CN201788127U - Large-torque actuator loading test bench - Google Patents
Large-torque actuator loading test bench Download PDFInfo
- Publication number
- CN201788127U CN201788127U CN2010202643440U CN201020264344U CN201788127U CN 201788127 U CN201788127 U CN 201788127U CN 2010202643440 U CN2010202643440 U CN 2010202643440U CN 201020264344 U CN201020264344 U CN 201020264344U CN 201788127 U CN201788127 U CN 201788127U
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- torque sensor
- oscillating cylinder
- servo
- valve
- hydraulic pump
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Abstract
A large-torque actuator loading test bench comprises a piece (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). The piece (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 large-torque actuator loading test bench overcomes the shortcomings of complicated structure and incapability of simulating the actual work conditions of products on an aircraft for testing wing flaps of an existing device for testing wing flaps, can simulate the actual work conditions of products on an aircraft for testing wing flaps, and is simple in structure and high in testing precision.
Description
Technical field
The utility model relates to a kind of large-torque actuator loading testboard, and 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 purpose of this utility model 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 purpose of this utility model reaches by following measure: large-torque actuator loading testboard, 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.
The utility model large-torque actuator loading testboard 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 utility model.
Fig. 2 is a structural representation of the present utility model.
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 utility model in detail below in conjunction with accompanying drawing, but they do not constitute to qualification of the present utility model, only do for example.Simultaneously by illustrating that advantage of the present utility model will become clear more and understanding easily.
Consult accompanying drawing as can be known: the utility model large-torque actuator loading testboard, 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.
The utility model large-torque actuator loading testboard principle of work 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 |
|---|---|---|---|
| CN2010202643440U CN201788127U (en) | 2010-07-20 | 2010-07-20 | Large-torque actuator loading test bench |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202643440U CN201788127U (en) | 2010-07-20 | 2010-07-20 | Large-torque actuator loading test bench |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201788127U true CN201788127U (en) | 2011-04-06 |
Family
ID=43820086
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010202643440U Expired - Lifetime CN201788127U (en) | 2010-07-20 | 2010-07-20 | Large-torque actuator loading test bench |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201788127U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101886994A (en) * | 2010-07-20 | 2010-11-17 | 武汉航达航空科技发展有限公司 | Large-torque actuator loading testboard |
-
2010
- 2010-07-20 CN CN2010202643440U patent/CN201788127U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101886994A (en) * | 2010-07-20 | 2010-11-17 | 武汉航达航空科技发展有限公司 | Large-torque actuator loading testboard |
| CN101886994B (en) * | 2010-07-20 | 2011-11-16 | 武汉航达航空科技发展有限公司 | Large-torque actuator loading testboard |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20110406 Effective date of abandoning: 20111116 |