A maintenance and fixing device for a civil aircraft radome

Abstract

This utility model relates to the field of civil aircraft maintenance technology, specifically disclosing a maintenance and fixing device for a civil aircraft radome. Multiple flexible pins are arranged in a ring array on a fixing platform. A locking switch is configured to lock the relative positions of the flexible pins and the fixing platform, allowing the pins to grip the radome. Multiple clamping members are arranged circumferentially on the outer periphery of the fixing platform, each clamping member abutting against the outer periphery of the radome. This configuration, introducing multiple flexible pins, a locking switch, and multiple clamping members, allows for both flexible adaptation and rigid locking of the radome structure. It can adapt to the curved shape and size of the radome structure, while the flexible adaptive characteristic ensures extremely high positioning accuracy. It enables precise fitting and stable fixing for repairing radome structures of various specifications and models of aircraft, offering convenient operation and high flexibility, effectively improving the maintenance efficiency and quality of civil aircraft radomes.

Description

Technical Field

[0001] This utility model relates to the field of civil aircraft maintenance technology, and in particular to a maintenance and fixing device for a civil aircraft radome. Background Technology

[0002] With the gradual development and progress of aviation technology, the number of civil aircraft is also increasing. As an essential component of civil aircraft, radar is located at the front of the aircraft. It is the window for electromagnetic waves and is used to protect the antenna and prevent the environment from affecting and interfering with the working state of the radar antenna.

[0003] Existing civil aircraft typically use radomes to provide structural protection for radar devices. Due to their location at the front of the aircraft, these radomes are highly susceptible to accidental damage, resulting in relatively frequent maintenance. Furthermore, since their primary function is to provide structural strength protection for the radar device at the front of the aircraft, radome structures are mostly made of fiberglass composite materials with good wave transmission to ensure strength requirements. Additionally, to ensure good aerodynamic performance, complex and varied curved surface designs are employed. The high probability of damage, the use of fiberglass composite materials, and the complex curved surface shapes make the maintenance of civil aircraft radome structures more difficult and complex, especially during off-site maintenance. Existing fixing methods cannot achieve stable positioning of the radome structure, easily leading to positioning deviations and significantly reducing subsequent maintenance efficiency and quality.

[0004] Therefore, there is an urgent need for a maintenance and fixing device for civil aircraft radomes to solve the above problems. Utility Model Content

[0005] The purpose of this invention is to provide a maintenance and fixing device for civil aircraft radomes, which can effectively improve the maintenance quality and efficiency of civil aircraft radomes.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] This utility model provides a maintenance and fixing device for a civil aircraft radome, comprising:

[0008] Fixed platform;

[0009] A clamping and fixing assembly includes a plurality of flexible pins, a locking switch, and a plurality of clamping members. The plurality of flexible pins are arranged in a circular array on the fixing platform. The locking switch is configured to lock the relative position between the plurality of flexible pins and the fixing platform so that the plurality of flexible pins grip the radar dome located therein. The plurality of clamping members are arranged circumferentially on the outer peripheral wall of the fixing platform, and each clamping member is used to abut against the outer peripheral edge of the radar dome.

[0010] As a preferred technical solution for the maintenance and fixing device of the aforementioned civil aircraft radome, the top of the flexible pin has a contact head, which is used to fit the radome, and the contact head is made of rubber material.

[0011] As a preferred technical solution for the maintenance and fixing device of the aforementioned civil aircraft radome, the maintenance and fixing device of the civil aircraft radome further includes a plurality of mounting ears, which protrude from the outer peripheral wall of the fixing platform. The plurality of mounting ears are correspondingly provided with a plurality of clamping members. The clamping members include a first clamping arm and a second clamping arm. One end of the first clamping arm is rotatably connected to the mounting ear, and the other end of the first clamping arm is fixedly connected to the second clamping arm. The second clamping arm is used to abut against the outer peripheral edge of the radome.

[0012] As a preferred technical solution for the maintenance and fixing device of the aforementioned civil aircraft radome, the clamping and fixing assembly further includes multiple locking members, each of which is correspondingly arranged with one of the multiple first clamping arms, and the locking members are used to lock or unlock the relative position between the first clamping arms and the mounting ears.

[0013] As a preferred technical solution for the maintenance and fixing device of the aforementioned civil aircraft radome, the maintenance and fixing device of the civil aircraft radome further includes several lifting components, all of which are tractively connected to the fixing platform and can drive the fixing platform to move in the vertical direction.

[0014] As a preferred technical solution for the maintenance and fixing device of the aforementioned civil aircraft radome, the maintenance and fixing device of the civil aircraft radome further includes a movable support assembly. The movable support assembly includes a support platform and a plurality of rollers. The plurality of rollers are rotatably connected to the support platform and supported on the ground. The plurality of lifting components are connected between the support platform and the fixed platform.

[0015] As a preferred technical solution for the maintenance and fixing device of the aforementioned civil aircraft radome, the lifting assembly includes a first shearing rod, a second shearing rod, a pulley, and a first driving member. The first shearing rod and the second shearing rod are hinged to each other. The pulley is rotatably connected to one end of the first shearing rod and rolls in contact with the support platform. The other end of the first shearing rod is hinged to the fixed platform. The two ends of the second shearing rod are respectively hinged to the fixed platform and the support platform. The first driving member is driven to the first shearing rod or the second shearing rod so that the first shearing rod and the second shearing rod can open or close, thereby driving the fixed platform to move in the vertical direction.

[0016] As a preferred technical solution for the maintenance and fixing device of the aforementioned civil aircraft radome, the first driving component is a hydraulic cylinder.

[0017] As a preferred technical solution for the maintenance and fixing device for the aforementioned civil aircraft radome, the maintenance and fixing device for the civil aircraft radome further includes a second driving component, which is fixedly mounted on the support platform, and the output end of the second driving component can drive the fixing platform to rotate.

[0018] As a preferred technical solution for the maintenance and fixing device of the aforementioned civil aircraft radome, the second driving component is a hydraulic cylinder.

[0019] The beneficial effects of this utility model are as follows:

[0020] This invention provides a maintenance and fixing device for civil aircraft radomes. The device includes a fixing platform and a clamping and fixing assembly. The clamping and fixing assembly includes multiple flexible pins, a locking switch, and multiple clamping members. The flexible pins are arranged in a circular array on the fixing platform. The locking switch is configured to lock the relative positions of the flexible pins and the fixing platform, allowing the flexible pins to grip the radome within them. The clamping members are arranged circumferentially on the outer periphery of the fixing platform, with each clamping member abutting against the outer periphery of the radome. This arrangement, with multiple flexible pins, a locking switch, and multiple clamping members, allows for sequential flexible adaptation and rigid locking of the radome structure. It can adapt to the curved shape and size of the radome structure, while the flexible adaptive characteristic ensures extremely high positioning accuracy. This enables precise fitting and stable fixing for repairing radome structures of various specifications and models of aircraft. The device is highly convenient and flexible, effectively improving the maintenance efficiency and quality of civil aircraft radomes. Attached Figure Description

[0021] Figure 1 A schematic diagram of the structure of the maintenance and fixing device for the radome of a civil aircraft provided by this utility model;

[0022] Figure 2 Partial structural diagram of the maintenance and fixing device for civil aircraft radomes provided by this utility model. Figure 1 ;

[0023] Figure 3 Partial structural diagram of the maintenance and fixing device for civil aircraft radomes provided by this utility model. Figure 2 .

[0024] in:

[0025] 1. Fixed platform; 2. Flexible pin; 3. Locking switch;

[0026] 4. Clamping component; 41. First clamping arm; 42. Second clamping arm;

[0027] 5. Mounting ear; 6. Locking element; 7. Support platform; 8. Roller; 9. First shearing rod; 10. Second shearing rod; 11. Pulley; 12. First driving element; 13. Second driving element. Detailed Implementation

[0028] The embodiments of this utility model are described in detail below. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model.

[0029] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are 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, and therefore should not be construed as a limitation of 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. The terms "first position" and "second position" refer to two different positions.

[0030] Unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing" should be interpreted broadly. For example, they can refer to fixed connections or detachable connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and connections within two components or interactions between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0031] Unless otherwise expressly specified and limited, "above" or "below" a second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of a second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" of a second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0032] The technical solution of this utility model will be further described below with reference to the accompanying drawings and specific embodiments.

[0033] like Figures 1 to 3 As shown, this embodiment provides a maintenance and fixing device for a civil aircraft radome. The device includes a fixing platform 1 and a clamping and fixing assembly. The clamping and fixing assembly includes multiple flexible pins 2, a locking switch 3, and multiple clamping members 4. The multiple flexible pins 2 are arranged in a circular array on the fixing platform 1. The locking switch 3 is configured to lock the relative position between the multiple flexible pins 2 and the fixing platform 1, so that the multiple flexible pins 2 tightly grip the radome located therein. The multiple clamping members 4 are arranged circumferentially on the outer peripheral wall of the fixing platform 1, and each clamping member 4 is used to abut against the outer peripheral edge of the radome. This configuration, introducing multiple flexible pins 2 and locking switches 3 in conjunction with multiple clamping members 4, allows for sequential flexible adaptation and rigid locking of the radome structure. It can adapt to the curved shape and size of the radome structure, while the flexible adaptive characteristic ensures extremely high positioning accuracy. It can achieve precise fitting and stable fixing for repairing radome structures of various specifications and models of aircraft, offering convenient operation and high flexibility, effectively improving the maintenance efficiency and quality of civil aircraft radomes.

[0034] It should be noted that the operator places the radome in the central area surrounded by multiple flexible pins 2 in a ring array. Because the surface of the radome is irregular, when it is placed in, its surface contacts the tops of each flexible pin 2. Under the radome's own weight or a slight initial pressure, the contour of the radome pushes the flexible pins 2 in contact with its protruding parts, causing them to retract radially outward. Simultaneously, the flexible pins 2 facing the recessed parts of the radome, under the action of spring force or their own weight, remain in place or extend further radially inward. The locking switch 3 is a central mechanism that controls the simultaneous locking of all flexible pins 2. It is typically a rotating handle, lever, or screw. Its function is to deprive all flexible pins 2 of their independent movement, making them a rigid whole, completely eliminating the ability of each flexible pin 2 to move independently. In other words, the previously freely movable "array of flexible pins 2" instantly transforms into a locked and fixed-shape rigid clamp tailored to the current radome. When it is necessary to remove the workpiece, simply release the locking switch 3. The locking force is released, and the array of flexible pins 2 returns to the "flexible" state. The operator can easily remove the radar dome. The flexible pins 2 may also be pushed back by the spring or when the workpiece is placed again, returning to the initial state and ready to clamp the next part.

[0035] Optionally, the top of the flexible pin 2 has a contact head for fitting the radome, and the contact head is made of rubber. This design can, to some extent, prevent secondary damage such as scratches and bumps to the radome structure. At the same time, the high coefficient of friction of the rubber material can provide a certain degree of restraint on the radome structure.

[0036] Optionally, in order to assist in fixing the radome structure and further enhance its fixing and clamping effect, the maintenance and fixing device for the civil aircraft radome also includes multiple mounting ears 5. The multiple mounting ears 5 protrude from the outer peripheral wall of the fixing platform 1. The multiple mounting ears 5 are correspondingly arranged with multiple clamping members 4. The clamping member 4 includes a first clamping arm 41 and a second clamping arm 42. The first clamping arm 41 and the second clamping arm 42 are vertically connected. One end of the first clamping arm 41 is rotatably connected to the mounting ear 5, and the other end of the first clamping arm 41 is fixedly connected to the second clamping arm 42. The second clamping arm 42 is used to abut against the outer peripheral edge of the radome.

[0037] Optionally, the clamping and fixing assembly also includes a plurality of locking members 6, which are configured one-to-one with a plurality of first clamping arms 41, and the locking members 6 are used to lock or unlock the relative position between the first clamping arms 41 and the mounting ears 5.

[0038] Optionally, in order to meet the operational needs of maintenance personnel of different heights and greatly improve the convenience, comfort and efficiency of maintenance personnel in repairing the radome structure, the maintenance fixing device for civil aircraft radomes also includes several lifting components. The lifting components are all connected to the fixing platform 1 and can drive the fixing platform 1 to move in the vertical direction.

[0039] Optionally, to facilitate the real-time movement and transfer of the maintenance and fixing device for the civil aircraft radome, the maintenance and fixing device for the civil aircraft radome also includes a movable support assembly. The movable support assembly includes a support platform 7 and several rollers 8. The rollers 8 are all rotatably connected to the support platform 7 and supported on the ground. Several lifting components are connected between the support platform 7 and the fixed platform 1. Further, the rollers 8 are omnidirectional wheels with a braking function.

[0040] Specifically, this embodiment provides an exemplary solution as follows: the lifting assembly includes a first shearing rod 9, a second shearing rod 10, a pulley 11, and a first driving member 12. The first shearing rod 9 and the second shearing rod 10 are hinged to each other. The pulley 11 is rotatably connected to one end of the first shearing rod 9 and rolls in contact with the support platform 7. The other end of the first shearing rod 9 is hinged to the fixed platform 1. Both ends of the second shearing rod 10 are respectively hinged to the fixed platform 1 and the support platform 7. The first driving member 12 is drively connected to the first shearing rod 9 or the second shearing rod 10, so that the first shearing rod 9 and the second shearing rod 10 can open or close, thereby driving the fixed platform 1 to move in the vertical direction. Further, the first driving member 12 is a hydraulic cylinder.

