Horizontal supporting rod buckling test equipment

Abstract

The utility model relates to horizontal supporting rod buckling test equipment which comprises a rack table top, a left loading wall plate and a right loading wall plate, wherein the left loading wall plate and the right loading wall plate are vertically arranged on the rack table top; a connecting part is arranged on the right side surface of the left loading wall plate, an electric servo cylinder is arranged on the right loading wall plate, the end part of a piston rod of the electric servo cylinder can be connected with one end of an undercarriage supporting rod, and the other end of the undercarriage supporting rod can be connected with the connecting part; after installation is completed, the undercarriage supporting rod and a piston rod of the electric servo cylinder are located on the same straight line, the electric servo cylinder is started, and the end of the piston rod of the electric servo cylinder moves leftwards to extrude the undercarriage supporting rod; a pressure sensor is further mounted at the connecting part; the horizontal supporting rod flexion testing equipment is further provided with a micro-displacement pressure measuring assembly in a matched mode. According to the scheme, the press machine can meet the test requirements of undercarriage supporting rods of existing models, can be upgraded to adapt to the test requirements of new models, and is an automatic, miniaturized and movable press machine for undercarriage supporting rod buckling tests, which is suitable for being used by troop repair factories.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft landing gears, in particular to a horizontal strut buckling test device. Background Art

[0002] The landing gear strut is a key load-bearing component on the aircraft landing gear. It is used to withstand various lateral forces that the landing gear is subjected to during operation. Therefore, the pressure test of the landing gear strut is an important task during the regular inspection and maintenance of the aircraft landing gear to ensure that its performance meets the working requirements. The compression buckling test of the landing gear strut needs to be completed with professional equipment. At present, the pressure testing equipment on the market that meets the performance requirements is mainly designed for testing slender products such as hydraulic cylinders and steel cables. In order to meet the versatility of the product, the installation size is large and the loading pressure is high. Therefore, hydraulic loading and vertical structure are generally used, and the foundation needs to be pre-buried during installation.

[0003] However, the existing equipment of this type has high installation height, large size, cannot be moved, and is complex to operate. It cannot meet the needs of troops for carrying and transferring for combat training. Therefore, the military repair shops are unable to equip it. The landing gear strut test is currently mainly carried out by overhaul shops, with a long test cycle, which affects combat efficiency.

[0004] Therefore, in order to overcome the shortcomings of the prior art, a horizontal strut compression buckling test device is proposed, which can adapt to the testing requirements of landing gear struts of various models, and is small in size, movable, and easy to carry. Utility Model Content

[0005] The purpose of the utility model is to overcome the deficiencies of the prior art and to provide a horizontal strut compression buckling test device that can meet the testing needs of landing gear struts of existing aircraft models and can be upgraded to adapt to the testing needs of new aircraft models. The device is small in size and movable, which is beneficial to improving the aircraft maintenance and troubleshooting capabilities of front-line troops and meeting aircraft maintenance needs.

[0006] The purpose of this utility model is achieved through the following technical solutions:

[0007] A horizontal strut compression buckling test device is used for pressure testing of landing gear struts, comprising a frame table, and a left loading wall panel and a right loading wall panel vertically arranged on the frame table; a connecting portion is provided on the right side surface of the left loading wall panel, and an electric servo cylinder is provided on the right loading wall panel, the piston rod end of the electric servo cylinder can be connected to one end of the landing gear strut, and the other end of the landing gear strut can be connected to the connecting portion; after installation, the landing gear strut and the piston rod of the electric servo cylinder are located on the same straight line, the electric servo cylinder is started, and the piston rod end of the electric servo cylinder moves to the left to squeeze the landing gear strut; a pressure sensor is also installed at the connecting portion; the horizontal strut compression buckling test device is also equipped with a micro-displacement pressure measuring component to measure the deformation amount of the landing gear strut. The pressure sensor is used to detect the pressure applied by the electric servo cylinder to the landing gear strut. The micro-displacement pressure measuring assembly can be arranged below the middle of the landing gear strut to detect the deformation of the landing gear strut under different pressures (the landing gear strut bends upward or downward under the squeezing of the piston rod), thereby realizing the strut compression buckling test under different pressures.

