CN202485859U - Device for checking helicopter engine torque system - Google Patents
Device for checking helicopter engine torque system Download PDFInfo
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- CN202485859U CN202485859U CN2012200024233U CN201220002423U CN202485859U CN 202485859 U CN202485859 U CN 202485859U CN 2012200024233 U CN2012200024233 U CN 2012200024233U CN 201220002423 U CN201220002423 U CN 201220002423U CN 202485859 U CN202485859 U CN 202485859U
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Abstract
The utility model discloses a device for checking a helicopter engine torque system. The device comprises an air pressure source, a standard pressure transducer (9), an excitation direct-current power source (14), an excitation alternating-current power source (15), a reversing switch (16), a reversing switch (17), a reversing switch (18) and a digital display (11). The device of the utility model is capable of checking airborne torque systems of the direct-current power supply type and the alternating-current power supply type, avoiding cross contamination of pressure mediums. In addition, the device, which is less affected by ambient temperature change, is capable of checking a sensor and a torque indicator of a helicopter torque system in an on-line manner.
Description
Technical field
The utility model belongs to helicopter-mounted instrument and meter collimation technique field, relates to the improvement of helicopter engine torque system calibration equipment.
Background technology
The engine torque system check device that existing certain serial helicopter uses is to be made up of a hydraulic power source and a pointer torque meter; Hydraulic power source produces certain pressure signal through the screw press device, and this signal passes to the on-board torque sensors and the torque meter of torque system calibration equipment and helicopter respectively.The mode that the indicating value through torque system calibration equipment upper spring cast pointer-type torque meter and the indicating value of airborne torque meter compare, the accuracy that comes the airborne torque system of verification.
The problem that prior art exists has:
1) existing torque system calibration equipment indicating instrument is pointer torque meter, and its pressure transmission mechanism is a bourdon tube, and this just causes the type torque system calibration equipment to use at normal temperatures, receives influence of temperature change bigger;
2) existing torque system calibration equipment can only be calibrated the airborne torque system of Alternating Current Power Supply type, and is single to type, can only calibrate certain serial helicopter basic model;
3) pressure medium of existing torque system calibration equipment pressure source is an aircraft fluid, when measuring the airborne pressure transducer of flying, can cause cross pollution inevitably more, damages the torsional moment test device easily; And it is thick that pressure is reconciled precision, and micrometering valve and retaining valve are not installed, and in use also inevitably has part hydraulic oil seepage, makes the output that force value can not be stable, causes measuring error;
4) can only off normal respectively verification helicopter torque sensor and torque meter do not meet the war fighting requirement of military secret.
Summary of the invention
The purpose of the utility model is: provide a kind of can verification direct current supply type and the airborne torque system of Alternating Current Power Supply type; Can avoid the cross pollution of pressure medium; It is less influenced by variation of ambient temperature, and through online mode just can verification helicopter torque system sensor and torque meter.
The technical scheme of the utility model is: helicopter engine torque system calibration equipment, form by a pneumatic supply, standard pressure transducer 9, the first excitation direct supply 10, the second excitation direct supply 14, excitation AC power 15, first reversing switch 16, second reversing switch 17, the 3rd reversing switch 18 and digital indicator 11;
Pneumatic supply is made up of air filter 1, first retaining valve 2, pitcher pump 3, second retaining valve 4, stop valve 5, vent valve 6, pressure micro actuator 7 and threeway 8; The output terminal of air filter 1 is communicated with the input end of first retaining valve 2 through pipeline; The output terminal of first retaining valve 2 is communicated with the input end of pitcher pump 3 through pipeline; The output terminal of pitcher pump 3 is communicated with the input end of second retaining valve 4 through pipeline; The output terminal of second retaining valve 4 is communicated with an end of stop valve 5 through pipeline; The other end of stop valve 5 is communicated with an end of vent valve 6 through pipeline, and vent valve 6 other ends are communicated with an end of pressure micro actuator 7 through pipeline, and the other end of pressure micro actuator 7 is communicated with the first port 8a of threeway 8 through pipeline; The second port 8b of threeway 8 is communicated with the pressure input port of standard pressure transducer 9 through pipeline, and the 3rd port 8c of threeway 8 is communicated with the pressure input port of helicopter engine torque sensor 12 through pipeline;
The signal output part of standard pressure transducer 9 is connected with the a3 end of second reversing switch 17; The b3 end of second reversing switch 17 is connected with the signal input part of digital indicator 11; The c3 end of second reversing switch 17 is connected with the signal input part of airborne torque system indicating gauge 13, and the output terminal of the first excitation direct supply 10 is connected with the power input of standard pressure transducer 9;
The second excitation direct supply 14 is connected with the a1 end of first reversing switch 16, and the b1 end of first reversing switch 16 is connected with the output terminal of excitation AC power 15, and c 1 end of first reversing switch 16 is connected with the power input of on-board torque sensors 12; The a2 end of the 3rd reversing switch 18 is connected with the signal output part of on-board torque sensors 12, and the b2 end of the 3rd reversing switch 18 is connected with the signal input part of airborne torque system indicating gauge 13; The c2 end of the 3rd reversing switch 18 is connected with the signal input part of digital indicator 11.
Advantage and the beneficial effect that the utlity model has are:
(1) the utility model torque system calibration equipment all adopts the digital circuit intelligence instrument, and operating ambient temperature range is (15 ℃～40 ℃), receives variation of ambient temperature less;
(2) the utility model torque system calibration equipment has merged the calibration of the airborne torque system of present direct current supply type and Alternating Current Power Supply type, has covered present whole certain type helicopter series, has expanded its range of application;
(3),, got rid of the shortcoming of hydraulic power supply from having changed the project organization of torsional moment test device in essence with pneumatic supply replacement liquid potential source;
(4) through the online and crosslinked mode of aircraft; Need not dismantle instrument and sensor on the helicopter engine torque system; Just can carry out the verification of torque measurement and indication mechanism accuracy and the investigation of concrete fault, avoid causing cross pollution, improve measuring accuracy.
Description of drawings
Fig. 1 is the utility model structural principle synoptic diagram.
Embodiment
Explain further details in the face of the present invention down.
Referring to Fig. 1; Helicopter engine torque system calibration equipment, its structure is formed: be made up of a pneumatic supply, standard pressure transducer 9, the first excitation direct supply 10, the second excitation direct supply 14, excitation AC power 15, first reversing switch 16, second reversing switch 17, the 3rd reversing switch 18 and digital indicator 11;
Pneumatic supply is made up of air filter 1, first retaining valve 2, pitcher pump 3, second retaining valve 4, stop valve 5, vent valve 6, pressure micro actuator 7 and threeway 8; The output terminal of air filter 1 is communicated with the input end of first retaining valve 2 through pipeline; The output terminal of first retaining valve 2 is communicated with the input end of pitcher pump 3 through pipeline; The output terminal of pitcher pump 3 is communicated with the input end of second retaining valve 4 through pipeline; The output terminal of second retaining valve 4 is communicated with an end of stop valve 5 through pipeline; The other end of stop valve 5 is communicated with an end of vent valve 6 through pipeline, and vent valve 6 other ends are communicated with an end of pressure micro actuator 7 through pipeline, and the other end of pressure micro actuator 7 is communicated with the first port 8a of threeway 8 through pipeline; The second port 8b of threeway 8 is communicated with the pressure input port of standard pressure transducer 9 through pipeline, and the 3rd port 8c of threeway 8 is communicated with the pressure input port of helicopter engine torque sensor 12 through pipeline;
The signal output part of standard pressure transducer 9 is connected with the a3 end of second reversing switch 17; The b3 end of second reversing switch 17 is connected with the signal input part of digital indicator 11; The c3 end of second reversing switch 17 is connected with the signal input part of airborne torque system indicating gauge 13, and the output terminal of the first excitation direct supply 10 is connected with the power input of standard pressure transducer 9;
The second excitation direct supply 14 is connected with the a1 end of first reversing switch 16, and the b1 end of first reversing switch 16 is connected with the output terminal of excitation AC power 15, and the c1 end of first reversing switch 16 is connected with the power input of on-board torque sensors 12.The a2 end of the 3rd reversing switch 18 is connected with the signal output part of on-board torque sensors 12, and the b2 end of the 3rd reversing switch 18 is connected with the signal input part of airborne torque system indicating gauge 13.The c2 end of the 3rd reversing switch 18 is connected with the signal input part of digital indicator 11.
The concrete job step and the principle of the utility model are:
(1) verification on-board torque sensors 12
Select different excitation power supplies through first reversing switch 16, airborne sensor 12 is encouraged.If on-board torque sensors 12 is an once-through type, the direct current second excitation direct supply 14 output terminals are connected with reversing switch a1 end, and reversing switch connects a1 end and c1 end; If on-board torque sensors 12 is an AC type, ac-excited power supply 15 output terminals are connected with reversing switch b1 end, and reversing switch connects b1 end and c1 end;
Adopt gas as pressure medium, avoided cross pollution.Adopt the pneumatic supply voltage supply simultaneously, and atmospheric pressure is filtered and the secondary pressure adjustment, satisfied the requirement of airborne pressure transducer calibrating, avoided the shortcoming of oil hydraulic system.Wherein pitcher pump 3 is the forced piston-cylinder of handle, and the pressure gas circuit is a double check valve, prevents that high pressure draught from refluxing; Stop valve 5 is a stop valve, closes stop valve 5 and can make back level gas circuit form closed air chamber, has guaranteed tonometric stability.Vent valve 6 is used for the quick drain gases at high pressure; Pressure micro actuator 7 is a spiral gyro-precession type pressure cylinder, is used for the pressure of accurate adjustment closed air chamber; Gaseous tension acts on to airborne sensor 12 and standard transducer 9 simultaneously; The a3 end and b3 end that connect second reversing switch 17 earlier; With the pressure of standard pressure transducer 9 detected gas, and indicate pressure signal with digital indicator 11, break off the a3 end and b3 end of second reversing switch 17 then; The a2 end and c2 end that connect the 3rd reversing switch 18; The pressure signal of airborne sensor inputs to digital indicator 11 and indicates, and twice indicated value of digital indicator 11 compares, thereby obtains the accuracy of airborne sensor and the judgement of performance.
(2) the airborne torque system indicating gauge 13 of verification
The a3 end of second reversing switch 17 is connected with the c3 end; The signal of standard transducer 9 is inputed to airborne torque system indicating gauge 13; Read the reading of the airborne torque system indicating gauge 13 of this moment, break off the a3 end and c3 end of second reversing switch 17 then, connect the a3 end and c3 end of second reversing switch 17; Give digital indicator 11 with the input signal of standard transducer 9, read the reading of the digital indicator 11 of this moment.Twice reading compared, thereby obtains the accuracy of airborne torque system indicating gauge 13 and the judgement of performance.
In the present embodiment; Air filter 1, first retaining valve 2, pitcher pump 3, second retaining valve 4, stop valve 5, vent valve 6, pressure micro actuator 7, standard pressure transducer 9, the first excitation direct supply 10, excitation AC power 15, first reversing switch 16, second reversing switch 17, the 3rd reversing switch 18 and digital indicator 11 all adopt finished parts, and the measuring accuracy of system can reach ± and 0.05%.
Claims (1)
1. helicopter engine torque system calibration equipment; Form by a pneumatic supply, a standard pressure transducer (9), the first excitation direct supply (10), the second excitation direct supply (14), excitation AC power (15), first reversing switch (16), second reversing switch (17), the 3rd reversing switch (18) and digital indicator (11), it is characterized in that:
Pneumatic supply is made up of air filter (1), first retaining valve (2), pitcher pump (3), second retaining valve (4), stop valve (5), vent valve (6), pressure micro actuator (7) and threeway (8); The output terminal of air filter (1) is communicated with the input end of first retaining valve (2) through pipeline; The output terminal of first retaining valve (2) is communicated with the input end of pitcher pump (3) through pipeline; The output terminal of pitcher pump (3) is communicated with the input end of second retaining valve (4) through pipeline; The output terminal of second retaining valve (4) is communicated with an end of stop valve (5) through pipeline; The other end of stop valve (5) is communicated with an end of vent valve (6) through pipeline; Vent valve (6) other end is communicated with an end of pressure micro actuator (7) through pipeline; The other end of pressure micro actuator (7) is communicated with the first port 8a of threeway (8) through pipeline, and the second port 8b of threeway (8) is communicated with the pressure input port of standard pressure transducer (9) through pipeline, and the 3rd port 8c of threeway (8) is communicated with the pressure input port of helicopter engine torque sensor (12) through pipeline;
The signal output part of standard pressure transducer (9) is connected with the a3 end of second reversing switch (17); The b3 end of second reversing switch (17) is connected with the signal input part of digital indicator (11); The c3 end of second reversing switch (17) is connected with the signal input part of airborne torque system indicating gauge (13), and the output terminal of excitation power supply 10 is connected with the power input of standard pressure transducer (9);
The second excitation direct supply (14) is connected with the a1 end of first reversing switch (16); The b1 end of first reversing switch (16) is connected with the output terminal of excitation AC power (15), and the c1 end of first reversing switch (16) is connected with the power input of on-board torque sensors (12); The a2 end of the 3rd reversing switch (18) is connected with the signal output part of on-board torque sensors (12), and the b2 end of the 3rd reversing switch (18) is connected with the signal input part of airborne torque system indicating gauge (13); The c2 end of the 3rd reversing switch (18) is connected with the signal input part of digital indicator (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200024233U CN202485859U (en) | 2012-01-05 | 2012-01-05 | Device for checking helicopter engine torque system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200024233U CN202485859U (en) | 2012-01-05 | 2012-01-05 | Device for checking helicopter engine torque system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202485859U true CN202485859U (en) | 2012-10-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012200024233U Expired - Fee Related CN202485859U (en) | 2012-01-05 | 2012-01-05 | Device for checking helicopter engine torque system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202485859U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103575437A (en) * | 2013-11-06 | 2014-02-12 | 中国第一汽车股份有限公司 | Method for real-time monitoring of torque state of calibration platform |
-
2012
- 2012-01-05 CN CN2012200024233U patent/CN202485859U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103575437A (en) * | 2013-11-06 | 2014-02-12 | 中国第一汽车股份有限公司 | Method for real-time monitoring of torque state of calibration platform |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20121010 Termination date: 20190105 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |