CN103644170A - Hydraulic low-pressure pulse experiment method of aircraft - Google Patents
Hydraulic low-pressure pulse experiment method of aircraft Download PDFInfo
- Publication number
- CN103644170A CN103644170A CN201310612009.3A CN201310612009A CN103644170A CN 103644170 A CN103644170 A CN 103644170A CN 201310612009 A CN201310612009 A CN 201310612009A CN 103644170 A CN103644170 A CN 103644170A
- Authority
- CN
- China
- Prior art keywords
- pressure
- pulse
- solenoid directional
- control valve
- directional control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to a hydraulic low-pressure pulse experiment method of an aircraft and belongs to a hydraulic pulse technology. The hydraulic low-pressure pulse experiment method comprises the steps of firstly providing initial pressure required by a test piece for a supercharged oil tank during a pulse experiment, driving a magnetic exchange valve by utilizing a signal generated by a control system when hydraulic pulse pressure begins to produce, and stilling keeping certain pressure after pulse waves attenuate, wherein the pressure is identical to rated pressure of the tested piece; adjusting a precise throttle valve, controlling flows entering a pressure reducing cylinder and achieving the purpose of accurately controlling pulse waveform parameters at an ascent stage. By adopting the hydraulic low-pressure pulse experiment method, the pulse experiment in a flexible connecting assembly qualification test of an aircraft fuel system is achieved, and conditions are provided for localization of flexible connecting assemblies of aircraft fuel systems in outer country.
Description
Technical field
The present invention relates to a kind of experimental technique of airplane hydraulic pressure action of low-voltage pulse, belong to hydraulic impulse technology.
Background technique
In Airplane Hydraulic Impulse Test System, existing test stand is comprised of power system, control system and pressurized cylinder.Larger because of hydraulic power system output power, this test stand is only applicable to the mesohigh impulse test that hydraulic pressure becomes annex.The assembly that flexibly connects for working pressure between 0.35MPa～2MPa carries out impulse test and does not also have.
Summary of the invention
In order to overcome above-mentioned defect, the object of the present invention is to provide a kind ofly for working pressure, between 0.35MPa～2MPa, to flexibly connect the experimental technique that assembly carries out the airplane hydraulic pressure action of low-voltage pulse of impulse test.
To achieve these goals, the present invention adopts following technological scheme:
An experimental technique for airplane hydraulic pressure action of low-voltage pulse, this experimental technique is realized in action of low-voltage pulse pilot system, and this test method is as follows:
A), while carrying out impulse test, first to pressurized fuel tank, fill the required initial pressure of testpieces, close stop valve, start oil sources, boost to the working pressure of test determination; In this stage, the position of solenoid directional control valve in closing, the flow of oil pump output stops at solenoid directional control valve oil-feed port end, the pressure position system pressure of solenoid directional control valve front end; And solenoid directional control valve is to being zero by the flow of this section of pipeline of test specimen end, the initial pressure that pressure provides to testpieces for pressurized fuel tank;
While B), starting to produce hydraulic impulse pressure, the signal driver solenoid directional control valve being produced by control system, solenoid directional control valve under this signal function, make spool fast moving open oil circuit make pressure oil through solenoid directional control valve pass to decompression cylinder hyperbaric chamber, the piston that promotes decompression cylinder moves rapidly, the pipeline end being directly connected with the low voltage terminal of decompression cylinder seals, by test specimen and coiler, there is elasticity, therefore form hydraulic impact and produce thus water hammer; Now, because solenoid directional control valve not yet cuts out, so still can maintain certain pressure after Pulse wave decay, this pressure should be with consistent by the rated pressure of test specimen;
C), when arriving the trailing edge of square wave control signal, solenoid directional control valve cuts out, the hyperbaric chamber of decompression cylinder is connected oil circuit, and the piston of decompression cylinder is just retracted into original position, and the pressure of test section also quickly falls to and approaches zero-bit; Under the condition of continuous impulse, start after half period next impulse test, now whole Pulse wave produces again; From controlled quentity controlled variable in the actual pressure P of testpieces inlet and TT&C system, compare, according to result relatively, control system regulates, and with this regulating system pressure, reaches the object of accurate control impuls waveform stabilization section parameter; When peak value departs from givenly while requiring amplitude, adjustment precision throttle valve, controls and enters decompression cylinder flow, reaches the object of accurate control ascent stage pulse shape parameter.
