Lifting tool for maintenance operation of light airplane

Abstract

The utility model discloses a lifting tool for light aircraft maintenance operation, and relates to the technical field of light aircraft maintenance equipment. A plurality of groups of liftable fuselage lifting mechanisms are arranged on the base frame along the lengthwise direction of the fuselage of the aircraft at intervals; a plurality of sets of liftable wing lifting mechanisms are arranged on the base frame in the transverse width direction of aircraft wings at intervals, and the wing lifting mechanisms are independent of the aircraft body lifting mechanism. The aircraft body lifting mechanism and the wing lifting mechanism are independently arranged, so that asynchronous lifting of the aircraft body and the wings is achieved, flexibility and convenience are improved, different requirements are met, meanwhile, overturning of the light aircraft in the maintenance process is prevented, and safety is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of light aircraft maintenance equipment, and particularly to a lifting tooling for light aircraft maintenance operations. Background Technique

[0002] The fuselage of a light aircraft is about 6 - 8 m long, about 2.3 - 2.8 m high, with a wingspan of about 8 - 11 m, an empty weight of about 350 - 500 kg, and has about 2 - 6 seats. It is a common private aircraft and training aircraft, such as cessna 172 aircraft or PA - 44 - 180 aircraft, etc. For the damaged maintenance of such aircraft during their service life, there is no need to enter a specific dockyard for maintenance like large aircraft such as Boeing and Airbus, and the technical requirements for the maintenance site and facilities are relatively low.

[0003] In light aircraft maintenance operations, jacks are usually used to lift specific parts of the aircraft at specific positions. However, when lifting the fuselage, it is easy to cause the aircraft to overturn, and the position of the jack remains unchanged, which is greatly restricted by the site, indicating that its convenience and safety are relatively low.

[0004] The Chinese patent document discloses a technology with the name of "a special aircraft bracket for aviation maintenance", the publication number of CN217230121U, and the publication date of August 19, 2022. In this technology, the aircraft is lifted by two groups of symmetric lifting components, and at the same time, through the auxiliary components, the staff can be sent to different height positions of the aircraft for maintenance. However, since the lifting components lift the aircraft fuselage and the wing part of the aircraft is not lifted, during the aircraft maintenance process, when removing or replacing components, the structural center of gravity of the aircraft is likely to change, increasing the risk of the aircraft overturning, indicating that its safety is relatively low. Content of the Utility Model

[0005] The technical object of the utility model is to provide a lifting tooling for light aircraft maintenance operations with relatively high convenience and safety, aiming at the deficiencies of the above - mentioned existing technologies.

[0006] The technical solution adopted by the utility model is as follows:

[0007] A lifting tooling for light aircraft maintenance operations includes a base frame;

[0008] On the base frame, along the longitudinal length direction of the aircraft fuselage, multiple groups of liftable fuselage lifting mechanisms are arranged at intervals;

[0009] On the base frame, along the transverse width direction of the aircraft wing, multiple groups of liftable wing lifting mechanisms are arranged at intervals, and the wing lifting mechanisms are independent of the fuselage lifting mechanisms.

[0010] The above technical measures achieve asynchronous lifting of the fuselage and the wings by independently arranging a fuselage lifting mechanism and a wing lifting mechanism, which is beneficial to improving flexibility and convenience, meeting different requirements, and at the same time is beneficial to preventing the light aircraft from tipping over during maintenance, thereby improving safety.

[0011] Further, the wing lifting mechanism is divided into two groups disposed on the left and right sides of the base frame, and the two groups of wing lifting mechanisms and the fuselage lifting mechanism on the base frame form a cross-shaped mating relationship in the top view direction.

[0012] The above technical measures form a cross-shaped mating relationship between the two groups of wing lifting mechanisms and the fuselage lifting mechanism in the top view direction, which is beneficial to enhancing the structural stability.

[0013] Further, the wing lifting mechanism has a support bottom plate, and a liftable structure formed with protrusions is connected to the support bottom plate;

[0014] A plurality of sets of traveling wheels are connected to the bottom of the support bottom plate;

[0015] The inner end of the support bottom plate is assembled on the corresponding side of the base frame with a linear slide rail structure, and the support bottom plate can linearly displace along the longitudinal direction of the base frame through the bottom traveling wheels.

[0016] The above technical measures can adjust the position of the support bottom plate according to the type of the wing by assembling the inner end of the support bottom plate on the corresponding side of the base frame with a linear slide rail structure and arranging a plurality of sets of traveling wheels at the bottom of the support bottom plate, thereby improving flexibility and convenience.

