CN202442867U - Test system of airplane rotary actuator - Google Patents

Test system of airplane rotary actuator Download PDF

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Publication number
CN202442867U
CN202442867U CN 201220026824 CN201220026824U CN202442867U CN 202442867 U CN202442867 U CN 202442867U CN 201220026824 CN201220026824 CN 201220026824 CN 201220026824 U CN201220026824 U CN 201220026824U CN 202442867 U CN202442867 U CN 202442867U
Authority
CN
China
Prior art keywords
rotary actuator
industrial computer
test
signal
control cabinet
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn - After Issue
Application number
CN 201220026824
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Chinese (zh)
Inventor
资雯
崔彦坤
方蕾
黄雄
刘明德
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Guangzhou Aircraft Maintenance Engineering Co Ltd
Original Assignee
Guangzhou Aircraft Maintenance Engineering Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Guangzhou Aircraft Maintenance Engineering Co Ltd filed Critical Guangzhou Aircraft Maintenance Engineering Co Ltd
Priority to CN 201220026824 priority Critical patent/CN202442867U/en
Application granted granted Critical
Publication of CN202442867U publication Critical patent/CN202442867U/en
Withdrawn - After Issue legal-status Critical Current
Anticipated expiration legal-status Critical

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Abstract

The utility model discloses a test system of an airplane rotary actuator. The test system comprises a test support, an industrial personal computer, a transmission shaft, an electric control cabinet, an angle sensor, a torque sensor, a pneumatic rotary loader and an adjusting device, wherein the rotary actuator is arranged on the test support, the transmission shaft is connected with an output shaft of the rotary actuator, the output shaft of the rotary actuator and the transmission shaft rotate synchronously, the angle sensor, the pneumatic rotary loader and the torque sensor are all arranged on the transmission shaft, the industrial personal computer is respectively connected with the electric control cabinet, the torque sensor, the angle sensor and the adjusting device, the adjusting device is connected with the pneumatic rotary loader, and the adjusting device can be used for adjusting load air pressure applied to the pneumatic rotary loader according to an instruction after receiving an instruction signal transmitted by the industrial personal computer, so that a torque load which is applied to the rotary actuator by the pneumatic rotary loader is adjusted. The test system disclosed by the utility model can be used for conveniently applying the load to the rotary actuator so as to realize the individual test of the rotary actuator.

