CN115791117A - Fatigue life testing device and method for airplane steering engine steel cable - Google Patents

Abstract

A test device and test method for the fatigue life of aircraft steering gear cables. The test device includes an electro-hydraulic servo actuator, a test platform, a pulley, a steel cable and a counterweight. The test platform is supported on a bracket, and the working surface of the test platform is vertical to the On the ground, there are multiple sets of pulleys on the working surface of the test platform. Each set of pulleys includes two steering pulleys and multiple track pulleys. Each set of pulleys forms a test track. The steering pulleys are located at both ends of the test track. The track pulleys simulate the aircraft. Constraint trajectory of the steering gear cable, the centerlines of the pulley grooves of all pulleys are in the same plane, and parallel to the working surface of the test platform, the steel cables are constrained by the pulley grooves, and the cables are arranged along the test track. It is connected with the electro-hydraulic servo actuator, and the other end of the steel cable hangs a counterweight, and the electro-hydraulic servo actuator is controlled by the control loading system.

Description

An aircraft steering gear cable fatigue life test device and test method

technical field

The application relates to aircraft design test technology, in particular to an aircraft steering gear cable fatigue life test device.

Background technique

The steel cable of the aircraft steering gear is broken due to fatigue. Now it is necessary to find out the life of the steel cable and compare it with the improvement plan, and provide data support for the improvement plan based on the test data. In the steering gear cable life test carried out this time, the test cable needs to bear a load of 80Kg. During the steering gear cable life test, the number of motion cycles in which the wires break in the steering gear generally reaches tens of thousands or even hundreds of thousands of times. The cable needs to simulate the state on the machine to reciprocate within a fixed stroke, the number of tests is large, the motion simulation stroke is more accurate, and the cable life test must be completed on time. The original method of manpower and motor drive cannot meet the test requirements and test quality. Therefore, a cable test life device that meets the load-bearing and displacement requirements and has a short test period is designed.

Contents of the invention

The purpose of this application is to provide a fatigue life test device for steel cables of aircraft steering gear that meets the requirements of bearing capacity and displacement and has a short test period. The device for the life test of the aircraft steering gear cable needs to achieve the following functions: improve the driving mode to meet the load-bearing requirements, realize the precise control of the displacement, integrate the original cable structure and the improved cable structure, and ensure the safety of the test and so on can meet the test requirements.

A device for fatigue life test of aircraft steering gear cables, characterized in that the test device contains an electro-hydraulic servo actuator, a test platform, a pulley, a steel cable and a counterweight, the test platform is supported on a support, and the test platform The working surface of the test platform is vertical to the ground. There are multiple sets of pulleys on the working surface of the test platform. Each set of pulleys includes two diverting pulleys and multiple track pulleys. Each set of pulleys forms a test track, and the diverting pulleys are located at both ends of the test track. , the track pulley simulates the restraint trajectory of the steel cables of the aircraft steering gear. The centerlines of the pulley grooves of all the pulleys are in the same plane and parallel to the working surface of the test platform. The steel cables are constrained by the pulley grooves, and the steel cables are arranged along the test track One end of the steel cable is connected with the electro-hydraulic servo actuator, and the other end of the steel cable is hung with a counterweight, and the electro-hydraulic servo actuator is controlled by the control loading system.

A kind of aircraft steering gear cable fatigue life test method, it is characterized in that comprising following content, 1) use above-mentioned aircraft steering gear cable fatigue life testing device; 2) reflect different aircraft steering gear steel cables with the test track of different pulley blocks Structural design; 3) Use a coherent steel cable to constrain the cables designed for multiple aircraft steering gear cables on different pulley blocks for counterweight loading; 4) Control the loading system to control the electro-hydraulic servo actuator repeatedly Telescopic, simulated aircraft steering gear manipulation frequency fatigue life test.

The beneficial effects of the application are as follows: 1) The electro-hydraulic servo coordinated loading system and the displacement sensor are used for real-time coordinated closed-loop control of the displacement in the cable test, and the loading accuracy is high. The test method satisfies the displacement and load-bearing requirements of the test, which is simple, reliable and safe, and the test scheme is relatively novel. 2) The test bench adopts four sets of multi-arc layouts, and the track pulleys with different wrap angles and different diameters are tested at the same time. At the same time, each set of pulleys corresponds to a section of test steel cable, which is convenient for the record of fatigue times in life tests and the number of broken wires and broken strands. The replacement of the cable greatly improves the test efficiency and reduces the loss of test equipment.

The present application will be further described in detail below in conjunction with the accompanying drawings of the embodiments.

Description of drawings

Figure 1 is a schematic diagram of the structure of the aircraft steering gear cable fatigue life test device.

Figure 2 is a block diagram of the control principle of the aircraft steering gear cable fatigue life test device.

Description of numbers in the figure: 1 bracket, 2 electro-hydraulic servo actuator, 3 steering pulley, 4 track pulley, 5 steel cable, 6 test platform, 7 counterweight, 8 workbench.

Detailed ways

Referring to the accompanying drawings, the aircraft steering gear cable fatigue life test device of the present application contains an electro-hydraulic servo actuator 2, a test platform 6, four block pulleys, a steel cable 5 and a counterweight 7, and the test platform 6 and electric The hydraulic servo actuators 2 are respectively supported on the brackets. The test platform 6 is a steel platform, and the working surface on one side is perpendicular to the ground. There are four sets of pulleys on the working surface of the test platform, and each set of pulleys contains two The steering pulley 3 and two track pulleys 4, each set of pulleys form a test track, the steering pulley 3 is located at both ends of the test track, the track pulley 4 simulates the constraint track of the steel cable of the aircraft steering gear, and the centerlines of the pulley grooves of all pulleys are at the same plane, and parallel to the working surface of the test platform 6, the steel cable 6 is constrained by the pulley groove, the steel cable 6 is composed of multi-section test steel cables, the steel cables 6 are arranged continuously along four test tracks, and the steel cables 6 One end is connected to the electro-hydraulic servo actuator 2, and the other end of the steel cable 6 hangs a counterweight 7, which simulates the operating tension of the steel cable of the aircraft steering gear, and a liftable workbench 8 is provided under the counterweight 7. For changing and adjusting counterweights.

When using the above-mentioned aircraft steering gear cable fatigue life test device for testing; the test tracks of different pulley blocks can be used to reflect different aircraft steering gear cable structure design states; Coherent steel cables are constrained to carry out counterweight loading on different pulley blocks; the electro-hydraulic servo actuator is controlled by the control loading system to repeatedly expand and contract, simulating the fatigue life test of the frequency of aircraft steering gear manipulation.

The electro-hydraulic servo actuator 2 is controlled by the control loading system. During implementation, the control loading system is shown in Figure 2, including displacement sensors, coordinated loading systems, control computers, hydraulic pump stations and hydraulic sub-stations. The displacement sensor is arranged on the electro-hydraulic servo actuator to measure the telescopic stroke of the electro-hydraulic servo actuator and feed it back to the hydraulic loading system. The hydraulic pump station provides the electro-hydraulic servo actuator 2 through the hydraulic sub-station. Hydraulic power source.

During specific implementation, four groups of different test trajectories can represent the design states of four different aircraft steering gear cables. It can simulate the wrapping angle of the improvement scheme of the steel cable of the aircraft steering gear, use the same pulley diameter as the original machine and the improvement scheme, simulate the state of the original machine and the state of the improvement scheme, and at the same time change the cable path through the steering pulley to avoid the test bench being too large .

Claims (4)

1. a kind of aircraft steering wheel cable fatigue life test device, it is characterized in that, this test device contains electro-hydraulic servo actuator, test platform, pulley, steel cable and counterweight, and described test platform is supported on the support, The working surface of the test platform is vertical to the ground. There are multiple sets of pulleys on the working surface of the test platform. Each set of pulleys includes two diverting pulleys and multiple track pulleys. Each set of pulleys forms a test track. At both ends, the track pulley simulates the restraint trajectory of the steel cable of the aircraft steering gear. The centerlines of the pulley grooves of all the pulleys are on the same plane and parallel to the working surface of the test platform. Track layout, one end of the steel cable is connected with the electro-hydraulic servo actuator, and the other end of the cable is suspended with a counterweight, and the electro-hydraulic servo actuator is controlled by the control loading system. 2. The aircraft steering gear cable fatigue life test device according to claim 1, wherein a displacement sensor is arranged on the electro-hydraulic servo actuator. 3. aircraft steering wheel cable fatigue life test device as claimed in claim 1, is characterized in that, the below of counterweight is provided with the workbench that can lift, is used for changing counterweight. 4. an aircraft steering gear cable fatigue life test method is characterized in that comprising the following content, 1) using the aircraft steering gear cable fatigue life testing device as claimed in claim 1 or 2 or 3; 2) using different block pulleys The test trajectory reflects different aircraft rudder cable structure designs; 3) the steel cables designed for multiple aircraft rudder cable structures are constrained by a coherent cable to carry out counterweight loading on different pulley blocks; 4) by The control loading system controls the repeated expansion and contraction of the electro-hydraulic servo actuator, and simulates the fatigue life test of the operating frequency of the aircraft steering gear.

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