CN104155087A - Fixed-wing aircraft rudder fatigue test system - Google Patents
Fixed-wing aircraft rudder fatigue test system Download PDFInfo
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- CN104155087A CN104155087A CN201410213270.0A CN201410213270A CN104155087A CN 104155087 A CN104155087 A CN 104155087A CN 201410213270 A CN201410213270 A CN 201410213270A CN 104155087 A CN104155087 A CN 104155087A
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- fixed wing
- yaw rudder
- wing machine
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- machine yaw
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Abstract
Disclosed is a fixed-wing aircraft rudder fatigue test system, which consists of a test bench, a hydraulic station, a rotary direct drive valve, an actuator tester, a digital storage oscilloscope, a pipe adapter, upper and lower connecting clamps, a load cell and a fixed-wing aircraft rudder; and the upper connecting clamp is installed directly on the test bench, the lower connecting clamp is connected to the test bench through the load cell, the fixed-wing aircraft rudder is installed between the upper and lower connecting clamps, the hydraulic station is connected to the rotary direct drive valve through an oil pipe, the rotary direct drive valve is then connected to the fixed-wing aircraft rudder, the actuator tester is connected to the rotary direct drive valve and the load cell through a circuit, and the digital storage oscilloscope is connected to the actuator tester to display relevant information on the fixed-wing aircraft rudder. The test system can simulate the actual operating status and loading form of the fixed-wing aircraft, and the test results have significant engineering application values for fatigue life prediction of the fixed-wing aircraft rudder.
Description
Technical field
The present invention relates to a kind of fixed wing machine yaw rudder torture test test macro, belong to experimental test technical field.
Background technology
Fixed wing machine yaw rudder in the course of the work, is bearing size and the alternate load that direction constantly changes, and when design and application, must examine its fatigue lifetime.Fixed wing machine yaw rudder is worked under hydraulic-driven usually used as a key subsystem of fixed wing machine control system, not only bears the hydraulic pressure of self actuator, but also bears extraneous aerodynamic loading effect.Conventional fatigue tester only can be simulated external pneumatic load, and can not simulate the effect of actuator hydraulic pressure.At present, still lack effectively and the test macro of practical fixed wing machine yaw rudder torture test.For this reason, the present invention is integrated into fixed wing machine yaw rudder torture test test macro by test-bed, Hydraulic Station, the direct driver's valve of rotation, actuator exerciser, digital storage oscilloscope, pipeline X-over, jockey, force cell and fixed wing machine yaw rudder.This test macro can real simulation fixed wing machine yaw rudder actual working state and loading, experimental test result is determined the longevity for the fatigue of fixed wing machine yaw rudder and is had important engineering using value.
Summary of the invention
1, object: the object of the invention is to provide a kind of fixed wing machine yaw rudder torture test test macro, and it can simulate real work state and the load of fixed wing machine yaw rudder, has simple, practical, efficient feature, and system operation cost is also lower.
2, technical scheme: a kind of fixed wing machine yaw rudder of the present invention torture test test macro, is comprised of test-bed, Hydraulic Station, the direct driver's valve of rotation, actuator exerciser, digital storage oscilloscope, pipeline X-over, upper and lower jockey, force cell and fixed wing machine yaw rudder.Position annexation between them is as follows: upper jockey is arranged on test-bed, lower jockey is connected with test-bed by force cell, force cell feeds back to actuator exerciser by the force signal recording, fixed wing machine yaw rudder is arranged between upper and lower jockey, actuator exerciser is connected with the direct driver's valve of rotation the aperture of controlling this valve by circuit, rotate direct driver's valve and be connected with fixed wing machine yaw rudder with Hydraulic Station by oil pipe, digital storage oscilloscope is connected the relevant information that shows fixed wing machine yaw rudder with actuator exerciser simultaneously.Wherein, the order of connection of test-bed, fixed wing machine yaw rudder, force cell and upper and lower jockey is as follows:
Test-bed → upper jockey → fixed wing machine yaw rudder → lower jockey → force cell → test-bed
Described test-bed is a fixing rigid frame platform, is intersecting parallels framed structure, it have rigidity large, be out of shape feature little, good stability, to guarantee the stable support of fixed wing machine yaw rudder in torture test process.
Described Hydraulic Station is conventional Hydraulic Station, need there be oil transportation mouth and oil return opening, oil transportation mouth is used for to the direct driver's valve conveying liquid force feed of rotation, and oil return opening passes back into Hydraulic Station for hydraulic oil, and the oil pressure that Hydraulic Station can provide need be greater than the test oil pressure of fixed wing machine yaw rudder and can keep stable.