Description

A kind of test macro of aircraft rotary actuator
Technical field
The utility model relates to the proving installation of aircraft drive disk assembly, more particularly, relates to a kind of test macro of aircraft rotary actuator.
Background technology
Aircraft rotary actuator (abbreviation rotary actuator) belongs to gearing in the aircraft pneumatic system, is used for the rotation transmission of the vitals such as elevating plane, yaw rudder, undercarriage of aircraft, and therefore the security to the aircraft rotary actuator has very high requirement.Yet; Domestic shortage is directed against the independent test of rotary actuator, but does whole performance test to rotary actuator together with its annex, is difficult to satisfy the technical requirement of test rotary actuator like this; Thereby be easy to occur some hidden failures, cause the reliability of its work to reduce.In addition, the existing method that rotary actuator is carried out load test is: utilize the mechanical means of cable wire suspension weight to carry out load.The method floor area of this load is big, and it is convenient inadequately to operate, and the loaded load limitation is big.
The utility model content
The purpose of the utility model is to provide a kind of test macro of aircraft rotary actuator, can realize rotary actuator is tested separately conveniently to the rotary actuator load.
The purpose of the utility model realizes through following technical scheme: a kind of test macro of aircraft rotary actuator; It comprises test bracket, industrial computer, transmission shaft, be used for to tested rotary actuator provide the different frequency testing power supply electrical control cabinet, be used to detect tested rotary actuator angle angular transducer, be used to detect tested rotary actuator moment of torsion and rotating speed torque sensor, be used for the regulating device that the pneumatic rotation loader of torque load directly is provided and is used to export and can regulate the loading air pressure of pneumatic rotation loader to rotary actuator; Rotary actuator is installed on the said test bracket; Said transmission shaft links to each other with the output shaft of rotary actuator; The output shaft and the transmission shaft of rotary actuator rotate synchronously; Said angular transducer, pneumatic rotation loader, torque sensor are installed on the transmission shaft; Said industrial computer links to each other with described electrical control cabinet, torque sensor, angular transducer and regulating device respectively; Be used to receive the signal that electrical control cabinet, torque sensor and angular transducer transmission come; And can send instruction with control electrical control cabinet and adjustment device work to electrical control cabinet and regulating device; Said regulating device links to each other with pneumatic rotation loader, and said regulating device can be regulated to load after receiving the next command signal of industrial computer transmission and loaded air pressure for said pneumatic rotation loader according to this instruction, acts on the torque load on the rotary actuator to regulate pneumatic rotation loader;
Said torque sensor feedback torque signal to industrial computer calculates and shows that the industrial computer output torque controls signal to regulating device, loads air pressure to pneumatic rotation loader by regulating device output; Said electrical control cabinet out-put supply to tested rotary actuator; Said angular transducer feedback angle signal to industrial computer shows; Said electrical control cabinet feedback voltage current signal to industrial computer calculates and shows, industrial computer output frequency control signal control electrical control cabinet exports tested rotary actuator to.
The said regulating device of the utility model comprises pressure regulator valve, ratio adjusting valve, the reversal valve that links to each other successively; The inlet of said pressure regulator valve links to each other with external air source; The control end of said ratio adjusting valve, the control end of reversal valve link to each other with the moment of torsion control signal output ends of industrial computer respectively, and the outlet of said reversal valve links to each other with the inlet of pneumatic rotation loader.
The said industrial computer of the utility model has the data collecting card that is used for acquired signal, said electrical control cabinet comprise the voltage signal that is used to feed back output voltage transmitter, be used to feed back the current transducer of the current signal of output; Said industrial computer is through the signal of data collecting card difference acquisition angles sensor, voltage transmitter, current transducer, torque sensor output.
Compared with prior art, the utility model technology has the following advantages:
(1) action of the industrial computer controllable testing of the utility model and demonstration test data result have realized the independent test to rotary actuator, to guarantee safety;
(2) industrial computer can load the adjusting of air pressure to pneumatic rotation loader through regulating device, thereby realizes the convenient load that loads of regulating, and satisfies various test needs.
Description of drawings
Fig. 1 is that the structure of the test macro of the utility model aircraft rotary actuator connects synoptic diagram;
Fig. 2 is that the module of the test macro of the utility model aircraft rotary actuator connects synoptic diagram;
Fig. 3 is the connection synoptic diagram of the utility model regulating device;
Fig. 4 gathers the connection synoptic diagram of feedback signal for the utility model industrial computer.
Among the figure: 1. rotary actuator; 2. rack; 21. electrical control cabinet; 22. industrial computer; 221. display screen;
3. angular transducer; 4. pneumatic rotation loader; 5. torque sensor; 6. transmission shaft; 7. test bracket;
8. pressure regulator valve; 9. ratio adjusting valve; 10. reversal valve; 11. external air source.
Embodiment
Below in conjunction with specific embodiment the utility model is further set forth.
Test macro like Fig. 1, a kind of aircraft rotary actuator shown in Figure 2; It comprises test bracket 7, industrial computer 22, transmission shaft 6, be used for to tested rotary actuator 1 provide the different frequency testing power supply electrical control cabinet 21, be used to detect tested rotary actuator angle angular transducer 3, be used to detect tested rotary actuator moment of torsion and rotating speed torque sensor 5, be used for the regulating device that the pneumatic rotation loader 4 of torque load directly is provided and is used to export and can regulate the loading air pressure of pneumatic rotation loader to rotary actuator, regulating device, electrical control cabinet and industrial computer are installed on the rack 2; Transmission shaft links to each other with the output shaft of rotary actuator; The output shaft and the transmission shaft of rotary actuator rotate synchronously; Angular transducer, pneumatic rotation loader, torque sensor are installed on the transmission shaft, and tested rotary actuator is installed on the test bracket, and tested rotary actuator is connected on the transmission shaft at torque sensor place through coupling mechanism; Again each sensor is connected with industrial computer through cable, accomplishes the connection setting of test; Wherein, industrial computer has the display screen 221 of the data that are used to show test results, and electrical control cabinet can provide the AC power of direct supply or different frequency;
Industrial computer links to each other with electrical control cabinet, torque sensor, angular transducer and regulating device respectively; Be used to receive the signal that electrical control cabinet, torque sensor and angular transducer transmission come; And can send instruction with control electrical control cabinet and adjustment device work to electrical control cabinet and regulating device; Regulating device links to each other with pneumatic rotation loader; Regulating device can be regulated to load after receiving the next command signal of industrial computer transmission and loaded air pressure for pneumatic rotation loader according to this instruction, acts on the torque load on the rotary actuator to regulate pneumatic rotation loader;
Torque sensor feedback torque signal to industrial computer calculates and on display screen, shows; The torque signal that industrial computer will feed back relatively calculates its deviation with the first value of establishing; Output torque controls signal to regulating device; Load air pressure to pneumatic rotation loader by regulating device output, implement load to transmission shaft, thereby keep output torque consistent with the moment of torsion of just establishing through pneumatic rotation loader; Electrical control cabinet out-put supply to tested rotary actuator, to drive the motor of tested rotary actuator, this motor links to each other with output shaft through the inner gear train of rotary actuator, and rotates synchronously; Show on the display screen of angular transducer feedback angle signal to industrial computer; Voltage and current signal to the industrial computer of electrical control cabinet feedback motor calculates and on display screen, shows; The supply frequency of industrial computer output frequency control signal control electrical control cabinet output; Power supply to use different frequency comes the motor of driven in rotation actuator, satisfies various test requests.
As shown in Figure 3; Regulating device comprises pressure regulator valve 8, ratio adjusting valve 9, the reversal valve 10 that links to each other successively; The inlet of pressure regulator valve links to each other with external air source 11; The control end of ratio adjusting valve, the control end of reversal valve link to each other with the moment of torsion control signal output ends of industrial computer respectively; The outlet of reversal valve links to each other with the inlet of pneumatic rotation loader, and the pneumatic rotation loader of the loading air pressure adjustment of passing ratio variable valve is carried in the torque load on the transmission shaft, through the direction of this torque load of reversal valve control; And transmission shaft is loaded torque load, that is to say rotary actuator is loaded torque load.
As shown in Figure 4, industrial computer has the data collecting card that is used for acquired signal, electrical control cabinet comprise the voltage signal that is used to feed back output voltage transmitter, be used to feed back the current transducer of the current signal of output; Industrial computer is through the signal of data collecting card difference acquisition angles sensor, voltage transmitter, current transducer, torque sensor output.
During test, start industrial computer, start testing software then.This testing software is the Labview software platform of NI company; This software platform adopts visual picture programming mode, the graphic programmed method of Graphics Application data stream programming language and process block, the very flow process of natural terrain registration certificate; And intuitively user interface controls is mapped on the data; Have objective interface, easy to operate, characteristics such as it is simple to programme.
Testing software start finish after, test macro will get into warm-up phase, can get into the test of aircraft rotary actuator after 15 minutes, this moment running software fixed in program, return 0 ° position after controlling pneumatic rotation loader left rotation and right rotation, accomplish fixed in setting.
In industrial computer, just establish the load value that input need load; At this moment, external air source gets into ratio adjusting valve after through the pressure regulator valve pressure regulation, and ratio adjusting valve is controlled by industrial computer; Industrial computer compares afterwards to the torque signal of numerical value and the torque sensor feedback of input, and moment of torsion controls signal to ratio adjusting valve; Apply torque load through reversal valve to rotary actuator, this reversal valve can apply the torque load of positive and negative direction to rotary actuator also by industrial computer control.Utilize the external air source pressure of 29PSI~145PSI, the moment scope that can load is 1.23Nm~402.46Nm.
The parameter that the test of rotary actuator is obtained is obtained by the angular transducer, torque sensor, voltage transmitter, the current transducer that are fixed on the test bracket; A/D data collecting card collection through NI PCI-6221 feeds back to industrial computer; In display screen, show; Demonstrate like drive current, stroke, rotational time, imposed load, switch the test result parameter such as whether to connect, simultaneously, have limit switch on the rotary actuator; When the output shaft of rotary actuator rotates to certain angle (this angle can be selected in 90 °~110 ° scopes); The voltage signal that touches one+5V of limit switch feedback to voltage transmitter, after industrial computer is received this signal, will be stopped the step motor of rotary actuator is supplied power; This moment, the output shaft of rotary actuator also stopped operating, thereby realized the control to the rotary actuator rotation; Also can pass through the feedback signal of voltage transmitter, current transducer accomplishes the potentiometric voltage ratio test of step motor.
The embodiment of the utility model is not limited thereto; According to foregoing; Ordinary skill knowledge and customary means according to this area; Do not breaking away under the above-mentioned basic fundamental thought of the utility model prerequisite, the utility model can also be made equivalent modifications, replacement or the change of other various ways, all should be interpreted as the protection domain that still belongs to the utility model.

