CN115791117A - Fatigue life testing device and method for airplane steering engine steel cable - Google Patents
Fatigue life testing device and method for airplane steering engine steel cable Download PDFInfo
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- CN115791117A CN115791117A CN202211421584.0A CN202211421584A CN115791117A CN 115791117 A CN115791117 A CN 115791117A CN 202211421584 A CN202211421584 A CN 202211421584A CN 115791117 A CN115791117 A CN 115791117A
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Abstract
The test device comprises an electro-hydraulic servo actuator, a test platform, pulleys, a steel cable and a balance weight, wherein the test platform is supported on a support, the working face of the test platform is perpendicular to the ground, a plurality of groups of pulleys are arranged on the working face of the test platform, each group of pulleys comprises two steering pulleys and a plurality of track pulleys, each group of pulleys forms a test track, the steering pulleys are located at two ends of the test track, the track pulleys simulate the constraint track of the airplane steering engine steel cable, the central lines of pulley grooves of all the pulleys are located on the same plane and are parallel to the working face of the test platform, the steel cable is constrained by the pulley grooves, the steel cable is arranged along the test track, one end of the steel cable is connected with the electro-hydraulic servo actuator, the balance weight is hung at the other end of the steel cable, and the electro-hydraulic servo actuator is controlled by a control loading system.
Description
Technical Field
The application relates to an airplane design test technology, in particular to a fatigue life test device for an airplane steering engine steel cable.
Background
The problem of wire breakage of the airplane steering engine steel cable due to fatigue needs to be found out at the end of the service life of the steel cable and compared with an improved scheme, and data support is provided for the improved scheme according to test data. The steering engine steel cable life test that develops this time, experimental steel cable need the force of 80Kg, and the motion cycle number that the broken silk appears in the steel cable generally reaches tens of thousands or even tens of thousands of times when carrying out steering engine steel cable life test, and simultaneously, the steel cable needs the analog machine on-state to carry out reciprocating motion in fixed stroke, and the number of times of testing is more, and motion simulation stroke is comparatively accurate, and need accomplish the steel cable life test on time. The original method of manpower and motor driving can not meet the test requirements and the test quality, so the steel cable test service life device which meets the requirements of bearing force and displacement and has short test period is designed.
Disclosure of Invention
The application aims to provide an aircraft steering engine steel cable fatigue life testing device which meets the requirements of bearing force and displacement and is short in test period. The device for testing the service life of the airplane steering engine steel cable needs to realize the following functions: the force-bearing requirement is realized by improving a driving mode, the accurate control of the displacement is realized, the original machine steel cable structure and the improved steel cable structure are integrated together, and the test requirements on the aspects of test safety and the like are met.
The utility model provides an aircraft steering wheel cable wire fatigue life test device, its characterized in that, this test device contains electro-hydraulic servo actuator, test platform, pulley, cable wire and counter weight, test platform support on the support, test platform's working face is perpendicular and ground, is equipped with the multiunit pulley on test platform's working face, every group pulley contains two diverting pulleys and a plurality of orbit pulley, every group pulley forms a experimental orbit, the diverting pulley is located the both ends of experimental orbit, the orbit pulley simulates the restraint orbit of aircraft steering wheel cable wire, the pulley groove central line of all pulleys is in the coplanar, and is parallel with test platform's working face, the cable wire receive the restraint of pulley groove, the cable wire is arranged along experimental orbit, the one end and the electro-hydraulic servo actuator of cable wire are connected, the cable wire other end hangs the counter weight, electro-hydraulic servo actuator control loading system's control.
A fatigue life test method for an airplane steering engine steel cable is characterized by comprising the following steps of 1) using the fatigue life test device for the airplane steering engine steel cable; 2) Reflecting different airplane steering engine steel cable structure designs by using test tracks of different pulley blocks; 3) Constraining a plurality of steel cables designed by the airplane steering engine steel cable structure on different pulley blocks by using a coherent steel cable to carry out counterweight loading; 4) The electro-hydraulic servo actuator is controlled by the control loading system to stretch repeatedly, and fatigue life tests of the airplane steering engine control frequency are simulated.
The beneficial effect of this application lies in: 1) The electro-hydraulic servo coordination loading system and the displacement sensor are adopted to carry out real-time coordination closed-loop control on the displacement in the steel cable test, the loading precision is high, the electro-hydraulic servo actuator is used for driving, the tension requirement of the counter weight simulator is utilized, the test method meets the displacement and force bearing requirements in the test, and the test method is simple, reliable and safe and is novel in test scheme. 2) The test bench adopts four groups of multi-arc-section layout modes, pulleys with different wrap angles and different diameter tracks are tested simultaneously, and each group of pulleys corresponds to one section of test steel cable, so that the service life test fatigue times are conveniently recorded, and the wire and strand broken steel cables are conveniently replaced, the test efficiency is greatly improved, and the loss of test equipment is reduced.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a structural schematic diagram of a fatigue life testing device for a steel cable of an aircraft steering engine.
FIG. 2 is a control schematic block diagram of a fatigue life testing device for an aircraft steering engine steel cable.
The numbering in the figures illustrates: the device comprises a support 1, an electro-hydraulic servo actuator 2, a steering pulley 3, a track pulley 4, a steel cable 5, a test platform 6, a counterweight 7 and a workbench 8.