[0017] Further, the wing lifting mechanism has two guide columns two formed with protrusions and arranged at intervals on the top of the support bottom plate, a hydraulic cylinder two located between the two guide columns two, and a wing support plate assembled between the two guide columns two with a linear slide rail structure and connected to the hydraulic cylinder two;

[0018] The bottom end of the hydraulic cylinder two is supported on the top of the support bottom plate;

[0019] During the vertical extension / retraction of the hydraulic cylinder two, the wing support plate rises / falls along the linear slide rail structure of the two guide columns two.

[0020] The above technical measures control the lifting of the wing support plate through the extension and retraction of the hydraulic cylinder two, realizing the lifting of the aircraft wing, and ensuring the stability of the wing support plate during the lifting process by making the wing support plate rise / fall along the linear slide rail structure of the two guide columns two.

[0021] Further, the wing support plate is composed of a guide plate and a panel, and the overall structure is a T-shaped structure;

[0022] The wing support plate is slidably assembled between two second guiding columns through the guiding plate, and the panel of the wing support plate is located above the two second guiding columns;

[0023] When lifting the aircraft wing, the panel of the wing support plate contacts the aircraft wing through a flexible gasket.

[0024] In the above technical measures, the wing support plate is integrally in a T-shaped structure, which is beneficial to enhancing stability; by arranging a flexible gasket on the panel of the wing support plate, damage to the skin of the light aircraft wing during the maintenance process can be avoided.

[0025] Further, the support bottom plate of the wing lifting mechanism has multiple groups of column connection positions arranged at intervals, and each group of column connection positions forms a cooperation relationship with different distances from the base frame;

[0026] The bottom ends of the two second guiding columns are detachably connected to the corresponding column connection positions of the support bottom plate.

[0027] The above technical measures can adjust the installation positions of the second guiding columns according to the type of the wing by arranging multiple groups of column connection positions on the support bottom plate and making the second guiding columns and the support bottom plate detachably connected, which is beneficial to improving flexibility and convenience.

[0028] Further, the fuselage lifting mechanisms on the base frame are three groups arranged at the front side, middle side and rear side along the longitudinal direction of the base frame.

[0029] The above technical measures realize the balanced support of the fuselage through the three groups of fuselage lifting mechanisms arranged at the front side, middle side and rear side, which is beneficial to improving stability.

[0030] Further, the fuselage lifting mechanism has two first guiding columns which are convexly formed on the top of the base frame and arranged at intervals, a first hydraulic cylinder located between the two first guiding columns, and a fuselage support plate which is assembled between the two first guiding columns in a linear slide rail structure and is connected to the first hydraulic cylinder;

[0031] The bottom end of the first hydraulic cylinder is supported on the base frame;

[0032] During the vertical extension / retraction of the first hydraulic cylinder, the fuselage support plate rises / falls along the linear slide rail structure of the two first guiding columns.

[0033] The above technical measures control the lifting and lowering of the fuselage support plate through the extension and retraction of the first hydraulic cylinder, realizing the lifting of the aircraft fuselage, and ensuring the stability of the fuselage support plate during the lifting and lowering process by making the fuselage support plate rise / fall along the linear slide rail structure of the two first guiding columns.

[0034] Further, the top of the fuselage support plate has a bearing surface with an arc-shaped concave structure, and the bearing surface of the fuselage support plate matches the contour structure of the corresponding section at the bottom of the aircraft fuselage;

[0035] When lifting the aircraft fuselage, the bearing surface of the fuselage support plate contacts the aircraft wing through a flexible gasket.

[0036] By setting the bearing surface of the fuselage support plate as an arc-shaped concave structure, the above technical measures make the bearing surface match the contour of the corresponding section at the bottom of the fuselage, which is beneficial to preventing the fuselage from tipping over and improving safety and stability; by setting a flexible gasket on the bearing surface of the fuselage support plate, damage to the skin of the light aircraft fuselage during the maintenance process can be avoided.

[0037] Further, the base frame is a truss structure;

[0038] Multiple groups of walking wheels are arranged at the bottom of the base frame;

[0039] A traction operation handle is assembled at the front end of the base frame, and the traction operation handle is used to apply thrust / pull force to the base frame.

[0040] By setting the traction operation handle, the above technical measures enable the tooling to be moved to a suitable position according to requirements, which is beneficial to improving flexibility and convenience; by setting the base frame as a truss structure, the material consumption is reduced while meeting the structural strength, which is beneficial to cost savings; by setting multiple groups of walking wheels, the tooling can be moved more conveniently, improving convenience and being beneficial to improving work efficiency.

[0041] One or more technical solutions provided by the present utility model have at least the following technical effects or advantages:

[0042] By independently setting the fuselage lifting mechanism and the wing lifting mechanism, asynchronous lifting of the fuselage and the wing is achieved, which is beneficial to improving flexibility and convenience, meeting different requirements, and at the same time is beneficial to preventing the light aircraft from tipping over during the maintenance process and improving safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] The drawings described herein are used to provide a further understanding of the embodiments of the present utility model and constitute a part of the present utility model, but do not limit the embodiments of the present utility model;

[0044] Figure 1 It is a schematic structural diagram of a lifting tooling for light aircraft maintenance operations in the present utility model;

[0045] Figure 2 It is a schematic structural diagram when the lifting tooling for light aircraft maintenance operations in the present utility model is in use;

[0046] Among them, 1 - base frame; 2 - fuselage lifting mechanism; 21 - first guiding column; 22 - fuselage support plate; 23 - first hydraulic cylinder; 3 - wing lifting mechanism; 31 - second guiding column; 32 - wing support plate; 33 - second hydraulic cylinder; 34 - support bottom plate; 4 - walking wheels; 5 - traction operating handle; 6 - support rod. Detailed implementation manners

[0047] In order to more clearly understand the above - mentioned objects, features and advantages of the present utility model, the present utility model will be further described in detail below with reference to the drawings and specific implementation manners. It should be noted that, without conflict, the embodiments of the present utility model and the features in the embodiments can be combined with each other.

[0048] In the following description, many specific details are set forth in order to fully understand the present utility model. However, the present utility model can also be implemented in other ways different from those described within the scope hereof. Therefore, the protection scope of the present utility model is not limited by the specific embodiments disclosed below.

[0049] Referring to Figure 1-2 , this embodiment provides a lifting tooling for light - aircraft maintenance operations, including a base frame 1;

[0050] On the base frame 1, along the longitudinal length direction of the aircraft fuselage, multiple groups of lift - able fuselage lifting mechanisms 2 are arranged at intervals;

[0051] On the base frame 1, along the transverse width direction of the aircraft wing, multiple groups of lift - able wing lifting mechanisms 3 are arranged at intervals, and the wing lifting mechanisms 3 are independent of the fuselage lifting mechanisms 2.

[0052] Among them, each group of fuselage lifting mechanisms 2 and each group of wing lifting mechanisms 3 can be independently controlled to lift.

[0053] The wing lifting mechanisms 3 are two groups respectively arranged on the left and right sides of the base frame 1, and the two groups of wing lifting mechanisms 3 and the fuselage lifting mechanisms 2 on the base frame 1 form a cross - shaped cooperation relationship in the top - view direction.

[0054] The wing lifting mechanism 3 has a support bottom plate 34, and a lift - able structure formed by protrusions is connected to the support bottom plate 34;

[0055] Multiple groups of walking wheels 4 are connected to the bottom of the support bottom plate 34;

[0056] Among them, six groups of walking wheels are connected to the bottom of the support bottom plate 34;

[0057] The inner end of the support bottom plate 34 is assembled on the corresponding side of the base frame 1 in a linear slide - rail structure, and the support bottom plate 34 can linearly displace along the longitudinal length direction of the base frame 1 through the bottom walking wheels 4.

[0058] The wing lifting mechanism 3 has two second guiding columns 31 that are integrally formed and protrude from the top of the support base plate 34 and are arranged at intervals, a second hydraulic cylinder 33 disposed between the two second guiding columns 31, and a wing support plate 32 that is assembled between the two second guiding columns 31 in a linear slide rail structure and is connected to the second hydraulic cylinder 33;

[0059] The bottom end of the second hydraulic cylinder 33 is supported on the top of the support base plate 34;

[0060] During the vertical extension / retraction of the second hydraulic cylinder 33, the wing support plate 32 rises / falls along the linear slide rail structure of the two second guiding columns 31.

[0061] The wing support plate 32 is composed of a guiding plate and a panel, and the overall structure is T-shaped;

[0062] Wherein, one end of the panel is provided with a bending structure, so that the panel can better fit wings of different shapes, improving stability and convenience.

[0063] The wing support plate 32 is slidably assembled between the two second guiding columns 31 through the guiding plate, and the panel of the wing support plate 32 is located above the two second guiding columns 31;

[0064] When lifting the aircraft wing, the panel of the wing support plate 32 contacts the aircraft wing through a flexible gasket.

[0065] Wherein, the flexible gasket can be sponge, rubber, etc.

[0066] The support base plate 34 of the wing lifting mechanism 3 has multiple groups of column connection positions arranged at intervals, and each group of column connection positions forms a cooperation relationship with different distances from the base frame 1;

[0067] Among them, the support base plate 34 has 20 groups of column connection positions.

[0068] The bottom ends of the two second guiding columns 31 are detachably connected to the corresponding column connection positions of the support base plate 34.

[0069] Wherein, the second guiding column 31 is connected to the support base plate 34 through bolts.

[0070] The fuselage lifting mechanisms 2 on the base frame 1 are three groups arranged at the front side, middle side, and rear side along the longitudinal direction of the base frame 1.

[0071] The fuselage lifting mechanism 2 has two first guiding columns 21 that are integrally formed and protrude from the top of the base frame 1 and are arranged at intervals, a first hydraulic cylinder 23 disposed between the two first guiding columns 21, and a fuselage support plate 22 that is assembled between the two first guiding columns 21 in a linear slide rail structure and is connected to the first hydraulic cylinder 23;

[0072] The bottom end of the first hydraulic cylinder 23 is supported on the base frame 1;

[0073] During the vertical extension / retraction of the first hydraulic cylinder 23, the fuselage support plate 22 rises / falls along the linear slide rail structure of the two first guide columns 21.

[0074] Among them, the top of each first guide column 21 is connected with two support rods 6, and a triangular support cooperation structure is formed among the base frame 1, the support rods 6 and the first guide columns 21, which is beneficial to enhancing the structural stability.

[0075] The top of the fuselage support plate 22 has a bearing surface with an arc-shaped concave structure, and the bearing surface of the fuselage support plate 22 matches the contour structure of the corresponding section at the bottom of the aircraft fuselage;

[0076] When lifting the aircraft fuselage, the bearing surface of the fuselage support plate 22 contacts the aircraft wing through a flexible gasket.

[0077] Among them, the flexible gasket can be sponge, rubber, etc.

[0078] The base frame 1 is a truss structure;

[0079] Multiple groups of walking wheels 4 are arranged at the bottom of the base frame 1;

[0080] A traction operation handle 5 is assembled at the front end of the base frame 1, and the traction operation handle 5 is used to apply thrust / pull force to the base frame 1.

[0081] Among them, 10 groups of walking wheels 4 are arranged at the bottom of the base frame 1.

[0082] During use, the staff operates the traction operation handle 5, uses the walking wheels 4 to move the tooling under the light aircraft to be repaired and adjusts it to a suitable position, adjusts the support bottom plate 34 to a suitable position according to the type of the light aircraft to be repaired and the type of the wing, and then adjusts the positions of the second guide columns 31, the second hydraulic cylinders 33 and the wing support plates 32 to match the type of the wing of the light aircraft to be repaired. Operate each first hydraulic cylinder 23 and the second hydraulic cylinders 33 to make each fuselage support plate 22 and the wing support plates 32 move upward, so as to lift the light aircraft to be repaired and complete the lifting of the light aircraft; the transfer of the aircraft to be repaired can be realized by operating the traction operation handle 5. During the repair process, according to the repair requirements, the staff can operate each first hydraulic cylinder 23 and the second hydraulic cylinders 33 to adjust the height positions of the wing support plates 32 and the fuselage support plates 22 in a non-synchronous lifting manner.

[0083] Although the preferred embodiments of the present invention have been described, those skilled in the art can make additional changes and modifications to these embodiments once they know the basic creative concept. Therefore, the appended claims are intended to be construed as including the preferred embodiments and all changes and modifications falling within the scope of the present invention.

[0084] Obviously, those skilled in the art can make various modifications and variations to the present utility model without departing from the spirit and scope of the present utility model. Thus, if these modifications and variations of the present utility model fall within the scope of the claims of the present utility model and their equivalent technologies, the present utility model is also intended to include these modifications and variations.

