Aircraft landing gear testing device

Abstract

The invention belongs to the technical field of aircraft structure strength tests, and relates to an aircraft landing gear test device. The device comprises a vertical beam (1), a central bottom beam (2), a side bottom beam (3), a cross beam (4), a longitudinal top beam (5), a cross top beam (6) and a loading beam (7), the side bottom beams (3) are arranged on the two sides of the bottom beam (2) to form a bearing base; the longitudinal top beams (5) and the transverse top beams (6) are arranged in a staggered manner to form a bearing ceiling; the force bearing base and the force bearing ceiling are installed at the bottom end and the top end of a frame defined by the vertical beams (1) respectively. The adjacent vertical beams (1) are connected at the bottom of the periphery of the frame through cross beams (4), and the adjacent vertical beams (1) are connected from the middle to the top of the periphery of the frame through loading beams (7). The aircraft landing gear test device is simple in structure and high in universality.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft structure strength testing, and in particular relates to an aircraft landing gear testing device. Background Art

[0002] At present, there are two types of landing gear test devices: general devices and special devices, both of which have certain limitations.

[0003] When the landing gear is tested with a universal device, it is necessary to install a horizontal bearing column and a fixed base on the bearing floor according to the size of the landing gear. The bearing floor must have the ability to anchor the test fixture. The universal device's demand for floor capacity limits the environment for conducting landing gear tests. When adjusting the compression of the landing gear buffer, the installation position of the horizontal bearing column must be adjusted to meet the loading requirements. At the same time, due to the uniqueness of the installation position of the horizontal bearing column, the hydraulic pipelines, monitoring equipment, display equipment, counterweight beams and other special devices supporting the test need to be separately installed. The frame, resulting in a large amount of test installation.

[0004] Special equipment for landing gear testing is usually dedicated to a certain type of landing gear. The loading position, frame space, etc. cannot be adjusted, and it is not very universal. Summary of the invention

[0005] In order to solve at least one of the above technical problems, the present application provides an aircraft landing gear test device, which mainly includes a vertical beam, a center bottom beam, a side bottom beam, a cross beam, a longitudinal top beam, a transverse top beam, and a loading beam;

[0006] The side bottom beams are arranged on both sides of the bottom beam to form a load-bearing base;

[0007] The longitudinal roof beams and the transverse roof beams are arranged alternately to form a load-bearing ceiling;

[0008] The load-bearing base and the load-bearing ceiling are respectively installed at the bottom and top of a frame formed by a plurality of vertical beams;

[0009] The frame is connected to adjacent vertical beams at the bottom by horizontal beams, and the frame is connected to adjacent vertical beams from the middle to the top by loading beams.

[0010] Among them, the vertical beams, cross beams, longitudinal top beams and transverse top beams are used to provide fixed interfaces for the hydraulic, monitoring, detection and display systems; the load-bearing base is used to provide a fixed interface for the loading system and landing gear; and the loading beam is used to provide a fixed interface for the loading system.

[0011] Preferably, the vertical beam, center bottom beam, side bottom beam, cross beam, longitudinal top beam and transverse top beam are all processed with HW350 I-beam, the reinforcement ribs and butt plates of the I-beam are 20mm thick and the material is Q345 steel. The loading beam is processed with 32b channel steel, the reinforcement plate is 15mm thick, the overall height is the same as that of the HW350 I-beam, and the butt plates on both sides are 20mm thick.

[0012] Preferably, the side bottom beam and the bottom beam of the load-bearing base are connected by bolts.

[0013] Preferably, the load-bearing base is machined with multiple rows of through holes for fixing the loading system and the landing gear.

[0014] Preferably, the hole spacing between the multiple rows of through holes on the load-bearing base is 200 mm.

[0015] Preferably, a plurality of groups of load-bearing base fixing holes are provided on the vertical beam, and the load-bearing base can adjust its installation height along the height direction.

[0016] Preferably, the loading beam is provided with an elongated hole for adjusting the installation position of the loading system.

[0017] Preferably, the vertical beam, the central bottom beam, the side bottom beam, the cross beam, the longitudinal top beam, the transverse top beam, and the loading beam are fixed together by bolts and then placed on the floor.

[0018] The aircraft landing gear test device of the present application is universal, can meet the test requirements of the front landing gear and the main landing gear, has low processing cost and is easy to install. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a structural schematic diagram of the aircraft landing gear test device of the present application.

[0020] Among them, 1-vertical beam, 2-center bottom beam, 3-side bottom beam, 4-cross beam, 5-longitudinal top beam, 6-cross top beam, 7-loading beam, 8-floor. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0022] The present application provides an aircraft landing gear test device, such as Figure 1 As shown, it mainly includes a vertical beam 1, a central bottom beam 2, a side bottom beam 3, a cross beam 4, a longitudinal top beam 5, a transverse top beam 6, and a loading beam 7;

[0023] The side bottom beams 3 are arranged on both sides of the bottom beam 2 to form a load-bearing base;

[0024] The longitudinal top beams 5 and the transverse top beams 6 are arranged alternately to form a load-bearing ceiling;

[0025] The load-bearing base and the load-bearing ceiling are respectively installed at the bottom and top of the frame formed by a plurality of vertical beams 1;

[0026] The frame is connected to adjacent vertical beams 1 at the bottom by a cross beam 4, and the frame is connected to adjacent vertical beams 1 at the middle to the top by a loading beam 7.

