CN103879565A - Aircraft ground test-run parameter detection device - Google Patents
Aircraft ground test-run parameter detection device Download PDFInfo
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- CN103879565A CN103879565A CN201210562438.XA CN201210562438A CN103879565A CN 103879565 A CN103879565 A CN 103879565A CN 201210562438 A CN201210562438 A CN 201210562438A CN 103879565 A CN103879565 A CN 103879565A
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Abstract
The invention relates to the technical field of measurements, and in particular to an aircraft ground test-run parameter detection device comprising a sensor, a signal conditioner, a data acquiring card, an industrial computer and a signal converter. The sensor is fixedly mounted in signal-measuring positions of an aircraft. Electrical signals produced by the sensor enter the data acquiring card through the signal conditioner, the data acquiring card converts the electrical signals into digital values from analog data and transmits to the industrial computer, and the industrial computer recovers and records the digital information. The signal converter is mounted between the sensor and the signal conditioner and is used for preventing signals of the sensor from losing due to electromagnetic interference before the signals enter the signal conditioner. The device adopts the signal converter, the aircraft ground test-run parameters are measured by the sensor before signal conversion is performed, data losing is avoided, electromagnetic interference resistance of the aircraft ground test-run parameter detection device during ground test run is improved, structure is simple, cost is low, and the device has high promotion and application value.
Description
Technical field
Relate to field of measuring technique, particularly relate to a kind of ground run parameter detection device that is applicable to outfield polytypic aircraft utilization.
Background technology
What prior art was used aircraft floor driving engine driving parameter detecting is that one is made up of sensor, signal conditioner, data collecting card and industrial computer, and industrial computer contains simple data processing and reducing program.Because aircraft floor test run is often in outdoor outfield, the huge mobile inconvenience of its test platform, is not suitable for the needs of aircraft in outfield test run.It need supply 220V reference power supply, is not easy to line using.During because of aircraft test run, electromagnetic environment is more severe, and it is very large that the associated electronic devices such as sensor and collector are disturbed impact, often occurs loss of data phenomenon, is difficult to the data of the whole commissioning process of complete collection.Its test be only driving engine correlation parameter, aircraft correlation parameter can not relate to.
Summary of the invention
For solving the technical matters of above-mentioned commissioning process loss of data under the severe electromagnetic environment of aircraft test run, the invention provides that a kind of anti-electromagnetic interference capability is strong, can finish gathers the aircraft floor test run parameter detection device of whole commissioning process data.
Aircraft floor test run parameter detection device, by sensor, signal conditioner, data collecting card and industrial computer composition, described sensor is fixedly mounted on airframe signal to be measured place, when test, the electromotive signal that sensor produces enters in data collecting card by signal conditioner, data collecting card sends electromotive signal to industrial computer from simulate data transfers digital numerical value to, industrial computer is by numerical information reduction record, it is characterized in that: also comprise signal converter, described signal converter is arranged between sensor and signal conditioner, prevent that the signal of sensor from forming the loss of signal before entering signal conditioner because of electromagnetic interference.
The present invention utilizes signal converter, the parameter of aircraft floor test run is carried out after sensor measurement to signal conversion, avoid loss of data, the ability of the anti-electromagnetic interference of aircraft floor test run parameter detection device while having improved ground run, and simple in structure, cost is low, has higher promotion and application and is worth.
Accompanying drawing explanation
Drawing of the present invention is described as follows:
Fig. 1: aircraft floor test run parameter detection device structural representation block diagram;
Fig. 2: aircraft floor test run parameter detection device and aircraft connection diagram;
Fig. 3: aircraft floor test run parameter detection device examine bench board schematic diagram portablely;
In figure: 1. bench board 2. industrial laptop 3. test cables and flexible pipe 4. aircraft 5. push handle 6. casees 7.
Air-inflation tyre 8. sensor 9. signal converter 10. signal conditioner 11. data collecting card 12. industrial computers 13.
The specific embodiment
Below in conjunction with accompanying drawing, that the present invention is further illustrated is as follows:
Aircraft floor test run parameter detection device, by sensor 8, signal conditioner 10, data collecting card 11 and industrial computer 12 form, described sensor 8 is fixedly mounted on airframe signal to be measured place, when test, the electromotive signal that sensor 8 produces enters in data collecting card 11 by signal conditioner 10, data collecting card 11 sends electromotive signal to industrial computer 12 from simulate data transfers digital numerical value to, industrial computer 12 is by numerical information reduction record, it is characterized in that: also comprise signal converter 9, described signal converter 9 is arranged between sensor 8 and signal conditioner 10, prevent that the signal of sensor from forming the loss of signal before entering signal conditioner because of electromagnetic interference.When use, sensor 8 is fixedly mounted on aircraft 4, and is connected with signal converter 9 by test cable and flexible pipe 3, connects successively on signal conditioner 10, data collecting card 11, industrial computer 12.
For further strengthening the antijamming capability of aircraft floor test run parameter detection device, design a case 6 that sheet metal is housing, the bench board 1 that sensor 8, signal conditioner 10, data collecting card 11 form is placed in case 6.
Described industrial computer can be selected industrial laptop 2.
Power supply in the present invention uses direct current and exchanges the inverter that can mutually change.
For ease of the line using of aircraft floor test run parameter detection device, in the bottom of case, air-inflation tyre 7 is installed, push handle 5 has been installed on casing.