Described pipeline X-over is many steps axial workpiece, for the oil inlet and outlet of Hydraulic Station and the joint between oil pipe, in order to the oil inlet and outlet of connected pipes and Hydraulic Station.
The direct driver's valve of described rotation is the accessory being connected with fixed wing machine yaw rudder, and there is the aperture of Electric Machine Control valve its inside.Rotate direct driver's valve hydraulic oil is sent to fixed wing machine yaw rudder, driven plunger moves axially, wherein the motor of by-pass valve control aperture is driven by actuator exerciser, to change piston movement direction and speed, form closed-loop control, the piston in fixed wing machine yaw rudder can be maintained to equilibrium position effectively.
Described actuator exerciser, for driving the electronic installation of the direct driver's valve motor of rotation, to the motor output control signal of the direct driver's valve of rotation, and receives the piston position signal of fixed wing machine yaw rudder feedback and the amount of force signal of force cell feedback.
Described digital storage oscilloscope is conventional oscillograph, in order to observe control and the feedback signal of fixed wing machine yaw rudder.
Described fixed wing machine yaw rudder is a kind of hydraulic servo driving of two-chamber single-piston rod, it is comprised of earrings, piston rod, actuator cylindrical shell, gudgeon, collar, lining, Reaction bar, Kick bar and coupling bolt, and whole system is connected by coupling bolt and fixes.Under the control of actuator exerciser, Hydraulic Station provides different pressure flows to fixed wing machine yaw rudder piston end surface two ends, and piston rod is stretched out retraction, and the earrings that piston rod is connected by the jockey with fixing maintains balance.Wherein the working pressure of Hydraulic Station is 21MPa, and the maximum working load of piston rod is 43.2KN.
Described upper and lower jockey is the threaded connector with dead eye, and its two ends are connected with test-bed with fixed wing machine yaw rudder (earrings, Reaction bar, Kick bar) respectively, to provide support to fixed wing machine yaw rudder.
Described force cell is conventional composite sensor for measuring force, the load bearing in order to measure fixed wing machine yaw rudder, and the force signals recording is fed back to actuator exerciser, wherein the range of force cell is greater than the maximum load that fixed wing machine yaw rudder bears.
3, advantage and effect: the invention has the beneficial effects as follows and can to fixed wing machine yaw rudder, carry out torture test test separately, can be the design of fixed wing machine yaw rudder, exploitation and checking and provide effect technique support, in addition, the present invention has advantages of simply, practical, efficient, low cost, can effectively complete fixed wing machine yaw rudder torture test test.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the present invention is further described.
Fig. 1 test-bed schematic diagram
Fig. 2 is pipeline X-over schematic diagram.
Fig. 3 is upper jockey schematic diagram.
Fig. 4 is lower jockey schematic diagram.
Fig. 5 is fixed wing machine yaw rudder torture test test system structure figure.
In Fig. 5: 1. test-bed, 2. go up jockey, 3. fixed wing machine yaw rudder, the 4. direct driver's valve of rotation, 5. pipeline X-over, 6. Hydraulic Station, 7. digital storage oscilloscope, 8. actuator exerciser, 9. plays jockey, 10. force cell.
Embodiment
Below in conjunction with drawings and Examples, the present invention is further described.
Embodiment: the specific embodiment of the present invention is described in conjunction with Fig. 1 to Fig. 5.
In Fig. 5, a kind of fixed wing machine yaw rudder of the present invention torture test test macro, by test-bed 1, Hydraulic Station 6, actuator exerciser 8, digital storage oscilloscope 7, rotate direct driver's valve 4, pipeline X-over 5, upper jockey 2, lower jockey 9, force cell 10 and fixed wing machine yaw rudder 3 and form.Position annexation between them is as follows: upper jockey 2, lower jockey 9 is connected with test-bed 1 by force cell 10, fixed wing machine yaw rudder 3 two ends are arranged on, lower jockey 2, on 9, Hydraulic Station 6 is connected with the direct driver's valve 4 of rotation by oil pipe, rotating direct driver's valve 4 is connected with fixed wing machine yaw rudder 3 again, actuator exerciser 8 is connected with the direct driver's valve 4 of rotation by circuit, digital storage oscilloscope 7 is connected the relevant information that shows fixed wing machine yaw rudder 3 with actuator exerciser 8, force cell 10 is connected with actuator exerciser 8 by circuit and feeds back the forces associated signal that fixed wing machine yaw rudder 3 bears.The rigid body framework platform that test-bed 1 in this embodiment is autonomous Design, is intersecting parallels framed structure, and it can provide stable support for fixed wing machine yaw rudder 3 by be connected fixing with ground in testing fatigue process.