Claims

1. A lifting tooling for light aircraft maintenance operations, comprising a base frame (1); On the base frame (1), along the longitudinal direction of the aircraft fuselage, multiple groups of liftable fuselage lifting mechanisms (2) are arranged at intervals; It is characterized in that: On the base frame (1), along the transverse width direction of the aircraft wing, multiple groups of liftable wing lifting mechanisms (3) are arranged at intervals, and the wing lifting mechanisms (3) are independent of the fuselage lifting mechanisms (2).

2. The lifting tooling for light aircraft maintenance operations according to claim 1, characterized in that: The wing lifting mechanisms (3) are two groups respectively arranged on the left and right sides of the base frame (1), and the two groups of wing lifting mechanisms (3) and the fuselage lifting mechanisms (2) on the base frame (1) form a cross-shaped matching relationship in the top view direction.

3. The lifting tooling for light aircraft maintenance operations according to claim 1 or 2, characterized in that: The wing lifting mechanism (3) has a support bottom plate (34), and a liftable structure formed by protrusions is connected to the support bottom plate (34); Multiple groups of traveling wheels (4) are connected to the bottom of the support bottom plate (34); The inner end of the support bottom plate (34) is assembled on the corresponding side of the base frame (1) with a linear slide rail structure, and the support bottom plate (34) can linearly displace along the longitudinal direction of the base frame (1) through the bottom traveling wheels (4).

4. The lifting tooling for light aircraft maintenance operations according to claim 3, characterized in that: The wing lifting mechanism (3) has two guide columns II (31) formed by protrusions on the top of the support bottom plate (34) and arranged at intervals, a hydraulic cylinder II (33) located between the two guide columns II (31), and a wing support plate (32) assembled between the two guide columns II (31) with a linear slide rail structure and connected to the hydraulic cylinder II (33); The bottom end of the hydraulic cylinder II (33) is supported on the top of the support bottom plate (34); During the vertical extension / retraction of the hydraulic cylinder II (33), the wing support plate (32) rises / falls along the linear slide rail structure of the two guide columns II (31).

5. The lifting tooling for light aircraft maintenance operations according to claim 4, characterized in that: The wing support plate (32) is composed of a guide plate and a panel, and is integrally in a T-shaped structure; The wing support plate (32) is slidably assembled between the two guide columns II (31) through the guide plate, and the panel of the wing support plate (32) is located above the two guide columns II (31); When lifting the aircraft wing, the panel of the wing support plate (32) contacts the aircraft wing through a flexible gasket.

6. The lifting tooling for light aircraft maintenance operations according to claim 4, characterized in that: The support bottom plate (34) of the wing lifting mechanism (3) has multiple groups of column connection positions arranged at intervals, and each group of column connection positions forms a cooperation relationship with different distances from the base frame (1); The bottom ends of the two guide columns II (31) are detachably connected to the corresponding column connection positions of the support bottom plate (34).

7. The lifting tooling for light aircraft maintenance operations according to claim 1 or 2, characterized in that: The fuselage lifting mechanism (2) on the base frame (1) is arranged in three groups at the front side, the middle part, and the rear side along the longitudinal direction of the base frame (1).

8. The lifting tooling for light aircraft maintenance operations according to claim 7, characterized in that: The fuselage lifting mechanism (2) has two first guide columns (21) which are convexly formed at the top of the base frame (1) and arranged at intervals, a first hydraulic cylinder (23) located between the two first guide columns (21), and a fuselage support plate (22) which is assembled between the two first guide columns (21) in a linear slide rail structure and is connected to the first hydraulic cylinder (23); The bottom end of the first hydraulic cylinder (23) is supported on the base frame (1); During the vertical extension / retraction of the first hydraulic cylinder (23), the fuselage support plate (22) rises / falls along the linear slide rail structure of the two first guide columns (21).

9. The lifting tooling for light aircraft maintenance operations according to claim 8, characterized in that: The top of the fuselage support plate (22) has a bearing surface with an arc-shaped concave structure, and the bearing surface of the fuselage support plate (22) matches the contour structure of the corresponding section at the bottom of the aircraft fuselage; When lifting the aircraft fuselage, the bearing surface of the fuselage support plate (22) contacts the aircraft wing through a flexible gasket.

10. The lifting tooling for light aircraft maintenance operations according to claim 1, characterized in that: The base frame (1) is a truss structure; Multiple groups of walking wheels (4) are arranged at the bottom of the base frame (1); A traction operation handle (5) is assembled at the front end of the base frame (1), and the traction operation handle (5) is used to apply thrust / pull force to the base frame (1).

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