Undercarriage structural strength test platform

Abstract

The utility model relates to the technical field of undercarriage strength test, and discloses an undercarriage structural strength test platform, which comprises an operation table, an assembly frame is fixedly mounted at the top end of the operation table, a penetrating groove is formed in one side of the assembly frame at the top end of the operation table, and a limiting mechanism is arranged in the penetrating groove; and the limiting mechanism comprises a motor, the motor is embedded in one side of the outer wall of the operation table, a two-way threaded rod is fixedly installed at the power output end of the motor, a sliding plate is slidably connected to the outer wall of the two-way threaded rod, and a clamping plate is fixedly installed on one side of the sliding plate. Through cooperation of the motor, the two-way threaded rod, the sliding plate, the clamping plate and the abutting block, an undercarriage can be automatically limited and clamped from the two sides, the situation that the undercarriage shakes or deviates when the strength is detected under pressure is avoided, automation is achieved, the effect is achieved, the trouble that workers need to assist in installation is avoided, and the working efficiency is improved. And the use convenience of the whole equipment is improved.

Description

Technical Field

[0001] This utility model relates to the field of landing gear strength testing technology, specifically a landing gear structural strength testing platform. Background Technology

[0002] Landing gear is a key component that supports the aircraft and absorbs impact energy during takeoff, landing, and ground movement. Its design and function are directly related to flight safety. When the aircraft is parked, taxiing, taking off, or landing, the landing gear bears the entire weight of the aircraft and ensures the aircraft's stable attitude on the ground. It consists of load-bearing struts, wheel assemblies, and other components.

[0003] The patent specification with announcement number CN212621365U discloses a landing gear strength testing device for fixed-wing aircraft. The landing gear is connected by screwing a threaded groove through the mounting hole of the landing gear. The first and second support frames have placement slots, which can be used to increase or decrease the test weight by inserting a counterweight into the placement slots according to the test weight. When testing is required, the hanging position of the lifting claw is released from the fixing block, allowing the first and second support frames to fall due to gravity. This causes the fixing block to slide down through the limiting slide groove, impacting the mounting plate and the landing gear below the mounting plate. Afterward, the operator can directly observe whether the landing gear breaks and determine whether it meets the strength requirements when installed on the bottom of an aircraft of different weights.

[0004] However, in implementing the relevant technology, the following problems were found in the above-mentioned design of a landing gear strength testing device for fixed-wing aircraft: Although the existing technology uses components such as counterweights to test the strength of the landing gear, in actual use, the landing gear needs to be fixed and limited by components such as fixing bolts, which requires multiple manual installations. The operation is too complicated and the workload is large, resulting in a slow testing process. Utility Model Content

[0005] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be construed as limiting the scope of the present invention.

[0006] Given that the existing technology requires multiple manual installations due to the need for fixing and limiting the landing gear with components such as fixing bolts, the operation is too complicated and the workload is too large, resulting in a slow overall testing process.

[0007] To achieve the above objectives, this utility model provides the following technical solution:

[0008] A landing gear structural strength testing platform includes an operating platform, an assembly frame is fixedly installed on the top of the operating platform, and an insertion groove is provided on one side of the assembly frame at the top of the operating platform, and a limit mechanism is provided inside the insertion groove.

[0009] The limiting mechanism includes a motor, which is embedded in one side of the outer wall of the operating table. A bidirectional threaded rod is fixedly installed on the power output end of the motor. A sliding plate is slidably connected to the outer wall of the bidirectional threaded rod, and a clamping plate is fixedly installed on one side of the sliding plate.

[0010] As a further improvement of this utility model: an abutment block is fixedly installed on the outer wall of the clamping plate, and a slot is provided on one side of the insertion groove corresponding to the position of the sliding plate.

[0011] As a further improvement of this utility model: the outer wall of the abutment block is provided with a mounting groove, and an abutment roller is rotatably connected inside the mounting groove.

[0012] As a further improvement of this utility model: a limiting groove is provided at the bottom of the inner end of the insertion groove, and a pressure mechanism is provided at the top of the assembly frame.

[0013] As a further embodiment of this utility model: the pressurizing mechanism includes a servo hydraulic device, which is embedded in the top of the assembly frame, and a pressure plate is fixedly installed on the power output end of the servo hydraulic device.

[0014] As a further improvement of this utility model: a limiting hole is provided inside the pressure plate, and a limiting rod extends out from inside the limiting hole.

[0015] As a further improvement of this utility model: a pressure block is fixedly installed at the bottom end of the pressure plate, and the pressure block has an installation hole inside.

[0016] As a further improvement of this utility model: a connecting post extends through the interior of the mounting hole, and a sleeve block is fixedly installed at the bottom end of the connecting post.

[0017] Compared with the prior art, the beneficial effects of this utility model are:

[0018] 1. This utility model, through the cooperation of a motor, a bidirectional threaded rod, a sliding plate, a clamping plate, and abutment blocks, can automatically limit and clamp the landing gear from both sides, preventing shaking or displacement when the strength is checked under pressure. It also achieves automation, avoiding the troublesome installation that requires manual assistance and improving the convenience of using the entire device.

[0019] 2. This utility model, through the cooperation of the pressure plate, limiting rod, pressure block, connecting column and sleeve block, can maintain the stability of the pressure plate displacement during strength testing under pressure, and can replace the sleeve block with one suitable for the cross-section of the load-bearing column according to the landing gear model, further improving the applicability of the entire equipment. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of a landing gear structural strength testing platform.

[0021] Figure 2 A schematic diagram of the control panel structure of a landing gear structural strength testing platform;

[0022] Figure 3 This is a schematic diagram of the sliding plate structure of a landing gear structural strength testing platform;

[0023] Figure 4 This is a schematic diagram of the contact block structure of a landing gear structural strength testing platform;

[0024] Figure 5 This is a schematic diagram of the pressure block structure of a landing gear structural strength testing platform;

[0025] In the diagram: 1. Operating table; 2. Assembly frame; 3. Insertion groove; 4. Limiting mechanism; 401. Motor; 402. Bidirectional threaded rod; 403. Sliding plate; 404. Clamping plate; 405. Abutting block; 406. Slot; 407. Placement groove; 408. Abutting roller; 5. Limiting groove; 6. Pressurizing mechanism; 601. Servo hydraulic equipment; 602. Pressurizing plate; 603. Limiting rod; 604. Limiting hole; 605. Pressurizing block; 606. Mounting hole; 607. Connecting column; 608. Sleeve block. Detailed Implementation

[0026] To make the above-mentioned objectives, features and advantages of this utility model more readily understood, the specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings.

[0027] Many specific details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the spirit of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0028] Secondly, the term "an embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single embodiment or an embodiment selectively excluded from other embodiments.

[0029] Example 1:

[0030] Please see Figures 1-4 This is the first embodiment of the present invention.

[0031] This embodiment provides a landing gear structural strength test platform, including an operating platform 1, an assembly frame 2 fixedly installed on the top of the operating platform 1, and an insertion groove 3 on one side of the assembly frame 2 at the top of the operating platform 1, with a limit mechanism 4 provided inside the insertion groove 3.

[0032] The limiting mechanism 4 includes a motor 401, which is embedded in one side of the outer wall of the operating table 1. A bidirectional threaded rod 402 is fixedly installed at the power output end of the motor 401. A sliding plate 403 is slidably connected to the outer wall of the bidirectional threaded rod 402. A clamping plate 404 is fixedly installed on one side of the sliding plate 403.

[0033] Specifically, an abutment block 405 is fixedly installed on the outer wall of the clamping plate 404, and a slot 406 is provided on one side of the groove 3 corresponding to the position of the sliding plate 403.

[0034] Furthermore, by sliding and engaging the slot 406 with the sliding plate 403, the stability of the clamping plate 404 during displacement can be improved, and wobbling or displacement can be avoided.

[0035] Specifically, the outer wall of the abutment block 405 is provided with a mounting groove 407, and the mounting groove 407 is rotatably connected to the abutment roller 408.