Claims (3)

1. the test macro of an aircraft rotary actuator; It is characterized in that: it comprises test bracket, industrial computer, transmission shaft, be used for to tested rotary actuator provide the different frequency testing power supply electrical control cabinet, be used to detect tested rotary actuator angle angular transducer, be used to detect tested rotary actuator moment of torsion and rotating speed torque sensor, be used for the regulating device that the pneumatic rotation loader of torque load directly is provided and is used to export and can regulate the loading air pressure of pneumatic rotation loader to rotary actuator; Rotary actuator is installed on the said test bracket; Said transmission shaft links to each other with the output shaft of rotary actuator; The output shaft and the transmission shaft of rotary actuator rotate synchronously; Said angular transducer, pneumatic rotation loader, torque sensor are installed on the transmission shaft; Said industrial computer links to each other with described electrical control cabinet, torque sensor, angular transducer and regulating device respectively; Be used to receive the signal that electrical control cabinet, torque sensor and angular transducer transmission come; And can send instruction with control electrical control cabinet and adjustment device work to electrical control cabinet and regulating device; Said regulating device links to each other with pneumatic rotation loader, and said regulating device can be regulated to load after receiving the next command signal of industrial computer transmission and loaded air pressure for said pneumatic rotation loader according to this instruction, acts on the torque load on the rotary actuator to regulate pneumatic rotation loader.
2. the test macro of aircraft rotary actuator according to claim 1; It is characterized in that: said regulating device comprises pressure regulator valve, ratio adjusting valve, the reversal valve that links to each other successively; The inlet of said pressure regulator valve links to each other with external air source; The control end of said ratio adjusting valve, the control end of reversal valve link to each other with the moment of torsion control signal output ends of industrial computer respectively, and the outlet of said reversal valve links to each other with the inlet of pneumatic rotation loader.
3. the test macro of aircraft rotary actuator according to claim 1 and 2; It is characterized in that: said industrial computer has the data collecting card that is used for acquired signal, said electrical control cabinet comprise the voltage signal that is used to feed back output voltage transmitter, be used to feed back the current transducer of the current signal of output; Said industrial computer is through the signal of data collecting card difference acquisition angles sensor, voltage transmitter, current transducer, torque sensor output.
CN 201220026824 2012-01-18 2012-01-18 Test system of airplane rotary actuator Withdrawn - After Issue CN202442867U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN 201220026824 CN202442867U (en) 2012-01-18 2012-01-18 Test system of airplane rotary actuator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN 201220026824 CN202442867U (en) 2012-01-18 2012-01-18 Test system of airplane rotary actuator