Hydraulic Station 6 is sent to the direct driver's valve 4 of rotation by the hydraulic oil of set pressure, rotates direct driver's valve 4 and hydraulic oil is sent to fixed wing machine yaw rudder 3 again, and driven plunger moves axially; And the ear ring bearing hole of fixed wing machine yaw rudder 3, Reaction rod bearing hole and Kick rod bearing hole are connected with upper and lower jockey 9,2 respectively to support for fixed wing machine yaw rudder 3 provides stable constraint, piston in fixed wing machine yaw rudder 3 can be maintained to equilibrium position effectively.Force cell 10 feeds back to actuator exerciser 8 by fixed wing machine yaw rudder 3 stressing conditions that record, actuator exerciser 8 rotates the direction of hydraulic oil and the aperture of valve in direct driver's valve 4 according to the feedback signal adjustment of force cell 10 again, form closed-loop control, make Hydraulic Station 6 impose on fixed wing machine yaw rudder 3 according to predetermined fatigue load spectrum.Because actuator exerciser 8 does not have display screen, therefore, it is connected with digital storage oscilloscope 7, to show stressing conditions and the corresponding piston displacement of fixed wing machine yaw rudder 3.1 passage that the force signal that actuator exerciser 8 is subject to the fixed wing machine yaw rudder 3 of force cell 10 feedbacks and valve break-make H channel signal offer digital storage oscilloscope 7, to show the stressing conditions of fixed wing machine yaw rudder 3 and aperture and the running of hydraulic power oil direction of rotating direct driver's valve 4, the demodulation of actuator exerciser 8 and Open-closed-loop H passage provide 2 passages of signal to digital storage oscilloscope 7, to show the piston displacement of fixed wing machine yaw rudder 3.Digital storage oscilloscope 7 can also calculate and show 1 passage peak-to-peak value and 2 passage peak-to-peak values, and the signal of yellow high frequency is 1 channel signal, and the signal of green low frequency is 2 channel signals.The electric wire one of being drawn by actuator exerciser 8 is divided into 3, one tunnels and connects fixed wing machine yaw rudder 3, one tunnels and connect force cell 10, one tunnels and connect and to rotate direct driver's valve 4.
Fixed wing machine yaw rudder 3 is hard-wired by ear ring bearing hole, Reaction rod bearing hole and Kick rod bearing hole, therefore need to design special jockey fixed wing machine yaw rudder 3 is connected with test-bed 1 (seeing Fig. 1), upper and lower jockey as shown in Figure 3, Figure 4.In addition, the female joint that the hydraulic pipeline joint of fixed wing machine yaw rudder 3 is M12 * 1, the threaded hole that Hydraulic Station 6 is M14 * 1.5 * 12, for this reason, has designed and has processed the adapter coupling 5 (as shown in Figure 2) between 1 pair of fluid pressure line and Hydraulic Station 6.
Like this, by this cover system designing, just can complete the torture test of fixed wing machine yaw rudder above tests.
Claims (1)
1. a fixed wing machine yaw rudder torture test test macro, is characterized in that: it is comprised of test-bed, Hydraulic Station, the direct driver's valve of rotation, actuator exerciser, digital storage oscilloscope, pipeline X-over, upper and lower jockey, force cell and fixed wing machine yaw rudder; Upper jockey is arranged on test-bed, lower jockey is connected with test-bed by force cell, force cell feeds back to actuator exerciser by the force signal recording, fixed wing machine yaw rudder is arranged between upper and lower jockey, actuator exerciser is connected with the direct driver's valve of rotation the aperture of controlling this valve by circuit, rotate direct driver's valve and be connected with fixed wing machine yaw rudder with Hydraulic Station by oil pipe, digital storage oscilloscope is connected the relevant information that shows fixed wing machine yaw rudder with actuator exerciser simultaneously; Wherein, the order of connection of test-bed, fixed wing machine yaw rudder, force cell and upper and lower jockey is as follows:
Test-bed → upper jockey → fixed wing machine yaw rudder → lower jockey → force cell → test-bed
Described test-bed is a fixing rigid frame platform, is intersecting parallels framed structure, it have rigidity large, be out of shape feature little, good stability, to guarantee the stable support of fixed wing machine yaw rudder in torture test process;
Described Hydraulic Station is conventional Hydraulic Station, need there be oil transportation mouth and oil return opening, oil transportation mouth is used for to the direct driver's valve conveying liquid force feed of rotation, and oil return opening passes back into Hydraulic Station for hydraulic oil, and the oil pressure that Hydraulic Station can provide need be greater than the test oil pressure of fixed wing machine yaw rudder and can keep stable;