Detailed Description
Referring to the attached drawings, the fatigue life testing device for the airplane steering engine steel cable comprises an electro-hydraulic servo actuator 2, a testing platform 6, four pulley blocks, a steel cable 5 and a counterweight 7, wherein the testing platform 6 and the electro-hydraulic servo actuator 2 are respectively supported on a support, the testing platform 6 is a steel platform, a working surface on one side of the testing platform is perpendicular to the ground, four groups of pulleys are arranged on the working surface of the testing platform, each group of pulleys comprises two steering pulleys 3 and two track pulleys 4, each group of pulleys forms a testing track, the steering pulleys 3 are positioned at two ends of the testing track, the track pulleys 4 simulate the constraint track of the airplane steering engine steel cable, the central lines of pulley grooves of all the pulleys are positioned on the same plane and are parallel to the working surface of the testing platform 6, the steel cable 6 is constrained by pulley grooves, the steel cable 6 is composed of a plurality of sections of testing steel cables, the steel cable 6 is continuously arranged along the four testing tracks, one end of the steel cable 6 is connected with the electro-hydraulic servo actuator 2, the other end of the steel cable 6 is suspended with the counterweight 7, the counterweight 7 simulates the operation tension born by the aircraft steering engine, and a working platform 8 capable of being lifted and arranged below the counterweight 7 and used for replacing and adjusting the counterweight.
When the fatigue life testing device for the airplane steering engine steel cable is used for testing; different airplane steering engine steel cable structure design states can be reflected by the test tracks of different pulley blocks; constraining a plurality of steel cables designed by the airplane steering engine steel cable structure on different pulley blocks by using a coherent steel cable to carry out counterweight loading; the electro-hydraulic servo actuator is controlled by the control loading system to stretch repeatedly, and fatigue life tests of the airplane steering engine control frequency are simulated.
The electro-hydraulic servo actuator 2 is controlled by a control loading system, and in implementation, the control loading system comprises a displacement sensor, a coordination loading system, a control computer, a hydraulic pump station and a hydraulic substation as shown in fig. 2. The displacement sensor is arranged on the electro-hydraulic servo actuator and used for measuring the telescopic stroke of the electro-hydraulic servo actuator and feeding back the telescopic stroke to the hydraulic loading system, and the hydraulic pump station provides a hydraulic power source for the electro-hydraulic servo actuator 2 through the hydraulic substation.
In specific implementation, four different test tracks can represent the design states of four different airplane steering engine steel cables. The wrap angle of the improved scheme of the airplane steering engine steel cable can be simulated, the diameter of the pulley which is the same as that of the original airplane and the improved scheme is used, the state of the original airplane and the state of the improved scheme are simulated, and meanwhile, the steel cable path is converted through the steering pulley, so that the overlarge test stand is avoided.
Claims (4)
1. The utility model provides an aircraft steering wheel cable wire fatigue life test device, its characterized in that, this test device contains electro-hydraulic servo actuator, test platform, pulley, cable wire and counter weight, test platform support on the support, test platform's working face is perpendicular and ground, is equipped with the multiunit pulley on test platform's working face, every group pulley contains two diverting pulleys and a plurality of orbit pulley, every group pulley forms a experimental orbit, the diverting pulley is located the both ends of experimental orbit, the orbit pulley simulates the restraint orbit of aircraft steering wheel cable wire, the pulley groove central line of all pulleys is in the coplanar, and is parallel with test platform's working face, the cable wire receive the restraint of pulley groove, the cable wire is arranged along experimental orbit, the one end and the electro-hydraulic servo actuator of cable wire are connected, the cable wire other end hangs the counter weight, electro-hydraulic servo actuator control loading system's control.
2. The fatigue life testing device for the airplane steering engine steel cable according to claim 1, wherein a displacement sensor is arranged on the electro-hydraulic servo actuator.
3. The fatigue life test device for the steel cable of the aircraft steering engine according to claim 1, wherein a liftable workbench is arranged below the counterweight and used for replacing the counterweight.
4. An aircraft steering engine steel cable fatigue life test method is characterized by comprising the following steps of 1) using the aircraft steering engine steel cable fatigue life test device according to claim 1, 2 or 3; 2) Reflecting different airplane steering engine steel cable structure designs by using test tracks of different pulley blocks; 3) Constraining a plurality of steel cables designed by the airplane steering engine steel cable structure on different pulley blocks by using a coherent steel cable to carry out counterweight loading; 4) The electro-hydraulic servo actuator is controlled by the control loading system to stretch repeatedly, and fatigue life tests of the airplane steering engine control frequency are simulated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211421584.0A CN115791117A (en) | 2022-11-14 | 2022-11-14 | Fatigue life testing device and method for airplane steering engine steel cable |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211421584.0A CN115791117A (en) | 2022-11-14 | 2022-11-14 | Fatigue life testing device and method for airplane steering engine steel cable |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115791117A true CN115791117A (en) | 2023-03-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211421584.0A Pending CN115791117A (en) | 2022-11-14 | 2022-11-14 | Fatigue life testing device and method for airplane steering engine steel cable |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115791117A (en) |
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2022
- 2022-11-14 CN CN202211421584.0A patent/CN115791117A/en active Pending
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