Device and method for testing torsional moment of undercarriage buffer

Abstract

The invention discloses an undercarriage buffer torsional moment testing device and a testing method. The testing device adopts a lead screw elevator to push a tested buffer piston rod to be compressed, and adopts a rotary speed reducer to drive the buffer piston rod to rotate through a torque arm and can move up and down along with the piston rod. According to the test method, the torsional moment of the buffer can be tested in the compression amount change process of the tested buffer, and the compression amount and the torsional angle of the buffer are recorded. The device is easy to install, the test scale is reduced, and the test cost can be saved.

Description

Technical Field

[0001] This invention relates to the field of landing gear testing technology, and in particular to a landing gear buffer torsional torque testing device and testing method. Background Technology

[0002] The buffer is a key component of the aircraft landing gear system, primarily used to ensure the aircraft's agile movement on the ground and mitigate landing impacts and turbulence. The buffer undergoes extension, retraction, and torsional movements during nose landing gear turns, main landing gear coordinated turns, and the three-dimensional retraction and extension of part of the landing gear. The buffer's torsional flexibility and torque are key factors affecting the landing gear's turning and three-dimensional retraction and extension performance. Therefore, testing the buffer's torsional torque is necessary during landing gear development. Existing testing equipment is complex, requires large-scale testing, and is costly. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to address the deficiencies mentioned in the background art by providing a landing gear buffer torsional torque testing device and testing method.

[0004] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: A landing gear buffer torsional torque testing device includes a base, a force transmission frame, a torsional loading mechanism, a compression mechanism, a fixed seat, a fixed pin, a hinge seat, a hinge rod, a first wire displacement sensor, and a second wire displacement sensor. The lower end of the force transmission frame is fixed to the base, and the force transmission frame is provided with horizontal first to third mounting plates from top to bottom; the first to third mounting plates are provided with coaxial mounting holes; The torsional loading mechanism includes a first motor, a rotary reducer, a connecting plate, a torque sensor, and a loading joint; The first motor and the rotary reducer are both fixed on the second mounting plate. The rotary reducer uses a hollow rotor, and the rotor of the rotary reducer is coaxial with the mounting hole of the second mounting plate. The output shaft of the first motor and the input shaft of the rotary reducer are coaxially fixed and used to drive the rotary reducer to work. The connecting plate is fixed on the rotor of the rotary reducer, and the center of the connecting plate is provided with a through hole coaxial with the rotor of the rotary reducer. The torque sensor is a hollow ring torque sensor; The loading joint includes a fixing plate, a loading plate, a loading pin, first to fourth torque arms, and first to sixth hinge shafts; Both the loading plate and the fixing plate are rectangular plates; The fixed plate has a through hole in its center, and the loading plate has a through hole in its center for engaging with the lower end of the piston rod of the landing gear buffer to be tested; and the loading plate has a pin hole on the side wall of the through hole in its center for engaging with the loading pin. The loading pin is used to cooperate with the pin hole on the loading plate and the pin hole at the lower end of the piston rod of the landing gear buffer under test for connecting the wheel axle, so as to fix the lower end of the piston rod of the landing gear buffer under test in the through hole in the center of the loading plate. One end of the first torque arm is hinged to one end of the loading plate via a first hinge shaft, and the other end is hinged to a second torque arm via a second hinge shaft; the other end of the second torque arm is hinged to one end of the fixed plate via a third hinge shaft; one end of the third torque arm is hinged to the other end of the loading plate via a fourth hinge shaft, and the other end is hinged to one end of the fourth torque arm via a fifth hinge shaft; the other end of the fourth torque arm is hinged to the other end of the fixed plate via a sixth hinge shaft; the first to sixth hinge shafts are parallel, such that the loading plate is located above the fixed plate and the through hole in the center of the loading plate is coaxial with the through hole in the center of the fixed plate; the first hinge shaft is perpendicular to the axis of the through hole in the center of the loading plate; One end of the torque sensor is fixedly connected to the connecting plate, and the other end is fixedly connected to the fixing plate, so that the loading joint is located between the second mounting plate and the third mounting plate, and the through hole in the center of the connecting plate, the torque sensor, and the through hole in the center of the fixing plate are coaxial. The compression mechanism includes a second motor and a screw jack, both of which are fixed to the third mounting plate. The lifting rod of the screw jack is coaxial with the mounting hole of the third mounting plate. One end of the lifting rod passes through the through hole in the center of the connecting plate, the rotor of the rotary reducer, the torque sensor, and the through hole in the center of the fixed plate, allowing it to move freely up and down. The output shaft of the second motor and the input shaft of the screw jack are coaxially fixed and used to drive the screw jack to work and apply pressure to the piston rod of the landing gear buffer under test, which is fixed to the through hole in the center of the loading plate. The fixed seat and the hinge seat are respectively disposed on both sides of the central through hole of the first mounting plate, and are both fixedly connected to the first mounting plate; The mounting base is a double-ear type mounting base, and its double ears are provided with pin holes for cooperating with the fixing pin; the fixing pin is used to cooperate with the pin holes on the mounting base and the pin holes on the retraction and extension actuator joint of the landing gear buffer under test, so as to fix the retraction and extension actuator of the landing gear buffer under test. One end of the hinge rod is hinged to the hinge seat, and the other end is used to hinge to the anti-torsion arm joint of the landing gear buffer to be tested. The first wire displacement sensor is fixed on the force transmission frame. Its wire is connected to the outer wall of the torque sensor and the wire is set horizontally. It is used to measure the displacement of the torque sensor in the circumferential direction, and then calculate the rotation angle of the piston rod of the landing gear buffer under test. The second wire displacement sensor is mounted on the connecting plate, and its wire is connected to the loading plate and is vertically arranged. It is used to measure the compression of the piston rod of the landing gear buffer under test.

