Aircraft inner flap hoisting method and hoisting equipment

Abstract

The present invention relates to the technical field of aircraft wing assembly, and provides a method and a lifting device for lifting an inner flap of an aircraft. The lifting method comprises the following steps: firstly adjusting a pulley frame trolley respectively located on two slide rails on the inner flap to a working position, then adjusting the positions of the outer flap and a ground spoiler to reduce the obstruction caused by the installation of the inner flap, analyzing the center of gravity position of the inner flap when in a working state on the aircraft body, adjusting the lifting device according to the parameters obtained by the analysis, and assembling the inner flap; using a crane to lift the inner flap and transport it to the installation position of the aircraft body, then connecting a torque tube with a connecting ear piece of one of the pulley frame trolleys, and connecting the connecting ear piece of the other pulley frame trolley with the connecting ear piece of the aircraft body to complete the installation of the inner flap, so that the inner flap can maintain an ideal installation posture during lifting, and can facilitate the installation of the inner flap while avoiding the influence of the surrounding structure during the lifting of the inner flap, thereby accurately and efficiently installing the inner flap.

Description

Technical Field

[0001] The present 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] To increase lift during takeoff and reduce drag and deceleration during landing, certain civil aircraft typically deploy variable-wing flaps on the trailing edge of the aircraft's wings. The flaps are connected to a pulley frame on the aircraft, using slide rails to provide guidance and support. The slide rails move linearly backward and deflect to create a gap with the fixed trailing edge of the wing, guiding high-pressure airflow toward the upper wing surface at high speed. This delays airflow separation and changes the wing's curvature, further increasing lift. The retraction and extension of the flaps are achieved through the slide rail motion mechanism in four states: takeoff, cruise, go-around, and landing. These correspond to four latching positions to meet the lift requirements of the aircraft under different operating conditions, thereby improving the aircraft's takeoff and landing performance.

[0003] Typically, the inner flap is hoisted using a sling on a horizontal boom, which is connected to a reserved lifting point on the flap. The horizontal boom is then hoisted by a crane to finally complete the flap hoisting operation. Existing aircraft assembly technology requires the provision of reserved lifting points on the flap, which is not conducive to optimizing the aircraft flap structural design. In addition, to ensure the smooth assembly of the aircraft flap, a boom of similar length to the flap is used. Therefore, when the flap is hoisted to the installation position, the overly long boom poses the risk of contact with 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 and 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 be accurately docked 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 labor costs and reduced the efficiency of aircraft on-site assembly.

[0005] Therefore, there is an urgent need for a method and a lifting device for lifting an aircraft inner flap 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 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 fixture, synchronize the pulley frame trolley on the first slide rail and the pulley frame trolley on the second slide rail of the inner flap to the working position and maintain a synchronized docking posture with the inner flap. Simultaneously, retract the outer flap to zero position and support the ground spoiler to the maximum opening.

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

[0011] S3. Install a sling connector on the inner flap, and select a sling with a corresponding length based on the parameters obtained in S2 to connect the sling connector and the sling rod;

[0012] S4. The crane lifts the inner flap via the boom and transports it to the installation location.

[0013] S5. Connecting the force transmission torque tube installed on the machine body to the first connecting lug of the pulley frame trolley on the first slide rail;

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

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

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

[0018] As a preferred technical solution of the above-mentioned sling, a gasket is provided 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 that is 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 plug-in direction of the above-mentioned plug and the above-mentioned slot is perpendicular to the plug-in 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 pin along the radial direction of the above-mentioned pin to maintain a fixed relationship between the above-mentioned pin and the above-mentioned process joint and the above-mentioned sling joint.

[0021] As an optimal technical solution for 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 to 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 multiple 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 are 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 synchronized docking posture with the inner flap, while retracting 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 the aircraft body; 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, using a crane to lift the inner flap via the lifting rod and transport it to an installation position; S5, connecting a force transmission torque tube installed on the aircraft body to a first connecting ear of the pulley frame trolley on the first slide rail; and S6, lowering the crane to align and connect the second connecting ear of the pulley frame trolley on the second slide rail with a third connecting ear fixed to the aircraft body.

[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 a matching hoisting rope length, so that the inner flap can maintain an ideal installation posture during hoisting, facilitating the installation of the inner flap while also avoiding the influence of surrounding structures during the inner flap hoisting. Thus, the inner flap can be installed accurately and efficiently. Moreover, the inner flap can be more conveniently connected to the crane through the hoist. 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 describing 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 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 of the inner flap and the fuselage. Figure 1 ;

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

[0031] Figure 4 is an assembly diagram of a sling 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 1 is a schematic structural diagram of a sling provided by an embodiment of the present invention;

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

[0035] Figure 8 1 is a schematic structural diagram of a boom provided by an embodiment of the present invention;

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

[0037] In the picture:

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

[0039] 20. Spreader; 21. Spreader connector; 22. Lifting rope; 221. Shackle; 23. Lifting rod; 231. Lifting ring; 232. Multi-hole eye plate; 24. Process connector; 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 with reference to the accompanying drawings and examples. It will be understood that the specific embodiments described herein are intended only to illustrate the present invention and are not intended to limit the present invention. It should also be noted that, for ease of description, the accompanying drawings only illustrate portions relevant to the present invention, not all structures.

[0042] In the description of the present invention, unless otherwise expressly specified or limited, the terms "connected," "connected," and "fixed" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integration; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention in specific circumstances.

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

[0044] In the description of this embodiment, the terms "upper," "lower," "right," and other orientations or positional relationships are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely for ease of description and simplified operation. They do not indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. Furthermore, the terms "first" and "second" are used solely for descriptive purposes and have no special meanings.

[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 fixture, synchronize the pulley frame trolley on the first slide rail and the pulley frame trolley on the second slide rail of the inner flap 10 in the working position and maintain a synchronized docking posture with the inner flap 10. At the same time, retract the outer flap to zero position and support the ground spoiler 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. Install the sling connector 21 on the inner flap 10. Select a sling rope 22 of corresponding length to connect the sling connector 21 and the sling rod 23 according to the parameters obtained in S2.

[0049] S4, the crane lifts the inner flap 10 via the boom 23 and transports it to the installation location;

[0050] S5. Connect the torque tube 30 mounted on the machine body to the first connecting lug 12 of the pulley carriage on the first slide rail;

[0051] S6. By lowering the crane, align and connect the second connecting ear 13 of the pulley frame trolley on the second slide rail with the third connecting ear 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 locking position on the fuselage, that is, the wingtip side of the inner flap 10 is higher and the wingroot side is lower, and the inclination angle of the inner flap 10 is about 34°.

[0054] Specifically, during the preparation stage, the two pulley frame trolleys on different slide rails of the inner flap 10 are first adjusted to the fourth position with the help of the flap support tooling, and the outer flap and 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 relevant software system is used to model the inner flap 10 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 boom 23. After the crane is connected to the boom 23, the inner flap 10 is lifted in the vertical direction, and the inner flap 10, which is in a suspended state at this time, is placed according to its posture in the fourth position. 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 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 fuselage. Then, the relative position of the inner flap 10 and the fuselage 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 fuselage. Specifically, the second connecting ear 13 of the pulley frame trolley and the third connecting ear 40 on the fuselage 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 of the inner flap 10 and the fuselage.

[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 lifting rope 22, the inner flap 10 can maintain an ideal installation posture during lifting, thereby facilitating the installation of the inner flap 10 and avoiding 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 to the sling 20. In this way, when the sling 20 is used to lift the inner flap 10, 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 blocking piece, which is plugged into the mounting hole 11, and the axial end face of the blocking piece is flush with the end face of the inner flap 10. After the inner flap 10 is installed, the blocking piece can be used to block 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 further provides a hoist 20 for use in the above-mentioned aircraft inner flap hoisting method. The hoist 20 includes a process connector 24, one end of which is threadedly connected to the mounting hole 11, and the process connector 24 corresponds one-to-one with the mounting hole 11. Specifically, the mounting hole 11 is a threaded hole, and one end of the process connector 24 is provided with an external thread. The process connector 24 is threadedly connected to the mounting hole 11. The threaded connection itself has a strong load-bearing capacity. When the process connector 24 is subjected to axial tension, it is not easy for the process connector 24 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 or 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 that plugs into the slot. The sling joint 21 and the process joint 24 are fixed together by the latch 25, and the plug-in direction of the plug and the slot is perpendicular to the plug-in direction of the latch 25 and the process joint 24. In this arrangement, the connection between the plug and the slot completes the initial positional limit 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, thereby maintaining 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. Thus, when the sling 20 lifts the inner flap 10 in the vertical direction, the process joint 24 and the sling joint 21 only generate vertical force on the latch 25 .

[0062] Optionally, the sling 20 further includes a safety pin 26 that is radially engaged with the latch 25 to maintain a fixed relationship between the latch 25, the process joint 24, and the sling joint 21. Specifically, the latch 25 includes an abutment portion and a connection portion. The connection portion passes through the sling joint 21 and the process joint 24 and then engages with the safety pin 26. At this time, the sling joint 21 and the process joint 24 are trapped between the abutment portion and the safety pin 26, preventing the process joint 24 and the sling joint 21 from loosening.

[0063] Optionally, the sling 20 further includes a sling rod 23 and a sling rope 22 , with sling rings 231 provided at both ends of the sling rod 23 , the sling rope 22 corresponding one-to-one to the sling joint 21 , one end of the sling rope 22 connected to the sling joint 21 , and the other end connected to the sling ring 231 .

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

[0065] Optionally, a multi-hole eye plate 232 is installed in the middle of the boom 23. The multi-hole eye plate 232 has multiple connection holes in sequence along the axial direction of the boom 23, and the driving crane can selectively connect to one of the connection holes. In this arrangement, the driving crane can change the tilt posture of the inner flap 10 in the equilibrium state by selecting the connection holes in different positions.

[0066] Furthermore, the above are only preferred embodiments of the present invention and the technical principles employed. Those skilled in the art will appreciate that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments, and substitutions are possible for those skilled in the art without departing from the scope of the present invention. Therefore, although the present invention has been described in detail through the above embodiments, the present invention is not limited to the above embodiments and may include many other equivalent embodiments without departing from the scope of the present invention. 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 to synchronize the pulley frame trolley on the first slide rail and the pulley frame trolley on the second slide rail in the inner flap (10) to a working position, and maintain a synchronous docking posture with the inner flap (10), while the outer flap is retracted to a zero position and the ground spoiler is supported to a maximum opening; S2. analyzing the posture and center of gravity position of the inner flap (10) when 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 the installation location; S5, connecting the force transmission torque tube (30) installed on the machine body to the first connecting ear (12) of the pulley frame trolley on the first slide rail; S6. By lowering the crane, the second connecting ear (13) of the pulley frame trolley on the second slide rail is aligned with and connected to the third connecting ear (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 face of the blocking piece is flush with the end face of the inner flap (10).

4. A lifting device, used in the aircraft inner flap lifting method according to claim 2, characterized in that: The hanger (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) one by one.

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), 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).

7. The spreader 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 spreader according to claim 7, characterized in that: The utility model also comprises 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) in a one-to-one manner, 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 spreader 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 spreader 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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