A test bench and test method for turning performance of an aircraft nose landing gear

Abstract

A kind of airplane nose landing gear turning performance test bench and test method contain nose landing gear test piece, rigid support frame and jacking device, the body of nose landing gear test piece is fixed on rigid support frame, wheel is supported on jacking device, turning mechanism drives the top plate of jacking device top by fixed shaft along with wheel rotation, the fixed shaft is connected with a loading actuator, the telescopic end of loading actuator is hinged with one end of fixed shaft, the other end of loading actuator is hinged on support frame by connecting seat, the loading actuator is controlled by torque loading controller, when carrying out turning performance test, nose inner cylinder and wheel are compressed using jacking device, so that wheel is in turnable state;According to the turning angle of wheel, predetermined torque is applied to fixed shaft using torque loading actuator.

Description

Technical Field

[0001] This invention belongs to the field of aviation testing, specifically relating to a test bench and test method for the turning performance of an aircraft nose landing gear. Background Technology

[0002] When an aircraft taxis on the ground or makes low-speed corrections, it performs a turning maneuver. During this maneuver, due to the deflection of the wheels, the tires experience a counter-torque; this torque is the turning torque. This torque is transmitted through the wheels to the anti-torsion arms, the turning mechanism, and the nose wheel steering system. In the laboratory, the turning torque is precisely simulated to fully and reliably validate the nose landing gear structure and the nose wheel steering system.

[0003] When an aircraft makes a turn, the turning actuator (rack) in the turning mechanism moves left and right under the control of the nose wheel turning system. The movement of the turning actuator (rack) drives the gear structure in the turning mechanism to rotate left and right, which in turn drives the anti-torsion arm connected to it to rotate. The rotation of the anti-torsion arm drives the nose wheel inner cylinder and the aircraft wheel to rotate.

[0004] When conducting front wheel turning tests in the laboratory, the front landing gear lifting device must be used to lift the front landing gear inner cylinder to simulate the compression state of the front landing gear under load. Turning operations can only be performed after the front landing gear is compressed under load.

[0005] Currently, the cornering torque loading scheme for front landing gears on domestic cornering performance test benches involves installing a bracket on the top plate of the jacking device to fix the torque loading actuator, and then applying cornering torque through the wheel axle. In this scheme, because the tire is an elastic body, factors such as usage time, inflation pressure, and external temperature all affect tire deformation. Therefore, even if the jacking device has a consistent lifting height, the wheel axle's position in the vertical direction cannot be kept consistent, making it difficult to install the loading actuator. Due to this problem, this scheme has not been implemented.

[0006] Another domestic method for applying turning torque involves using a static load to replace the actual turning torque. In the laboratory, after the lifting device lifts the inner cylinder of the nose wheel, when the nose wheel turns, the tire rubs against the top plate of the lifting device, and this friction provides torque. Since the tire is not rotating at this time, it is equivalent to performing a turning operation while the aircraft is stationary. This method uses a static load to replace the actual turning torque, and this torque is inconsistent with the turning torque during aircraft movement. The turning torque is greatly affected by the friction system of the top plate of the lifting device and cannot be controlled. In this case, the laboratory can only conduct functional tests on the nose wheel turning system and cannot conduct precise performance tests.

[0007] The two current domestic front-wheel steering torque loading schemes cannot truly achieve the loading of steering torque, which makes it impossible to conduct performance tests on the front wheel steering system in the laboratory and to fully complete the verification tests of the front wheel steering system. As a result, the front wheel steering system cannot be fully tested and verified in the laboratory, and the problems of the front wheel steering system cannot be discovered and exposed in time. Problems discovered later are difficult to solve in terms of schedule and cost, causing many inconveniences to the finalization and development of the front wheel steering system. Summary of the Invention

[0008] To overcome the shortcomings of the existing technology, the purpose of this application is to provide a test bench and test method for the turning performance of aircraft nose landing gear. A rigid support frame is used to suspend the nose landing gear test piece, and a lifting device is installed at the bottom of the test piece. The lifting device ensures that the inner cylinder of the nose landing gear is in a compressed state, providing the preconditions for the turning test. A torque loading actuator provides a set torque load to the anti-torsion arm and the turning mechanism, thereby improving the test effect of the aircraft nose landing gear turning performance.