Claims (7)
1. aircraft floor test run parameter detection device, by sensor (8), signal conditioner (10), data collecting card (11) and industrial computer (12) composition, described sensor (8) is fixedly mounted on airframe signal to be measured place, when test, the electromotive signal that sensor (8) produces enters in data collecting card (11) by signal conditioner (10), data collecting card (11) sends electromotive signal to industrial computer (12) from simulate data transfers digital numerical value to, industrial computer (12) is by numerical information reduction record, it is characterized in that: also comprise signal converter (9), described signal converter (9) is arranged between sensor (8) and signal conditioner (10), prevent that the signal of sensor from forming the loss of signal before entering signal conditioner because of electromagnetic interference.
2. aircraft floor test run parameter detection device according to claim 1, it is characterized in that: design the case (6) that a sheet metal is housing, the bench board (1) that sensor (8), signal conditioner (10), data collecting card (11) form is placed in case (6).
3. aircraft floor test run parameter detection device according to claim 1, is characterized in that: described industrial computer is selected industrial laptop (2).
4. aircraft floor test run parameter detection device according to claim 3, is characterized in that: industrial laptop (2) is connected with printout (14).
5. aircraft floor test run parameter detection device according to claim 3, is characterized in that: industrial laptop (2) can be connected in real time with liquid crystal display (13), display measurement numerical value intuitively.
6. according to the aircraft floor test run parameter detection device described in claim 1,2,3,4,5 arbitrary claims, it is characterized in that: the power supply in the present invention uses direct current and exchanges the inverter that can mutually change.
7. according to the aircraft floor test run parameter detection device described in claim 1,2,3,4,5 arbitrary claims, it is characterized in that: in the bottom of case (6), air-inflation tyre (7) is installed, push handle (5) has been installed on case (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210562438.XA CN103879565A (en) | 2012-12-23 | 2012-12-23 | Aircraft ground test-run parameter detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210562438.XA CN103879565A (en) | 2012-12-23 | 2012-12-23 | Aircraft ground test-run parameter detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103879565A true CN103879565A (en) | 2014-06-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210562438.XA Pending CN103879565A (en) | 2012-12-23 | 2012-12-23 | Aircraft ground test-run parameter detection device |
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| CN (1) | CN103879565A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105291936A (en) * | 2015-11-23 | 2016-02-03 | 中国航天空气动力技术研究院 | Ground integrated test apparatus for UAV (unmanned aerial vehicle) undercarriages |
| CN111665054A (en) * | 2020-05-22 | 2020-09-15 | 成都飞机工业（集团）有限责任公司 | Portable engine digital regulator detection device |
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| US4179740A (en) * | 1977-09-02 | 1979-12-18 | Malin John R | Vehicle performance analyzer |
| JPS5757235A (en) * | 1980-09-24 | 1982-04-06 | Toyota Motor Corp | Measuring method for friction torque of engine |
| CN201016857Y (en) * | 2006-12-25 | 2008-02-06 | 成都发动机（集团）有限公司 | Rotary automatic temperature measuring device |
| CN101183045A (en) * | 2007-11-22 | 2008-05-21 | 江西洪都航空工业集团有限责任公司 | Airplane engines ground starting up system tester |
| CN201277910Y (en) * | 2008-10-22 | 2009-07-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Test parameter measurement system for aero engine |
| CN102147333A (en) * | 2011-01-05 | 2011-08-10 | 哈尔滨飞机工业集团有限责任公司 | Over-rotation test system for electrical-adjustable bi-motored helicopter turbo shaft engine |
| CN102539163A (en) * | 2010-12-27 | 2012-07-04 | 贵州双阳飞机制造厂 | Aircraft engine detection device |
| CN102680233A (en) * | 2011-03-17 | 2012-09-19 | 北汽福田汽车股份有限公司 | Motor failure diagnosis device and method |
-
2012
- 2012-12-23 CN CN201210562438.XA patent/CN103879565A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4179740A (en) * | 1977-09-02 | 1979-12-18 | Malin John R | Vehicle performance analyzer |
| JPS5757235A (en) * | 1980-09-24 | 1982-04-06 | Toyota Motor Corp | Measuring method for friction torque of engine |
| CN201016857Y (en) * | 2006-12-25 | 2008-02-06 | 成都发动机（集团）有限公司 | Rotary automatic temperature measuring device |
| CN101183045A (en) * | 2007-11-22 | 2008-05-21 | 江西洪都航空工业集团有限责任公司 | Airplane engines ground starting up system tester |
| CN201277910Y (en) * | 2008-10-22 | 2009-07-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Test parameter measurement system for aero engine |
| CN102539163A (en) * | 2010-12-27 | 2012-07-04 | 贵州双阳飞机制造厂 | Aircraft engine detection device |
| CN102147333A (en) * | 2011-01-05 | 2011-08-10 | 哈尔滨飞机工业集团有限责任公司 | Over-rotation test system for electrical-adjustable bi-motored helicopter turbo shaft engine |
| CN102680233A (en) * | 2011-03-17 | 2012-09-19 | 北汽福田汽车股份有限公司 | Motor failure diagnosis device and method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105291936A (en) * | 2015-11-23 | 2016-02-03 | 中国航天空气动力技术研究院 | Ground integrated test apparatus for UAV (unmanned aerial vehicle) undercarriages |
| CN111665054A (en) * | 2020-05-22 | 2020-09-15 | 成都飞机工业（集团）有限责任公司 | Portable engine digital regulator detection device |
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Application publication date: 20140625 |
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