CN202187977U - Performance test system for large-scale hydraulic component of airplane - Google Patents
Performance test system for large-scale hydraulic component of airplane Download PDFInfo
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- CN202187977U CN202187977U CN2011202319530U CN201120231953U CN202187977U CN 202187977 U CN202187977 U CN 202187977U CN 2011202319530 U CN2011202319530 U CN 2011202319530U CN 201120231953 U CN201120231953 U CN 201120231953U CN 202187977 U CN202187977 U CN 202187977U
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- 238000011056 performance test Methods 0.000 title claims abstract description 16
- 238000012360 testing method Methods 0.000 claims abstract description 86
- 238000005259 measurement Methods 0.000 claims abstract description 5
- 239000002828 fuel tank Substances 0.000 claims description 10
- 239000012530 fluid Substances 0.000 claims description 8
- 239000000945 filler Substances 0.000 claims description 7
- 239000000446 fuel Substances 0.000 claims description 7
- 230000008676 import Effects 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
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Abstract
The utility model discloses a performance test system of large-scale hydraulic component of aircraft, which belongs to the field of hydraulic motor test, and comprises a mounting seat provided with a test piece hydraulic motor or a coaxial test piece hydraulic pump, a hydraulic system supplied with oil by an oil tank and an oil pump motor set, and a dynamometer loaded with a gearbox and connected to the test piece motor; the oil pump motor set is formed by combining an axial plunger pump and an asynchronous motor; the hydraulic system is provided with two sets of oil inlet joints and oil return joints which are respectively connected with the test piece hydraulic motor and the test piece hydraulic pump, and the hydraulic system further comprises a reversing switch for switching the oil inlet and oil return directions of the test piece. The utility model discloses hydraulic pump motor's selection and outfit the operational environment that has truly simulated aircraft hydraulic motor to the flexibility ratio is high, stability is good. A plurality of measurement and control devices in the system monitor the test condition in real time and reflect the test condition to a computer, so that the development of test work is facilitated.
Description
Technical field
The utility model relates to a kind of simulated testing system of aircraft hydraulic element, relates in particular to a kind of Performance Test System of aircraft large hydraulic element.
Background technique
PTU hydraulic transmission and oil hydraulic motor all are hydraulic element important in the aircarrier aircraft, in the maintenance of aircarrier aircraft, occupy critical role.The full name of PTU is a power switching device, is a coaxial oil hydraulic pump-motor sub-assembly, and when PTU control valve was opened, motor was accepted the pressure from hydraulic system A, makes revolution; Oil hydraulic pump is accepted from the fuel feeding of hydraulic system B fuel tank and to droope snoot and slat standby pressure to be provided; Housing oil return cooling is simultaneously also lubricated motor and oil hydraulic pump.The kinetic energy of PTU is to utilize a hydraulic system to recover the work of another hydraulic system, improves the reliability of hydraulic system.
Because the driving power of PTU hydraulic transmission and oil hydraulic motor is big; Hydraulic flow is big; Imitation specimen environment of operation aboard preferably often in design process, more mainly due to piping design branch road, the joint of existing product, be unfavorable for that big flow passes through; And, receive the influence that starts inrush current and can make line voltage rapid drawdown when starting, thereby influence electrical network and miscellaneous part because test specimen power is bigger; In addition, because the test request precision is high, some crucial element to be tested also needs external buying.
The model utility content
Goal of the invention: in order to overcome the deficiency that exists in the existing technology, the utility model provide a kind of rationally distributed, running is stable and the observing and controlling Performance Test System of aircraft large hydraulic element accurately.
Technological scheme: for realizing above-mentioned purpose; The Performance Test System of the aircraft large hydraulic element of the utility model; Comprise the working area that test specimen oil hydraulic motor or coaxial test specimen oil hydraulic pump are installed, it is characterized in that: this test system comprises by the hydraulic system of fuel tank, Oil pump electrical machinery group fuel feeding, is loaded with gearbox and is connected to the measurement of power equipment of test specimen motor; Said Oil pump electrical machinery group is combined by axial piston pump and asynchronous motor; Said hydraulic system is provided with two groups of fuel inlet fittings and is connected with the test specimen oil hydraulic pump with the test specimen oil hydraulic motor respectively with back leakage connection, and said hydraulic system also comprises the reverser that switches test specimen oil-feed oil return direction.
Wherein, Said axial piston pump is adjustable for manually, compares combined coupling, the pump support of having saved of axial piston pump and asynchronous motor with traditional oil pump-coupling-motor Placement; And do not need the installation base plate of bulk, axial length has shortened 1/3～1/4 approximately.Measurement of power equipment and gearbox have been realized tests such as the motor survey is turned round, motor loading.
Said asynchronous motor is equipped with the soft starting device that is used to realize reduced-voltage starting, is used for control because test specimen power is bigger, receives the influence that starts inrush current and can make line voltage rapid drawdown when starting, thereby influence electrical network and miscellaneous part.
Said reverser comprises first switch and the second switch that is parallel to test specimen oil hydraulic motor filler opening, and the 3rd switch and the 4th switch that are parallel to test specimen oil hydraulic pump return opening; Link to each other between said first switch and the 4th switch and be communicated with the fuel tank in-line, between said second switch and the 3rd switch continuous and with the tank drainback pipeline connection.
When first switch, the 3rd switch opens; When second switch, the three or four switch on; The work fluid that provides from the Oil pump electrical machinery group gets into the filler opening of test specimen oil hydraulic motor through first switch; From the oil outlet of test specimen oil hydraulic motor through one-way valve combination oil circuit oil sump tank, with the coaxial test specimen oil hydraulic pump of test specimen oil hydraulic motor with fluid from test specimen oil hydraulic pump import oil return through the 3rd switch oil sump tank.
When second switch, the 4th switch opens, first switch, the 3rd switch on are promptly carried out and are switched test specimen oil-feed oil return, and test specimen oil hydraulic motor is originally carried out the oil hydraulic pump function, and test specimen oil hydraulic pump is originally carried out the function of oil hydraulic motor.Can test the another kind of pattern of PTU like this.
When only testing to single test specimen oil hydraulic motor, only need first switch, the 3rd switch opens, second switch, the 4th switch on get final product.
Said hydraulic system comprises that also being located at test specimen oil hydraulic motor return opening and test specimen oil hydraulic pump filler opening is used to prevent the fluid one-way valve set of string mutually.Said one-way valve set comprises 1 ~ 2 pair of one-way valve that connects test specimen oil hydraulic motor and test specimen oil hydraulic pump respectively, and one-way valve plays the non-return effect.Also be provided with the oil filter in the one-way valve outlet.
Said hydraulic system also comprises pump discharge one-way valve, the oil-feed flowmeter that is connected to the test specimen inlet from axial piston pump successively; And the inlet pressure modulating valve that is parallel to the Oil pump electrical machinery group; And from the unidirectional deceleration valve of oil return flowmeter and the radiator of test specimen outlet oil sump tank; And from the oil return of test specimen housing with housing return pressure modulating valve.
In order to reduce system vibration, said hydraulic system also comprises the accumulator of being located at axial plunger pump discharge and unidirectional deceleration valve ingress respectively.
Institute's inlet pressure modulating valve comprises the proportional pressure control valve and the safety valve of parallel connection, is used to regulate the test specimen inlet pressure.The outlet oil return of proportional pressure control valve and safety valve is connected to the inlet of radiator.
The import of said test specimen oil hydraulic motor and test specimen oil hydraulic pump also is provided with pressure transducer with outlet and is connected with computer communication with temperature transducer.
Said hydraulic system also comprises oil system, and this oil system is connected with the fitting seat of test specimen oil hydraulic motor, test specimen oil hydraulic pump through conduit, and the speed change gear in the gearbox is lubricated.
Said hydraulic system also comprises the oil filter of cleaning fluid, and said oil filter is distributed in the outlet of Oil pump electrical machinery group, is used to filter the oil sources of fuel tank; Be distributed in one-way valve set outlet end, be used to filter the oil return fluid through test specimen, test specimen housing oil return circuit also is provided with the oil filter, and the oil return flowmeter enters the mouth out and also is provided with the filter of oil return oil.
Oil sources oil system selects axial piston pump for use, at first can satisfy high pressure and the traffic requirement that is not less than 200L/min greater than 21Mpa, and secondly efficient is high, and the life-span is long, and reliability is high, is convenient to Flow-rate adjustment.
Beneficial effect: the Performance Test System driving power of the aircraft large hydraulic element of the utility model reaches more than the 130kw; Fuel delivery 0 ~ 200L/min is manually adjustable; Working pressure 21Mpa; Can satisfy big flow fluid work requirements, the selection of hydraulic pump motor and the running environment of aircraft oil hydraulic motor that has been equipped with real simulation, and flexibility ratio is high, good stability.The many places measuring and controlling equipment is monitored in real time test case and is reflected in the system, and test parameter is stored in the computer, can access at any time to check and print and record is beneficial to carrying out of test job and studies.
Description of drawings
Fig. 1 is the system architecture figure of the utility model;
Fig. 2 is mechanism's block diagram of the utility model;
Fig. 3 is the hydraulic schematic diagram of the utility model.
Embodiment
Below in conjunction with accompanying drawing the utility model is done explanation further.
In conjunction with Fig. 1, Fig. 2, shown in Figure 3; The Performance Test System of the disclosed aircraft large hydraulic of the utility model element; Comprise the fitting seat that test specimen oil hydraulic motor 101 or coaxial test specimen oil hydraulic pump 102 are installed, this test system comprises by the hydraulic system of fuel tank 2, Oil pump electrical machinery group 3 fuel feeding, is loaded with gearbox 4 and is connected to the measurement of power equipment 5 of test specimen motor 101; Oil pump electrical machinery group 3 is combined by axial piston pump 301 and asynchronous motor 302, and asynchronous motor 302 is equipped with the soft starting device 303 that is used to realize reduced-voltage starting.
The import of test specimen oil hydraulic motor 101 connects 101A joint and 101B joint respectively with outlet, and the import of test specimen oil hydraulic pump 102 connects 102B joint and 102A joint respectively with outlet.
Hydraulic system also comprises the reverser 6 that switches test specimen oil-feed oil return direction.Specifically, reverser 6 comprises first switch 601 and second switch 602 that is parallel to test specimen oil hydraulic motor 101 filler openings, and the 3rd switch 603 and the 4th switch 604 that are parallel to test specimen oil hydraulic pump 102 return openings; Link to each other between first switch 601 and the 3rd switch 603 and is communicated with fuel tank 2 in-lines, continuous and be communicated with between second switch 602 and the 3rd switch 604 with fuel tank 2 return lines.
Hydraulic system comprises that also being located at test specimen oil hydraulic motor 101 return openings and test specimen oil hydraulic pump 102 filler openings is used to prevent the fluid one-way valve set 7 of string mutually.The one-way valve set comprises 2 pairs of one-way valves that connect test specimen oil hydraulic motor and test specimen oil hydraulic pump respectively, and one-way valve plays the non-return effect.Also be provided with the oil filter in the one-way valve outlet.
Be connected to pump discharge one-way valve 8, the oil-feed flowmeter 9a of test specimen inlet successively from axial piston pump 301; And the inlet pressure modulating valve 10 that is parallel to Oil pump electrical machinery group 3; And from oil return flowmeter 9b, unidirectional deceleration valve 11 and the radiator 12 of test specimen outlet oil sump tank 2; And from the housing return pressure modulating valve 13 of test specimen housing oil return.
Hydraulic system also comprises the accumulator 9a that is located at axial piston pump 301 outlets, and the accumulator 9b that is located at unidirectional deceleration valve 11 ingress.
Inlet pressure modulating valve 10 comprises the proportional pressure control valve 15 and safety valve 16 of parallel connection.
The import of test specimen oil hydraulic motor 101 and test specimen oil hydraulic pump 102 also is provided with pressure transducer with outlet and is connected with computer communication with temperature transducer.
Claims (8)
1. the Performance Test System of an aircraft large hydraulic element; Comprise the fitting seat that test specimen oil hydraulic motor (101) or coaxial test specimen oil hydraulic pump (102) are installed, it is characterized in that: this test system comprises by the hydraulic system of fuel tank (2), Oil pump electrical machinery group (3) fuel feeding, is loaded with gearbox (4) and is connected to the measurement of power equipment (5) of test specimen motor (101); Said Oil pump electrical machinery group (3) is combined by axial piston pump (301) and asynchronous motor (302); Said hydraulic system is provided with two groups of fuel inlet fittings and is connected with test specimen oil hydraulic pump (102) with test specimen oil hydraulic motor (101) respectively with back leakage connection, and said hydraulic system also comprises the reverser (6) that switches test specimen oil-feed oil return direction.
2. the Performance Test System of aircraft large hydraulic element according to claim 1; It is characterized in that: said reverser (6) comprises first switch (601) and the second switch (602) that is parallel to test specimen oil hydraulic motor (101) filler opening, and the 3rd switch (603) and the 4th switch (604) that are parallel to test specimen oil hydraulic pump (102) return opening; Link to each other between said first switch (601) and the 3rd switch (603) and is communicated with fuel tank (2) in-line, continuous and be communicated with between said second switch (602) and the 3rd switch (604) with fuel tank (2) return line.