[0027] Among them, the vertical beam 1, the horizontal beam 4, the longitudinal top beam 5, and the horizontal top beam 6 are used to provide fixed interfaces for the hydraulic, monitoring, detection, and display systems; the load-bearing base is used to provide a fixed interface for the loading system and the landing gear; and the loading beam 7 is used to provide a fixed interface for the loading system.

[0028] The present application conducts modular design on the aircraft landing gear test device. Each modular structure is processed by steel, which is light in weight, easy to install, convenient to process, and low in cost. Each modular structure can be connected by bolts and other connectors, and the connection interface is consistent. The installation position and the number of each modular structure can be adjusted according to the test requirements.

[0029] The aircraft landing gear test device provided in the present application has a simple structure and strong versatility, and can meet the ground strength test requirements of landing gears of different sizes, effectively reduce the processing cost of the test fixture, shorten the test preparation cycle, and standardize the test site management.

[0030] In some optional embodiments, the vertical beam 1, the center bottom beam 2, the side bottom beam 3, the cross beam 4, the longitudinal top beam 5, and the cross top beam 6 are all processed with HW350 I-beams, the reinforcement ribs and the butt plates of the I-beams are 20 mm thick, and the material is Q345 steel. The loading beam 7 is processed with 32b channel steel, the reinforcement plate is 15 mm thick, the overall height is the same as that of the HW350 I-beam, and the butt plates on both sides are 20 mm thick.

[0031] In this embodiment, the vertical beam 1, the center bottom beam 2, the side bottom beam 3, the cross beam 4, the longitudinal top beam 5, and the transverse top beam 6 are produced by welding H-shaped steel and steel plates and then machining, and the loading beam 7 is produced by welding hot-rolled channel steel and steel plates and then machining.

[0032] In some optional embodiments, the side bottom beam 3 of the load-bearing base is connected to the bottom beam 2 by bolts.

[0033] In some optional embodiments, the load-bearing base is processed with multiple rows of through holes for fixing the loading system and the landing gear. The hole spacing of the multiple rows of through holes on the load-bearing base is 200 mm.

[0034] In some optional embodiments, a plurality of groups of load-bearing base fixing holes are provided on the vertical beam 1, and the load-bearing base can adjust its installation height along the height direction.

[0035] In some optional embodiments, the loading beam 7 is provided with a long hole for adjusting the installation position of the loading system.

[0036] In some optional embodiments, the vertical beam 1 , the central bottom beam 2 , the side bottom beam 3 , the cross beam 4 , the longitudinal top beam 5 , the transverse top beam 6 , and the loading beam 7 are fixed together by bolts and placed on the floor 8 .

[0037] In this embodiment, the device adopts a self-balancing design, and the test load is balanced internally, and there is no need to fix the frame on the ground.

[0038] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An aircraft landing gear test device, characterized in that: It comprises a vertical beam (1), a central bottom beam (2), a side bottom beam (3), a cross beam (4), a longitudinal top beam (5), a transverse top beam (6), and a loading beam (7); The side bottom beams (3) are arranged on both sides of the bottom beam (2) to form a load-bearing base; The longitudinal top beams (5) and the transverse top beams (6) are arranged in a staggered manner to form a load-bearing ceiling; The load-bearing base and the load-bearing ceiling are respectively installed at the bottom and top of a frame formed by a plurality of vertical beams (1); The frame is connected to adjacent vertical beams (1) at the bottom via a cross beam (4), and the frame is connected to adjacent vertical beams (1) at the middle to the top via a loading beam (7); Among them, the vertical beam (1), the horizontal beam (4), the longitudinal top beam (5) and the horizontal top beam (6) are used to provide fixed interfaces for the hydraulic, monitoring, detection and display systems, the load-bearing base is used to provide a fixed interface for the loading system and the landing gear, and the loading beam (7) is used to provide a fixed interface for the loading system.

2. The aircraft landing gear test device according to claim 1, characterized in that: The vertical beam (1), the center bottom beam (2), the side bottom beam (3), the cross beam (4), the longitudinal top beam (5) and the cross top beam (6) are all processed by HW350 I-beam. The thickness of the reinforcing rib and the butt plate of the I-beam is 20 mm and the material is Q345 steel. The loading beam (7) is processed by 32b channel steel. The thickness of the reinforcing plate is 15 mm. The overall height is the same as that of the HW350 I-beam. The thickness of the butt plates on both sides is 20 mm.

3. The aircraft landing gear test device according to claim 1, characterized in that: The side bottom beam (3) of the load-bearing base is connected to the bottom beam (2) via bolts.

4. The aircraft landing gear test device according to claim 1, characterized in that: The load-bearing base is processed with multiple rows of through holes for fixing the loading system and the landing gear.

5. The aircraft landing gear test device according to claim 4, characterized in that: The hole spacing between the multiple rows of through holes on the load-bearing base is 200 mm.

6. The aircraft landing gear test device according to claim 1, characterized in that: A plurality of groups of bearing base fixing holes are arranged on the vertical beam (1), and the bearing base can adjust its installation height along the height direction.

7. The aircraft landing gear test device according to claim 1, characterized in that: The loading beam (7) is provided with a long hole for adjusting the installation position of the loading system.

8. The aircraft landing gear test device according to claim 1, characterized in that: The vertical beam (1), the central bottom beam (2), the side bottom beam (3), the cross beam (4), the longitudinal top beam (5), the transverse top beam (6) and the loading beam (7) are fixedly connected together by bolts and then placed on the floor (8).

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