[0008] In a preferred embodiment of this scheme, a guide rail is provided on the upper left side of the rack table, and the left loading wallboard can be slidably installed on the guide rail; a screw rod pair without a self-locking function is also provided on the upper left side of the rack table, and the moving part of the screw rod pair is the left loading wallboard, so that the left loading wallboard can be driven to move left and right by the screw of the screw rod pair.

[0009] In a preferred embodiment of the present scheme, the horizontal strut compression buckling test equipment further includes at least two rods symmetrically arranged on the right loading wallboard; the right end of the rod is vertically installed on the right loading wallboard, and the left loading wallboard corresponds to the rod with a through hole, and the left end of the rod passes through the through hole to the left; the rod is provided with an insertion hole, and a detachable insertion limit block is inserted in the insertion hole. After installation, the left side of the left loading wallboard abuts against the limit block. The load of the horizontal strut compression buckling test equipment can reach tens of tons, and the setting of the limit block can limit the left loading wallboard to prevent the left loading wallboard from moving to the left under the pressure of the piston rod.

[0010] In a preferred embodiment of the present scheme, a threaded section is provided at the right end of the rod, a mounting hole is provided on the right loading wall plate, and the right end of the rod passes through the mounting hole and is screwed onto the right loading wall plate via two nuts.

[0011] In a preferred embodiment of the present scheme, the horizontal brace compression buckling test equipment further comprises an electrical control system, which comprises an electrical control device and an operating screen; the operating screen, the electric servo cylinder and the pressure sensor are respectively connected to the electrical control device by telecommunication.

[0012] In a preferred embodiment of the present scheme, the screw pair includes a screw, a screw sub-support one, and a screw sub-support two, and the two ends of the screw are rotatably mounted on the screw sub-support one and the screw sub-support two respectively; the left loading wall panel is located between the screw sub-support one and the screw sub-support two, and a threaded hole is provided at the lower part of the left loading wall panel, and the screw is threadedly matched with the threaded hole; a handwheel is also provided after the left end of the screw passes through the screw sub-support one.

[0013] In a preferred embodiment of the present scheme, a connecting ear is respectively provided at both ends of the landing gear strut; an ear plate is respectively provided on the right side surface of the left loading wall panel and the end of the piston rod of the electric servo cylinder, and the ear plate and the connecting ears at both ends of the landing gear strut can be correspondingly connected through a pin shaft.

[0014] Furthermore, in a preferred embodiment of the present solution, the connecting ear portion is a double-ear ear plate, both ear plates are single-ear ear plates, and the two single-ear ear plates are located on the same straight line as the piston rod of the electric servo cylinder.

[0015] In a preferred embodiment of the present scheme, a circular hole is provided on the right loading wall panel, the electric servo cylinder is installed on the right side of the right loading wall panel through a plurality of bolts, and the piston rod of the electric servo cylinder passes through the circular hole to the left of the right loading wall panel.

[0016] In a preferred embodiment of the present solution, the rack table is installed on a bracket, and four universal wheels and a plurality of adjustable foot cups are provided at the bottom of the bracket.

[0017] In a preferred embodiment of the present solution, an accessory box and an electrical control cabinet are provided inside the bracket, and the electrical control device is arranged in the electrical control cabinet.

[0018] In a preferred embodiment of the present solution, a lifting ear is respectively provided on the top of the left loading wall panel and the right loading wall panel.

[0019] The beneficial effects of the utility model are:

[0020] (1) The horizontal strut compression buckling test equipment of this scheme has a left loading wall plate and a right loading wall plate arranged on its frame table; an electric servo cylinder is arranged on the right loading wall plate, and an ear plate is respectively arranged at the piston rod end of the electric servo cylinder and the right side of the left loading wall plate, and the connecting ears at both ends of the landing gear strut can be connected to the two ear plates accordingly. A pressure sensor is also arranged on the right side of the left loading wall plate, and the displacement of the servo electric cylinder is controlled by the electrical operation screen of the test equipment to adjust the pressure applied to the landing gear strut. The micro-displacement pressure measuring assembly is placed below the middle of the landing gear strut to detect the deformation amount of the landing gear strut under different pressures, so as to realize the compression buckling test and deformation amount detection of each pressure section of the landing gear strut;

[0021] In addition, during the compression buckling test, the external installation dimensions of the aircraft main strut and the front strut differ greatly. In order to facilitate the installation and testing, a non-self-locking screw rod auxiliary mechanism is provided on the frame table, and the left loading wall panel on the pressure sensor side is installed as its moving part, so that the position of the left loading wall panel can be flexibly adjusted by adjusting the hand wheel at the outer end of the screw rod, and the distance between the left loading wall panel and the right loading wall panel can be adjusted, so that this scheme can be applied to the installation of different types of test pieces. According to the stress conditions of different struts during operation, simulation tests of struts of different types are carried out on the equipment of this scheme;

[0022] (2) The frame table of the horizontal strut compression buckling test equipment is installed on the bracket, and an electrical control device is arranged inside the bracket. The operation screen, the electric servo cylinder, and the pressure sensor are respectively connected to the electrical control device by telecommunication to facilitate the automation of the compression buckling test. The bottom of the bracket of this scheme is also provided with four universal wheels and a plurality of adjustable foot cups, so that this scheme can form a miniaturized and movable press machine for the compression buckling test of the landing gear strut, which is beneficial to improving the aircraft maintenance and troubleshooting capabilities of the front-line troops and meeting the aircraft maintenance needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the structure of the utility model;

[0024] Figure 2 It is a schematic diagram of the front view of the utility model;

[0025] Figure 3 It is a three-dimensional schematic diagram of the utility model. DETAILED DESCRIPTION

[0026] The technical solution of the present utility model is further described in detail below in conjunction with the accompanying drawings, but the protection scope of the present utility model is not limited to the following.

[0027] like Figure 1 to Figure 3 As shown, a horizontal strut compression buckling test device is mainly composed of a bracket 10, a frame table 3, a left loading wall panel 1, a right loading wall panel 2, an electric servo cylinder 4, a pressure sensor and an electrical control system.

[0028] Among them, the left loading wall panel 1 and the right loading wall panel 2 are vertically arranged on the frame table 3; a connecting part is provided on the right side surface of the left loading wall panel 1, and an electric servo cylinder 4 is provided on the right loading wall panel 2, the piston rod end of the electric servo cylinder 4 can be connected to one end of the landing gear support rod 5, and the other end of the landing gear support rod 5 can be connected to the connecting part, and the landing gear support rod 5 and the piston rod of the electric servo cylinder 4 are located on the same straight line, the pressure sensor is installed at the connecting part, and the micro-displacement pressure measuring assembly can be placed below the middle part of the landing gear support rod 5.

[0029] At the same time, in this embodiment, the electrical control system includes an electrical control device and an operation screen 11; the operation screen 11, the electric servo cylinder 4, and the pressure sensor are respectively connected to the electrical control device by telecommunication. During the test, the electric servo cylinder 4 is started through the operation screen, and the piston rod end of the electric servo cylinder 4 moves to the left. The displacement of the servo electric cylinder can be adjusted through the operation screen, thereby adjusting the pressure applied to the landing gear strut. The micro-displacement pressure measuring assembly is placed below the middle of the landing gear strut to detect the deformation of the landing gear strut 5 under different pressures, thereby realizing the compression buckling test and deformation detection of each pressure section of the landing gear strut 5.

[0030] Further preferably, in the present embodiment, the bracket 10 is welded with a rectangular steel pipe with a strong bending coefficient, and an electrical control cabinet 1003 and an accessory box 1002 are arranged in its rectangular frame to facilitate the installation of electrical control components required by the press (horizontal strut compression test equipment) and accessories required during the pressure test; a galvanized flat steel plate that has been machined is arranged on the bracket 10 as a frame table 3; a left loading wall panel 1 and a right loading wall panel 2 are vertically installed on the left and right sides of the frame table 3 respectively, and the left loading wall panel 1 and the frame table 3 are connected by a screw pair without a self-locking function. A handwheel 803 is provided at one end of the screw. By adjusting the handwheel 803, the setting position of the left loading wall panel 1 can be adjusted, thereby flexibly adjusting the installation of the test piece, so that the present equipment is suitable for use with landing gear struts 5 of different models.

[0031] refer to Figure 1 As shown, further, in this solution, four universal wheels 1001 and six adjustable feet are provided at the bottom of the bracket 10 to facilitate the movement and transfer of the equipment; in addition, in order to facilitate the transportation of the equipment, a lifting ear is also provided on the top of the left loading wall panel 1 and the right loading wall panel 2 respectively.

[0032] Preferably, in this embodiment, the distance between the bracket 10 and the ground space is 200 mm, so as to facilitate the transportation of the entire press by a forklift. When the equipment is moved to a space where forklift transportation is restricted, the position of the press can be manually moved and adjusted; after moving to the required position, the press is fixed and supported by the six adjustable feet underneath to prevent shaking.

[0033] In order to realize the adjustable installation of the left loading wall panel 1, specifically, in this scheme, a guide rail 7 is provided on the upper left side of the rack table 3, and the guide rail 7 is set left and right. The left loading wall panel 1 can be slid left and right on the guide rail 7; a screw pair without self-locking function is provided on the upper left side of the rack table 3, and the moving part of the screw pair is the left loading wall panel 1, and the left loading wall panel 1 is driven to move left and right by the rotation of the screw 8 of the screw pair.

[0034] refer to Figure 2As shown, in this embodiment, the screw pair includes a screw 8, a screw sub-support 801, and a screw sub-support 802. The two ends of the screw 8 are rotatably mounted on the screw sub-support 801 and the screw sub-support 802 respectively; the left loading wall panel 1 is located between the screw sub-support 801 and the screw sub-support 802, and a threaded hole is provided at the lower part of the left loading wall panel 1, and the screw 8 is threadedly matched with the threaded hole.

[0035] Furthermore, in order to ensure that the left loading wall panel 1 has good stability after the electric servo cylinder 4 is started, in this scheme, two rods 9 are provided on the right loading wall panel 2, and the two rods 9 are symmetrically arranged. The right end of the rod 9 is vertically installed on the right loading wall panel 2, and the left loading wall panel 1 is provided with a through hole corresponding to the rod 9, and the left end of the rod 9 passes through the through hole to the left; the rod 9 is also provided with an insertion hole, and a detachable insertion limit block 901 is inserted in the insertion hole. After the installation is completed, the left side surface of the left loading wall panel 1 is abutted against the limit block 901, and the limit block 901 limits the left loading wall panel, which can prevent the left loading wall panel 1 from moving to the left under the pressure of the piston rod.

[0036] In this embodiment, a threaded section is respectively provided at both ends of the rod 9, and a mounting hole is provided on the right loading wall plate 2. The right end of the rod 9 passes through the mounting hole and is screwed on the right loading wall plate 2 via two nuts, so as to facilitate the disassembly and installation of the rod 9, and the design of the threaded section can facilitate the fine adjustment of the left and right positions of the limit block 901 to better adapt to the landing gear strut 5. In addition, the detachable design can facilitate the selection of rods 9 with different insertion hole settings according to different models of the landing gear strut 5.

[0037] Furthermore, in the present solution, a connecting ear 501 is respectively provided at both ends of the landing gear strut 5; an ear plate 6 is respectively provided on the right side surface of the left loading wall panel 1 and the end of the piston rod of the electric servo cylinder 4, and the ear plate 6 and the connecting ear 501 at both ends of the landing gear strut 5 can be correspondingly connected through a pin shaft. In a preferred embodiment of the present solution, the connecting ear 501 is a double-ear ear plate, and the two ear plates 6 are both single-ear ear plates, and the two single-ear ear plates and the piston rod of the electric servo cylinder 4 are located on the same straight line.

[0038] Furthermore, in this embodiment, a round hole is provided on the right loading wall panel 2, and the electric servo cylinder 4 is installed on the right side of the right loading wall panel 2 through multiple bolts, and the piston rod of the electric servo cylinder 4 passes through the right loading wall panel 2 to the left from the round hole.

[0039] The above is only a preferred embodiment of the utility model. It should be understood that the utility model is not limited to the form disclosed herein, and should not be regarded as excluding other embodiments, but can be used in various other combinations, modifications and environments, and can be modified within the scope of the concept described herein through the above teachings or the technology or knowledge of the relevant field. The changes and modifications made by those skilled in the art do not deviate from the spirit and scope of the utility model, and should be within the scope of protection of the claims attached to the utility model.

Claims

1. A horizontal strut compression buckling test device for use in a pressure test of a landing gear strut (5), characterized in that: It comprises a rack table (3), and a left loading wallboard (1) and a right loading wallboard (2) vertically arranged on the rack table (3); The right side surface of the left loading wall panel (1) is provided with a connecting portion, and the right loading wall panel (2) is provided with an electric servo cylinder (4), the piston rod end of the electric servo cylinder (4) can be connected to one end of the landing gear support rod (5), and the other end of the landing gear support rod (5) can be connected to the connecting portion; After the installation is completed, the landing gear support rod (5) and the piston rod of the electric servo cylinder (4) are located on the same straight line, and the electric servo cylinder (4) is started, and the end of the piston rod of the electric servo cylinder (4) moves to the left to squeeze the landing gear support rod (5); A pressure sensor is also installed at the connecting portion; The horizontal strut compression buckling test device is also equipped with a micro-displacement pressure measuring assembly for measuring the deformation amount of the landing gear strut (5).

2. A horizontal brace bar compression buckling test device according to claim 1, characterized in that: A guide rail (7) is provided on the upper left side of the frame table (3), and the left loading wall panel (1) is slidably mounted on the guide rail (7); A screw rod pair without a self-locking function is also provided on the upper left side of the frame table (3), and the moving part of the screw rod pair is the left loading wall panel (1).

3. A horizontal brace bar compression buckling test device according to claim 2, characterized in that: The horizontal brace compression buckling test device further comprises at least two rods (9) symmetrically arranged on the right loading wallboard (2); The right end of the rod (9) is vertically mounted on the right loading wallboard (2); the left loading wallboard (1) is provided with a through hole corresponding to the rod (9); and the left end of the rod (9) passes through the through hole to the left; The rod (9) is provided with an insertion hole, in which a detachable limit block (901) is inserted. After installation, the left side surface of the left loading wall panel (1) abuts against the limit block (901).

4. A horizontal brace bar compression buckling test device according to claim 3, characterized in that: The right end of the rod (9) is provided with a threaded section, and the right loading wallboard (2) is provided with a mounting hole. The right end of the rod (9) passes through the mounting hole and is screwed onto the right loading wallboard (2) via two nuts.

5. A horizontal brace bar compression buckling test device according to claim 2, characterized in that: The horizontal brace compression buckling test device further comprises an electrical control system, wherein the electrical control system comprises an electrical control device and an operating screen (11); The operating panel (11), the electric servo cylinder (4) and the pressure sensor are respectively connected to the electric control device via telecommunication.

6. A horizontal brace bar compression buckling test device according to claim 2, characterized in that: The screw pair comprises a screw (8), a screw pair support 1 (801), and a screw pair support 2 (802), and the two ends of the screw (8) are rotatably mounted on the screw pair support 1 (801) and the screw pair support 2 (802) respectively; The left loading wall plate (1) is located between the first screw auxiliary support (801) and the second screw auxiliary support (802). A threaded hole is provided at the lower part of the left loading wall plate (1), and the screw (8) is threadedly matched with the threaded hole. A hand wheel (803) is also provided after the left end of the lead screw (8) passes through the lead screw auxiliary support (801).

7. A horizontal brace bar compression buckling test device according to claim 2, characterized in that: The two ends of the landing gear strut (5) are respectively provided with a connecting ear (501); The right side surface of the left loading wall panel (1) and the piston rod end of the electric servo cylinder (4) are respectively provided with an ear plate (6), and the ear plate (6) and the connecting ears (501) at both ends of the landing gear support rod (5) can be correspondingly connected through a pin shaft.

8. A horizontal brace bar compression buckling test device according to claim 2, characterized in that: The right loading wall plate (2) is provided with a round hole, the electric servo cylinder (4) is installed on the right side of the right loading wall plate (2) through a plurality of bolts, and the piston rod of the electric servo cylinder (4) passes through the right loading wall plate (2) to the left from the round hole.

9. A horizontal brace bar compression buckling test device according to claim 2, characterized in that: The frame table (3) is installed on the bracket (10), and the bottom of the bracket (10) is provided with four universal wheels (1001) and a plurality of adjustable foot cups.

10. The horizontal brace bar compression buckling test device according to claim 2, characterized in that: A lifting ear is respectively provided on the top of the left loading wall panel (1) and the right loading wall panel (2).

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