[0041] Optionally, the maintenance mounting device for the civil aircraft radome also includes a second drive component 13. The second drive component 13 is fixedly mounted on the support platform 7, and its output end can drive the mounting platform 1 to rotate. With this configuration, the second drive component 13 can drive the mounting platform 1 to achieve single-axis rotation, thereby completing the lifting and rotation of the mounting platform 1 to meet the maintenance personnel's requirements for repair height and observation angle. Further, the second drive component 13 is a hydraulic cylinder.

[0042] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this utility model should be included within the protection scope of the claims of this utility model.

Claims

1. A maintenance and fixing device for a civil aircraft radome, characterized in that, include: Fixed platform (1); The clamping and fixing assembly includes a plurality of flexible pins (2), a locking switch (3), and a plurality of clamping members (4). The plurality of flexible pins (2) are arranged in a circular array on the fixing platform (1). The locking switch (3) is configured to lock the relative position between the plurality of flexible pins (2) and the fixing platform (1) so that the plurality of flexible pins (2) hold the radar dome located therein. The plurality of clamping members (4) are arranged on the outer peripheral wall of the fixing platform (1) in a circumferential direction, and each clamping member (4) is used to abut against the outer peripheral edge of the radar dome.

2. The maintenance and fixing device for a civil aircraft radome according to claim 1, characterized in that, The top of the flexible pin (2) has a contact head for fitting the radar dome, and the contact head is made of rubber material.

3. The maintenance and fixing device for a civil aircraft radome according to claim 1, characterized in that, The maintenance and fixing device for the civil aircraft radome also includes multiple mounting ears (5), which protrude from the outer peripheral wall of the fixing platform (1). The multiple mounting ears (5) are correspondingly arranged with multiple clamping members (4). The clamping member (4) includes a first clamping arm (41) and a second clamping arm (42). One end of the first clamping arm (41) is rotatably connected to the mounting ear (5), and the other end of the first clamping arm (41) is fixedly connected to the second clamping arm (42). The second clamping arm (42) is used to abut against the outer peripheral edge of the radome.

4. The maintenance and fixing device for a civil aircraft radome according to claim 3, characterized in that, The clamping and fixing assembly also includes a plurality of locking members (6), which are respectively arranged in a one-to-one correspondence with a plurality of first clamping arms (41), and the locking members (6) are used to lock or unlock the relative position between the first clamping arms (41) and the mounting ears (5).

5. The maintenance and fixing device for a civil aircraft radome according to any one of claims 1-4, characterized in that, The maintenance and fixing device for the civil aircraft radome also includes several lifting components, all of which are connected to the fixing platform (1) and can drive the fixing platform (1) to move in the vertical direction.

6. The maintenance and fixing device for a civil aircraft radome according to claim 5, characterized in that, The maintenance and fixing device for the civil aircraft radome also includes a movable support assembly, which includes a support platform (7) and a number of rollers (8). The rollers (8) are rotatably connected to the support platform (7) and supported on the ground. The lifting assembly is connected between the support platform (7) and the fixed platform (1).

7. The maintenance and fixing device for a civil aircraft radome according to claim 6, characterized in that, The lifting assembly includes a first shearing rod (9), a second shearing rod (10), a pulley (11), and a first driving member (12). The first shearing rod (9) and the second shearing rod (10) are hinged to each other. The pulley (11) is rotatably connected to one end of the first shearing rod (9) and rolls in contact with the support platform (7). The other end of the first shearing rod (9) is hinged to the fixed platform (1). The two ends of the second shearing rod (10) are respectively hinged to the fixed platform (1) and the support platform (7). The first driving member (12) is driven to the first shearing rod (9) or the second shearing rod (10) so that the first shearing rod (9) and the second shearing rod (10) can open or close, thereby driving the fixed platform (1) to move in the vertical direction.

8. The maintenance and fixing device for a civil aircraft radome according to claim 7, characterized in that, The first driving component (12) is a hydraulic cylinder.

9. The maintenance and fixing device for a civil aircraft radome according to claim 7, characterized in that, The maintenance and fixing device for the civil aircraft radome also includes a second drive component (13), which is fixedly mounted on the support platform (7), and the output end of the second drive component (13) can drive the fixing platform (1) to rotate.

10. The maintenance and fixing device for a civil aircraft radome according to claim 9, characterized in that, The second driving component (13) is a hydraulic cylinder.

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