Wing overturning equipment for small aircraft

Abstract

The utility model discloses small aircraft wing turnover equipment which comprises a base, universal wheels are arranged on the periphery of the bottom of the base, a limiting assembly is further arranged at the bottom of the base, the small aircraft wing turnover equipment further comprises fixing frames which are oppositely arranged at the upper end of the base, the inner top walls of the fixing frames are connected with the upper end of the base through sliding rods, and the inner top walls of the fixing frames are connected with the upper end of the base through sliding rods. The sliding rods on the two sides vertically penetrate through the two ends of the lifting plate in a sliding mode. A lifting shell is further arranged on the upper end face of the base, a lifting assembly is arranged in the lifting shell, and the lifting end of the lifting assembly is connected with the lifting plate and used for controlling the lifting plate to vertically move up and down; and the outer side of the lifting plate is connected with the mounting frame through a fixing plate. According to the utility model, an operator can drive the flange plate to directly descend to an ideal lowest mounting position, so that the preparation workload before butt joint is reduced, and the efficiency and the safety of the mounting operation of the aircraft wing are improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft installation, especially to a small aircraft wing turnover equipment. BACKGROUND

[0002] At present, in the assembly stage of the small aircraft wing, the vertical posture is usually adopted for operation, which can more effectively utilize the production space, and when the butt joint installation of the fuselage and the wing is involved in the subsequent overall aircraft assembly process, the wing originally in the vertical posture needs to be turned over to the horizontal posture.

[0003] Chinese patent 202022551029.2 discloses a small aircraft wing turnover device, comprising a base frame, a foot jack installed on the base frame, a rotating frame installed on the base frame, the foot jack being connected with the rotating frame for controlling the vertical up-and-down movement of the rotating frame, a wing rotating device installed on the rotating frame, the wing rotating device comprising a rotatable clamp arm, the aircraft wing being detachably installed on the clamp arm, the aircraft wing being turned over through the rotation of the clamp arm, and a control assembly installed on the rotating frame for transmission control of the rotation of the clamp arm. The small aircraft wing turnover device simply controls the lifting and lowering actions of the wing installation, moves the turnover device forward and backward according to the assembly requirements, has strong versatility, and is easy to operate. The wing turnover device has simple and ingenious structure, can be operated by one person, has low labor cost and low manufacturing cost, has high work safety and efficiency, brings huge economic benefits, and is easy to popularize and apply in various aircraft manufacturers.

[0004] The aircraft wing turnover device adjusts the height of the flange plate through the foot jack, but the foot jack cannot lower the flange plate to the ideal lowest position, so it is necessary to use other auxiliary equipment or manual operation to lift the aircraft wing to a certain height, so that the corresponding installation part of the aircraft wing can reach the state of butt joint installation with the flange plate at a higher position, and then the flange plate can be used to install the aircraft wing. This operation method is troublesome and increases the workload, so a small aircraft wing turnover device is proposed to solve the above problems. UTILITY MODEL CONTENTS

[0005] (I) Utility model purpose

[0006] To solve the technical problems in the background art, the utility model provides a small aircraft wing turnover device, which can make the operator drive the flange plate to directly drop to the ideal lowest installation position through the lifting assembly, reduce the preparation workload before butt joint, and improve the efficiency and safety of aircraft wing installation operation.

[0007] (II) Technical scheme

[0008] The utility model provides a kind of small aircraft wing turnover equipment, including base, the periphery of the bottom of base is equipped with universal wheel, the bottom of base is also equipped with limiting assembly, further including the fixed frame of being set to the upper end of base opposite setting, the inner top wall of fixed frame is connected by slide rod between the upper end of base, the both sides slide rod vertical sliding penetrates the both ends of lifting plate;

[0009] The upper end surface of the base is also provided with a lifting shell, and the lifting shell is internally provided with a lifting assembly. The lifting end of the lifting assembly is connected with the lifting plate, for controlling the lifting plate to move vertically up and down.