[0005] As a further optimization of the landing gear buffer torsional torque testing device of the present invention, the force transmission frame and the first to third mounting plates are all made of low alloy high-strength structural steel.

[0006] The present invention also discloses a method for testing the torsional moment of the landing gear buffer using the landing gear buffer torsional moment testing device, comprising the following steps: Step 1), fix the lower end of the piston rod of the landing gear buffer to be tested in the through hole in the center of the loading plate by the loading pin, fix the retraction and extension actuator joint of the landing gear buffer to be tested to the fixed seat by the fixing pin, and hinge the end of the hinge rod away from the hinge seat to the anti-torsion arm joint of the landing gear buffer to be tested. Step 2), control the second motor to work, so that the lifting rod of the screw jack pushes the piston rod of the landing gear buffer under test, adjusts the compression of the buffer under test, and measures and records the compression of the piston rod of the landing gear buffer under test through the first wire displacement sensor; Step 3) Control the first motor to work and twist the piston rod of the buffer. Record the torque of the piston rod of the landing gear buffer under test through the torque sensor. At the same time, measure the displacement of the torque sensor in the circumferential direction through the first wire displacement sensor, and then calculate the rotation angle of the piston rod of the landing gear buffer under test.

[0007] Compared with the prior art, the present invention, employing the above technical solution, has the following technical effects: This invention can test the torsional torque of a test buffer during changes in its compression, and record the compression and torsional angle. The testing device is simple to install, reducing the scale of the test and saving testing costs. Attached Figure Description

[0008] Figure 1 This is a schematic diagram of the structure of the present invention; Figure 2 This is a schematic diagram of the torsion loading mechanism in this invention; Figure 3 This is a schematic diagram of the compression mechanism in this invention; Figure 4 This is a schematic diagram of the structure of the landing gear buffer to be tested being installed on this invention.

[0009] In the diagram, 1-base, 2-force transmission frame, 3-first motor, 4-rotation reducer, 5-connecting plate, 6-torque sensor, 7-loading connector, 8-second motor, 9-screw jack, 10-first mounting plate, 11-third mounting plate, 12-fixed seat, 13-hinge seat, 14-hinge rod, 15-landing gear buffer under test, 16-first cable displacement sensor, 17-second cable displacement sensor, 18-fixed plate, 19-loading plate, 20-first torque arm, 21-second torque arm, 22-third torque arm, 23-fourth torque arm, 24-loading pin, 25-retraction and extension actuator connector for the landing gear buffer under test, 26-anti-torsion arm connector for the landing gear buffer under test, 27-piston rod of the landing gear buffer under test, 28-lifting rod of the screw jack. Detailed Implementation

[0010] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings: This invention can be implemented in many different forms and should not be considered limited to the embodiments described herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully express the scope of the invention to those skilled in the art. In the drawings, components are enlarged for clarity.

[0011] It should be understood that although the terms first, second, third, etc., may be used herein to describe various elements, components, and / or parts, these elements, components, and / or parts are not limited by these terms. These terms are merely used to distinguish elements, components, and / or parts from one another. Therefore, the first element, component, and / or part discussed below may be a second element, component, or part without departing from the teachings of this invention.

[0012] like Figure 1 As shown, the present invention discloses a landing gear buffer torsional torque testing device, including a base, a force transmission frame, a torsional loading mechanism, a compression mechanism, a fixed seat, a fixed pin, a hinge seat, a hinge rod, a first wire displacement sensor and a second wire displacement sensor. The lower end of the force transmission frame is fixed to the base, and the force transmission frame is provided with horizontal first to third mounting plates from top to bottom; the first to third mounting plates are provided with coaxial mounting holes; like Figure 2 As shown, the torsional loading mechanism includes a first motor, a rotary reducer, a connecting plate, a torque sensor, and a loading joint; The first motor and the rotary reducer are both fixed on the second mounting plate. The rotary reducer uses a hollow rotor, and the rotor of the rotary reducer is coaxial with the mounting hole of the second mounting plate. The output shaft of the first motor and the input shaft of the rotary reducer are coaxially fixed and used to drive the rotary reducer to work. The connecting plate is fixed on the rotor of the rotary reducer, and the center of the connecting plate is provided with a through hole coaxial with the rotor of the rotary reducer. The torque sensor is a hollow ring torque sensor; The loading joint includes a fixing plate, a loading plate, a loading pin, first to fourth torque arms, and first to sixth hinge shafts; Both the loading plate and the fixing plate are rectangular plates; The fixed plate has a through hole in its center, and the loading plate has a through hole in its center for engaging with the lower end of the piston rod of the landing gear buffer to be tested; and the loading plate has a pin hole on the side wall of the through hole in its center for engaging with the loading pin. The loading pin is used to cooperate with the pin hole on the loading plate and the pin hole at the lower end of the piston rod of the landing gear buffer under test for connecting the wheel axle, so as to fix the lower end of the piston rod of the landing gear buffer under test in the through hole in the center of the loading plate. One end of the first torque arm is hinged to one end of the loading plate via a first hinge shaft, and the other end is hinged to a second torque arm via a second hinge shaft; the other end of the second torque arm is hinged to one end of the fixed plate via a third hinge shaft; one end of the third torque arm is hinged to the other end of the loading plate via a fourth hinge shaft, and the other end is hinged to one end of the fourth torque arm via a fifth hinge shaft; the other end of the fourth torque arm is hinged to the other end of the fixed plate via a sixth hinge shaft; the first to sixth hinge shafts are parallel, such that the loading plate is located above the fixed plate and the through hole in the center of the loading plate is coaxial with the through hole in the center of the fixed plate; the first hinge shaft is perpendicular to the axis of the through hole in the center of the loading plate; One end of the torque sensor is fixedly connected to the connecting plate, and the other end is fixedly connected to the fixing plate, so that the loading joint is located between the second mounting plate and the third mounting plate, and the through hole in the center of the connecting plate, the torque sensor, and the through hole in the center of the fixing plate are coaxial. like Figure 1 , Figure 3 As shown, the compression mechanism includes a second motor and a screw jack, wherein both the second motor and the screw jack are fixed to the third mounting plate; the lifting rod of the screw jack and the mounting hole of the third mounting plate are coaxial, and one end of the lifting rod passes through the through hole in the center of the connecting plate, the rotor of the rotary reducer, the torque sensor, and the through hole in the center of the fixed plate in sequence, and can move up and down freely; the output shaft of the second motor and the input shaft of the screw jack are coaxially fixed and connected to drive the screw jack to work and apply pressure to the piston rod of the landing gear buffer under test, which is fixed to the through hole in the center of the loading plate; The fixed seat and the hinge seat are respectively disposed on both sides of the central through hole of the first mounting plate, and are both fixedly connected to the first mounting plate; The mounting base is a double-ear type mounting base, and its double ears are provided with pin holes for cooperating with the fixing pin; the fixing pin is used to cooperate with the pin holes on the mounting base and the pin holes on the retraction and extension actuator joint of the landing gear buffer under test, so as to fix the retraction and extension actuator of the landing gear buffer under test. One end of the hinge rod is hinged to the hinge seat, and the other end is used to hinge to the anti-torsion arm joint of the landing gear buffer to be tested. The first wire displacement sensor is fixed on the force transmission frame. Its wire is connected to the outer wall of the torque sensor and the wire is set horizontally. It is used to measure the displacement of the torque sensor in the circumferential direction, and then calculate the rotation angle of the piston rod of the landing gear buffer under test. The second wire displacement sensor is mounted on the connecting plate, with its wire connected to the loading plate and the wire set vertically. It is used to measure the compression of the piston rod of the landing gear buffer under test.

[0013] The force transmission frame and the first to third mounting plates are preferably made of low-alloy high-strength structural steel.

[0014] The present invention also discloses a method for testing the torsional moment of the landing gear buffer using the landing gear buffer torsional moment testing device, comprising the following steps: Step 1): Fix the lower end of the piston rod of the landing gear buffer to be tested into the through hole in the center of the loading plate using a loading pin. Secure the retraction / extension actuator joint of the landing gear buffer to be tested to the fixed seat using a fixing pin. Hinge the end of the hinge rod away from the hinge seat to the anti-torsion arm joint of the landing gear buffer to be tested. Figure 4 As shown; Step 2), control the second motor to work, so that the lifting rod of the screw jack pushes the piston rod of the landing gear buffer under test, adjusts the compression of the buffer under test, and measures and records the compression of the piston rod of the landing gear buffer under test through the first wire displacement sensor; Step 3) Control the first motor to work and twist the piston rod of the buffer. Record the torque of the piston rod of the landing gear buffer under test through the torque sensor. At the same time, measure the displacement of the torque sensor in the circumferential direction through the first wire displacement sensor, and then calculate the rotation angle of the piston rod of the landing gear buffer under test.

[0015] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein.

[0016] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A landing gear buffer torsional torque testing device, characterized in that, It includes a base, a force transmission frame, a torsion loading mechanism, a compression mechanism, a fixed seat, a fixed pin, a hinge seat, a hinge rod, a first wire displacement sensor, and a second wire displacement sensor; The lower end of the force transmission frame is fixed to the base, and the force transmission frame is provided with horizontal first to third mounting plates from top to bottom; the first to third mounting plates are provided with coaxial mounting holes; The torsional loading mechanism includes a first motor, a rotary reducer, a connecting plate, a torque sensor, and a loading joint; The first motor and the rotary reducer are both fixed on the second mounting plate. The rotary reducer uses a hollow rotor, and the rotor of the rotary reducer is coaxial with the mounting hole of the second mounting plate. The output shaft of the first motor and the input shaft of the rotary reducer are coaxially fixed and used to drive the rotary reducer to work. The connecting plate is fixed on the rotor of the rotary reducer, and the center of the connecting plate is provided with a through hole coaxial with the rotor of the rotary reducer. The torque sensor is a hollow ring torque sensor; The loading joint includes a fixing plate, a loading plate, a loading pin, first to fourth torque arms, and first to sixth hinge shafts; Both the loading plate and the fixing plate are rectangular plates; The fixed plate has a through hole in its center, and the loading plate has a through hole in its center for engaging with the lower end of the piston rod of the landing gear buffer to be tested; and the loading plate has a pin hole on the side wall of the through hole in its center for engaging with the loading pin. The loading pin is used to cooperate with the pin hole on the loading plate and the pin hole at the lower end of the piston rod of the landing gear buffer under test for connecting the wheel axle, so as to fix the lower end of the piston rod of the landing gear buffer under test in the through hole in the center of the loading plate. One end of the first torque arm is hinged to one end of the loading plate via a first hinge shaft, and the other end is hinged to a second torque arm via a second hinge shaft; the other end of the second torque arm is hinged to one end of the fixed plate via a third hinge shaft; one end of the third torque arm is hinged to the other end of the loading plate via a fourth hinge shaft, and the other end is hinged to one end of the fourth torque arm via a fifth hinge shaft; the other end of the fourth torque arm is hinged to the other end of the fixed plate via a sixth hinge shaft; the first to sixth hinge shafts are parallel, such that the loading plate is located above the fixed plate and the through hole in the center of the loading plate is coaxial with the through hole in the center of the fixed plate; the first hinge shaft is perpendicular to the axis of the through hole in the center of the loading plate; One end of the torque sensor is fixedly connected to the connecting plate, and the other end is fixedly connected to the fixing plate, so that the loading joint is located between the second mounting plate and the third mounting plate, and the through hole in the center of the connecting plate, the torque sensor, and the through hole in the center of the fixing plate are coaxial. The compression mechanism includes a second motor and a screw jack, both of which are fixed to the third mounting plate. The lifting rod of the screw jack is coaxial with the mounting hole of the third mounting plate. One end of the lifting rod passes through the through hole in the center of the connecting plate, the rotor of the rotary reducer, the torque sensor, and the through hole in the center of the fixed plate, allowing it to move freely up and down. The output shaft of the second motor and the input shaft of the screw jack are coaxially fixed and used to drive the screw jack to work and apply pressure to the piston rod of the landing gear buffer under test, which is fixed to the through hole in the center of the loading plate. The fixed seat and the hinge seat are respectively disposed on both sides of the central through hole of the first mounting plate, and are both fixedly connected to the first mounting plate; The mounting base is a double-ear type mounting base, and its double ears are provided with pin holes for cooperating with the fixing pin; the fixing pin is used to cooperate with the pin holes on the mounting base and the pin holes on the retraction and extension actuator joint of the landing gear buffer under test, so as to fix the retraction and extension actuator of the landing gear buffer under test. One end of the hinge rod is hinged to the hinge seat, and the other end is used to hinge to the anti-torsion arm joint of the landing gear buffer to be tested. The first wire displacement sensor is fixed on the force transmission frame. Its wire is connected to the outer wall of the torque sensor and the wire is set horizontally. It is used to measure the displacement of the torque sensor in the circumferential direction, and then calculate the rotation angle of the piston rod of the landing gear buffer under test. The second wire displacement sensor is mounted on the connecting plate, and its wire is connected to the loading plate and is vertically arranged. It is used to measure the compression of the piston rod of the landing gear buffer under test.

2. The landing gear buffer torsional torque testing device according to claim 1, characterized in that, The force transmission frame and the first to third mounting plates are all made of low-alloy high-strength structural steel.

3. A method for testing the torsional torque of a landing gear buffer based on the landing gear buffer torsional torque testing device according to claim 1, characterized in that, Includes the following steps: Step 1), fix the lower end of the piston rod of the landing gear buffer to be tested in the through hole in the center of the loading plate by the loading pin, fix the retraction and extension actuator joint of the landing gear buffer to be tested to the fixed seat by the fixing pin, and hinge the end of the hinge rod away from the hinge seat to the anti-torsion arm joint of the landing gear buffer to be tested. Step 2), control the second motor to work, so that the lifting rod of the screw jack pushes the piston rod of the landing gear buffer under test, adjusts the compression of the buffer under test, and measures and records the compression of the piston rod of the landing gear buffer under test through the first wire displacement sensor; Step 3) Control the first motor to work and twist the piston rod of the buffer. Record the torque of the piston rod of the landing gear buffer under test through the torque sensor. At the same time, measure the displacement of the torque sensor in the circumferential direction through the first wire displacement sensor, and then calculate the rotation angle of the piston rod of the landing gear buffer under test.

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