Described pipeline X-over is many steps axial workpiece, for the oil inlet and outlet of Hydraulic Station and the joint between oil pipe, in order to the oil inlet and outlet of connected pipes and Hydraulic Station;
The direct driver's valve of described rotation is the accessory being connected with fixed wing machine yaw rudder, and there is the aperture of Electric Machine Control valve its inside; Rotate direct driver's valve hydraulic oil is sent to fixed wing machine yaw rudder, driven plunger moves axially, and wherein the motor of by-pass valve control aperture is driven by actuator exerciser, to change piston movement direction and speed, form closed-loop control, the piston in fixed wing machine yaw rudder is maintained to equilibrium position effectively;
Described actuator exerciser, for driving the electronic installation of the direct driver's valve motor of rotation, to the motor output control signal of the direct driver's valve of rotation, and receives the piston position signal of fixed wing machine yaw rudder feedback and the amount of force signal of force cell feedback;
Described digital storage oscilloscope is conventional oscillograph, in order to observe control and the feedback signal of fixed wing machine yaw rudder;
Described fixed wing machine yaw rudder is a kind of hydraulic servo driving of two-chamber single-piston rod, it is comprised of earrings, piston rod, actuator cylindrical shell, gudgeon, collar, lining, Reaction bar, Kick bar and coupling bolt, and whole system is connected by coupling bolt and fixes; Under the control of actuator exerciser, Hydraulic Station provides different pressure flows to fixed wing machine yaw rudder piston end surface two ends, and piston rod is stretched out retraction, and the earrings that piston rod is connected by the jockey with fixing maintains balance; Wherein the working pressure of Hydraulic Station is 21MPa, and the maximum working load of piston rod is 43.2KN;
Described upper and lower jockey is the threaded connector with dead eye, and its two ends are connected with test-bed with earrings, Reaction bar, the Kick bar of fixed wing machine yaw rudder respectively, to provide support to fixed wing machine yaw rudder;
Described force cell is composite sensor for measuring force, the load bearing in order to measure fixed wing machine yaw rudder, and the force signals recording is fed back to actuator exerciser, wherein the range of force cell is greater than the maximum load that fixed wing machine yaw rudder bears.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410213270.0A CN104155087A (en) | 2014-05-20 | 2014-05-20 | Fixed-wing aircraft rudder fatigue test system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410213270.0A CN104155087A (en) | 2014-05-20 | 2014-05-20 | Fixed-wing aircraft rudder fatigue test system |
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| CN104155087A true CN104155087A (en) | 2014-11-19 |
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| CN201410213270.0A Pending CN104155087A (en) | 2014-05-20 | 2014-05-20 | Fixed-wing aircraft rudder fatigue test system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105975704A (en) * | 2016-05-13 | 2016-09-28 | 中国航空工业集团公司西安飞机设计研究所 | Airplane suspension joint structure fatigue test design method |
| CN110789735A (en) * | 2019-12-05 | 2020-02-14 | 中国飞机强度研究所 | Force-controllable double-beam clamping device |
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| JP2009204519A (en) * | 2008-02-28 | 2009-09-10 | Mitsubishi Heavy Ind Ltd | Test load applying method and test load applying mechanism |
| CN103439096A (en) * | 2013-08-19 | 2013-12-11 | 北京航空航天大学 | Helicopter tail rotor booster fatigue test system |
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| US6446510B1 (en) * | 2000-07-24 | 2002-09-10 | Kulite Semiconductor Products, Inc. | Force transducer assembly |
| JP2009204519A (en) * | 2008-02-28 | 2009-09-10 | Mitsubishi Heavy Ind Ltd | Test load applying method and test load applying mechanism |
| CN103439096A (en) * | 2013-08-19 | 2013-12-11 | 北京航空航天大学 | Helicopter tail rotor booster fatigue test system |
| CN103439131A (en) * | 2013-08-19 | 2013-12-11 | 北京航空航天大学 | Fatigue testing system for large-tonnage helicopter tail rotor servo actuator |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105975704A (en) * | 2016-05-13 | 2016-09-28 | 中国航空工业集团公司西安飞机设计研究所 | Airplane suspension joint structure fatigue test design method |
| CN105975704B (en) * | 2016-05-13 | 2019-06-28 | 中国航空工业集团公司西安飞机设计研究所 | A kind of design method of aircraft suspension joint fatigue test of structure |
| CN110789735A (en) * | 2019-12-05 | 2020-02-14 | 中国飞机强度研究所 | Force-controllable double-beam clamping device |
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Application publication date: 20141119 |