[0010] The outer side of the lifting plate is connected with the mounting bracket through a fixed plate. The upper end surface of the mounting bracket is connected with a limiting shell through a plurality of second hydraulic push rods distributed at intervals. The limiting shell is internally provided with a rotation stabilizing assembly. A second motor is arranged on the outer end surface of the limiting shell. The output shaft of the second motor is coaxially connected with the clamp arm through the rotation stabilizing assembly.

[0011] Preferably, the limiting assembly comprises a first hydraulic push rod and an anti-skid plate. The bottom of the base is connected with the anti-skid plate through the first hydraulic push rod.

[0012] Preferably, the lifting assembly comprises a first motor, a lifting block, a threaded rod and a connecting block. The first motor is arranged on the upper end surface of the slide rod. The threaded rod is rotatably connected between the inner walls on the upper and lower sides of the slide rod. The output shaft of the first motor penetrates the upper end surface of the slide rod and is coaxially connected with the upper end of the threaded rod. The lifting block is threadedly sleeved on the outer end surface of the threaded rod. One end of the connecting block penetrates the outer end surface of the slide rod and is connected with the outer end surface of the lifting block. The other end of the threaded rod is connected with the lifting plate.

[0013] Preferably, the threaded rod and the slide rods on both sides are arranged in parallel.

[0014] Preferably, the outer end surface of the mounting bracket is provided with a mounting shell. The limiting shell is located in the mounting shell. The outer end surface of the limiting shell is connected with the side blocks on both sides. A plurality of second slide rods vertically slide and penetrate the side blocks on both sides. The both ends of the second slide rods are connected with the mounting bracket.

[0015] Preferably, the rotational stabilization component includes a limiting groove, a limiting wheel, and a drive shaft. The multiple limiting grooves are spaced apart inside the limiting housing. The limiting wheel is rotatably connected to the inside of the limiting groove. The drive shaft passes through the middle of the limiting housing and coaxially passes through the multiple limiting wheels. One end of the drive shaft is coaxially connected to the output shaft of the second motor, and the other end of the drive shaft is coaxially connected to the clamp arm.

[0016] Preferably, the end of the clamp arm away from the limiting housing is provided with a flange for detachable connection to the aircraft wing.

[0017] Compared with the prior art, the above-mentioned technical solution of this utility model has the following beneficial technical effects:

[0018] 1. This small aircraft wing tilting device uses a first motor to drive a threaded rod to rotate. When the threaded rod rotates, it can drive the lifting block to move vertically. When the lifting block moves vertically, it can drive the lifting plate to move vertically through the connecting block. When the lifting plate moves vertically, it can drive the mounting frame to move vertically through the fixed plate. This allows the operator to drive the flange directly to the ideal lowest installation position, reducing the amount of preparation work before docking and improving the efficiency and safety of aircraft wing installation operations.

[0019] 2. In this small aircraft wing tilting device, when the lifting plate is being raised or lowered, the lifting plate can slide vertically on the slide bars on both sides, thereby ensuring the stability of the lifting plate during the raising and lowering process.

[0020] 3. This small aircraft wing flipping device, through multiple second hydraulic push rods, can drive the limiting shell to move up and down for fine adjustment, thereby driving the flange to move up and down for fine adjustment as well. This allows for quick correction and precise adjustment of the wing installation position by making timely adjustments to the flange's up and down movement. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the structure of a small aircraft wing flipping device proposed in this utility model.

[0022] Figure 2 This is a cross-sectional view of the lifting component in a small aircraft wing flipping device proposed in this utility model.

[0023] Figure 3 This is a diagram showing the internal structure of the housing in a small aircraft wing-flipping device proposed in this utility model.

[0024] Figure 4 This is a cross-sectional view of the limiting shell in a small aircraft wing flipping device proposed in this utility model.

[0025] Mark No. : 1, first motor; 2, lifting plate; 3, fixed frame; 4, lifting shell; 5, sliding rod; 6, first hydraulic push rod; 7, anti-skid plate; 8, base; 9, universal wheel; 10, fixed plate; 11, mounting shell; 12, clamp arm; 13, flange plate; 14, lifting block; 15, threaded rod; 16, connecting block; 17, second motor; 18, limiting shell; 19, mounting frame; 20, second hydraulic push rod; 21, second sliding rod; 22, side block; 23, limiting groove; 24, limiting rotating wheel; 25, transmission shaft. DETAILED DESCRIPTION

[0026] To make the purpose, technical scheme and advantages of the utility model clearer and more intelligible, the utility model will be further described in detail below in combination with specific implementation manners and with reference to the drawings. It should be understood that these descriptions are only exemplary and are not intended to limit the scope of the utility model. In addition, in the following description, the description of known structures and technologies is omitted to avoid unnecessary confusion of the concept of the utility model.

[0027] In the description of the utility model, it should be pointed out that the orientation or position relationship indicated by the terms "upper", "lower", "inner", "outer", "front end", "rear end", "two ends", "one end" and "the other end" is based on the orientation or position relationship shown in the drawings, and is only for the convenience of describing the utility model and simplifying the description, and therefore cannot be understood as limiting the utility model in a specific orientation, construction and operation. Therefore, it cannot be understood as limiting the utility model. In addition, the terms "first" and "second" are only for the purpose of description and cannot be understood as indicating or implying relative importance.

[0028] In the description of the utility model, it should be pointed out that unless otherwise explicitly specified and limited, the terms "mounting", "provided with", "connection" and the like should be understood broadly, for example, "connection" can be fixed connection, welding, riveting, bonding and the like, or can be detachable connection, threaded connection, key connection, pin connection and the like, or integral connection; can be mechanical connection or electrical connection; can be directly connected or indirectly connected through an intermediate medium; can be the communication between two elements. For ordinary skilled persons in the art, the specific meaning of the above terms in the utility model can be understood according to the specific circumstances.

[0029] As Figures 1-4 shown, the utility model provides a kind of small aircraft wing turnover equipment, including base 8, the periphery of the bottom of base 8 is equipped with universal wheel 9, the bottom of base 8 is also equipped with limiting component, it also includes the fixed frame 3 of setting to the upper end of base 8 relative setting, the inner top wall between fixed frame 3 and the upper end of base 8 is connected by sliding rod 5, two sides sliding rod 5 vertically sliding penetrates the two ends of lifting plate 2;

[0030] The upper end face of the base 8 is further provided with a lifting shell 4, the inside of the lifting shell 4 is provided with a lifting assembly, the lifting end of the lifting assembly is connected with the lifting plate 2, and the lifting plate 2 is used for controlling vertical up-down movement of the lifting plate 2.

[0031] The outer side of the lifting plate 2 is connected with the mounting frame 19 through the fixed plate 10, the upper end face of the mounting frame 19 is connected with the limiting shell 18 through a plurality of second hydraulic push rods 20 which are distributed at intervals, the inside of the limiting shell 18 is provided with a rotation stabilizing assembly, the outer end face of the limiting shell 18 is provided with the second motor 17, the output shaft of the second motor 17 is coaxially connected with the clamp arm 12 through the rotation stabilizing assembly, and the end, away from the limiting shell 18, of the clamp arm 12 is provided with a flange plate 13 which can be detachably connected with the airplane wing, wherein the airplane wing can be installed through the flange plate 13.

[0032] In the utility model, when in use, the lifting plate 2 is first lowered to the ideal lowest installation position through the lifting assembly, then the small airplane wing is installed through the flange plate 13, then the lifting plate 2 is lifted to the position for installing the airplane body through the lifting assembly, then the rotation stabilizing assembly is rotated through the second motor 17, the small airplane wing installed on the flange plate 13 can be rotated through the clamp arm 12 of the rotation stabilizing assembly, and finally the small airplane wing can be installed; and the side block 22 can be adjusted up and down through a plurality of second hydraulic push rods 20 to quickly correct and finely adjust the wing installation position.

