CN214729785U - Test support for testing position sensor of adjustable flow valve of airplane - Google Patents
Test support for testing position sensor of adjustable flow valve of airplane Download PDFInfo
- Publication number
- CN214729785U CN214729785U CN202120831853.5U CN202120831853U CN214729785U CN 214729785 U CN214729785 U CN 214729785U CN 202120831853 U CN202120831853 U CN 202120831853U CN 214729785 U CN214729785 U CN 214729785U
- Authority
- CN
- China
- Prior art keywords
- sensor
- guide rail
- position sensor
- angle
- support
- 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.)
- Active
Links
Images
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
A test support for testing an adjustable circulating valve position sensor of an airplane comprises an angle sensor, a large guide rail, a small guide rail, a sensor support and an angle sensor, wherein the small guide rail is arranged on the large guide rail, the sensor support is positioned on the small guide rail to fix the position sensor to be tested, one side of the sensor support is provided with the angle sensor connected to an actuating rod on the position sensor, and the other side of the angle sensor, different from the sensor support, is provided with a torque sensor, so that the angle of the actuating rod is positioned through the angle sensor, and the torque sensor is used for measuring and returning torque; therefore, the utility model discloses simple structure, convenient operation has established adjustable circulation valve position sensor's test ability, has practiced thrift the cost of maintenance of this annex, has improved work efficiency.
Description
Technical Field
The utility model relates to a technical field of aircraft annex maintenance especially relates to a test support of adjustable circulation valve position sensor of test aircraft.
Background
The adjustable flow valve position sensor is composed of two differential rotary transformers arranged on the same rotating shaft, the shape of the adjustable flow valve position sensor is shown in figure 1, the internal structure of the adjustable flow valve position sensor is shown in figure 2, and the adjustable flow valve position sensor comprises a shell 1, an electric connector 2, a sensitive sleeve 3, a return spring 4 and an actuating rod 5. The two differential rotary transformers are encapsulated in a sealed shell 1 made of light alloy materials by using high polymer materials. The output shaft of the sensor is provided with an actuating rod and a return spring. The actuating rod is marked with scale marks for indicating the zero-degree position of the sensor.
The position sensor is controlled by an adjustable flow valve. The deflector rod of the adjustable circulation valve drives the rotating shaft of the position sensor to drive the sensor to move. The maximum mechanical angular displacement of the position sensor is 105 degrees and the effective angular displacement is 80 degrees. The primary coil of each differential rotary transformer of the position sensor is excited by a sine wave signal with the amplitude of 7.07VRMS and the frequency of 3000Hz, and the secondary coil of each differential transformer induces two paths of signals with the amplitude of 3000Hz sine waves changing linearly in the range of 1.6-6.8VRMS according to the angle position.
The adjustable flow valve position sensor is an accessory installed on a CFM56 model engine of an A320 series airplane, OEM specifies that major repairs are required to be performed on the engine every 12000 hours, the accessories are disassembled and replaced by 64 in 2017 national aviation, the repair sending cost is 120 million RMB, and the cost is very high and the efficiency is low.
In recent years, some domestic accessory manufacturers can perform manual testing of accessories according to a service manual. However, such an operation is complicated and has poor accuracy.
Therefore, in view of the above-mentioned drawbacks, the designer of the present invention develops a test frame for testing an adjustable position sensor of a circulation valve of an aircraft by combining experience and achievement from long-term related industries through careful research and design to overcome the above-mentioned drawbacks.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a test support of adjustable circulation valve position sensor of test aircraft, its simple structure, convenient operation has established adjustable circulation valve position sensor's test ability, has practiced thrift the cost of maintenance of this annex, has improved work efficiency.
In order to achieve the above object, the utility model discloses a test support of adjustable circulation valve position sensor of test aircraft, including angle sensor, big guide rail, little guide rail, sensor support and angle sensor, its characterized in that:
the small guide rail is arranged on the large guide rail, the sensor support is positioned on the small guide rail to fix the position sensor to be tested, one side of the sensor support is provided with an angle sensor connected to the position sensor to actuate the rod, and the other side of the angle sensor, different from the sensor support, is provided with a torque sensor so as to position the angle of the actuating rod through the angle sensor and utilize the torque sensor to measure and return torque.
Wherein: the small guide rail is arranged on the large guide rail in a sliding mode through a plurality of sliding blocks at the lower end, and a limiting device is arranged between the small guide rail and the large guide rail to position the small guide rail.
Wherein: the sensor support is provided with a positioning through hole corresponding to the three mounting holes of the position sensor base, and three hand-screwed positioning shafts respectively penetrate through the mounting holes and the positioning through hole to fix the position sensor and the sensor support on the small guide rail.
Wherein: the lower end of the sensor bracket is provided with a sliding block which can slide on the small guide rail.
Wherein: the small guide rail is provided with a limiting block for limiting the sensor bracket.
Wherein: the other side of the torque sensor, which is different from the angle sensor, is connected with a motor and a speed reducer, and an output shaft of the motor is connected to the speed reducer.
Wherein: the output shaft of the speed reducer is connected to a torque sensor, and the angle sensor is connected to a bearing hole of the actuating rod through a connecting shaft.
Wherein: and the reflector is arranged between the angle sensor and the position sensor so as to determine the specific angle of the actuating rod of the position sensor.
According to the above content, the utility model discloses a test support of adjustable circulation valve position sensor of test aircraft has following effect:
1. the testing capability of the adjustable flow valve position sensor is established, and the maintenance cost of the accessory is saved. The working efficiency is improved.
2. Human factor errors are reduced, unsafe factors are reduced, and tested pieces, test equipment and workers are protected.
The details of the present invention can be obtained from the following description and the attached drawings.
Drawings
Fig. 1 shows a schematic view of an adjustable flow valve position sensor.
Fig. 2 shows a schematic internal construction of an adjustable flow-through valve position sensor.
Fig. 3 shows a schematic structural diagram of a test rack for testing an aircraft adjustable flow valve position sensor according to the present invention.
Fig. 4 shows a top view of the present invention.
Reference numerals:
10. an angle sensor; 11. a large guide rail; 12. a small guide rail; 13. a sensor holder; 14. a limiting block; 15. a position sensor; 16. a torque sensor; 17. a speed reducer; 18. a motor; 19. a connecting shaft; 20. a reflective mirror; 21. the positioning shaft is screwed by hand.
Detailed Description
Referring to fig. 3 and 4, a test rack for testing an adjustable flow valve position sensor of an aircraft is shown.
The test support for testing the adjustable circulating valve position sensor of the airplane comprises an angle sensor 10, a large guide rail 11, a small guide rail 12, a sensor support 13 and an angle sensor 16, wherein the small guide rail 12 is arranged on the large guide rail 11, the sensor support 13 is positioned on the small guide rail 12 to fixedly install a position sensor 15 to be tested, one side of the sensor support 13 is provided with the angle sensor 10 connected to an actuating rod on the position sensor 15, the other side, different from the sensor support 13, of the angle sensor 10 is provided with a torque sensor 16, so that the position sensor 15 is positioned through the sensor support 13, the angle of the actuating rod is positioned through the angle sensor 10, and the torque sensor 16 is utilized to measure and return torque.
The small guide rail 12 can be arranged on the large guide rail 11 through a plurality of sliding blocks at the lower end in a sliding manner, and a limiting device is arranged between the small guide rail 12 and the large guide rail 11 to position the small guide rail 12.
Wherein, sensor support 13 is equipped with the positioning hole corresponding to the three mounting hole of position sensor 15 base, and three hand is twisted location axle 21 and is run through mounting hole and positioning hole respectively to be fixed in on little guide rail 12 with position sensor 15 and sensor support 13, the lower extreme of sensor support 13 is equipped with the slider of slidable in little guide rail 12, and little guide rail 12 is equipped with the stopper 14 of spacing sensor support 13.
Wherein, the other side of the torque sensor 16 different from the angle sensor 10 is connected with a motor 18 and a speed reducer 17, the output shaft of the motor 18 is connected to the speed reducer 17, the output shaft of the speed reducer 17 is connected to the torque sensor 16, the angle sensor 16 is connected to the bearing hole of the actuating rod through a connecting shaft 19, and a reflective mirror 20 is arranged between the angle sensor 10 and the position sensor 15 to determine the specific angle of the actuating rod of the position sensor.
From this, because the torque value when the service manual required measuring sensor pole to be located 0 and 80, fixed the sensor, satisfy the measuring position of adjusting the sensor pole at 0 and 80, in concrete operation, fix position sensor on the sensor support through 3 hand-twist location axles, the slider in the rethread sensor support lower extreme pushes with little guide rail cooperation, inserts the connecting axle in the bearing hole on the pole of moving, fixes the sensor support through hand-twist location axle.
Then, the motor is controlled to adjust the angle of the actuating rod, whether the actuating rod and the scribed line on the shell are collinear is observed through the reflector to determine the mechanical 0 degree, the return torque value can be measured after the mechanical 0 degree is confirmed, and then the motor is controlled to rotate the shaft to 80 degrees, and the return torque value when the angle is 80 degrees is measured.
According to the content, the utility model discloses an automatic test of adjustable circulation valve position sensor liberates the technician from loaded down with trivial details manual work and has improved the measuring accuracy, has opened OEM technical blockade's situation, and in addition, Ameco has established the maintenance ability of this kind of annex, has filled the vacancy of maintenance ability. At least 100 ten thousand yuan of maintenance cost can be saved for the country every year.
It is to be understood that the above description and illustrations are exemplary only and are not intended to limit the present disclosure, application, or uses. While embodiments have been described in the embodiments and depicted in the drawings, the present invention is not limited to the particular examples illustrated by the drawings and described in the embodiments as the best mode presently contemplated for carrying out the teachings of the present invention, and the scope of the present invention is intended to include any embodiments that fall within the foregoing description and the appended claims.
Claims (8)
1. The utility model provides a test support of adjustable circulation valve position sensor of test aircraft, includes angle sensor, big guide rail, little guide rail, sensor support and angle sensor, its characterized in that:
the small guide rail is arranged on the large guide rail, the sensor support is positioned on the small guide rail to fix the position sensor to be tested, one side of the sensor support is provided with an angle sensor connected to the position sensor to actuate the rod, and the other side of the angle sensor, different from the sensor support, is provided with a torque sensor so as to position the angle of the actuating rod through the angle sensor and utilize the torque sensor to measure and return torque.
2. A test rack for testing an adjustable flow valve position sensor for an aircraft as claimed in claim 1, wherein: the small guide rail is arranged on the large guide rail in a sliding mode through a plurality of sliding blocks at the lower end, and a limiting device is arranged between the small guide rail and the large guide rail to position the small guide rail.
3. A test rack for testing an adjustable flow valve position sensor for an aircraft as claimed in claim 1, wherein: the sensor support is provided with a positioning through hole corresponding to the three mounting holes of the position sensor base, and three hand-screwed positioning shafts respectively penetrate through the mounting holes and the positioning through hole to fix the position sensor and the sensor support on the small guide rail.
4. A test rack for testing an adjustable flow valve position sensor for an aircraft according to claim 3, wherein: the lower end of the sensor bracket is provided with a sliding block which can slide on the small guide rail.
5. A test rack for testing an adjustable flow valve position sensor for an aircraft as claimed in claim 4, wherein: the small guide rail is provided with a limiting block for limiting the sensor bracket.
6. A test rack for testing an adjustable flow valve position sensor for an aircraft as claimed in claim 1, wherein: the other side of the torque sensor, which is different from the angle sensor, is connected with a motor and a speed reducer, and an output shaft of the motor is connected to the speed reducer.
7. A test rack for testing an adjustable flow valve position sensor for an aircraft as claimed in claim 6, wherein: the output shaft of the speed reducer is connected to a torque sensor, and the angle sensor is connected to a bearing hole of the actuating rod through a connecting shaft.
8. A test rack for testing an adjustable flow valve position sensor for an aircraft as claimed in claim 1, wherein: and the reflector is arranged between the angle sensor and the position sensor so as to determine the specific angle of the actuating rod of the position sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120831853.5U CN214729785U (en) | 2021-04-22 | 2021-04-22 | Test support for testing position sensor of adjustable flow valve of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120831853.5U CN214729785U (en) | 2021-04-22 | 2021-04-22 | Test support for testing position sensor of adjustable flow valve of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214729785U true CN214729785U (en) | 2021-11-16 |
Family
ID=78611993
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120831853.5U Active CN214729785U (en) | 2021-04-22 | 2021-04-22 | Test support for testing position sensor of adjustable flow valve of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214729785U (en) |
-
2021
- 2021-04-22 CN CN202120831853.5U patent/CN214729785U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101344495B (en) | Measuring apparatus for reflection index of wave suction material | |
| CN201488848U (en) | Rotary bearing torque tester | |
| CN102156047B (en) | Loading simulation device for test bed of wind turbine | |
| CN202994470U (en) | Dynamic performance testing system for pilotless aircraft | |
| CN201266180Y (en) | Measuring apparatus for reflection index of wave suction material | |
| CN101271036A (en) | Sun wing hinge moment testing device | |
| CN111380698A (en) | Be used for new energy automobile to drive power assembly to dragging test bench structure | |
| CN203798570U (en) | A quick accurate centering device of engine for bench test | |
| CN105716662A (en) | Automatic measurement assembly table for slewing bearing | |
| CN214729785U (en) | Test support for testing position sensor of adjustable flow valve of airplane | |
| CN108955489B (en) | Pitch measuring device of adjustable-pitch propeller | |
| CN102879458B (en) | Damage detector based on piezomagnetic effect | |
| CN208751455U (en) | A kind of adjustable pitch propeller pitch measurement device | |
| CN219244489U (en) | Detachable tower mapping tool for wind power gear box | |
| CN210570545U (en) | Aero-engine single-blade surface roughness detection device | |
| CN209446061U (en) | A kind of project cost measuring scale | |
| CN208736307U (en) | A kind of pipe diameter measuring device of Corrosionproof thermal pipe with anodic trip | |
| CN201575880U (en) | Large-blade weight moment over-range testing device | |
| CN204988621U (en) | Horizontal reed dynamometer calibrating device | |
| CN109060358B (en) | The comprehensive performance test bed frame of shipboard, centering method and test method | |
| CN204900302U (en) | A fan blade testing arrangement that is used for support of fan blade test and contains support | |
| CN112078827A (en) | Multifunctional propeller measuring instrument and measuring method | |
| CN102384707A (en) | Cam lift measurement device | |
| CN209102754U (en) | A kind of diesel engine speed sensor calibration device | |
| CN108981747B (en) | Wave direction calibrating device for wave buoy |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |