CN101886994A - Large-torque actuator loading testboard - Google Patents
Large-torque actuator loading testboard Download PDFInfo
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- CN101886994A CN101886994A CN 201010231542 CN201010231542A CN101886994A CN 101886994 A CN101886994 A CN 101886994A CN 201010231542 CN201010231542 CN 201010231542 CN 201010231542 A CN201010231542 A CN 201010231542A CN 101886994 A CN101886994 A CN 101886994A
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- torque sensor
- oscillating cylinder
- servo
- valve
- hydraulic pump
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Abstract
The invention relates to a large-torque actuator loading testboard comprising a part (3) to be tested, a servo motor (1), an input torque sensor (2), an output torque sensor (4), an oscillating cylinder (5), a servo valve (7) and a hydraulic pump (8), wherein the part (3) to be tested is positioned between the input torque sensor (2) and the output torque sensor (4); the servo motor (1) is connected with the input torque sensor (2); the output torque sensor (4) is connected with the oscillating cylinder (5); the servo valve (7) is positioned between the oscillating cylinder (5) and the hydraulic pump (8); one end of the servo valve (7) is connected with the oscillating cylinder (5), and the other end of the servo valve (7) is connected with the hydraulic pump (8). The invention overcomes the defects that the traditional device for testing wing flaps has a complex structure and can not test a plan by simulating the actual working conditions of a product on the plane, can test the plane by simulating the actual working conditions of the product on the plane and has simple structure and high test accuracy.
Description
Technical field
The present invention relates to a kind of large-torque actuator loading testboard, it is a kind of testing apparatus that is used for the performance test of wing flap actuator.
Background technology
The maneuverability of aircraft depends on the motion of wing flap actuator to a great extent, is provided with wing flap on the back edge of wing, and wing flap raises by push rod, idle pulley and crank and hydraulic actuation connector in a conventional way and reduces.
The existing apparatus structure complexity that is used to test wing flap can not be tested it by analog equipment actual condition aboard.Therefore study a kind of can its large-torque actuator loading testboard of testing being had great importance analog equipment actual condition aboard.
Summary of the invention
The objective of the invention is to overcome the weak point of existing test board, and a kind of large-torque actuator loading testboard that is used for the performance test of wing flap actuator is provided.
The objective of the invention is to reach: large-torque actuator loading testboard by following measure, it comprises by test specimen, it is characterized in that it also comprises servomotor, the input torque sensor, the output torque sensor, oscillating cylinder, servo-valve, hydraulic pump, described by test specimen between input torque sensor and output torque sensor, servomotor is connected with the input torque sensor, the output torque sensor is connected with oscillating cylinder, servo-valve is between oscillating cylinder and hydraulic pump, and the fluid of hydraulic pump outlet enters the inlet of servo-valve, and two chambeies of the outlet of servo-valve and oscillating cylinder are connected.
In technique scheme, described oscillating cylinder is the rack-and-pinion hydraulic cylinder.
In technique scheme, it also comprises computer measurement and control system, and described computer measurement and control system is respectively with servomotor, input torque sensor, be connected by test specimen, output torque sensor, servo-valve, hydraulic pump.
In technique scheme, between described oscillating cylinder and computer measurement and control system, scrambler is arranged.
Large-torque actuator loading testboard of the present invention can be to being added torsion load by the output shaft of test specimen, torque range is 0～15000Nm (is 2.5 rev/mins at rotating speed), the direction-agile of torque (promptly can both provide 0～15000Nm torsion load with counter clockwise direction clockwise), and in scope, can regulate easily; In 300～15000Nm scope, the torque departure be displayed value ± 1.5%; Loading control can controlling torque the ascending velocity of load, promptly the ascending velocity of load can be set among 100～1500Nm/sec more arbitrarily; The angular displacement of UUT (by test specimen) output shaft can accurately be measured.
Large-torque actuator loading testboard provides a servomotor, this motor with connected by the input shaft of test specimen, in order to drive by test specimen, the rated speed of motor is 600 rev/mins, motor speed is scalable in 0～600 rev/min of scope, and speed control error is ± 1%; Motor can provide the 60Nm torque in 0～600 rev/min the range of speeds; The sense of rotation of motor is variable, and promptly in clockwise and counter clockwise direction, motor has the identical performance that drags.
Description of drawings
Fig. 1 is a structural representation block scheme of the present invention.
Fig. 2 is a structural representation of the present invention.
1. servomotors among the figure, 2. input torque sensor, 3. by test specimen, 4. output torque sensor, 5. oscillating cylinder, 6. computer measurement and control system, 7. servo-valve, 8. hydraulic pump, 9. scrambler.
Embodiment
Describe performance of the present invention in detail below in conjunction with accompanying drawing, but they do not constitute limitation of the invention, only do for example.Simultaneously by illustrating that advantage of the present invention will become clear more and understanding easily.
Consult accompanying drawing as can be known: large-torque actuator loading testboard of the present invention, it comprises by test specimen 3, it also comprises servomotor 1, input torque sensor 2, output torque sensor 4, oscillating cylinder 5, servo-valve 7, hydraulic pump 8, described by test specimen 3 between input torque sensor 2 and output torque sensor 4, servomotor 1 is connected with input torque sensor 2, output torque sensor 4 is connected with oscillating cylinder 5, servo-valve 7 is between oscillating cylinder 5 and hydraulic pump 8, and the fluid of hydraulic pump 8 outlets enters the inlet of servo-valve 7, and two chambeies of the outlet of servo-valve 7 and oscillating cylinder 5 are connected.
Described oscillating cylinder 5 is the rack-and-pinion hydraulic cylinder.
It also comprises computer measurement and control system 6, and described computer measurement and control system is respectively with servomotor 1, input torque sensor 2, be connected by test specimen 3, output torque sensor 4, servo-valve 7, hydraulic pump 8.
Between described oscillating cylinder 5 and computer measurement and control system 6, scrambler 9 is arranged.
Large-torque actuator loading testboard principle of work of the present invention is as follows:
In order to reach by test specimen (the wing flap actuator of Airbus 320, be contained in 1,2,3,4 erect-positions of every side wing respectively) rotating speed of input section and the requirement of moment of torsion, drag being provided by a test specimen input section employing servomotor, can control motor speed by frequency converter, input torque sensor measurement moment of torsion.
In general hydraulic torque servo-drive system, the general hydraulic electric motor that adopts loads, but its shortcoming is in commutation the dead band to be arranged, and has influenced control accuracy, so native system adopts bidentate wheel tooth bar hydraulic cylinder as moment of torsion topworks, can effectively reduce the dead band.Its principle of work is that the rack drives gear is passed through in the to-and-fro movement of hydraulic cylinder, changes into forward and reverse swing rotation of gear shaft, simultaneously the thrust of linear actuator is changed into the output torque of gear shaft.
Adopt servo-valve as control element, by regulating the input current of servo-valve, can regulating spool aperture size, and then the pressure reduction at control bidentate wheel tooth bar hydraulic cylinder two ends, reach the purpose of control oscillating cylinder output torque.Carry out closed-loop control by output terminal being turned round the signal of refusing sensor and the input current of servo-valve, can realize accurately loading.The control of loading speed also can realize by the input current that circuit is controlled servo-valve.
The control of test board is based on the Automatic Control of Labiew (existing software), can show and control input and output moment size, the loading speed of output loading moment can be set, can show the rotational angle of product, can the acquisition system data and curve plotting on request.System can also be provided with the higher limit of input and output moment, and the higher limit of the rotational angle of product is protected product.
Claims (4)
1. large-torque actuator loading testboard, it comprises by test specimen (3), it is characterized in that it also comprises servomotor (1), input torque sensor (2), output torque sensor (4), oscillating cylinder (5), servo-valve (7), hydraulic pump (8), describedly be positioned between input torque sensor (2) and the output torque sensor (4) by test specimen (3), servomotor (1) is connected with input torque sensor (2), output torque sensor (4) is connected with the output shaft of oscillating cylinder (5), servo-valve (7) is positioned between oscillating cylinder (5) and the hydraulic pump (8), and the fluid of hydraulic pump (8) outlet enters the inlet of servo-valve (7), and two chambeies of the outlet of servo-valve (7) and oscillating cylinder (5) are connected.
2. large-torque actuator loading testboard according to claim 1 is characterized in that described oscillating cylinder (5) is the rack-and-pinion hydraulic cylinder.
3. large-torque actuator loading testboard according to claim 1 and 2, it is characterized in that it also comprises computer measurement and control system (6), described computer measurement and control system is respectively with servomotor (1), input torque sensor (2), be connected by test specimen (3), output torque sensor (4), servo-valve (7), hydraulic pump (8).