[0033] In an optional embodiment, the limiting assembly comprises the first hydraulic push rod 6 and the antiskid plate 7, and the bottom of the base 8 is connected with the antiskid plate 7 through the first hydraulic push rod 6.

[0034] It should be noted that, in order to prevent the base 8 from sliding when being moved through the plurality of universal wheels 9, the first hydraulic push rod 6 can be started to drive the antiskid plate 7 to descend and contact the ground, thereby preventing the base 8 from sliding.

[0035] In an optional embodiment, the lifting assembly comprises the first motor 1, the lifting block 14, the threaded rod 15 and the connecting block 16, the first motor 1 is arranged on the upper end face of the slide rod 5, the threaded rod 15 is rotationally connected between the inner walls on the upper and lower sides of the slide rod 5, the output shaft of the first motor 1 penetrates the upper end face of the slide rod 5 and is coaxially connected with the upper end of the threaded rod 15, the lifting block 14 is threadedly sleeved on the outer end face of the threaded rod 15, one end of the connecting block 16 penetrates the outer end face of the slide rod 5 and is connected with the outer end face of the lifting block 14, the other end of the threaded rod 15 is connected with the lifting plate 2, and the threaded rod 15 is parallelly arranged between the two slide rods 5.

[0036] It should be noted that the first motor 1 is started, the first motor 1 can drive the threaded rod 15 to rotate, the threaded rod 15 can drive the lifting block 14 to vertically lift when rotating, the lifting block 14 can drive the lifting plate 2 to lift through the connecting block 16 when lifting, and the lifting plate 2 can drive the mounting frame 19 to lift through the fixed plate 10 when lifting.

[0037] In an optional embodiment, the outer end surface of the mounting frame 19 is provided with the mounting shell 11, the limiting shell 18 is located inside the mounting shell 11, the outer end surface of the limiting shell 18 is connected with the side blocks 22 on both sides, respectively, a plurality of second sliding rods 21 vertically slide through the side blocks 22 on both sides, and the two ends of the plurality of second sliding rods 21 are connected with the mounting frame 19 on the inner top wall of the mounting shell 11.

[0038] It should be noted that the mounting frame 19 can drive the limiting shell 18 to lift through the plurality of second hydraulic push rods 20 when lifting, so that the limiting shell 18 can be fine-tuned up and down, and when the limiting shell 18 lifts, the side blocks 22 on both sides of the limiting shell 18 can slide and lift on the plurality of second sliding rods 21 connected therewith, thereby ensuring stable lifting of the limiting shell 18.

[0039] In an optional embodiment, the rotation stabilizing assembly comprises a limiting groove 23, a limiting rotating wheel 24 and a transmission shaft 25, a plurality of limiting grooves 23 are spaced apart and arranged inside the limiting shell 18, the limiting rotating wheel 24 is rotatably connected inside the limiting groove 23, the transmission shaft 25 penetrates the middle part of the limiting shell 18, the transmission shaft 25 coaxially penetrates the plurality of limiting rotating wheels 24, one end of the transmission shaft 25 is coaxially connected with the output shaft of the second motor 17, and the other end of the transmission shaft 25 is coaxially connected with the clamp arm 12.

[0040] It should be noted that the second motor 17 is started, the second motor 17 can drive the clamp arm 12 to rotate through the transmission shaft 25, and the transmission shaft 25 can drive the plurality of limiting rotating wheels 24 to rotate in the plurality of limiting grooves 23 connected therewith when rotating, thereby ensuring the stability of the rotation of the clamp arm 12.

[0041] It should be understood that the above specific embodiments of the present application are only used for illustrative or explanatory purposes of the principles of the present application, and do not constitute a limitation on the present application. Therefore, any modification, equivalent replacement, improvement, etc. made without departing from the spirit and scope of the present application shall be included in the protection scope of the present application. In addition, the appended claims of the present application are intended to cover all changes and modifications falling within the scope and boundaries of the appended claims, or the equivalent forms of such scope and boundaries.

Claims

1. A small aircraft wing turnover device, comprising a base (8), the bottom of which is provided with universal wheels (9) around the periphery, and the bottom of which is also provided with a limiting assembly, characterized in that, It also includes the fixed frame (3) arranged at the opposite end of the base (8), the inner top wall of the fixed frame (3) is connected with the upper end of the base (8) through the slide rod (5), and the slide rod (5) on both sides vertically slides through the two ends of the lifting plate (2); The upper end surface of the base (8) is also provided with a lifting shell (4), the lifting shell (4) is provided with a lifting assembly inside, the lifting end of the lifting assembly is connected with the lifting plate (2), and the lifting plate (2) is used for controlling the vertical up and down movement of the lifting plate (2); The outer side of the lifting plate (2) is connected with the mounting frame (19) through the fixed plate (10), the upper end surface of the mounting frame (19) is connected with the limiting shell (18) through a plurality of second hydraulic push rods (20) distributed at intervals, the limiting shell (18) is provided with a rotating stabilizing assembly inside, and a second motor (17) is arranged on the outer end surface of the limiting shell (18), the output shaft of the second motor (17) is coaxially connected with the clamp arm (12) through the rotating stabilizing assembly.

2. A small aircraft wing rollover device according to claim 1 wherein, The limiting assembly includes a first hydraulic push rod (6) and an anti-skid plate (7), and the bottom of the base (8) is connected with the anti-skid plate (7) through the first hydraulic push rod (6).

3. A small aircraft wing rollover device according to claim 1 wherein, The lifting assembly includes a first motor (1), a lifting block (14), a threaded rod (15) and a connecting block (16), the first motor (1) is arranged on the upper end surface of the slide rod (5), the threaded rod (15) is rotatably connected between the inner walls on the upper and lower sides of the slide rod (5), the output shaft of the first motor (1) penetrates the upper end surface of the slide rod (5) and is coaxially connected with the upper end of the threaded rod (15), the lifting block (14) is threadedly sleeved on the outer end surface of the threaded rod (15), one end of the connecting block (16) penetrates the outer end surface of the slide rod (5) and is connected with the outer end surface of the lifting block (14), and the other end of the threaded rod (15) is connected with the lifting plate (2).

4. A small aircraft wing tipping device as claimed in claim 3, wherein, The threaded rod (15) and the slide rod (5) on both sides are arranged in parallel.

5. A small aircraft wing rollover device as defined in claim 1 wherein, The outer end surface of the mounting frame (19) is provided with a mounting shell (11), the limiting shell (18) is located in the mounting shell (11), the outer end surfaces of the limiting shell (18) are connected with the side blocks (22) on both sides respectively, a plurality of second slide rods (21) vertically slide through the side blocks (22) on both sides, and the two ends of the second slide rods (21) are connected with the mounting frame (19) on the inner top wall of the mounting shell (11).

6. A small aircraft wing rollover device as defined in claim 1 wherein, The rotation stabilizing assembly comprises limiting grooves (23), limiting rotating wheels (24) and a transmission shaft (25), multiple limiting grooves (23) are arranged at intervals in the interior of the limiting shell (18), the limiting rotating wheels (24) are rotationally connected to the interior of the limiting grooves (23), the transmission shaft (25) penetrates the middle part of the limiting shell (18), the transmission shaft (25) coaxially penetrates multiple limiting rotating wheels (24), one end of the transmission shaft (25) is coaxially connected with the output shaft of the second motor (17), the other end of the transmission shaft (25) is coaxially connected with the clamp arm (12).

7. A small aircraft wing rollover device as defined in claim 1 wherein, The clamp arm (12) is provided with a flange plate (13) which can be detachably connected with the airplane wing at the end away from the limiting shell (18).

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