[0036] Furthermore, the contact roller 408 can limit the load-bearing struts of the landing gear, and when they rub against each other during the compression process, the contact roller 408 rotates under force to avoid excessive friction and damage to the paint surface of the landing gear, and can be used to limit the landing gear with load-bearing struts of different inner diameters.

[0037] In use, the landing gear is first placed into the slot 3 of the control panel 1. Then, the motor 401 is started through the control terminal of the whole device, which drives the bidirectional threaded rod 402 to rotate. Under the limit of the slot 406, the sliding plate 403 drives the corresponding clamping plate 404 to move, so that the clamping plate 404 extends the load-bearing strut of the landing gear from both sides. The contact block 405 has an arc groove that can fit fully, and the contact roller 408 connected to the mounting slot 407 can prevent friction and collision during the clamping process, which would damage the paint.

[0038] In summary, the opening and closing of the motor 401 can fix and clamp the landing gear to maintain its position, thus preventing deviation during strength testing. It avoids the need for manual intervention and is cumbersome and troublesome to use bolts or other fixing methods, thus achieving a certain degree of automation. At the same time, when the anti-roller 408 clamps and fixes the load-bearing strut of the landing gear, it can prevent excessive clamping and shaking under pressure, as well as excessive friction that could damage the paint surface.

[0039] Example 2:

[0040] Please see Figure 1 , Figure 2 and Figure 5 This is the second embodiment of the present utility model.

[0041] Specifically, a limiting groove 5 is provided at the bottom of the inner end of the insertion groove 3, and a pressure mechanism 6 is provided at the top of the assembly frame 2.

[0042] Furthermore, the insertion groove 3 can limit the movement of the wheel assembly at the bottom of the landing gear, preventing excessive swaying under pressure.

[0043] Specifically, the pressurizing mechanism 6 includes a servo hydraulic device 601, which is embedded in the top of the assembly frame 2, and a pressure plate 602 is fixedly installed at the power output end of the servo hydraulic device 601.

[0044] Furthermore, the servo hydraulic device 601 can use a servo motor to drive an oil pump and precisely adjust the oil pressure through a proportional servo valve, thereby applying pressure as needed and controlling it through the device's control terminal.

[0045] Specifically, a limit hole 604 is provided inside the pressure plate 602, and a limit rod 603 extends out from inside the limit hole 604.

[0046] Furthermore, during the displacement of the pressure plate 602, it slides along the limiting rod 603 through the limiting hole 604 to avoid deviation. The limiting rod 603 is fixed between the operating table 1 and the assembly frame 2.

[0047] Specifically, a pressure block 605 is fixedly installed at the bottom of the pressure plate 602, and the pressure block 605 has an installation hole 606 inside.

[0048] Furthermore, the pressure block 605 can concentrate the pressure, thereby applying it more effectively to the top of the landing gear.

[0049] Specifically, a connecting post 607 extends through the interior of the mounting hole 606, and a sleeve block 608 is fixedly installed at the bottom end of the connecting post 607.

[0050] Furthermore, the sleeve block 608 is provided with a reserved groove to accommodate the top of the landing gear support strut, and is threadedly connected to the pressure block 605 via the connecting column 607, which facilitates replacement according to different support strut models and improves applicability.

[0051] In use, the force applied by the servo hydraulic device 601 is first adjusted according to the control terminal of the equipment, so that the pressure plate 602 slides along the limit rod 603 through the limit hole 604, and the pressure is accumulated by the pressure block 605, so that the sleeve block 608 is pressed against the landing gear for strength testing. The threaded connection between the mounting hole 606 and the connecting column 607 makes it easy to replace the sleeve block 608 with the corresponding reserved slot according to the landing gear model, thus improving the overall applicability.

[0052] In summary, the cooperation of the limiting rod 603 and the limiting hole 604 can improve the stability of the displacement process of the pressure plate 602. The pressure gathered by the pressure block 605 can better press down on the landing gear for strength testing. In addition, depending on the landing gear model, the sleeve block 608 with the reserved groove that conforms to the load-bearing strut can be replaced. This allows for testing of different landing gear models, improving the overall applicability and comprehensiveness.

[0053] It is important to note that the constructions and arrangements of this application shown in several different exemplary embodiments are merely illustrative. Although only a few embodiments are described in detail in this disclosure, those who consult this disclosure will readily understand that many modifications are possible (e.g., changes in the size, dimensions, structure, shape, and proportions of various elements, as well as parameter values ​​(e.g., temperature, pressure, etc.), mounting arrangements, use of materials, color, orientation, etc.) without substantially departing from the novel teachings and advantages of the subject matter described in this application). For example, an element shown as integrally formed may be composed of multiple parts or elements, the position of elements may be inverted or otherwise altered, and the nature or number or position of discrete elements may be changed or altered. Therefore, all such modifications are intended to be included within the scope of this utility model. The order or sequence of any process or method steps may be changed or rearranged according to alternative embodiments. In the claims, any "device plus function" clause is intended to cover the structure described herein that performs the function, and not only structural equivalents but also equivalent structures. Without departing from the scope of this invention, other substitutions, modifications, alterations, and omissions may be made in the design, operation, and arrangement of the exemplary embodiments. Therefore, this invention is not limited to the specific embodiments, but extends to various modifications that still fall within the scope of the appended claims.

[0054] Furthermore, in order to provide a concise description of exemplary embodiments, not all features of actual embodiments (i.e., those features that are not relevant to the best mode of carrying out the present invention as currently considered, or those features that are not relevant to implementing the present invention) may be omitted.

[0055] It should be understood that numerous specific implementation decisions can be made during the development of any actual implementation method, and in any engineering or design project. Such development efforts may be complex and time-consuming, but for those of ordinary skill in the art who benefit from this disclosure, the development effort will be a routine work of design, manufacturing, and production without requiring much experimentation.

[0056] It should be noted that the above embodiments are only used to illustrate the technical solution of this utility model and are not intended to limit it. Although this utility model has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solution of this utility model without departing from the spirit and scope of the technical solution of this utility model, and all such modifications or substitutions should be covered within the scope of the claims of this utility model.

Claims

1. A landing gear structural strength testing platform, comprising an operating platform (1), characterized in that: An assembly frame (2) is fixedly installed on the top of the operating table (1), and a through groove (3) is provided on one side of the assembly frame (2) at the top of the operating table (1). A limit mechanism (4) is provided inside the through groove (3). The limiting mechanism (4) includes a motor (401), which is embedded in one side of the outer wall of the operating table (1). The power output end of the motor (401) is fixedly installed with a bidirectional threaded rod (402). The outer wall of the bidirectional threaded rod (402) is slidably connected with a sliding plate (403), and a clamping plate (404) is fixedly installed on one side of the sliding plate (403).

2. The landing gear structural strength testing platform according to claim 1, characterized in that: The outer wall of the clamping plate (404) is fixedly installed with an abutment block (405), and a slot (406) is opened on one side of the insertion groove (3) corresponding to the position of the sliding plate (403).

3. The landing gear structural strength testing platform according to claim 2, characterized in that: The outer wall of the abutment block (405) is provided with a mounting groove (407), and the mounting groove (407) is rotatably connected to an abutment roller (408).

4. The landing gear structural strength testing platform according to claim 1, characterized in that: A limiting groove (5) is provided at the bottom of the inner end of the insertion groove (3), and a pressure mechanism (6) is provided at the top of the assembly frame (2).

5. The landing gear structural strength testing platform according to claim 4, characterized in that: The pressurizing mechanism (6) includes a servo hydraulic device (601), which is embedded in the top of the assembly frame (2), and a pressure plate (602) is fixedly installed on the power output end of the servo hydraulic device (601).

6. The landing gear structural strength testing platform according to claim 5, characterized in that: The pressure plate (602) has a limiting hole (604) inside, and a limiting rod (603) extends out of the limiting hole (604).

7. The landing gear structural strength testing platform according to claim 5, characterized in that: A pressure block (605) is fixedly installed at the bottom of the pressure plate (602), and the pressure block (605) has an installation hole (606) inside.

8. The landing gear structural strength testing platform according to claim 7, characterized in that: A connecting post (607) extends through the interior of the mounting hole (606), and a sleeve block (608) is fixedly installed at the bottom end of the connecting post (607).

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