Publications (1)

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CN 201220026824 Withdrawn - After Issue CN202442867U (en) 2012-01-18 2012-01-18 Test system of airplane rotary actuator

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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102564762A (en) * 2012-01-18 2012-07-11 广州飞机维修工程有限公司 Testing system of airplane rotating actuator
CN103454104A (en) * 2013-08-20 2013-12-18 北京航空航天大学 Large helicopter main blade steering machine fatigue test system
US8955425B2 (en) 2013-02-27 2015-02-17 Woodward, Inc. Rotary piston type actuator with pin retention features
US9163648B2 (en) 2013-02-27 2015-10-20 Woodward, Inc. Rotary piston type actuator with a central actuation assembly
US9234535B2 (en) 2013-02-27 2016-01-12 Woodward, Inc. Rotary piston type actuator
US9476434B2 (en) 2013-02-27 2016-10-25 Woodward, Inc. Rotary piston type actuator with modular housing
US9593696B2 (en) 2013-02-27 2017-03-14 Woodward, Inc. Rotary piston type actuator with hydraulic supply
US9631645B2 (en) 2013-02-27 2017-04-25 Woodward, Inc. Rotary piston actuator anti-rotation configurations
US9816537B2 (en) 2013-02-27 2017-11-14 Woodward, Inc. Rotary piston type actuator with a central actuation assembly
CN110296816A (en) * 2019-07-09 2019-10-01 中国航发哈尔滨东安发动机有限公司 A kind of test device

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102564762B (en) * 2012-01-18 2015-05-20 广州飞机维修工程有限公司 Testing system of airplane rotating actuator
CN102564762A (en) * 2012-01-18 2012-07-11 广州飞机维修工程有限公司 Testing system of airplane rotating actuator
US9593696B2 (en) 2013-02-27 2017-03-14 Woodward, Inc. Rotary piston type actuator with hydraulic supply
US8955425B2 (en) 2013-02-27 2015-02-17 Woodward, Inc. Rotary piston type actuator with pin retention features
US9163648B2 (en) 2013-02-27 2015-10-20 Woodward, Inc. Rotary piston type actuator with a central actuation assembly
US10030679B2 (en) 2013-02-27 2018-07-24 Woodward, Inc. Rotary piston type actuator
US9234535B2 (en) 2013-02-27 2016-01-12 Woodward, Inc. Rotary piston type actuator
US9476434B2 (en) 2013-02-27 2016-10-25 Woodward, Inc. Rotary piston type actuator with modular housing
US10458441B2 (en) 2013-02-27 2019-10-29 Woodward, Inc. Rotary piston actuator anti-rotation configurations
US9631645B2 (en) 2013-02-27 2017-04-25 Woodward, Inc. Rotary piston actuator anti-rotation configurations
US9709078B2 (en) 2013-02-27 2017-07-18 Woodward, Inc. Rotary piston type actuator with a central actuation assembly
US9816537B2 (en) 2013-02-27 2017-11-14 Woodward, Inc. Rotary piston type actuator with a central actuation assembly
US10767669B2 (en) 2013-02-27 2020-09-08 Woodward, Inc. Rotary piston type actuator with a central actuation assembly
CN103454104B (en) * 2013-08-20 2015-12-02 北京航空航天大学 A kind of big payload helicopter main oar steering wheel fatigue test system
CN103454104A (en) * 2013-08-20 2013-12-18 北京航空航天大学 Large helicopter main blade steering machine fatigue test system
CN110296816A (en) * 2019-07-09 2019-10-01 中国航发哈尔滨东安发动机有限公司 A kind of test device

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GR01 Patent grant
C14 Grant of patent or utility model
AV01 Patent right actively abandoned

Granted publication date: 20120919

Effective date of abandoning: 20150520

RGAV Abandon patent right to avoid regrant