On solenoid directional control valve oil circuit, increase constrictor.
Water hammer has another name called (water hammer).
Because solenoid directional control valve not yet cuts out, so still can maintain certain pressure after Pulse wave decay, this section of pressure is called " steady operation pressure ".
Function of the present invention is:
A) for the testpieces of different cavity volumes, system output stream amount is adjustable.
B) adopt low power hydraulic power system, cancel the accumulator in hydraulic power system, at pump discharge place, increase surge flask, reduce the pressure pulsation of hydraulic system.
C) adopt decompression cylinder, to improve system pressure.
D) between decompression cylinder and testpieces, increase constrictor.
Beneficial effect of the present invention:
Action of low-voltage pulse test method of the present invention has solved aircraft fuel system and has flexibly connected the impulse test in assembly evaluation test, for China's aircraft fuel system flexibly connects assembly production domesticization, provides condition.
Accompanying drawing explanation
Fig. 1 is the structural representation of mesolow impulse test system of the present invention.
Fig. 2 is the enlarged diagram of mesolow impulse test system medium power components of system as directed of the present invention.
Fig. 3 is the enlarged diagram for constrictor position in mesolow impulse test system of the present invention.
Fig. 4 is typical pulse plotted curve.
In figure: 1-fuel tank 2-air-strainer 3-level meter (4; 5; 21)-stop valve 6-oil pump 7-AC motor 8-radiator 9-oil return oil filter 10-surge flask (11; 22)-one-way valve 12-high pressure oil filter 13-relief valve 14-safety valve 15-precise throttling valve 16-constrictor 17-solenoid directional control valve 18-decompression cylinder 19-air filter 20-coiler 23-pressurized fuel tank 24-temperature transducer 25-pressure transducer 26-testpieces.
Embodiment
Below in conjunction with accompanying drawing, describe the present invention:
An experimental technique for airplane hydraulic pressure action of low-voltage pulse, this experimental technique is realized in action of low-voltage pulse pilot system, and this test method is characterized in that:
A), while carrying out impulse test, fill the required initial pressure of testpieces 26 first to pressurized fuel tank 25, close stop valve 21, start oil sources, boost to the working pressure of test determination; In this stage, the position of solenoid directional control valve 17 in closing, the flow of oil pump 6 outputs stops at solenoid directional control valve 17 oil-feed port ends, the pressure position system pressure of solenoid directional control valve 17 front ends; And solenoid directional control valve 17 is to being zero by the flow of this section of pipeline of test specimen end, the initial pressure that pressure provides to testpieces for pressurized fuel tank 25;
While B), starting to produce hydraulic impulse pressure, the signal driver solenoid directional control valve 17 being produced by control system, solenoid directional control valve under this signal function, make spool fast moving open oil circuit make pressure oil through solenoid directional control valve 17 pass to decompression cylinder 18 hyperbaric chamber, the piston that promotes decompression cylinder 18 moves rapidly, the pipeline end being directly connected with the low voltage terminal of decompression cylinder 18 seals, by test specimen and coiler 20, there is elasticity, therefore form hydraulic impact and produce thus water hammer; Now, because solenoid directional control valve 17 not yet cuts out, so still can maintain certain pressure after Pulse wave decay, this pressure should be with consistent by the rated pressure of test specimen;
C), when arriving the trailing edge of square wave control signal, solenoid directional control valve 17 cuts out, the hyperbaric chamber of decompression cylinder 18 is connected oil circuit, and the piston of decompression cylinder 18 is just retracted into original position, and the pressure of test section also quickly falls to and approaches zero-bit; Under the condition of continuous impulse, start after half period next impulse test, now whole Pulse wave produces again; From controlled quentity controlled variable in the actual pressure P of testpieces inlet and TT&C system, compare, according to result relatively, control system regulates, and with this regulating system pressure, reaches the object of accurate control impuls waveform stabilization section parameter; When peak value departs from givenly while requiring amplitude, adjustment precision throttle valve 15, controls and enters decompression cylinder 18 flows, reaches the object of accurate control ascent stage pulse shape parameter.
