CN201636133U - Helicopter hydraulic system debugging device - Google Patents
Helicopter hydraulic system debugging device Download PDFInfo
- Publication number
- CN201636133U CN201636133U CN2010201744514U CN201020174451U CN201636133U CN 201636133 U CN201636133 U CN 201636133U CN 2010201744514 U CN2010201744514 U CN 2010201744514U CN 201020174451 U CN201020174451 U CN 201020174451U CN 201636133 U CN201636133 U CN 201636133U
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- oil
- hydraulic system
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- air
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Abstract
The utility model discloses a helicopter hydraulic system debugging device, which relates to a hydraulic system and aims to provide a helicopter hydraulic system debugging device which is free from using the hydraulic power unit of an aircraft when in test. The key point of the technical solution of the utility model is that a power-driven three-way valve, a centrifugal pump, an oil filter, a pressure gage and a second switch are arranged on an oil supply line between an oil outlet of an oil tank and an oil inlet of the aircraft hydraulic system in sequence; an outlet oil line is provided with a solenoid directional valve, a digital temperature gauge, an air-cooling radiator and a switch; the outlet oil line between the solenoid directional valve and the air-cooling radiator is provided with a first bypass oil line connected with the third outlet of the power-driven three-way valve; the oil supply line between the outlet oil line between the air-cooling radiator and the switch, and the oil filter and the second switch is provided with a second bypass oil line, the oil outlet of a proportional relief valve on the second bypass oil line is connected with the outlet oil line, and the oil inlet of the proportional relief valve is connected with the oil supply line. The utility model is applied to the test of the aircraft hydraulic system.
Description
Technical field:
The utility model relates to a kind of hydraulic system, particularly a kind of helicopter hydraulic system commissioning device.
Background technique:
Reliability in order to ensure plane hydraulic system, during the aircraft grounding its hydraulic system is detected, present detection is to utilize the hydraulic power unit on the aircraft to drive the skyborne action of whole driver element simulated aircraft, detect debugging, because the time of this inspection debugging, generally than long 5-10 of the time of aircraft flight doubly this detection made the lost of life of the hydraulic power unit on the aircraft a lot.
Summary of the invention:
The purpose of this utility model provides a kind of helicopter hydraulic system commissioning device that does not use the hydraulic power unit on the aircraft to detect.Technical solution of the present utility model is, comprise fuel tank, fuel feeding road and oil circuit, it is characterized in that: on the oil outlet of fuel tank and the fuel feeding road between the plane hydraulic system filler opening, be provided with electric T-shaped valve successively, centrifugal pump, the oil filter, pressure gauge, second switch, on the oil circuit between the oil outlet of the return opening of fuel tank and plane hydraulic system, be provided with solenoid directional control valve successively, digital thermometer, air-cooled radiator and switch, being provided with on one side the road binders road on the oil circuit between solenoid directional control valve and the air-cooled radiator exports with electric T-shaped valve the 3rd and is connected, on the fuel feeding road between the oil circuit between air-cooled radiator and the switch and oil filter and the second switch, be provided with two bypass oil circuits, the oil outlet of the proportional pressure control valve on this two bypasses oil circuit is connected with oil circuit, and the filler opening of proportional pressure control valve is connected with the fuel feeding road.The utility model has the advantage that the hydraulic power unit on the aircraft does not participate in ground detection thereby prolonged the working life of motor compared with the prior art.
Description of drawings:
Accompanying drawing is the utility model helicopter hydraulic debugging device systems figure.
Embodiment:
In conjunction with above accompanying drawing the utility model is elaborated, on the oil circuit between the oil outlet of the return opening of fuel tank 13 and helicopter hydraulic system, be connected in series solenoid directional control valve 1 successively, air-cooled radiator 3, switch 6, on the fuel feeding road between the filler opening of the oil outlet of fuel tank 1 and helicopter hydraulic system, be connected in series electric T-shaped valve 12 successively, centrifugal pump 11, one-level oil filter 10, filter 9 of secondary oil and second switch 7, on the oil circuit between solenoid directional control valve 1 and the air-cooled radiator 3, be provided with the road binders road, one side that is communicated with another outlet of electric T-shaped valve 12, between solenoid directional control valve 1 and air-cooled radiator 3, be provided with digital thermometer 2, between oily filter 9 of the secondary on fuel feeding road and second switch 7, be provided with two bypass oil circuits, the other end of this two bypasses oil circuit and above-mentioned air-cooled radiator 3 are communicated with oil circuit between the switch 6, be connected to proportional pressure control valve 5 on this two bypasses oil circuit, be provided with pressure gauge 4 on the oil circuit between air-cooled radiator 3 and the switch 6, pressure gauge 8 is located on the oil feeding line between fuel feeding road secondary oil screen 9 and the second switch 7.
Working principle of the present utility model is, 1, self-circulation purifying fluid, when needs detect helicopter hydraulic system, should clean the oil in the fuel tank 13 earlier, close the second switch 7 on switch on the oil circuit 6 and the fuel feeding road this moment, start centrifugal pump 11, the oil in the fuel tank from oil outlet through electric T-shaped valve 12, centrifugal pump 11, one-level oil filter 10, secondary oil filter 9, proportional pressure control valve 5, air-cooled radiator 3 and solenoid directional control valve 1 back into fuel tank; 2, plane hydraulic system is debugged, after repeatedly circulation makes oil in the fuel tank reach standard-required, can detect helicopter hydraulic system, should open switch 6,7 this moment, oil in the fuel tank enters helicopter hydraulic system after the air-cooled radiator 3 on the oil circuit, solenoid directional control valve are gone into fuel tank 1 time from vent line, can every requirement of helicopter hydraulic system be detected,, can start air-cooled radiator 3 and lower the temperature because the testing process hydraulic fluid temperature can raise; 3, to the aircraft repairing, when helicopter hydraulic system is detected when finding the shortage of oil in the hydraulic system, should carry out repairing earlier, open second switch 7, simultaneously solenoid directional control valve on the oil circuit 1 and fuel tank are cut off, start centrifugal pump, the oil in the fuel tank enters helicopter hydraulic system and refuels through electric T-shaped valve 12, centrifugal pump 11, oil filter 10,9, second switch 7.Can close centrifugal pump after oil mass is suitable.Said detecting system can place to be convenient in the car move.
Claims (1)
1. helicopter hydraulic system commissioning device, comprise fuel tank, fuel feeding road and oil circuit, it is characterized in that: on the oil outlet of fuel tank and the fuel feeding road between the plane hydraulic system filler opening, be provided with electric T-shaped valve successively, centrifugal pump, the oil filter, pressure gauge, second switch, on the oil circuit between the oil outlet of the return opening of fuel tank and plane hydraulic system, be provided with solenoid directional control valve successively, digital thermometer, air-cooled radiator and switch, being provided with on one side the road binders road on the oil circuit between solenoid directional control valve and the air-cooled radiator exports with electric T-shaped valve the 3rd and is connected, on the fuel feeding road between the oil circuit between air-cooled radiator and the switch and oil filter and the second switch, be provided with two bypass oil circuits, the oil outlet of the proportional pressure control valve on this two bypasses oil circuit is connected with oil circuit, and the filler opening of proportional pressure control valve is connected with the fuel feeding road.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201744514U CN201636133U (en) | 2010-04-20 | 2010-04-20 | Helicopter hydraulic system debugging device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201744514U CN201636133U (en) | 2010-04-20 | 2010-04-20 | Helicopter hydraulic system debugging device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201636133U true CN201636133U (en) | 2010-11-17 |
Family
ID=43080624
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201744514U Expired - Fee Related CN201636133U (en) | 2010-04-20 | 2010-04-20 | Helicopter hydraulic system debugging device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201636133U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103644170A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Hydraulic low-pressure pulse experiment method of aircraft |
| CN113757200A (en) * | 2021-08-31 | 2021-12-07 | 三一汽车制造有限公司 | Hydraulic system, engineering machinery and control method thereof |
-
2010
- 2010-04-20 CN CN2010201744514U patent/CN201636133U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103644170A (en) * | 2013-11-28 | 2014-03-19 | 江西洪都航空工业集团有限责任公司 | Hydraulic low-pressure pulse experiment method of aircraft |
| CN103644170B (en) * | 2013-11-28 | 2016-05-11 | 江西洪都航空工业集团有限责任公司 | A kind of test method of airplane hydraulic pressure action of low-voltage pulse |
| CN113757200A (en) * | 2021-08-31 | 2021-12-07 | 三一汽车制造有限公司 | Hydraulic system, engineering machinery and control method thereof |
| CN113757200B (en) * | 2021-08-31 | 2023-05-12 | 三一汽车制造有限公司 | Hydraulic system, engineering machinery and control method of hydraulic system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20101117 Termination date: 20130420 |