3. the Performance Test System of aircraft large hydraulic element according to claim 1 is characterized in that: said hydraulic system comprises that also being located at test specimen oil hydraulic motor (101) return opening and test specimen oil hydraulic pump (102) filler opening is used to prevent the fluid one-way valve set (7) of string mutually.
4. the Performance Test System of aircraft large hydraulic element according to claim 1 is characterized in that: said asynchronous motor (302) is equipped with the soft starting device (303) that is used to realize reduced-voltage starting.
5. the Performance Test System of aircraft large hydraulic element according to claim 1 is characterized in that, said hydraulic system also comprises: the pump discharge one-way valve (8), the oil-feed flowmeter (9a) that are connected to the test specimen inlet from axial piston pump (301) successively; And the inlet pressure modulating valve (10) that is parallel to Oil pump electrical machinery group (3); And from oil return flowmeter (9b), unidirectional deceleration valve (11) and the radiator (12) of test specimen outlet oil sump tank (2); And from the housing return pressure modulating valve (13) of test specimen housing oil return.
6. the Performance Test System of aircraft large hydraulic element according to claim 5 is characterized in that: said hydraulic system also comprises the accumulator of being located at axial piston pump (301) outlet and unidirectional deceleration valve (11) ingress respectively.
7. the Performance Test System of aircraft large hydraulic element according to claim 5 is characterized in that: institute's inlet pressure modulating valve (10) comprises the proportional pressure control valve (15) and the safety valve (16) of parallel connection.
8. the Performance Test System of aircraft large hydraulic element according to claim 1 is characterized in that: the import of said test specimen oil hydraulic motor (101) and test specimen oil hydraulic pump (102) also is provided with pressure transducer with outlet and is connected with computer communication with temperature transducer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011202319530U CN202187977U (en) | 2011-07-04 | 2011-07-04 | Performance test system for large-scale hydraulic component of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011202319530U CN202187977U (en) | 2011-07-04 | 2011-07-04 | Performance test system for large-scale hydraulic component of airplane |
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| Publication Number | Publication Date |
|---|---|
| CN202187977U true CN202187977U (en) | 2012-04-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2011202319530U Expired - Fee Related CN202187977U (en) | 2011-07-04 | 2011-07-04 | Performance test system for large-scale hydraulic component of airplane |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102200152A (en) * | 2011-07-04 | 2011-09-28 | 南京王行航空附件维修工程有限公司 | Performance test system of large-size airplane hydraulic element |
| CN103410719A (en) * | 2013-03-12 | 2013-11-27 | 北京理工大学 | Capacity electricity loaded hydraulic pump testing device |
| CN105045301A (en) * | 2015-08-03 | 2015-11-11 | 江西洪都航空工业集团有限责任公司 | Method for adjusting pulse test flow precisely |
| CN109883744A (en) * | 2019-02-22 | 2019-06-14 | 柳州北斗星液压科技有限公司 | A kind of device and method for excavator thermal equilibrium analysis |
| WO2019201266A1 (en) * | 2018-04-17 | 2019-10-24 | 珠海英搏尔电气股份有限公司 | Emc test system applicable to rotating load, and test method thereof |
-
2011
- 2011-07-04 CN CN2011202319530U patent/CN202187977U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102200152A (en) * | 2011-07-04 | 2011-09-28 | 南京王行航空附件维修工程有限公司 | Performance test system of large-size airplane hydraulic element |
| CN103410719A (en) * | 2013-03-12 | 2013-11-27 | 北京理工大学 | Capacity electricity loaded hydraulic pump testing device |
| CN103410719B (en) * | 2013-03-12 | 2016-05-04 | 北京理工大学 | A kind of volume electricity loads test-bed for pump device |
| CN105045301A (en) * | 2015-08-03 | 2015-11-11 | 江西洪都航空工业集团有限责任公司 | Method for adjusting pulse test flow precisely |
| WO2019201266A1 (en) * | 2018-04-17 | 2019-10-24 | 珠海英搏尔电气股份有限公司 | Emc test system applicable to rotating load, and test method thereof |
| US11237198B2 (en) | 2018-04-17 | 2022-02-01 | Zhuhai Empower Electric Co., Ltd. | EMC test system for rotating load and a test method thereof |
| CN109883744A (en) * | 2019-02-22 | 2019-06-14 | 柳州北斗星液压科技有限公司 | A kind of device and method for excavator thermal equilibrium analysis |
| CN109883744B (en) * | 2019-02-22 | 2021-05-07 | 柳州北斗星液压科技有限公司 | A device and method for heat balance analysis of excavator |
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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: 20120411 Termination date: 20150704 |
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| EXPY | Termination of patent right or utility model |