CN102707739B - Working state control system and control method for pumping oil supply simulation chamber - Google Patents
Working state control system and control method for pumping oil supply simulation chamber Download PDFInfo
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- CN102707739B CN102707739B CN201210188648.7A CN201210188648A CN102707739B CN 102707739 B CN102707739 B CN 102707739B CN 201210188648 A CN201210188648 A CN 201210188648A CN 102707739 B CN102707739 B CN 102707739B
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Abstract
The invention belongs to the technical field of aviation, and relates to a working state control system and a working state control method for a pumping oil supply simulation chamber. The control system comprises an air inlet electro-hydraulic servo regulating valve, an air exhaust electro-hydraulic servo regulating valve, a magnetostrictive liquid level sensor, an electric centrifugal pump, a computer control system and corresponding connecting pipelines. The control method comprises the following steps that: air pressure in the simulation chamber is regulated, so that the inlet pressure or flow of a low-pressure pump of an engine meets simulation requirements; fuel oil enters the simulation chamber from an oil supply pipeline to raise an oil level; when the oil level is raised to the highest point, the magnetostrictive liquid level sensor and the computer control system jointly starts the electric centrifugal pump to discharge the oil; when the oil level is lowered to the lowest point, the magnetostrictive liquid level sensor and the computer control system jointly stops the electric centrifugal pump to stop discharging the oil; and in the whole test process, the oil level in the simulation chamber is repeated between the highest point and the lowest point to keep a pumping oil supply working state. Problems about the simulation of low-pressure pumping oil supply test conditions of a plurality of engines are solved.
Description
Technical field
The invention belongs to aeronautical technology field, relate to a kind of suction fuel feeding simulation box operation status control system and control method thereof.
Background technology
Conventionally a set of analogue means that, the simulation of aircraft fuel system suction fuel feeding test condition is made up of a simulation box, a set of computer measurement and control system (comprising hardware, software two parts), hydraulic oil source, pumped vacuum systems and system pipeline is realized.Wherein simulation box is used for simulated engine (or APU) low-lift pump inlet pressure or flow, and the fuel oil flowing out from engine (or APU) low-lift pump porch while taking up suction for oil test.This just requires in whole aircraft fuel system suction fuel feeding simulation test procedure, and simulation box remains that existing certain gas-phase space can carry again inflow this duty of fuel oil wherein continually.For large aircraft, need simulate many engines and APU suction for oil condition, and the suction fuel supply flow rate of every engine reaches thousands of kg/h, whole duration of test runs at least 1 hour simultaneously.Due to test site limited space, this simulation box volume is limited, can not be infinitely great, if effectively do not controlled, fuel oil can be full of very soon simulation box in the time that test not yet finishes.
Summary of the invention
The object of the invention is: a kind of control system that can make the limited simulation box of volume keep for a long time large flow suction fuel feeding duty is provided.
In addition, the present invention also provides a kind of control method of aspirating fuel feeding simulation box duty.
The technical scheme that the present invention takes is: a kind of suction fuel feeding simulation box operation status control system, it comprises air inlet electro-hydraulic servo variable valve, the electro-hydraulic servo variable valve of bleeding, magnetostriction type level sensing, electric centrifugal pump, ball valve, flowmeter, oil pressure sensor, computer control system and corresponding connecting line, wherein, air inlet electro-hydraulic servo variable valve and the electro-hydraulic servo variable valve of bleeding are installed in simulation box top, air inlet electro-hydraulic servo variable valve is logical atmosphere directly, and the electro-hydraulic servo variable valve of bleeding is connected with pumped vacuum systems; Described Liquid Level Sensor Based on Magnetostriction is vertically mounted on simulation box top, and its measuring staff length at least equals the height of simulation box, is provided with along with the variation of liquid level fluctuates and also can produces the ball float of corresponding current signal on measuring staff; Described electric centrifugal pump is arranged on simulation box bottom, and its inlet port is positioned at simulation box, and electric centrifugal pump discharge is communicated with return line, and pump oil mass is greater than oil feed line oil inlet quantity; Described computer control system and air inlet electro-hydraulic servo variable valve, bleed electro-hydraulic servo variable valve and engine suction fuel feeding simulation pipeline are connected, formation closed-loop control; In addition, computer control system is connected with Liquid Level Sensor Based on Magnetostriction and electric centrifugal pump, forms closed-loop control.
Described every engine suction fuel feeding simulation pipeline is by ball valve, flowmeter, oil pressure sensor and oil feed line composition, ball valve one end is connected with simulation box, one end is connected with flowmeter outlet, flowmeter import is connected with the engine low-lift pump inlet end of oil feed line, oil pressure sensor is arranged on engine low-lift pump porch, and flowmeter is all connected with computer control system with oil pressure sensor.
In simulation box, fuel level arranges two reference mark: oil level highs and lows, and wherein, gas-phase space volume more than oil level peak is at least 3% of simulation box total measurement (volume); The pasta of oil level minimum point is at least higher than electric centrifugal pump inlet port 50mm.
In the time that needs are simulated many engine suctions for oil condition and its state consistency, every engine suction fuel feeding simulation pipeline is merged near one end of simulation box at ball valve, so only need a simulation box just can simulate many engine suctions for oil condition;
A kind of suction fuel feeding simulation box working state control method, it comprises the steps:
Step 1: regulate simulation box internal gas pressure
Make engine low-lift pump inlet pressure or flow meet simulation requirement;
Step 2: fuel oil enters simulation box from oil feed line, oil level rises;
Step 3: in the time that simulation box oil level rises to peak, send corresponding current signal by Liquid Level Sensor Based on Magnetostriction 3 to computer control system, start electric centrifugal pump 4 by computer control system, by electric centrifugal pump, the fuel oil in simulation box is discharged;
Step 4: because electric centrifugal pump pump oil mass is greater than the oil inlet quantity of oil feed line, therefore oil level constantly declines, in the time that oil level drops to minimum point, send corresponding current signal by Liquid Level Sensor Based on Magnetostriction to computer control system, close electric centrifugal pump by computer control system, stop draining the oil;
Step 5: under the continuous oil-feed of oil feed line, in simulation box, oil level constantly rises, and during to peak, then is drained the oil by computer control electric centrifugal pump, so circulates repeatedly, thereby in whole experimentation, keeps large flow suction fuel feeding duty.
Advantage of the present invention is: the present invention makes to aspirate fuel feeding simulation box and leaves all the time certain gas-phase space in long-time process of the test, can many engines of real time modelling (or APU) low-lift pump inlet pressure, can load again and emit in time the fuel oil in continuous inflow simulation box, the limited and very large difficult problem of suction fuel supply flow rate of the simulation box volume that run into while having solved the suction of large aircraft fuel system for oil test.
Brief description of the drawings
Fig. 1 is that the present invention aspirates fuel feeding simulation box operation status control system schematic diagram;
Fig. 2 is the process flow diagram that the present invention aspirates fuel feeding simulation box working state control method,
Wherein, bleed electro-hydraulic servo variable valve, 3-Liquid Level Sensor Based on Magnetostriction, 4-electric centrifugal pump, 5-ball valve, 6-flowmeter, 7-oil pressure sensor of 1-air inlet electro-hydraulic servo variable valve, 2-.
Embodiment
Illustrate the specific embodiment of the present invention below in conjunction with accompanying drawing:
Refer to accompanying drawing 1, it is that the present invention aspirates fuel feeding simulation box operation status control system schematic diagram.Described suction fuel feeding simulation box operation status control system comprises air inlet electro-hydraulic servo variable valve 1, the electro-hydraulic servo variable valve 2 of bleeding, magnetostriction type level sensing 3, electric centrifugal pump 4, ball valve 5, flowmeter 6, oil pressure sensor 7, computer control system and corresponding connecting line, wherein, air inlet electro-hydraulic servo variable valve 1 and the electro-hydraulic servo variable valve 2 of bleeding are installed in simulation box top, air inlet electro-hydraulic servo variable valve 1 is logical atmosphere directly, and the electro-hydraulic servo variable valve 2 of bleeding is connected with pumped vacuum systems; Described Liquid Level Sensor Based on Magnetostriction 3 is vertically mounted on simulation box top, and its measuring staff length at least equals the height of simulation box, is provided with along with the variation of liquid level fluctuates and also can produces the ball float of corresponding current signal on measuring staff; Described electric centrifugal pump 4 is arranged on simulation box bottom, and its inlet port is positioned at simulation box, and oil pump outlet is communicated with return line, and pump oil mass is greater than oil feed line oil inlet quantity; Described every engine suction fuel feeding simulation pipeline is by ball valve 5, flowmeter 6, oil pressure sensor 7 and oil feed line composition, ball valve 5 one end are connected with simulation box, one end is connected with flowmeter 6 outlets, flowmeter 6 imports are connected with the engine low-lift pump inlet end of oil feed line, and oil pressure sensor 7 is arranged on engine low-lift pump porch; Described computer control system is connected with oil pressure sensor 7, and forms closed-loop control with air inlet electro-hydraulic servo variable valve 1, the electro-hydraulic servo variable valve 2 of bleeding, flowmeter 6; In addition, computer control system is connected with Liquid Level Sensor Based on Magnetostriction 3 and electric centrifugal pump 4, forms closed-loop control.
The electric centrifugal pump 4 that the present invention aspirates fuel feeding simulation box operation status control system starts and normal running conditions is not subject to the restriction of environmental pressure, and its pump oil flow is greater than the summation of many engines suction fuel supply flow rates.In addition, in suction fuel feeding simulation box, fuel level arranges two reference mark: oil level highs and lows.Wherein, determining of oil level peak: this gas-phase space volume more than oil level is at least 3% of simulation box total measurement (volume).Determining of oil level minimum point: the pasta of this oil level is at least higher than electric centrifugal pump 4 inlet port 50mm.
Like this, in aircraft fuel system suction fuel feeding process of the test, in the time flowing to the fuel level arrival peak of simulation box, computer control system starts electric centrifugal pump 4, and the fuel oil in simulation box is drained; When oil level drops to minimum point, computer control system is closed electric centrifugal pump 4, causes that oil pump is dry turns impaired in case its inlet port exposes pasta.Therefore the present invention makes to aspirate fuel feeding simulation box and leaves all the time certain gas-phase space in long-time process of the test, can many engines of real time modelling (or APU) low-lift pump inlet pressure, can load again and emit in time the fuel oil in continuous inflow simulation box, the limited and very large difficult problem of suction fuel supply flow rate of the simulation box volume that run into while having solved the suction of large aircraft fuel system for oil test.
Refer to Fig. 2, provide the present invention below and aspirate the implementation process of fuel feeding simulation box working state control method, its idiographic flow is as follows:
Step 1: regulate simulation box internal gas pressure
Make engine low-lift pump inlet pressure or flow meet simulation requirement;
Step 2: fuel oil enters simulation box from oil feed line, oil level rises;
Step 3: in the time that simulation box oil level rises to peak, send corresponding current signal by Liquid Level Sensor Based on Magnetostriction 3 to computer control system, start electric centrifugal pump 4 by computer control system, by electric centrifugal pump 4, the fuel oil in simulation box is discharged;
Step 4: because electric centrifugal pump 4 pump oil masses are greater than the oil inlet quantity of oil feed line, therefore oil level constantly declines, in the time that oil level drops to minimum point, send corresponding current signal by Liquid Level Sensor Based on Magnetostriction 3 to computer control system, close electric centrifugal pump 4 by computer control system, stop draining the oil;
Step 5: under the continuous oil-feed of oil feed line, in simulation box, oil level constantly rises, during to peak, then is drained the oil by computer control electric centrifugal pump 4, and so circulation repeatedly, can be in whole process of the test, keeps large flow suction fuel feeding duty.
The present invention can be applicable to aircraft fuel system suction fuel feeding test simulation, also can be applicable to aerial fuel dump test simulation, and is well used on certain series aircraft, has produced positive technique effect.
Claims (5)
1. a suction fuel feeding simulation box operation status control system, it is characterized in that: comprise air inlet electro-hydraulic servo variable valve (1), the electro-hydraulic servo variable valve (2) of bleeding, Liquid Level Sensor Based on Magnetostriction (3), electric centrifugal pump (4), every engine suction fuel feeding simulation pipeline, computer control system and corresponding connecting line, wherein, air inlet electro-hydraulic servo variable valve (1) and the electro-hydraulic servo variable valve (2) of bleeding are installed in simulation box top, air inlet electro-hydraulic servo variable valve (1) is logical atmosphere directly, the electro-hydraulic servo variable valve (2) of bleeding is connected with pumped vacuum systems, described Liquid Level Sensor Based on Magnetostriction (3) is vertically mounted on simulation box top, and its measuring staff length at least equals the height of simulation box, is provided with along with the variation of liquid level fluctuates and also can produces the ball float of corresponding current signal on measuring staff, described electric centrifugal pump (4) is arranged on simulation box bottom, and its inlet port is positioned at simulation box, and electric centrifugal pump (4) outlet is communicated with return line, and pump oil mass is greater than oil feed line oil inlet quantity, described computer control system and air inlet electro-hydraulic servo variable valve (1), bleed electro-hydraulic servo variable valve (2) and engine suction fuel feeding simulation pipeline are connected, formation closed-loop control, in addition, computer control system is connected with Liquid Level Sensor Based on Magnetostriction (3) and electric centrifugal pump (4), forms closed-loop control.
2. suction fuel feeding simulation box operation status control system according to claim 1, it is characterized in that: described every engine suction fuel feeding simulation pipeline is by ball valve (5), flowmeter (6), oil pressure sensor (7) and oil feed line composition, ball valve (5) one end is connected with simulation box, one end is connected with flowmeter (6) outlet, flowmeter (6) import is connected with the engine low-lift pump inlet end of oil feed line, oil pressure sensor (7) is arranged on engine low-lift pump porch, and flowmeter is all connected with computer control system with oil pressure sensor.
3. suction fuel feeding simulation box operation status control system according to claim 2, it is characterized in that: in simulation box, fuel level arranges two reference mark: oil level highs and lows, wherein, gas-phase space volume more than oil level peak is at least 3% of simulation box total measurement (volume); The pasta of oil level minimum point is at least higher than electric centrifugal pump inlet port 50mm.
4. suction fuel feeding simulation box operation status control system according to claim 3, it is characterized in that: in the time that needs are simulated many engine suctions for oil condition and its state consistency, every engine suction fuel feeding simulation pipeline is merged near one end of simulation box at ball valve (5), thereby only need a simulation box just can simulate many engine suctions for oil condition.
5. a suction fuel feeding simulation box working state control method, is characterized in that, comprises the steps:
Step 1: regulate simulation box internal gas pressure
Make engine low-lift pump inlet pressure or flow meet simulation requirement;
Step 2: fuel oil enters simulation box from oil feed line, oil level rises;
Step 3: in the time that simulation box oil level rises to peak, send corresponding current signal by Liquid Level Sensor Based on Magnetostriction (3) to computer control system, start electric centrifugal pump (4) by computer control system, by electric centrifugal pump (4), the fuel oil in simulation box is discharged;
Step 4: because electric centrifugal pump (4) pump oil mass is greater than the oil inlet quantity of oil feed line, therefore oil level constantly declines, in the time that oil level drops to minimum point, send corresponding current signal by Liquid Level Sensor Based on Magnetostriction (3) to computer control system, close electric centrifugal pump (4) by computer control system, stop draining the oil;
Step 5: under the continuous oil-feed of oil feed line, in simulation box, oil level constantly rises, during to peak, drained the oil by computer control electric centrifugal pump (4) again, so circulate repeatedly, thereby in whole experimentation, keep large flow suction fuel feeding duty.
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| CN201210188648.7A CN102707739B (en) | 2012-06-08 | 2012-06-08 | Working state control system and control method for pumping oil supply simulation chamber |
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| CN201210188648.7A CN102707739B (en) | 2012-06-08 | 2012-06-08 | Working state control system and control method for pumping oil supply simulation chamber |
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| CN102707739B true CN102707739B (en) | 2014-11-12 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102926882A (en) * | 2012-10-24 | 2013-02-13 | 哈尔滨东安发动机（集团）有限公司 | Engine ground test start oil supply control system |
| DE102014016421B4 (en) * | 2014-11-06 | 2018-06-07 | Audi Ag | Method for operating a fluid-carrying device and corresponding fluid-carrying device |
| CN105003341B (en) * | 2015-06-23 | 2017-06-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of engine oil flow regulating control system and control method |
Citations (5)
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| CN2258608Y (en) * | 1995-09-28 | 1997-07-30 | 北京航空航天大学 | Measuring instrument for airplane fuel quantity |
| CN101226402A (en) * | 2007-12-13 | 2008-07-23 | 陕西飞机工业（集团）有限公司 | Method and apparatus for detecting airplane digital type fuel oil measurement control system |
| CN101930231A (en) * | 2010-08-27 | 2010-12-29 | 武汉航达航空科技发展有限公司 | Test device of fuel controller |
| CN202033073U (en) * | 2011-03-23 | 2011-11-09 | 景博 | Semi-physical simulation platform for digital fuel oil measuring system |
| CN202092736U (en) * | 2011-04-12 | 2011-12-28 | 沈阳圣飞航空科技有限公司 | Sensor tester for fuel quantity of aircrafts |
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- 2012-06-08 CN CN201210188648.7A patent/CN102707739B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2258608Y (en) * | 1995-09-28 | 1997-07-30 | 北京航空航天大学 | Measuring instrument for airplane fuel quantity |
| CN101226402A (en) * | 2007-12-13 | 2008-07-23 | 陕西飞机工业（集团）有限公司 | Method and apparatus for detecting airplane digital type fuel oil measurement control system |
| CN101930231A (en) * | 2010-08-27 | 2010-12-29 | 武汉航达航空科技发展有限公司 | Test device of fuel controller |
| CN202033073U (en) * | 2011-03-23 | 2011-11-09 | 景博 | Semi-physical simulation platform for digital fuel oil measuring system |
| CN202092736U (en) * | 2011-04-12 | 2011-12-28 | 沈阳圣飞航空科技有限公司 | Sensor tester for fuel quantity of aircrafts |
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