[0009] A test bench for the turning performance of an aircraft nose landing gear includes a nose landing gear test piece, a rigid support frame, and a lifting device. The nose landing gear test piece includes a turning mechanism, an anti-torsion arm, a nose landing gear inner cylinder, and a wheel. The turning mechanism is connected to the upper end of the anti-torsion arm via a fixed shaft, and the lower end of the anti-torsion arm is connected to the nose landing gear inner cylinder. The wheel is fixed to the lower end of the nose landing gear inner cylinder. The body of the nose landing gear test piece is fixed on the rigid support frame, and the wheel is supported on the lifting device. The top of the lifting device has a rotatable top plate. The turning mechanism drives the wheel and the top plate of the lifting device to rotate together via the fixed shaft. The fixed shaft is connected to a torque loading actuator, which includes a loading actuating cylinder. The telescopic end of the loading actuating cylinder is hinged to one end of the fixed shaft, and the other end of the loading actuating cylinder is hinged to the support frame via a connecting seat. The loading actuating cylinder is controlled by a torque loading controller.

[0010] The aforementioned aircraft nose landing gear turning performance test bench is characterized in that a torque sensor is provided on the telescopic end of the loading actuator of the torque loading actuator, and the torque sensor is electrically connected to the torque loading controller.

[0011] The aforementioned aircraft nose landing gear turning performance test bench is characterized in that one end of the fixed shaft is provided with a horizontal double-ear joint, and the fixed shaft is hinged to the telescopic end of the loading actuator cylinder through the horizontal double-ear joint.

[0012] A method for testing the turning performance of an aircraft nose landing gear, characterized by comprising the following: 1) using the aforementioned aircraft nose landing gear turning performance test bench; 2) during the turning performance test, using a jacking device to compress the nose landing gear inner cylinder and the wheel, so that the wheel is in a turning state; 3) using a turning mechanism to drive the wheel and the top plate at the top of the jacking device to rotate together via a fixed shaft, and simultaneously using a torque loading actuator to apply a predetermined torque to the fixed shaft according to the turning angle of the wheel.

[0013] The beneficial effects of this application are as follows: The aircraft nose landing gear turning performance test bench and test method provided by this application can offer simple, reliable, and accurate torque loading for aircraft nose landing gear turning. This ensures that the functional and performance tests of the aircraft nose wheel turning system are conducted in a laboratory environment, allowing for the early detection of design problems in the nose wheel turning system and avoiding the problems that can easily arise from large workloads, high costs, and tight deadlines associated with design changes when issues are discovered during flight testing. This aircraft nose landing gear turning performance test bench and test method are compact, highly practical, easy to install, and have low production and operating costs. The torque loading method is simple and reliable. Furthermore, it allows for early response analysis of the nose wheel turning system, enabling optimization of the nose wheel turning system design.

[0014] The present application will be further described in detail below with reference to the accompanying drawings of the embodiments. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structural principle of an aircraft nose landing gear turning performance test bench.

[0016] Figure 2 This is a schematic diagram of the principle of the torque loading actuator for turning.

[0017] The numbers in the diagram are explained as follows: 1-fixed shaft, 2-loading actuator cylinder, 3-torque sensor, 4-turning mechanism, 5-support frame, 6-anti-torsion arm, 7-front lifting inner cylinder, 8-machine wheel, 9-lifting device, 10-connecting seat, 11-double lug joint. Detailed Implementation

[0018] Referring to the attached drawings, the aircraft nose landing gear turning performance test bench of this application includes a nose landing gear test piece, a rigid support frame 5, and a lifting device 9. The nose landing gear test piece includes a turning mechanism 4, an anti-torsion arm 6, a nose landing gear inner cylinder 7, and a wheel 8. The turning mechanism 4 is connected to the upper end of the anti-torsion arm 6 via a fixed shaft 1, and the lower end of the anti-torsion arm 6 is connected to the nose landing gear inner cylinder 7. The wheel 8 is fixed to the lower end of the nose landing gear inner cylinder 7. The body of the nose landing gear test piece is fixed on the rigid support frame 5, and the wheel 8 is supported on the lifting device 9. The top of the device 9 is equipped with a rotatable top plate. The turning mechanism 4 drives the wheel 8 and the top plate of the lifting device 9 to rotate together via the fixed shaft 1. A prominent feature of this test bench is that it is equipped with a turning torque loading actuator. The torque loading actuator is connected to the fixed shaft 1. This torque loading actuator contains a loading actuating cylinder 2. The telescopic end of the loading actuating cylinder 2 is hinged to one end of the fixed shaft 1, and the other end of the loading actuating cylinder 2 is hinged to the support frame 5 via the connecting seat 10. The loading actuating cylinder 2 is controlled by the torque loading controller. The fixed shaft 1 on the front landing gear test piece is specially made for the test. One end of the fixed shaft 1 is equipped with a horizontal double-ear joint 11. The fixed shaft 1 is hinged to the telescopic end of the loading actuating cylinder 2 via the horizontal double-ear joint 11.

[0019] The front test specimen is suspended in mid-air using a rigid support frame 5. A lifting device 9 is installed at the bottom of the test specimen. The lifting device 9 ensures that the inner cylinder 7 of the front test specimen is in a compressed state, providing the prerequisite for the turning test. The top of the lifting device 9 is equipped with a freely rotatable top plate. When turning, the top plate rotates together with the wheel 8, without generating turning torque. The turning torque is provided by the loading actuator 2.

[0020] In order to accurately sense the turning torque, a torque sensor 3 is installed on the telescopic end of the loading actuator 2. The torque sensor 3 is connected to the torque loading controller by an electrical signal via a cable.

[0021] When conducting the aircraft nose landing gear turning performance test using the aforementioned aircraft nose landing gear turning performance test bench, the jacking device 9 compresses the nose landing gear inner cylinder 7 and the wheel 8, making the wheel 8 in a turning state. During the test, the turning mechanism 4 drives the wheel 8 and the top plate at the top of the jacking device 9 to rotate together through the fixed shaft 1. At the same time, according to the turning angle of the wheel 8, the loading actuator 2 of the torque loading actuator applies a predetermined torque to the fixed shaft 1. The magnitude of this torque is then fed back to the torque loading controller through the torque sensor 3, realizing closed-loop control of the turning torque.

[0022] To facilitate the application of torque, when the wheel 8 is in the neutral position, the axis of the loading actuator 2 should ideally coincide with the axis of the fixed shaft 1. This position facilitates the installation and fixation of the loading actuator 2. Simultaneously, it ensures that when the wheel 8 rotates left or right, the movement trajectories of the fixed shaft 1 and the loading actuator 2 are symmetrical along the neutral position of the wheel, facilitating the control of the application torque.

[0023] The wheel 8 turns under the action of the turning mechanism 4. Since the axis of the fixed shaft 1 and the loading actuator 2 will be deflected when the torque is applied, the double-ear joint 11 on the fixed shaft 1 is preferably horizontal in practice to prevent the double-ear joint 11 from interfering with the loading actuator 2.

Claims

1. A test bench for the turning performance of an aircraft nose landing gear, comprising a nose landing gear test piece, a rigid support frame, and a lifting device, wherein the nose landing gear test piece includes a turning mechanism, an anti-torsion arm, a nose landing gear inner cylinder, and a wheel; the turning mechanism is connected to the upper end of the anti-torsion arm via a fixed shaft, the lower end of the anti-torsion arm is connected to the nose landing gear inner cylinder, and the wheel is fixed to the lower end of the nose landing gear inner cylinder; the body of the nose landing gear test piece is fixed on the rigid support frame, and the wheel is supported on the lifting device; the top of the lifting device is provided with a rotatable top plate; the turning mechanism drives the wheel and the top plate of the lifting device to rotate together via the fixed shaft, characterized in that... The fixed shaft is connected to a torque loading actuator, which includes a loading actuating cylinder. The telescopic end of the loading actuating cylinder is hinged to one end of the fixed shaft, and the other end of the loading actuating cylinder is hinged to the support frame via a connecting seat. The loading actuating cylinder is controlled by a torque loading controller.

2. The aircraft nose landing gear turning performance test bench as described in claim 1, characterized in that, A torque sensor is provided on the telescopic end of the loading actuator cylinder of the torque loading actuator, and the torque sensor is electrically connected to the torque loading controller.

3. The aircraft nose landing gear turning performance test bench as described in claim 1, characterized in that, One end of the fixed shaft is provided with a horizontal double-ear joint, and the fixed shaft is hinged to the telescopic end of the loading actuator cylinder through the horizontal double-ear joint.

4. A method for testing the turning performance of an aircraft nose landing gear, characterized in that... It includes the following: 1) using the aircraft nose landing gear turning performance test bench as described in claim 1, 2 or 3; 2) during the turning performance test, the nose landing gear inner cylinder and the wheel are compressed by a jacking device to make the wheel turnable; 3) the turning mechanism drives the wheel and the top plate at the top of the jacking device to rotate together through a fixed shaft, and at the same time, according to the turning angle of the wheel, a torque loading actuator applies a predetermined torque to the fixed shaft.

5. The aircraft nose landing gear turning performance test method as described in claim 1, characterized in that, When the wheel is in the neutral position, the axis of the loading actuator cylinder coincides with the axis of the fixed shaft.

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