Wing assembly angle adjusting device for small aircraft

Abstract

The utility model discloses a small aircraft wing assembling angle adjusting device which comprises a supporting plate, lifting frames are arranged at the two ends of the bottom of the supporting plate, the small aircraft wing assembling angle adjusting device further comprises a lifting plate, an open groove is formed in the middle of the supporting plate in a penetrating mode, and a protective shell is arranged at the bottom of the supporting plate and located at the bottom of the open groove. The lifting plate is located in the protective shell, lifting mechanisms connected with the inner wall of the protective shell are arranged at the two ends of the lifting plate, the middle of the upper end of the lifting plate is connected with the bottom of a bottom plate through a rotating assembly, a wing placing plate is arranged at the upper end of the bottom plate, and side blocks are arranged on the two sides of the bottom plate; threaded rods are arranged at the tops of the side edge blocks correspondingly, and the threaded rods on the two sides vertically penetrate through the two ends of the limiting plate. According to the utility model, parts for limiting the wings of the small aircraft can be hidden in the protective shell, so that direct contact of external factors such as impact is prevented, and the service life is prolonged.

Description

TECHNICAL FIELD

[0001] The utility model relates to wing assembly technical field especially relates to a small airplane wing assembly angle adjusting device. BACKGROUND

[0002] In the manufacturing and maintenance process of small airplane, the wing assembly angle plays a key role in the flight performance of the airplane. The appropriate wing assembly angle can optimize the aerodynamic performance of the airplane, improve the flight stability, maneuverability and fuel efficiency.

[0003] Chinese patent 202222935200.9 provides a small airplane wing assembly angle adjusting device, which comprises a bracket in U-shaped structure, a telescopic lifting column is installed on the upper part of both ends of the bracket, a mounting plate is fixed on the upper part of the telescopic column, a screw sleeve is arranged on the center position of the lower surface of the mounting plate, a rotating rod is connected with the screw sleeve through threads in the inside of the screw sleeve, the upper end of the rotating rod is movably connected with the connecting column below the connecting table through the mounting plate, the upper surface of the connecting table is provided with a wing placing plate matched with the shape of the airplane wing, and the one end of the upper surface of the connecting table is movably installed with a pressing rod through the connecting plate. The utility model can keep a freely movable state when the wing is placed on the connecting table, so that the wing angle can be easily changed when the wing is connected with the fuselage, the butt joint between the wing and the main body of the airplane is completed, the staff does not need to adjust other supporting points, the labor amount is reduced, and the work efficiency is improved.

[0004] However, the angle adjusting device has the following problems: when the parts for limiting the wing are not in actual limiting operation and are in a non-working state, they are easily affected by various external forces from the external environment, which may cause damage to these limiting parts, thereby affecting the subsequent use. SUMMARY

[0005] (I) Utility model purpose

[0006] To solve the technical problems in the background art, the utility model provides a small airplane wing assembly angle adjusting device, which can hide the parts for limiting the small airplane wing in the inside of the protective shell through the lifting mechanism, prevent direct contact with external factors such as impact, and prolong the service life.

[0007] (II) Technical scheme

[0008] The utility model provides a small airplane wing assembly angle adjusting device, including support plate, both ends of support plate bottom are equipped with elevating stand, still include elevating plate, the middle part of support plate is penetrated with the slot, the bottom of support plate and located the bottom of slot is equipped with protective housing, elevating plate is located the inside of protective housing, elevating plate both ends are equipped with the elevating mechanism of with protective housing inner wall connects, elevating plate upper end's middle part is connected with the bottom of bottom plate through rotating component, the upper end of bottom plate is equipped with wing placement plate, both sides of bottom plate are equipped with side block, the top of side block is equipped with threaded rod, both sides threaded rod vertical penetration in both ends of limiting plate, fixed nut is connected with threaded rod outer end face and located the top of limiting plate, the middle part of limiting plate lower extreme is equipped with the pressure block.

[0009] Preferably, the elevating mechanism includes a second transmission rod, a universal ball, a drive motor, a first transmission rod, and a first elevating block. The universal ball is arranged at one end of the elevating plate. The first elevating block is arranged at the other end of the elevating plate. The second transmission rod is arranged between the inner bottom wall of the protective housing and the bottom of the support plate and penetrates the universal ball. The first transmission rod is rotatably connected between the inner bottom wall of the protective housing and the bottom of the support plate and penetrates the first elevating block. The drive motor is arranged at the bottom of the protective housing. The output shaft of the drive motor penetrates the bottom of the protective housing and is coaxially connected with the bottom of the first transmission rod.

[0010] Preferably, the outer end surface of the first transmission rod is threaded, and the first transmission rod is threadedly connected with the first elevating block. The outer end surface of the second transmission rod is smooth, and the second transmission rod is slidably connected with the universal ball.

[0011] Preferably, both sides of the outer end surface of the elevating stand are equipped with auxiliary stands, and the bottom of the auxiliary stand is located on the same plane as the bottom of the elevating stand.

[0012] Preferably, the width of the slot is longer than the width of the wing placement plate, and the length of the slot is greater than the length of the bottom plate and both side side blocks.

[0013] Preferably, the utility model further includes a spring, which is sleeved on the outer end surface of the threaded rod and located between the limiting plate and the side block.

[0014] Preferably, the rotating component includes a mounting block, a universal ball, and a support rod. The mounting block is arranged at the middle part of the lower end surface of the bottom plate. The upper end surface of the elevating plate is connected with the universal ball through the support rod. The universal ball is movably connected in the movable groove of the bottom of the mounting block.

[0015] Compared with the prior art, the above technical scheme of the utility model has the following beneficial technical effects:

[0016] 1、 this small airplane wing assembly angle adjusting device, through starting drive motor, drive motor can drive first transmission rod to rotate, first transmission rod can drive lifting plate to lift along with it through first lifting block when rotating, and lifting plate can drive universal ball to slide and lift on second transmission rod when lifting, so as to ensure the stability of lifting plate lifting, so that when being in non-working state, the component for limiting small airplane wing can be hidden inside protective shell, prevent direct contact of external factors such as impact, prolong service life.

[0017] 2、 this small airplane wing assembly angle adjusting device, by driving the fixed nut on both sides to rotate, so as to drive the limiting plate to descend, so that it can limit the airplane wing of different thickness, improve the applicability. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 The utility model provides a small airplane wing assembly angle adjusting device structural schematic diagram.

[0019] Figure 2 The utility model provides a small airplane wing assembly angle adjusting device perspective view.

[0020] Figure 3 The utility model provides a small airplane wing assembly angle adjusting device Figure 1 The utility model provides a small airplane wing assembly angle adjusting device

[0021] Figure 4 The utility model provides a small airplane wing assembly angle adjusting device Figure 2 The utility model provides a small airplane wing assembly angle adjusting device

[0022] Figure 5 The utility model provides a small airplane wing assembly angle adjusting device internal structure diagram of protective shell.

[0023] Fig. 1 is mounting block, 2 is support rod, 3 is protective shell, 4 is lifting frame, 5 is auxiliary frame, 6 is limiting plate, 7 is pressing block, 8 is bottom plate, 9 is wing placement plate, 10 is slotted, 11 is spring, 12 is side block, 13 is support plate, 14 is drive motor, 15 is fixed nut, 16 is threaded rod, 17 is lifting plate, 18 is first transmission rod, 19 is second transmission rod, 20 is universal ball, 21 is first lifting block, 22 is second lifting block. DETAILED DESCRIPTION

[0024] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to specific embodiments and accompanying drawings. It should be understood that these descriptions are merely exemplary and not intended to limit the scope of this utility model. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concept of this utility model.

[0025] In the description of this utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "front end," "rear end," "both ends," "one end," and "the other end," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0026] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," and "connected," etc., should be interpreted broadly. For example, "connected" can be a fixed connection, such as welding, riveting, or bonding; it can also be a detachable connection, such as threaded connection, keyed connection, or pin 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; or it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0027] like Figures 1-5 As shown, the present invention proposes a small aircraft wing assembly angle adjustment device, including a support plate 13, with lifting frames 4 at both ends of the bottom of the support plate 13 for driving the support plate 13 to move up and down, and a lifting plate 17. A slot 10 is passed through the middle of the support plate 13. A protective shell 3 is provided at the bottom of the support plate 13 and at the bottom of the slot 10. The lifting plate 17 is located inside the protective shell 3. Lifting mechanisms are provided at both ends of the lifting plate 17 and connected to the inner wall of the protective shell 3. The middle of the upper end of the lifting plate 17 is connected to the bottom of the base plate 8 through a rotating component. A wing placement plate 9 is provided at the upper end of the base plate 8. Side blocks 12 are provided on both sides of the base plate 8. Threaded rods 16 are provided at the top of the side blocks 12. The threaded rods 16 on both sides pass vertically through both ends of the limiting plate 6. Fixing nuts 15 are threadedly connected to the outer end face of the threaded rods 16 and located above the limiting plate 6. A pressure block 7 is provided at the middle of the lower end of the limiting plate 6.

[0028] The utility model discloses a small airplane wing installation limiting device, including support plate 13, protective shell 3, wing placing plate 9, limiting plate 6, lifting mechanism, the bottom of support plate 13 is provided with the protective shell 3, the bottom of protective shell 3 is provided with wing placing plate 9, and the bottom of wing placing plate 9 is provided with limiting plate 6, and the bottom of limiting plate 6 is provided with lifting mechanism.

[0029] In an alternative embodiment, the lifting mechanism includes a second transmission rod 19, a universal ball 20, a drive motor 14, a first transmission rod 18, and a first lifting block 21. The universal ball 20 is located at one end of the lifting plate 17, the first lifting block 21 is located at the other end of the lifting plate 17, the second transmission rod 19 is located between the bottom wall of the protective shell 3 and the bottom of the support plate 13 and penetrates the universal ball 20, the first transmission rod 18 is rotationally connected between the bottom wall of the protective shell 3 and the bottom of the support plate 13 and penetrates the first lifting block 21, the drive motor 14 is located at the bottom of the protective shell 3, the output shaft of the drive motor 14 penetrates the bottom of the protective shell 3 and is coaxially connected with the bottom of the first transmission rod 18, the outer end surface of the first transmission rod 18 is threaded, and the first transmission rod 18 is threadedly connected with the first lifting block 21. The outer end surface of the second transmission rod 19 is smooth, and the second transmission rod 19 is slidingly connected with the universal ball 20.

[0030] It should be noted that starting the drive motor 14 can drive the first transmission rod 18 to rotate. When the first transmission rod 18 rotates, it can drive the lifting plate 17 to lift through the first lifting block 21, and the lifting plate 17 can drive the universal ball 20 to slide and lift on the second transmission rod 19 when lifting, thereby ensuring the stability of the lifting plate 17.

[0031] In an alternative embodiment, the outer end surface of the lifting frame 4 is provided with an auxiliary frame 5 on both sides.

[0032] It should be noted that the auxiliary frame 5 on both sides can improve the stability of the lifting frame 4 when placed.

[0033] In an alternative embodiment, the width of the slot 10 is longer than the width of the wing placing plate 9, and the length of the slot 10 is longer than the length of the bottom plate 8 and the two side blocks 12, so as to ensure that the inside of the protective shell 3 can be accessed through the slot 10.

[0034] In an alternative embodiment, a spring 11 is further included, which is sleeved on the outer end surface of the threaded rod 16 and located between the limiting plate 6 and the side block 12.

[0035] It should be noted that when the aircraft wing needs to be placed on the wing placing plate 9, the limiting plate 6 can be supported by the spring 11, so that the limiting plate 6 does not need to be lifted when the aircraft wing is installed; and when the limiting plate 6 is lowered by rotating the fixing nut 15, the spring 11 will contract, and when the limiting of the wing needs to be released, the fixing nut 15 only needs to be rotated in the opposite direction, and the spring 11 will push the limiting plate 6 up to the initial position by using the elastic restoring force.

[0036] In an alternative embodiment, the rotating assembly includes the mounting block 1, the universal ball 20 and the support rod 2, the mounting block 1 is arranged at the middle of the lower end surface of the bottom plate 8, the upper end surface of the lifting plate 17 is connected with the universal ball 20 through the support rod 2, and the universal ball 20 is movably connected in the movable slot at the bottom of the mounting block 1.

[0037] It should be noted that the universal ball 20 moves in the movable slot in the mounting block 1, so as to adjust the position and angle of the limiting wing, so that it can better complete the butt joint with the main body of the aircraft.

[0038] Although the embodiments of the present application have been shown and described, it should be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A small aircraft wing assembly angle adjustment device comprising a support plate (13), both ends of the bottom of the support plate (13) are provided with lifting frames (4), characterized in that, Also include the lifting plate (17), the middle part of the support plate (13) is through the slot (10), the bottom of the support plate (13) and located at the bottom of the slot (10) is equipped with protective shell (3), the lifting plate (17) is located in the protective shell (3) inside, the lifting plate (17) both ends are equipped with lifting mechanism connected with the inner wall of the protective shell (3), the middle part of the lifting plate (17) upper end is connected with the bottom plate (8) bottom through the rotating assembly, the bottom plate (8) upper end is equipped with wing placing plate (9), both sides of the bottom plate (8) are equipped with side block (12), the top of the side block (12) is equipped with threaded rod (16), both sides of the threaded rod (16) are vertically through the both ends of the limiting plate (6), the fixed nut (15) is threadedly connected to the outer end face of the threaded rod (16) and located above the limiting plate (6), the middle part of the limiting plate (6) lower end is equipped with pressure block (7).

2. A small aircraft wing assembly angle adjustment device as claimed in claim 1, wherein, The lifting mechanism comprises a second transmission rod (19), a universal ball (20), a drive motor (14), a first transmission rod (18) and a first lifting block (21), the universal ball (20) is arranged at one end of the lifting plate (17), the first lifting block (21) is arranged at the other end of the lifting plate (17), the second transmission rod (19) is arranged between the inner bottom wall of the protective shell (3) and the bottom of the support plate (13) and penetrates the universal ball (20), the first transmission rod (18) is rotatably connected between the inner bottom wall of the protective shell (3) and the bottom of the support plate (13) and penetrates the first lifting block (21), the drive motor (14) is arranged at the bottom of the protective shell (3), the output shaft of the drive motor (14) penetrates the bottom of the protective shell (3) and is coaxially connected with the bottom of the first transmission rod (18).

3. A small aircraft wing assembly angle adjustment device as claimed in claim 2, wherein, The outer end face of the first transmission rod (18) is threadedly arranged, and the first transmission rod (18) is threadedly connected with the first lifting block (21), the outer end face of the second transmission rod (19) is smoothly arranged, and the second transmission rod (19) is slidingly connected with the universal ball (20).

4. The wing assembly angle adjustment device for a light aircraft as defined in claim 1, wherein, The outer end face of the lifting frame (4) is equipped with auxiliary frame (5) on both sides, and the bottom of the auxiliary frame (5) is located on the same plane as the bottom of the lifting frame (4).

5. The wing assembly angle adjustment device for a light aircraft as defined in claim 1, wherein, The width of the slot (10) is longer than the width of the wing placing plate (9), and the length of the slot (10) is greater than the length of the bottom plate (8) and both sides of the side block (12).

6. A small aircraft wing assembly angle adjustment device as claimed in claim 1, wherein, Also include the spring (11), the spring (11) is sleeved on the outer end face of the threaded rod (16) and located between the limiting plate (6) and the side block (12).

7. The wing assembly angle adjustment device for a light aircraft as defined in claim 1 wherein, The rotating assembly comprises a mounting block (1), a universal ball (20) and a supporting rod (2), the mounting block (1) is arranged at the middle of the lower end surface of the bottom plate (8), the upper end surface of the lifting plate (17) is connected with the universal ball (20) through the supporting rod (2), and the universal ball (20) is movably connected in the movable groove at the bottom of the mounting block (1).

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