4. large-torque actuator loading testboard according to claim 3 is characterized in that between described oscillating cylinder (5) and computer measurement and control system (6) scrambler (9) being arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102315421A CN101886994B (en) | 2010-07-20 | 2010-07-20 | Large-torque actuator loading testboard |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102315421A CN101886994B (en) | 2010-07-20 | 2010-07-20 | Large-torque actuator loading testboard |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101886994A true CN101886994A (en) | 2010-11-17 |
| CN101886994B CN101886994B (en) | 2011-11-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010102315421A Expired - Fee Related CN101886994B (en) | 2010-07-20 | 2010-07-20 | Large-torque actuator loading testboard |
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| CN (1) | CN101886994B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288481A (en) * | 2011-07-08 | 2011-12-21 | 中国飞机强度研究所 | Vacuumizing loading equipment and test method thereof |
| CN103969106A (en) * | 2014-04-15 | 2014-08-06 | 上海理工大学 | Pulling-twisting combined fatigue test table |
| CN104483115A (en) * | 2014-12-03 | 2015-04-01 | 宝鸡石油机械有限责任公司 | Multipurpose torque loading operation test method and device |
| CN104976981A (en) * | 2014-04-10 | 2015-10-14 | 哈尔滨飞机工业集团有限责任公司 | Flap position indicator verification system |
| CN105891028A (en) * | 2016-06-01 | 2016-08-24 | 上海电缆研究所 | Metal wire vibration fatigue testing machine and metal wire vibration fatigue testing method |
| CN106428627A (en) * | 2016-10-26 | 2017-02-22 | 广州飞机维修工程有限公司 | Airplane front aileron actuator testing platform of airliner |
| CN109515740A (en) * | 2018-11-05 | 2019-03-26 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft flap system torsional moment measurement method |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU182921U1 (en) * | 2017-12-06 | 2018-09-05 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Loading device for bench testing of the steering surface |
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| US4046001A (en) * | 1974-07-02 | 1977-09-06 | Lion Fat & Oil Co. Limited | Apparatus for measuring restoring force necessary for raising folded portions of hard paper boxes |
| CN2663973Y (en) * | 2003-10-23 | 2004-12-15 | 同济大学 | Long stroke multi-direction loading synchronous following equipment for test machine |
| CN101290269A (en) * | 2008-05-30 | 2008-10-22 | 杭州邦威机电控制工程有限公司 | Initiative and follow-up loading structure experiment system |
| CN101561459A (en) * | 2009-06-04 | 2009-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Damage-tolerance testing method for lower wall panel of airplane outboard wing |
| CN201476969U (en) * | 2009-07-06 | 2010-05-19 | 青岛四方车辆研究所有限公司 | Bogie fatigue testing stand |
| CN201788127U (en) * | 2010-07-20 | 2011-04-06 | 武汉航达航空科技发展有限公司 | Large-torque actuator loading test bench |
-
2010
- 2010-07-20 CN CN2010102315421A patent/CN101886994B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4046001A (en) * | 1974-07-02 | 1977-09-06 | Lion Fat & Oil Co. Limited | Apparatus for measuring restoring force necessary for raising folded portions of hard paper boxes |
| CN2663973Y (en) * | 2003-10-23 | 2004-12-15 | 同济大学 | Long stroke multi-direction loading synchronous following equipment for test machine |
| CN101290269A (en) * | 2008-05-30 | 2008-10-22 | 杭州邦威机电控制工程有限公司 | Initiative and follow-up loading structure experiment system |
| CN101561459A (en) * | 2009-06-04 | 2009-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Damage-tolerance testing method for lower wall panel of airplane outboard wing |
| CN201476969U (en) * | 2009-07-06 | 2010-05-19 | 青岛四方车辆研究所有限公司 | Bogie fatigue testing stand |
| CN201788127U (en) * | 2010-07-20 | 2011-04-06 | 武汉航达航空科技发展有限公司 | Large-torque actuator loading test bench |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288481A (en) * | 2011-07-08 | 2011-12-21 | 中国飞机强度研究所 | Vacuumizing loading equipment and test method thereof |
| CN102288481B (en) * | 2011-07-08 | 2014-03-19 | 中国飞机强度研究所 | Vacuumizing loading equipment and test method thereof |
| CN104976981A (en) * | 2014-04-10 | 2015-10-14 | 哈尔滨飞机工业集团有限责任公司 | Flap position indicator verification system |
| CN103969106A (en) * | 2014-04-15 | 2014-08-06 | 上海理工大学 | Pulling-twisting combined fatigue test table |
| CN103969106B (en) * | 2014-04-15 | 2016-03-02 | 上海理工大学 | Tension-torsion composite fatigue testing table |
| CN104483115A (en) * | 2014-12-03 | 2015-04-01 | 宝鸡石油机械有限责任公司 | Multipurpose torque loading operation test method and device |
| CN105891028A (en) * | 2016-06-01 | 2016-08-24 | 上海电缆研究所 | Metal wire vibration fatigue testing machine and metal wire vibration fatigue testing method |
| CN105891028B (en) * | 2016-06-01 | 2018-09-25 | 上海电缆研究所有限公司 | Metal wire rod vibration fatigue machine and metal wire rod vibration fatigue test method |
| CN106428627A (en) * | 2016-10-26 | 2017-02-22 | 广州飞机维修工程有限公司 | Airplane front aileron actuator testing platform of airliner |
| CN106428627B (en) * | 2016-10-26 | 2023-02-28 | 广州飞机维修工程有限公司 | Testboard for front aileron actuator of civil aviation passenger plane |
| CN109515740A (en) * | 2018-11-05 | 2019-03-26 | 西安飞机工业（集团）有限责任公司 | A kind of aircraft flap system torsional moment measurement method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101886994B (en) | 2011-11-16 |
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