CN102192215A - Test system of airplane hydraulic power conversion device - Google Patents
Test system of airplane hydraulic power conversion device Download PDFInfo
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- CN102192215A CN102192215A CN2010101272541A CN201010127254A CN102192215A CN 102192215 A CN102192215 A CN 102192215A CN 2010101272541 A CN2010101272541 A CN 2010101272541A CN 201010127254 A CN201010127254 A CN 201010127254A CN 102192215 A CN102192215 A CN 102192215A
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Abstract
The invention discloses a test system of an airplane hydraulic power conversion device. The test system is provided with a high-pressure oil-supplying pipeline, a high-pressure oil return pipeline and two high-pressure oil-supplying systems, wherein the two high-pressure oil-supplying systems are used for simulating oil supplying respectively and individually for a hydraulic motor and a hydraulic pump in a PTU (parallel transmission unit) under the actual working environment; the test system is mainly characterized in that an oil supplying line is provided with four pressure regulating valves, namely a pressure regulating valve C, a pressure regulating valve D, a pressure regulating valve E and a pressure regulating valve F, and the functions of the pressure regulating valves are that not only can the pressure of the oil supplying line be regulated, but also the pressure regulating valves are used for selecting the oil supplying directions; the test system is also provided with a shell oil return pipeline connected with the PTU; and the shell oil return pipeline is connected in series with a shell oil return pressure gauge, a shell oil return flowmeter, a shell oil return filter and a pressure regulating valve for shell oil return. Because the test system simulates the working environment of the PTU in an all-around mode, the PTU can be subjected to performance index detection conveniently, and the detection efficiency and detection accuracy are also improved.
Description
Technical field
The present invention relates to a kind of Performance Test System of air equipment, specifically is a kind of test system of aircraft hydraulic power conversion equipment.The test system of hydraulic power conversion equipment.Design of the present invention can make things convenient for comprehensively the hydraulic power conversion equipment is carried out the test of every performance index.
Background technique
The wing flap of aircraft belongs to liter, and the resistance system is that aircraft improves lift in order to take off.Be divided into droope snoot, three parts of trailing edge flap and leading edge slat.Under normal circumstances, leading edge portion is to be handled and definite its position by the valve that trailing edge flap drives with running wire, is handled by the valve on the spare package under the spare condition.The power-converting assembly of aircraft hydraulic pressure is called for short PTU (POWER TRANSFER UNIT), and its effect is to provide hydraulic pressure to the droope snoot of aircraft and slat.Power-converting assembly (PTU) is made up of coaxial oil hydraulic motor and oil hydraulic pump, oil hydraulic motor is by the pressure of PTU control valve acceptance from hydraulic system A, oil hydraulic motor is rotated, oil hydraulic pump is accepted to provide standby pressure from the fuel feeding of hydraulic system B fuel tank and to droope snoot and slat, oil hydraulic motor uses the A system pressure to drive the oil hydraulic pump of B system fuel feeding, when the B of system engine-driving pumping pressure was lower than normal value, PTU pressure can be used for normal running or slat operation automatically.The effect of the housing oil return in oil hydraulic motor and the oil hydraulic pump is cooling and Lubricants pressure motor and oil hydraulic pump.The operating conditions of PTU: 1, aircraft aloft; 2, wing flap is not received and less than 15 units; 3, if B system engine driven pump low pressure is lower than 2350psi and delayed time 0.5 second.
The hydraulic power conversion equipment is a power unit important on the aircarrier aircraft, and the quality of this component capabilities directly has influence on flight safety.So the test to parts is most important.At present, domestic power switching device PTU test bench commonly used, simple structure, function singleness can only be tested the simple PTU of section construction, but then can't meet the demands for the test of baroque Air Passenger aircraft and other types PTU.Such as the PTU that pressure reduction control valve is arranged, require to detect the forward and reverse performance index under system's pressure reduction changes.Aircarrier aircraft changes down the fault part and all is sent to external repairing, the expense costliness, and the cycle is very long, to very inconvenience of user.
Summary of the invention
In order to overcome above-mentioned deficiency, the object of the invention is to provide a kind of working environment of simulated aircraft hydraulic power conversion equipment, can not only be easily carry out index and detect, but also make the efficient of detection and the accurate test system of very high aircraft hydraulic power conversion equipment every performance of PTU.
To achieve these goals, the technical solution used in the present invention is: the test system of aircraft hydraulic power conversion equipment, include motor, oil feed pump, fuel tank, oil pressure gauge, flowmeter, pressure regulator valve A, pressure regulator valve B, hydraulic oil constitutes a fuel oil injection piping through oil pressure gauge, flowmeter, pressure regulator valve A again through the oil feed pump of driven by motor in the fuel tank; After two pipeline parallel connections that the oil drain out of the oil hydraulic motor assembly of aircraft hydraulic power conversion equipment and oil hydraulic pump assembly is connected, be connected with fuel tank after being connected in series pressure regulator valve B again.It is characterized in that: this test system also is provided with pressure regulator valve C, pressure regulator valve D, pressure regulator valve E, pressure regulator valve F, pressure regulator valve C, pressure regulator valve D, pressure regulator valve E, pressure regulator valve F is concatenated into a closing pipe line by hydraulic tube, the port of described fuel oil injection piping is connected on the pipeline between pressure regulator valve C and the pressure regulator valve D, pipeline between pressure regulator valve C and the pressure regulator valve E is provided with the oil circuit interface that is connected with the oil hydraulic motor assembly of aircraft hydraulic power conversion equipment, and the pipeline between pressure regulator valve D and the pressure regulator valve F is provided with the oil circuit interface that is connected with the oil hydraulic pump assembly of aircraft hydraulic power conversion equipment; This test system also is provided with oil filter B, return line flowmeter, selector valve, flow-limiting valve B, radiator, hydraulic oil is filtered B, return line flowmeter, selector valve, flow-limiting valve B, radiator through oil and is formed a high pressure oil return line to fuel tank, and the port of high pressure oil return line is connected on the pipeline between pressure regulator valve E and the pressure regulator valve F.
Pipeline between the oil drain out of the oil hydraulic motor assembly of described aircraft hydraulic power conversion equipment and the inlet port of oil hydraulic pump assembly is provided with oil filter A.
Be parallel with flow-limiting valve A on the described pressure regulator valve A.Flow-limiting valve A is identical with the effect of flow-limiting valve B, all is the pressure reduction that is used for controlling power-converting assembly (PTU) oil hydraulic motor and oil hydraulic pump, and carries out Performance Detection under the pressure reduction situation of change.
Described fuel tank is provided with the supercharging air valve.The effect of supercharging air valve is: make the fluid foaming in the fuel tank reduce to minimum, prevent vacuum or superpressure damage fuel tank, improve the operating conditions of oil hydraulic pump, prevent vent plug.
Also be provided with thermocouple on the described fuel tank in order to monitoring fuel tank temperature.The effect of thermocouple is: monitoring fuel tank temperature prevents that the fuel tank temperature is too high, when the too high then power-off protection of temperature.
Be provided with relief valve with the high pressure oil return line on the described fuel oil injection piping.Described relief valve comes down to a safety valve, and when oil pressure was too high, high pressure oil was discharged from relief valve, plays the effect of release, thereby the components and parts in pipeline and the pipeline play the certain protection effect.
Also be provided with accumulator on the described high pressure oil return line, described accumulator is connected on the high pressure oil return line by pressure regulator valve G.
Described test system also is provided with two housing return lines that are connected with the oil hydraulic pump assembly with the oil hydraulic motor assembly of aircraft hydraulic power conversion equipment, is serially connected with the pressure regulator valve of housing return pressure table, housing oil return flowmeter, housing oil return filter and housing oil return on the described housing return line.The effect of housing oil return filter: the one, the impurity in the fluid is removed in the housing oil return before the fuel tank; The 2nd, be used for the housing abrasive dust and detect, thus the good condition of inspection oil hydraulic motor assembly and oil hydraulic pump assembly.
The described pipeline port that is connected with aircraft hydraulic power conversion equipment is provided with the hydraulic fluid pressure table.
Also be provided with oil filter C in the described fuel oil injection piping, the effect of oil filter C is high-voltage oil liquid is transported to the impurity of removing before the PTU in the fluid.
Beneficial effect of the present invention: since this test system full-scope simulation the working environment of aircraft hydraulic power conversion equipment, can not only be easily carry out index and detect, but also improve detection efficiency and detect accurately every performance of PTU; The user need not spend the expensive external repairing of sending again, and maintaining unit will be with lower maintenance cost, and better quality and shorter cycle provide service for the user.
Description of drawings
The present invention is described in further detail below in conjunction with accompanying drawing.
Fig. 1 is a structural representation of the present invention.
Among the figure: 1. motor; 2. oil feed pump; 3. fuel tank; 4. oil pressure gauge; 5. flowmeter; 6. pressure regulator valve A; 7. pressure regulator valve B; 8. aircraft hydraulic power conversion equipment; 9. oil hydraulic motor assembly; 10. oil hydraulic pump assembly; 11. oil filter C; 12. pressure regulator valve C; 13. pressure regulator valve D; 14. pressure regulator valve E; 15. pressure regulator valve F; 16. fuel oil injection piping; 17. oil filter B; 18. selector valve; 19. flow-limiting valve B; 20. radiator; 21. high pressure oil return line; 22. oil filter A; 23. flow-limiting valve A; 24. supercharging air valve; 25. thermocouple; 26. relief valve; 27. accumulator; 28. pressure regulator valve G; 29. housing return line; 30. housing return pressure table; 31. housing oil return flowmeter; 32. housing oil return filter; 33. the pressure regulator valve of housing oil return; 34. hydraulic fluid pressure table; 35. return line flowmeter.
Embodiment
As shown in Figure 1, the test system of aircraft hydraulic power conversion equipment, include motor 1, oil feed pump 2, fuel tank 3, oil pressure gauge 4, flowmeter 5, pressure regulator valve A 6, pressure regulator valve B 7, hydraulic oil constitutes a fuel oil injection piping 16 through oil pressure gauge 4, flowmeter 5, pressure regulator valve A6 again through the oil feed pump 2 that motor 1 drives in the fuel tank 3; After two pipeline parallel connections that the oil drain out of the oil hydraulic motor assembly 9 of aircraft hydraulic power conversion equipment 8 and oil hydraulic pump assembly 10 is connected, be connected in series pressure regulator valve B 7 backs again and be connected with fuel tank 3.It is characterized in that: this test system also is provided with pressure regulator valve C12, pressure regulator valve D13, pressure regulator valve E14, pressure regulator valve F15, pressure regulator valve C12, pressure regulator valve D13, pressure regulator valve E14, pressure regulator valve F15 is concatenated into a closing pipe line by hydraulic tube, the port of described fuel oil injection piping 16 is connected on the pipeline between pressure regulator valve C12 and the pressure regulator valve D13, pipeline between pressure regulator valve C12 and the pressure regulator valve E14 is provided with the oil circuit interface that is connected with the oil hydraulic motor assembly 9 of aircraft hydraulic power conversion equipment 8, and the pipeline between pressure regulator valve D13 and the pressure regulator valve F15 is provided with the oil circuit interface that is connected with the oil hydraulic pump assembly 10 of aircraft hydraulic power conversion equipment; This test system also is provided with oil filter B17, return line flowmeter 35, selector valve 18, flow-limiting valve B19, radiator 20, hydraulic oil is filtered B17, return line flowmeter 35, selector valve 18, flow-limiting valve B19, radiator 20 through oil and is formed a high pressure oil return line 21 to fuel tank 3, and the port of high pressure oil return line 21 is connected on the pipeline between pressure regulator valve E14 and the pressure regulator valve F15.
Pipeline between the oil drain out of the oil hydraulic motor assembly 9 of described aircraft hydraulic power conversion equipment 8 and the inlet port of oil hydraulic pump assembly 10 is provided with oil filter A22.
Be parallel with flow-limiting valve A23 on the described pressure regulator valve A6.
Described fuel tank 3 is provided with supercharging air valve 24.
Also be provided with thermocouple 25 on the described fuel tank 3 in order to monitoring fuel tank temperature.
Be provided with relief valve 26 with high pressure oil return line 21 on the described fuel oil injection piping 16.
Also be provided with accumulator 27 on the described high pressure oil return line 21, described accumulator 27 is connected on the high pressure oil return line 21 by pressure regulator valve G28.
Described test system also is provided with two housing return lines 29 that are connected with oil hydraulic pump assembly 10 with the oil hydraulic motor assembly 9 of aircraft hydraulic power conversion equipment 8, is serially connected with the pressure regulator valve 33 of housing return pressure table 30, housing oil return flowmeter 31, housing oil return filter 32 and housing oil return on the described housing return line 29.
The described pipeline port that is connected with aircraft hydraulic power conversion equipment 8 is provided with hydraulic fluid pressure table 34.
Also be provided with oil filter C11 in the described fuel oil injection piping 16.
Working principle: established fuel oil injection piping and high pressure oil return line in the test system of aircraft hydraulic power conversion equipment, be used for simulating under the actual working environment and be the oil hydraulic motor of PTU and oil hydraulic pump two high-pressure fuel supply systems of independent fuel feeding respectively; This test system main feature is: having designed four pressure regulator valves on the fuel feeding road is pressure regulator valve C 12, pressure regulator valve D 13, pressure regulator valve E 14, pressure regulator valve F 15, its effect not only can be regulated fuel feeding road pressure, but also is used to select the fuel feeding direction.When carrying out the forward detection, pressure regulator valve C 12 and pressure regulator valve F 15 open, pressure regulator valve D 13 and pressure regulator valve E 14 close, high pressure oil in the fuel oil injection piping is behind pressure regulator valve A6, advance in the oil hydraulic motor assembly 9 of PTU through pressure regulator valve C 12 again, because oil hydraulic motor assembly 9 and oil hydraulic pump assembly 10 are coaxial, high pressure oil drives oil hydraulic motor assembly 9, oil hydraulic motor assembly 9 drives oil hydraulic pump assembly 10 and begins rotation, and the hydraulic oil part that oil hydraulic motor assembly 9 is discharged flows back to fuel tank 3 through one-way valve, pressure regulator valve B7; Another part of hydraulic oil, after oil filter A22 filters, become high pressure oil by 10 suctions of oil hydraulic pump assembly, enter in the high pressure oil return line 21 through pressure regulator valve F15 again, flow into fuel tanks 3 through oil filter B17, return line flowmeter 35, selector valve 18, flow-limiting valve B19, radiator 20.
Otherwise, when PTU being carried out the counterrotating test, pressure regulator valve C 12 and pressure regulator valve F 15 close, pressure regulator valve D 13 and pressure regulator valve E 14 open, high pressure oil in the fuel oil injection piping is behind pressure regulator valve A6, advance in the oil hydraulic pump assembly 10 of PTU through pressure regulator valve D 13 again, because oil hydraulic motor assembly 9 and oil hydraulic pump assembly 10 are coaxial, high pressure oil drives oil hydraulic pump assembly 10, oil hydraulic pump assembly 10 drives oil hydraulic motor assembly 9 and begins rotation, and the hydraulic oil part that oil hydraulic pump assembly 10 is discharged is through one-way valve, pressure regulator valve B7 flows back to fuel tank 3; Another part of hydraulic oil, after oil filter A22 filters, become high pressure oil by 9 suctions of oil hydraulic motor assembly, enter in the high pressure oil return line 21 through pressure regulator valve E14 again, flow into fuel tanks 3 through oil filter B17, return line flowmeter 35, selector valve 18, flow-limiting valve B19, radiator 20.
Oil hydraulic motor among the PTU and oil hydraulic pump variable assembly are connected to housing return line 29 respectively, the pressure regulator valve 33 of housing return pressure table 30, housing oil return flowmeter 31, housing oil return filter 32 and the housing oil return of housing oil return in housing return line 29 flows back to fuel tank 3.
In addition, on oil hydraulic motor assembly oil drain out and pipeline that oil hydraulic pump assembly inlet port is connected, four one-way valves have been designed, when the oil of oil hydraulic motor assembly oil drain out flows out, this oil liquid pressure is about 70PSI, through one-way valve, oil filter A22, enter oil hydraulic pump assembly inlet port through one-way valve again, although the pipeline that is connected with oil hydraulic pump assembly inlet port with oil hydraulic motor assembly oil drain out has two, but have only one must filter oily inhalant liquid press pump assembly in the pipeline of A22, so increased the oil absorption of oil hydraulic pump assembly through oil.
Claims (10)
1. the test system of an aircraft hydraulic power conversion equipment, include motor (1), oil feed pump (2), fuel tank (3), oil pressure gauge (4), flowmeter (5), pressure regulator valve A (6), pressure regulator valve B (7), the interior hydraulic oil of fuel tank (3) constitutes a fuel oil injection piping (16) through oil pressure gauge (4), flowmeter (5), pressure regulator valve A (6) again through the oil feed pump (2) that motor (1) drives; After two pipeline parallel connections that the oil drain out of the oil hydraulic motor assembly (9) of aircraft hydraulic power conversion equipment (8) and oil hydraulic pump assembly (10) is connected, be connected in series pressure regulator valve B (7) back again and be connected with fuel tank (3).It is characterized in that: this test system also is provided with pressure regulator valve C (12), pressure regulator valve D (13), pressure regulator valve E (14), pressure regulator valve F (15), pressure regulator valve C (12), pressure regulator valve D (13), pressure regulator valve E (14), pressure regulator valve F (15) is concatenated into a closing pipe line by hydraulic tube, the port of described fuel oil injection piping (16) is connected on the pipeline between pressure regulator valve C (12) and the pressure regulator valve D (13), pipeline between pressure regulator valve C (12) and the pressure regulator valve E (14) is provided with the oil circuit interface that is connected with the oil hydraulic motor assembly (9) of aircraft hydraulic power conversion equipment (8), and the pipeline between pressure regulator valve D (13) and the pressure regulator valve F (15) is provided with the oil circuit interface that is connected with the oil hydraulic pump assembly (10) of aircraft hydraulic power conversion equipment; This test system also is provided with oil filter B (17), return line flowmeter (35), selector valve (18), flow-limiting valve B (19), radiator (20), hydraulic oil is filtered B (17), return line flowmeter (35), selector valve (18), flow-limiting valve B (19), radiator (20) through oil and is formed a high pressure oil return line (21) to fuel tank (3), and the port of high pressure oil return line (21) is connected on the pipeline between pressure regulator valve E (14) and the pressure regulator valve F (15).
2. the test system of aircraft hydraulic power conversion equipment according to claim 1 is characterized in that: the pipeline between the oil drain out of the oil hydraulic motor assembly (9) of described aircraft hydraulic power conversion equipment (8) and the inlet port of oil hydraulic pump assembly (10) is provided with oil filter A (22).
3. the test system of aircraft hydraulic power conversion equipment according to claim 1 is characterized in that: be parallel with flow-limiting valve A (23) on the described pressure regulator valve A (6).
4. the test system of aircraft hydraulic power conversion equipment according to claim 1 is characterized in that: described fuel tank (3) is provided with supercharging air valve (24).
5. the test system of aircraft hydraulic power conversion equipment according to claim 1, it is characterized in that: also be provided with accumulator (27) on the described high pressure oil return line (21), described accumulator (27) is connected on the high pressure oil return line (21) by pressure regulator valve G (28).
6. the test system of aircraft hydraulic power conversion equipment according to claim 1 is characterized in that: described fuel oil injection piping (16) is gone up and high pressure oil return line (21) is provided with relief valve (26).
7. the test system of aircraft hydraulic power conversion equipment according to claim 1 is characterized in that: also be provided with the thermocouple (25) in order to monitoring fuel tank temperature on the described fuel tank (3).
8. the test system of aircraft hydraulic power conversion equipment according to claim 1, it is characterized in that: described test system also is provided with two housing return lines (29) that are connected with oil hydraulic pump assembly (10) with the oil hydraulic motor assembly (9) of aircraft hydraulic power conversion equipment (8), is serially connected with the pressure regulator valve (33) of housing return pressure table (30), housing oil return flowmeter (31), housing oil return filter (32) and housing oil return on the described housing return line (29).
9. the test system of aircraft hydraulic power conversion equipment according to claim 1 is characterized in that: the described pipeline port that is connected with aircraft hydraulic power conversion equipment (8) is provided with hydraulic fluid pressure table (34).
10. the test system of aircraft hydraulic power conversion equipment according to claim 1 is characterized in that: also be provided with oil filter C (11) in the described fuel oil injection piping (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101272541A CN102192215A (en) | 2010-03-18 | 2010-03-18 | Test system of airplane hydraulic power conversion device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101272541A CN102192215A (en) | 2010-03-18 | 2010-03-18 | Test system of airplane hydraulic power conversion device |
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| CN102192215A true CN102192215A (en) | 2011-09-21 |
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| CN2010101272541A Pending CN102192215A (en) | 2010-03-18 | 2010-03-18 | Test system of airplane hydraulic power conversion device |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103742484A (en) * | 2014-01-06 | 2014-04-23 | 索特传动设备有限公司 | Motor decelerator test system |
| CN107607308A (en) * | 2017-10-23 | 2018-01-19 | 何木栋 | The hydraulic pressure energy supply test device of multichannel pressure-adjusting type brake system of car |
| CN107620749A (en) * | 2017-10-23 | 2018-01-23 | 何木栋 | Hydraulic pressure energy supply test device with housing return line |
| CN107620751A (en) * | 2017-10-23 | 2018-01-23 | 何木栋 | Multifunction hydraulic energizes test device |
| CN107620750A (en) * | 2017-10-23 | 2018-01-23 | 何木栋 | Hydraulic pressure energy supply test device with supercharging air valve |
| CN107630846A (en) * | 2017-10-23 | 2018-01-26 | 何木栋 | Bivalve parallel hydraulic energizes test device |
| CN107630867A (en) * | 2017-10-23 | 2018-01-26 | 何木栋 | Hydraulic pressure energy supply test device with radiator |
| CN107630866A (en) * | 2017-10-23 | 2018-01-26 | 何木栋 | Hydraulic pressure energy supply test device with temperature sensor |
| CN107630865A (en) * | 2017-10-23 | 2018-01-26 | 何木栋 | The hydraulic pressure energy supply test device of brake system of car |
| CN107676337A (en) * | 2017-10-23 | 2018-02-09 | 何木栋 | Hydraulic pressure energy supply test device with oil filter |
| CN107676335A (en) * | 2017-10-23 | 2018-02-09 | 何木栋 | Remove the hydraulic pressure energy supply test device of impurity in fluid |
| CN107677489A (en) * | 2017-10-23 | 2018-02-09 | 何木栋 | Hydraulic pressure energy supply test device with accumulator |
| CN107677462A (en) * | 2017-10-23 | 2018-02-09 | 何木栋 | Double-hydraulic tabular form hydraulic pressure energizes test device |
| CN107676336A (en) * | 2017-10-23 | 2018-02-09 | 何木栋 | Hydraulic pressure energy supply test device with overflow valve |
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| CN201705756U (en) * | 2010-03-18 | 2011-01-12 | 上海航新航宇机械技术有限公司 | Testing system of airplane hydraulic power conversion device |
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| JPS59175602A (en) * | 1983-03-25 | 1984-10-04 | Maruma Jusharyo Kk | Oil tank of tester for hydraulic apparatus |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103742484A (en) * | 2014-01-06 | 2014-04-23 | 索特传动设备有限公司 | Motor decelerator test system |
| CN107607308A (en) * | 2017-10-23 | 2018-01-19 | 何木栋 | The hydraulic pressure energy supply test device of multichannel pressure-adjusting type brake system of car |
| CN107620749A (en) * | 2017-10-23 | 2018-01-23 | 何木栋 | Hydraulic pressure energy supply test device with housing return line |
| CN107620751A (en) * | 2017-10-23 | 2018-01-23 | 何木栋 | Multifunction hydraulic energizes test device |
| CN107620750A (en) * | 2017-10-23 | 2018-01-23 | 何木栋 | Hydraulic pressure energy supply test device with supercharging air valve |
| CN107630846A (en) * | 2017-10-23 | 2018-01-26 | 何木栋 | Bivalve parallel hydraulic energizes test device |
| CN107630867A (en) * | 2017-10-23 | 2018-01-26 | 何木栋 | Hydraulic pressure energy supply test device with radiator |
| CN107630866A (en) * | 2017-10-23 | 2018-01-26 | 何木栋 | Hydraulic pressure energy supply test device with temperature sensor |
| CN107630865A (en) * | 2017-10-23 | 2018-01-26 | 何木栋 | The hydraulic pressure energy supply test device of brake system of car |
| CN107676337A (en) * | 2017-10-23 | 2018-02-09 | 何木栋 | Hydraulic pressure energy supply test device with oil filter |
| CN107676335A (en) * | 2017-10-23 | 2018-02-09 | 何木栋 | Remove the hydraulic pressure energy supply test device of impurity in fluid |
| CN107677489A (en) * | 2017-10-23 | 2018-02-09 | 何木栋 | Hydraulic pressure energy supply test device with accumulator |
| CN107677462A (en) * | 2017-10-23 | 2018-02-09 | 何木栋 | Double-hydraulic tabular form hydraulic pressure energizes test device |
| CN107676336A (en) * | 2017-10-23 | 2018-02-09 | 何木栋 | Hydraulic pressure energy supply test device with overflow valve |
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Application publication date: 20110921 |