For working pressure, great Rong between 0.35MPa～2MPa flexibly connects assembly, and because its pulse process fluid decrement is little, its needed power and system pressure are also relatively little.In order to reduce system moment output power, in hydraulic system, cancelled accumulator, with surge flask, replace the pressure pulsation of accumulator absorption pump generation as Fig. 2, avoided when solenoid directional control valve 17 commutation because accumulator is that system repairing causes the excessive problem of low voltage terminal moment input power to decompression cylinder 18.
In pulse oil return process, because oil return flow velocity makes too soon the pressure of test section quickly fall to zero-bit and produces negative pressure.For head it off, on solenoid directional control valve 17 oil circuits, increase constrictor 16 and see Fig. 3, reduce oil return flow velocity, thereby avoid in testpieces, producing negative pressure in pulse oil return process.
Select the hydraulic power system of flow 17L/min, system power 5.5 KW, coordinate solenoid directional control valve 17 and decompression cylinder 18, by relief valve 13, regulate hydraulic power system delivery pressure, accurately Control experiment part working pressure stable section pulse shape parameter, makes working pressure stable section pulse shape meet the requirement of Fig. 4 pulse curve.
With pressurized fuel tank 23, for test repairing, by regulating pressurized fuel tank boost pressure, accurately control low pressure stable section pulse shape parameter, make low pressure stable section pulse shape meet the requirement of Fig. 4 pulse curve
By precise throttling valve 15, regulate and enter decompression cylinder input end uninterrupted, accurately control ascent stage pulse shape parameter, make ascent stage and stable section pulse shape meet the requirement of Fig. 4 pulse curve.
At electromagnetism, change 17 and fill 16 of current limlitings on valve oil circuit, reduce oil return flow velocity, thereby avoid in testpieces, producing negative pressure in pulse oil return process, make descending branch pulse shape meet the requirement of Fig. 4 pulse curve.
Claims (2)
1. an experimental technique for airplane hydraulic pressure action of low-voltage pulse, this experimental technique is realized in action of low-voltage pulse pilot system, and this test method is characterized in that:
A), while carrying out impulse test, fill the required initial pressure of testpieces (26) first to pressurized fuel tank (25), close stop valve (21), start oil sources, boost to the working pressure of test determination; In this stage, the position of solenoid directional control valve (17) in closing, the flow of oil pump (6) output stops at solenoid directional control valve (17) oil-feed port end, the pressure position system pressure of solenoid directional control valve (17) front end; And solenoid directional control valve (17) is to being zero by the flow of this section of pipeline of test specimen end, pressure is the initial pressure that pressurized fuel tank (25) provides to testpieces;
While B), starting to produce hydraulic impulse pressure, the signal driver solenoid directional control valve (17) being produced by control system, solenoid directional control valve under this signal function, make spool fast moving open oil circuit make pressure oil through solenoid directional control valve (17) pass to decompression cylinder (18) hyperbaric chamber, the piston that promotes decompression cylinder (18) moves rapidly, the pipeline end being directly connected with the low voltage terminal of decompression cylinder (18) seals, by test specimen and coiler (20), there is elasticity, therefore form hydraulic impact and produce thus water hammer; Now, because solenoid directional control valve (17) not yet cuts out, so still can maintain certain pressure after Pulse wave decay, this pressure should be with consistent by the rated pressure of test specimen;
C), when arriving the trailing edge of square wave control signal, solenoid directional control valve (17) cuts out, the hyperbaric chamber of decompression cylinder (18) is connected oil circuit, and the piston of decompression cylinder (18) is just retracted into original position, and the pressure of test section also quickly falls to and approaches zero-bit; Under the condition of continuous impulse, start after half period next impulse test, now whole Pulse wave produces again; From controlled quentity controlled variable in the actual pressure P of testpieces inlet and TT&C system, compare, according to result relatively, control system regulates, and with this regulating system pressure, reaches the object of accurate control impuls waveform stabilization section parameter; When peak value departs from givenly while requiring amplitude, adjustment precision throttle valve (15), controls and enters decompression cylinder (18) flow, reaches the object of accurate control ascent stage pulse shape parameter.
2. the experimental technique of airplane hydraulic pressure action of low-voltage pulse according to claim 1, is characterized in that: on solenoid directional control valve (17) oil circuit, increase constrictor (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310612009.3A CN103644170B (en) | 2013-11-28 | 2013-11-28 | A kind of test method of airplane hydraulic pressure action of low-voltage pulse |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310612009.3A CN103644170B (en) | 2013-11-28 | 2013-11-28 | A kind of test method of airplane hydraulic pressure action of low-voltage pulse |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103644170A true CN103644170A (en) | 2014-03-19 |
| CN103644170B CN103644170B (en) | 2016-05-11 |
Family
ID=50249435
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310612009.3A Active CN103644170B (en) | 2013-11-28 | 2013-11-28 | A kind of test method of airplane hydraulic pressure action of low-voltage pulse |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103644170B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104843195A (en) * | 2015-04-13 | 2015-08-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Verifying device and usage method thereof |
| 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 |
| CN108612707A (en) * | 2016-12-12 | 2018-10-02 | 大陆汽车电子(芜湖)有限公司 | Jet pump test method |
| CN110217407A (en) * | 2019-05-17 | 2019-09-10 | 陕西飞机工业（集团）有限公司 | A kind of experimental rig of hydraulic actuator |
| CN110673663A (en) * | 2019-09-05 | 2020-01-10 | 中国航发北京航科发动机控制系统科技有限公司 | Hydraulic control system and method for testing fuel metering assembly of aircraft engine |
| CN111852991A (en) * | 2020-07-06 | 2020-10-30 | 珠海格力智能装备有限公司 | Intelligent control device and method for electric pulse oil pressure test equipment |
| CN112208789A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业集团有限责任公司 | Hydraulic pulse sine wave test device and method for airplane |
| CN112664516A (en) * | 2020-11-25 | 2021-04-16 | 河南航天液压气动技术有限公司 | Fuzzy control theory-based high-lift-rate water hammer generator and working method thereof |
| CN116608165A (en) * | 2023-07-20 | 2023-08-18 | 北京科技大学 | Ultralow pulse high-pressure fluid generating device and method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19730237A1 (en) * | 1997-07-15 | 1999-01-21 | Gunter Prof Dr Ing Riedel | Circuit for dynamic impulse test of fluid structure elements using capacitive energy |
| CN2672643Y (en) * | 2003-12-10 | 2005-01-19 | 天津市精研工程机械传动有限公司 | Pulse test table for hydraulic soft tube assembly |
| CN201636133U (en) * | 2010-04-20 | 2010-11-17 | 新乡平原航空技术工程有限公司 | Helicopter hydraulic system debugging device |
| CN201696394U (en) * | 2010-06-03 | 2011-01-05 | 西北工业大学 | High-pressure hydraulic pulse test system for aircraft |
| CN102011766A (en) * | 2010-11-15 | 2011-04-13 | 陕西飞机工业（集团）有限公司 | Pressure-resistance and adjustment test bed for aircraft hydraulic system |
| CN102445399A (en) * | 2011-12-12 | 2012-05-09 | 麦格思维特(上海)流体工程有限公司 | Pulse test bench and pressurizer |
| CN103016453A (en) * | 2012-12-14 | 2013-04-03 | 浙江大学 | Impulse test system of hydraulic hose |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1163058A1 (en) * | 1983-04-07 | 1985-06-23 | Производственное Объединение "Гомсельмаш" | Stand for dynamic tests of hydraulic system hoses |
-
2013
- 2013-11-28 CN CN201310612009.3A patent/CN103644170B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19730237A1 (en) * | 1997-07-15 | 1999-01-21 | Gunter Prof Dr Ing Riedel | Circuit for dynamic impulse test of fluid structure elements using capacitive energy |
| CN2672643Y (en) * | 2003-12-10 | 2005-01-19 | 天津市精研工程机械传动有限公司 | Pulse test table for hydraulic soft tube assembly |
| CN201636133U (en) * | 2010-04-20 | 2010-11-17 | 新乡平原航空技术工程有限公司 | Helicopter hydraulic system debugging device |
| CN201696394U (en) * | 2010-06-03 | 2011-01-05 | 西北工业大学 | High-pressure hydraulic pulse test system for aircraft |
| CN102011766A (en) * | 2010-11-15 | 2011-04-13 | 陕西飞机工业（集团）有限公司 | Pressure-resistance and adjustment test bed for aircraft hydraulic system |
| CN102445399A (en) * | 2011-12-12 | 2012-05-09 | 麦格思维特(上海)流体工程有限公司 | Pulse test bench and pressurizer |
