Figure 6;

[0035] Figure 8 is a schematic structural diagram of a suspension rod provided by an embodiment of the present invention;

[0036] Fig. 9 It is a schematic structural diagram of an inner flap provided by an embodiment of the present invention.

[0037] In the figure:

[0038] 10. Inner flap; 11. Mounting hole; 12. First connecting ear piece; 13. Second connecting ear piece;

[0039] 20. Lifting device; 21. Lifting device joint; 22. Lifting rope; 221. Shackle; 23. Lifting rod; 231. Lifting ring; 232. Multi-hole eye plate; 24. Process joint; 25. Latch; 26. Safety pin;

[0040] 30. force transmission torque tube; 40. third connecting ear. DETAILED DESCRIPTION

[0041] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0042] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0043] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0044] In the description of this embodiment, the terms "upper", "lower", "right", etc., directions or positional relationships are based on the directions or positional relationships shown in the drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0045] like Figures 1 to 3 As shown, the present application provides a method for hoisting an aircraft inner flap, comprising:

[0046] S1. Using the flap support tooling, the pulley frame trolley on the first slide rail and the pulley frame trolley on the second slide rail of the inner flap 10 are both synchronized in the working position and maintained in a synchronized docking posture with the inner flap 10, while the outer flap is received at zero position and the ground spoiler is supported to the maximum opening;

[0047] S2. Analyze the posture and center of gravity position of the inner flap 10 when it is in a working state on the fuselage;

[0048] S3, installing the hanger joint 21 on the inner flap 10, and selecting a hanger rope 22 of corresponding length to connect the hanger joint 21 and the hanger rod 23 according to the parameters obtained in S2;

[0049] S4, the crane lifts the inner flap 10 through the suspension rod 23 and transports it to the installation position;

[0050] S5, connecting the force transmission torque tube 30 installed on the machine body to the first connecting ear piece 12 of the pulley frame trolley on the first slide rail;

[0051] S6. By lowering the crane, align and connect the second connecting ear piece 13 of the pulley frame trolley on the second slide rail with the third connecting ear piece 40 fixed on the machine body.

[0052] It should be noted that the installation condition of the inner flap 10 is that all system components and structural components except the inner flap 10 are assembled on the outer wing.

[0053] In this embodiment, the inner flap 10 is installed in the fourth position on the fuselage, that is, the wingtip side of the inner flap 10 is high, the wingroot side is low, and the inclination angle of the inner flap 10 is about 34°.

[0054] Specifically, during the preparation stage, the two pulley frame trolleys of the inner flap 10 located on different slide rails are first adjusted to the fourth position with the help of the flap support tooling, and the outer flap and the ground spoiler are adjusted at the same time to reduce the obstruction of the two on the installation process of the inner flap 10. Then the inner flap 10 is modeled using the relevant software system and its center of gravity when it is in the fourth position. During the transportation stage, the sling joint 21 is first installed on the inner flap 10, and then the length of each sling rope 22 is adjusted according to the position parameters of the center of gravity obtained by analysis. Then the sling rope 22 connects the sling joint 21 and the suspension rod 23. After the crane is connected to the suspension rod 23, the inner flap 10 is lifted in the vertical direction, and the inner flap 10 in the suspended state at this time is placed according to its posture in the fourth position, and the crane transports the inner flap 10 to the connection position of the fuselage; during the installation stage, the force transmission torque tube 30 is first connected to the pulley frame located on the first slide rail. The first connecting ear 12 of the trolley is connected, which completes the preliminary connection between the inner flap 10 and the body, and then the relative position of the inner flap 10 and the body is adjusted by driving, and the second connecting ear 13 of the pulley frame trolley on the second slide rail is aligned and connected with the third connecting ear 40 fixed on the body. Specifically, the second connecting ear 13 of the pulley frame trolley and the third connecting ear 40 on the body are both provided with through holes. After the two through holes are coaxially aligned, they are connected and fixed using threaded fasteners, thereby completing the connection process between the inner flap 10 and the body.

[0055] Through the aircraft inner flap hoisting method of the present invention, by calculating the center of gravity of the inner flap 10 and optimizing the design of the matching length of the hoisting rope 22, the inner flap 10 can maintain an ideal installation posture during lifting, which facilitates the installation of the inner flap 10 and avoids the influence of the surrounding structure during the lifting of the inner flap 10, thereby accurately and efficiently installing the inner flap 10.

[0056] Optionally, four mounting holes 11 are provided on the circumferential side of the inner flap 10. Specifically, the four mounting holes 11 are provided on the main beam structure of the inner flap 10 body, and are respectively provided around the four vertex corners of the inner flap 10, for connecting the sling 20, so that when the inner flap 10 is lifted by the sling 20, the four circumferential vertex corners of the inner flap 10 are evenly stressed, so that the inner flap 10 can still maintain balance in a suspended state.

[0057] Optionally, each mounting hole 11 is equipped with a plugging piece, which is plugged into the mounting hole 11, and the axial end face of the plugging piece is flush with the end face of the inner flap 10. After the inner flap 10 is installed, the plugging piece can be used to plug the mounting hole 11 to keep the structure of the inner flap 10 intact.

[0058] like Figures 4 to 9 As shown, the present application also provides a hoist 20, which is applied to the above-mentioned aircraft inner flap hoisting method, and the hoist 20 includes a process joint 24, one end of which is threadedly connected to the mounting hole 11, and the process joint 24 corresponds to the mounting hole 11. Specifically, the mounting hole 11 is a threaded hole, one end of the process joint 24 is provided with an external thread, and the process joint 24 is threadedly connected to the mounting hole 11. The threaded connection itself has a strong bearing capacity. When the process joint 24 is subjected to a tensile force along its axial direction, it is not easy for it to be displaced and loosened along the axial direction with the inner flap 10.

[0059] Optionally, a gasket is provided between the process joint 24 and the inner flap 10. The provision of the gasket can protect the surface of the inner flap 10 from being scratched and damaged by friction with the process joint 24.

[0060] Optionally, the sling 20 further includes a sling joint 21 and a latch 25, one of the process joint 24 and the sling joint 21 is provided with a slot, and the other is provided with a plug plugged into the slot, the sling joint 21 and the process joint 24 are fixed by the latch 25, and the plugging direction of the plug and the slot is perpendicular to the plugging direction of the latch 25 and the process joint 24. In this configuration, the connection between the plug and the slot completes the initial position limiting of the sling joint 21 and the process joint 24, and the latch 25 simultaneously penetrates the sling joint 21 and the process joint 24, so that the plug cannot be unlocked after being plugged into the slot, so as to maintain the fixed relationship between the sling joint 21 and the process joint 24.

[0061] Preferably, the plugging direction of the latch 25 and the process joint 24 is horizontal, so that when the hanger 20 lifts the inner flap 10 in the vertical direction, the process joint 24 and the hanger joint 21 only generate vertical force on the latch 25 .

[0062] Optionally, the sling 20 further includes a safety pin 26, which is plugged with the plug 25 along the radial direction of the plug 25 to maintain the fixed relationship between the plug 25 and the process joint 24 and the sling joint 21. Specifically, the plug 25 includes an abutment portion and a connection portion, and the connection portion penetrates the sling joint 21 and the process joint 24 and then plugs with the safety pin 26. At this time, the sling joint 21 and the process joint 24 are limited between the abutment portion and the safety pin 26, so that the process joint 24 and the sling joint 21 cannot be loosened.

[0063] Optionally, the sling 20 also includes a sling rod 23 and a sling rope 22, and both ends of the sling rod 23 are respectively provided with sling rings 231, the sling rope 22 corresponds to the sling joint 21 one by one, one end of the sling rope 22 is connected to the sling joint 21, and the other end is connected to the sling ring 231.

[0064] Optionally, a shackle 221 is fixed to one end of the lifting rope 22, and the shackle 221 is connected to the sling joint 21. Such an arrangement facilitates the loading and unloading of the lifting rope 22 and the sling joint 21.

[0065] Optionally, a multi-hole eye plate 232 is installed in the middle of the suspension rod 23, and the multi-hole eye plate 232 is provided with a plurality of connection holes in sequence along the axial direction of the suspension rod 23, and the traveling crane can select one of the connection holes to connect. In this way, the traveling crane can change the tilting posture of the inner flap 10 in a balanced state according to the connection holes in different positions.

[0066] In addition, the above are only preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present invention. Therefore, although the present invention has been described in more detail through the above embodiments, the present invention is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. A method for hoisting an aircraft inner flap, characterized in that: include: S1. Using a flap support tool, the pulley frame trolley on the first slide rail and the pulley frame trolley on the second slide rail of the inner flap (10) are both synchronized in the working position and maintained in a synchronized docking posture with the inner flap (10), while the outer flap is retracted to the zero position and the ground spoiler is supported to the maximum opening; S2, analyzing the posture and center of gravity position of the inner flap (10) when it is in a working state on the fuselage; S3, installing a sling joint (21) on the inner flap (10), and selecting a sling rope (22) of corresponding length to connect the sling joint (21) and the sling rod (23) according to the parameters obtained in S2; S4, the crane lifts the inner flap (10) via the suspension rod (23) and transports it to an installation location; S5, connecting the force transmission torque tube (30) installed on the machine body to the first connecting ear piece (12) of the pulley frame trolley on the first slide rail; S6. By lowering the crane, the second connecting ear piece (13) of the pulley frame trolley on the second slide rail is aligned and connected with the third connecting ear piece (40) fixed on the machine body.

2. The method for hoisting an aircraft inner flap according to claim 1, characterized in that: Four mounting holes (11) are provided on the circumferential side of the inner flap (10).

3. The method for hoisting an aircraft inner flap according to claim 2, characterized in that: Each of the mounting holes (11) is provided with a blocking piece, the blocking piece is plugged into the mounting hole (11), and the axial end surface of the blocking piece is flush with the end surface of the inner flap (10).

4. A lifting device, used in the method for lifting an aircraft inner flap according to claim 2, characterized in that: The hanger (20) comprises a process joint (24), one end of which is threadedly connected to the mounting hole (11), and the process joint (24) corresponds one-to-one to the mounting hole (11).

5. The sling according to claim 4, characterized in that: A gasket is provided between the process joint (24) and the inner flap (10).

6. The sling according to claim 4, characterized in that: It also includes a sling joint (21) and a latch (25), wherein one of the process joint (24) and the sling joint (21) is provided with a slot, and the other is provided with a plug that is plugged into the slot, the sling joint (21) and the process joint (24) are fixed by the latch (25), and the plugging direction of the plug and the slot is perpendicular to the plugging direction of the latch (25) and the process joint (24).

7. The sling according to claim 6, characterized in that: It also includes a safety pin (26), which is plugged into the latch (25) along the radial direction of the latch (25) to maintain a fixed relationship between the latch (25), the process joint (24) and the hanger joint (21).

8. The sling according to claim 7, characterized in that: It also includes a suspension rod (23) and a suspension rope (22), wherein both ends of the suspension rod (23) are respectively provided with suspension rings (231), the suspension rope (22) corresponds to the suspension joint (21) one by one, one end of the suspension rope (22) is connected to the suspension joint (21), and the other end is connected to the suspension ring (231).

9. The sling according to claim 8, characterized in that: A shackle (221) is fixed to one end of the lifting rope (22), and the shackle (221) is connected to the lifting device joint (21).

10. The sling according to claim 8, characterized in that: A multi-hole eye plate (232) is installed in the middle of the suspension rod (23), and the multi-hole eye plate (232) is provided with a plurality of connection holes in sequence along the axial direction of the suspension rod (23), and the crane can be connected to one of the connection holes.

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