| CN103016453A (en) * | 2012-12-14 | 2013-04-03 | 浙江大学 | Impulse test system of hydraulic hose |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104843195A (en) * | 2015-04-13 | 2015-08-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Verifying device and usage method thereof |
| 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 |
| CN108612707A (en) * | 2016-12-12 | 2018-10-02 | 大陆汽车电子(芜湖)有限公司 | Jet pump test method |
| CN110217407A (en) * | 2019-05-17 | 2019-09-10 | 陕西飞机工业（集团）有限公司 | A kind of experimental rig of hydraulic actuator |
| CN110673663A (en) * | 2019-09-05 | 2020-01-10 | 中国航发北京航科发动机控制系统科技有限公司 | Hydraulic control system and method for testing fuel metering assembly of aircraft engine |
| CN110673663B (en) * | 2019-09-05 | 2023-03-24 | 中国航发北京航科发动机控制系统科技有限公司 | Hydraulic control system and method for testing fuel metering assembly of aircraft engine |
| CN111852991A (en) * | 2020-07-06 | 2020-10-30 | 珠海格力智能装备有限公司 | Intelligent control device and method for electric pulse oil pressure test equipment |
| CN111852991B (en) * | 2020-07-06 | 2022-04-22 | 珠海格力智能装备有限公司 | Intelligent control device and method for electric pulse oil pressure test equipment |
| CN112208789A (en) * | 2020-10-10 | 2021-01-12 | 江西洪都航空工业集团有限责任公司 | Hydraulic pulse sine wave test device and method for airplane |
| CN112664516A (en) * | 2020-11-25 | 2021-04-16 | 河南航天液压气动技术有限公司 | Fuzzy control theory-based high-lift-rate water hammer generator and working method thereof |
| CN116608165A (en) * | 2023-07-20 | 2023-08-18 | 北京科技大学 | Ultralow pulse high-pressure fluid generating device and method |
| CN116608165B (en) * | 2023-07-20 | 2023-10-13 | 北京科技大学 | Ultralow pulse high-pressure fluid generating device and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103644170B (en) | 2016-05-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103644170A (en) | Hydraulic low-pressure pulse experiment method of aircraft | |
| CN108356128A (en) | High-pressure forming method | |
| CN203414260U (en) | Water flow test apparatus for turbine blade of aeroengine | |
| CN102678409B (en) | Sequential turbocharging type electronic control common rail oil injection system | |
| CN109236775A (en) | A kind of big flow ratio valve module and its control method based on high-speed switch valve guide adjusting | |
| CN105181475A (en) | Impulse test system supercharged through servo electric cylinder | |
| CN104329164A (en) | Free piston engine | |
| CN207568956U (en) | Deflect the hydraulic system of pulse test bench | |
| CN110985462B (en) | Hydraulic system for eliminating pulse test actuating cylinder and pipeline gas thereof | |
| CN202926500U (en) | Electronic control common rail fuel injecting system provided with two-stage supercharged piston | |
| CN102691604B (en) | Multi-stage boosting electric-control common-rail oil injection system | |
| CN106837934A (en) | Thermostatically controlled hydraulic hose pulse test bench | |
| CN106050804B (en) | A kind of pilot system of hydraulic shock waveform control | |
| CN204284032U (en) | Single actuator automatic switchover rapid movement oil hydraulic circuit | |
| CN201464180U (en) | Hydraulic servomotor displacement test apparatus | |
| CN113090596B (en) | Servomotor system with thermal redundancy backup oil supply and control method thereof | |
| CN202579378U (en) | Intelligent tensioning system | |
| CN204175430U (en) | A kind of free-piston engine | |
| CN102900579A (en) | Variable-oil injection pressure double-boosting common-trail oil injection system | |
| CN104564854A (en) | Multi-executer heavy load digital hydraulic loop based on high-voltage common rail cabin | |
| CN203452856U (en) | Electro-hydraulic servo hydraulic actuator of turbine adjustment system | |
| CN205138903U (en) | Servo booster and pulse testing system who contains it | |
| CN204025238U (en) | A kind of high-voltage electrical apparatus ratio pressure regulating system | |
| CN103470385B (en) | Low-speed marine diesel engine high-pressure common rail fuel injection control systems | |
| CN106121890B (en) | Rail pressure regulating valve for common-rail system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |