CN100580233C - Fuel delivery system and method providing regulated electrical output - Google Patents
Fuel delivery system and method providing regulated electrical output Download PDFInfo
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- CN100580233C CN100580233C CN200580023439A CN200580023439A CN100580233C CN 100580233 C CN100580233 C CN 100580233C CN 200580023439 A CN200580023439 A CN 200580023439A CN 200580023439 A CN200580023439 A CN 200580023439A CN 100580233 C CN100580233 C CN 100580233C
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03G—SPRING, WEIGHT, INERTIA OR LIKE MOTORS; MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOT OTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISE PROVIDED FOR
- F03G7/00—Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for
- F03G7/08—Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for recovering energy derived from swinging, rolling, pitching or like movements, e.g. from the vibrations of a machine
Abstract
In a mobile fuel delivery vehicle, providing bulk aircraft fuel from a pressurized fuel reservoir to an aircraft, a method of regulating electrical output of an electrical power source, includes the steps of: (a) receiving, in a fluid path, the bulk aircraft fuel from the pressurized reservoir; (b) controlling flow rate of the fuel along the fluid path; (c) fluidically rotating a shaft of the electrical power source in the fluid path, in response to step (b); (d) sensing rotation speed of the electrical power source by measuring number of revolutions per a time period; (e) setting a predetermined rotation speed for the electrical power source; (f) measuring a difference between the sensed rotation speed of step (d) and the set predetermined rotation speed of step (e); and (g) modifying the flow rate of the fuel along the fluid path based on step (f) and, in turn, the electrical output of the electrical power source.
Description
Cross reference with related application
The application requires the U.S. Provisional Application No.60/570 in application on May 12nd, 2004, the preference of U.S.'s non-provisional application of not specifying application number of application on May 9th, 243 and 2005.
Technical field
The present invention relates generally to and be used for holding oil sump (pressurizedreservoir) provides portable fuel make up vehicle from bulk fuel (bulk fuel) to aircraft and method from pressurized at the busy airport place.More precisely, the present invention relates to have the bulk fuel delivery control system and the method for feedback control, wherein, drive hydraulically powered power supply, so that regulate electricity output from power supply with stabilized speed.
Background technique
When refueling to aircraft on the landing machine level ground on large-scale airport, usually fuel is offered the fuel tap that is positioned on each aircraft parking with very big pressure by underground mains (main).Fuel vehicle arrives (roll up) aircraft place and is connected between nearest the fuel tap and the fuel filter circuit on the aircraft.
This car is carried out several helps and is provided and pass on the service of fuel.For example, fuel vehicle have hose reel, filter, water isolator and in order to measure for toward the fuel quantity of aircraft so that the flowmeter that charges.Many these or other assistant services need available pressurized air and/or active force.
License to Coatsville December 4 calendar year 2001, the U.S. Patent No. 6 of the Owen Watkins of the General Transervice Co., Ltd of PA, 324,840 disclose a kind of bulk fuel delivery control system, are used for operating hydraulically powered power supply with constant speed.At this its integral body is incorporated herein by reference.
Described in the patent of Watkins, this bulk fuel delivery control system comprises hydraulically powered power supply, and it is used for operation assisting device, and for example air is subjected to press and alternator.Several ambulatory monitors link to each other by the fuel controlling plumbing fixtures with valve.Flow monitors track body flow rate and adjust valve with the flow through flow rate of fluid driven power source of adjusting.
The present invention provides a kind of improved fuel delivery system by the inventor's invention of same position, and it comprises the fluid driven power source with constant speed work.
Summary of the invention
In order to satisfy these needs and other needs, in view of its purposes, the present invention includes mobile fuel transport vehicle, it holds oil sump from fuel under pressure provides aircraft fuel in bulk to aircraft, and it also provides stable electrical output.Method of the present invention is regulated the electricity output of power supply, and may further comprise the steps: (a) in fluid path, receive the aircraft fuel in bulk that holds oil sump from described pressurized; (b) flow rate of the fuel of control on the described fluid path; (c) in response to step (b), the axle of power supply on the described fluid path of Flow Control ground rotation; (d) by measuring the rotating cycle in each time period, detect the rotating speed of described power supply; (e) be described power settings desired speed; (f) difference between the desired speed that sets of the rotating speed that detected of measurement procedure (d) and step (e); And, change, and then change the electricity output of described power supply along the flow rate of the fuel of described fluid path (g) based on step (f).
System and method of the present invention also comprises by velocity transducer being coupled to described power supply and the direct rotating cycle (RPM) that detects the per minute of described power supply, detects the rotating speed of described power supply.Method also comprises exports the equipment that needs electrical input signal in the described vehicle that offers with the electricity from described power supply.
System and method of the present invention also comprises, arrange that on described fluid path valve is so that be controlled at the flow rate of the fuel in the described fluid path, and come control valve electrically according to measured difference between described power supply rotating speed that is detected and the desired speed that sets, thereby change is along the flow rate of the fuel of described fluid path.Described valve can dynamically move at least 5 degree in less than 50 milliseconds, and moves to full close position from fully open position in less than 1 second.
Another one embodiment of the present invention comprises a kind of system and method, and it is adjusted in the electricity output of the power supply on the mobile fuel transport vehicle, and described mobile fuel transport vehicle holds oil sump from fuel under pressure provides aircraft fuel in bulk to aircraft.This another embodiment may further comprise the steps: (a) hold oil sump from described fuel under pressure and receive described aircraft fuel in bulk; (b) described aircraft fuel in bulk is divided into along main fluid path flow and secondary fluid path and flows; (c) control is along the flow rate of the fuel in described main fluid path; (d) in response to step (c), the axle of the described power supply in the described secondary fluid path of Flow Control ground rotation; (e) by measuring the rotating cycle in each time period, detect the rotating speed of described power supply; (f) be described power settings desired speed; (g) difference between the desired speed that sets of the rotating speed that detected of measurement procedure (e) and step (f); And, change, and then change the electricity output of described power supply along the flow rate of the fuel in described main fluid path (h) based on step (g).
An embodiment more of the present invention is a kind of mobile fuel transport vehicle, and it is used for holding oil sump from fuel under pressure and provides aircraft fuel in bulk to aircraft.A kind of method of the present invention is regulated the electricity output of alternator by the turbo machine in described vehicle.Said method comprising the steps of: (a) hold oil sump and receive described aircraft fuel in bulk from described fuel under pressure; (b) described aircraft fuel in bulk is divided into along main fluid path flow and secondary fluid path and flows; (c) control is along the flow rate of the fuel in described main fluid path; (d) in response to step (c), the axle of the described turbo machine in the described secondary fluid path of Flow Control ground rotation; (e) rotating speed of the described turbo machine of detection; (f) be that described turbo machine is set desired speed; (g) difference between the desired speed that sets of the rotating speed that detected of measurement procedure (e) and step (f); And, change, and then change the electricity output of described alternator along the flow rate of the fuel in described main fluid path (h) based on step (g).Described method also comprises, carries out the control loop algorithm in FPGA control (PLC), to control the rotating speed of described turbo machine.The rotating speed of controlling described turbo machine comprises by changing by the output loading on the described turbine driven described alternator, controls the rotating speed of described turbo machine so that it is near constant.
Should be appreciated that the time, above-mentioned whole describe and following detailed description is exemplary for the present invention, rather than limit it.
Description of drawings
When the detailed description below reading in conjunction with the accompanying drawings, the present invention will be by best understanding.Comprise in the accompanying drawings:
Fig. 1 is the planimetric map of leading supply vehicle, and it is used for holding oil sump from fuel and provides bulk fuel to aircraft;
Fig. 2 is according to an embodiment of the invention, the schematic block diagram of the bulk fuel delivery control system of fuel make up car among Fig. 1;
Fig. 3 A and 3B are the schematic block diagrams that illustrates by the performed exemplary ratio of the programmable logic controller (PLC) that comprises in the fuel delivery system of Fig. 2 (PLC), integration, differential control;
Fig. 4 A-4G describes according to embodiments of the invention, by the logical flow chart of the performed method of the present invention of the PLC of Fig. 2; And
Fig. 5 is according to another embodiment of the present invention, the schematic block diagram of the bulk fuel delivery control system of the fuel make up vehicle of Fig. 1.
Embodiment
The invention provides a kind of bulk fuel delivery control system, wherein, drive fluid driven power source by fuel stream with constant speed, so that the auxiliary device of action need firm power.
With particular reference to accompanying drawing, Fig. 1 shows fuel make up vehicle 6 now.Described fuel make up vehicle is generally used for fuel is guided to aircraft 14 from fuel under pressure tap 4.This tap provides bulk fuel from the underground oil sump 2 that holds of fuel make up facility to the fuel tank (not shown) of aircraft.It should be appreciated by those skilled in the art that holding oil sump 2 also can be positioned at the face of land, hold the oil sump source such as moving.
The first fuel transport pipe (fueling couple) 10 of fuel make up vehicle 6 is connected to tap, is used for accepting fuel from holding oil sump 2.This transport pipe keeps fluid to be connected with the bulk fuel delivery control system 8 of fuel make up vehicle 6.Bulk fuel delivery control system 8 comprises the fluid driven power source 28 (for example, the turbo machine shown in Fig. 2 28) that is used for operation assisting device.The second fuel transport pipe 12 keeps fluid to be connected with bulk fuel delivery control system 8, and it is connected to aircraft 14 to carry out fuel make up.By this method, fuel under pressure flows in the bulk fuel delivery control system 8 of fuel make up car 6, comes to refuel for aircraft 14.
The inventor finds that situation shown in Figure 1 has unique problem.First problem is from the fluid flow pressure that is changing all the time of holding oil sump 2.Because the quantity of operating fuel make up vehicle changes, so the flow pressure of fluid also can change.Correspondingly, the source pressure of fuel transport pipe 10 also is constantly to change.The inlet of transport pipe 10 (the perhaps inlet among Fig. 2 22) pressure can approximately change between the 50-250psi.For example, inlet pressure may be reduced to 60psi from 100psi in less than 3 seconds.Second problem is the flow rate of variation that is connected to the nozzle (not shown) place of fuel transport pipe 12.Along with aircraft fuel tank is filled, nozzle pressure can constantly change.For security consideration, nozzle pressure (oil groove pressure) is limited in 40psi.Yet nozzle pressure may increase to 100psi in about 0.5 second.The 3rd problem is the electrical load that is connected to primary power supply, and it also is constantly to change.Primary power supply, alternator for example may have the different loads value of wide range.This load typically has the peak value up to 60 amperes, and may reduce to 5 amperes low.Along with the fuel make up vehicle is shifted to another from an airplane and come supply energy source, load is fluctuation thereupon also.Such as, the lifting box on the fuel make up vehicle (lift basket) is when being activated, and almost moment increases sharply to 40 amperes in load.Yet, after lifting box is closed, load almost moment 40 amperes of prompt drops.Battery (load) by the alternator charging on the vehicle needs more electric current to recharge.Along with the variation of electrical load, drive the necessary horsepower of fluid driven power source 28 (for example, the turbo machine among Fig. 2 28) number and also change thereupon.The invention solves these problems.
Refer now to Fig. 2, will describe the bulk fuel delivery control system 8 of configuration according to the present invention.Flow through as the inlet 22 of bulk fuel pipeline by the bulk fuel that the first fuel transport pipe 10 provides.Then, bulk fuel is divided into along the main fluid path with along secondary fluid path, is designated as 24 and 26 respectively.A part that provides to the fuel of inlet 22 is provided secondary fluid path 26.The remainder of bulk fuel is sent to rotary control valve 32 along main fluid path 24.
It should be understood that fuel quantity in main fluid path and the secondary fluid path depends on the flow rate at 22 places that enter the mouth.If this flow rate is reduced to 250 gpms following (for example), then most of fuel secondary fluid path of flowing through, this is because the speed that control system attempts to regulate turbo machine.
It should be understood that term " main fluid path " and " secondary fluid path " and do not mean that most of fuel to flow through the main fluid path and have only the fraction fuel secondary fluid path of flowing through.In fact, according to the flow rate at inlet 22 places, secondary fluid path may occupy most of fluid, and may have only the fraction fuel main fluid path of flowing through, as mentioned above.Opposite situation also is possible.
Secondary fluid path 26 is coupled to fluid driven power source, such as turbo machine 28.When outlet 40 from inlet 22 direction of flow when moving, the axle of turbo machine 28 will rotate.The rotation of the axle of turbo machine 28 causes the rotation of pulley 29, and then makes engine rotation in the alternator 30.Alternator 30 provides about 56 volts constant charge voltage to battery, and described battery provides 48 volts specified to export to various devices and other loads, and aircraft fuel supply situation is needed just for this.Alternator 30 provides the mode of burning voltage output (Vout) will be described below.
Main fluid path 24 is connected to rotary control valve 32, with fuel from enter the mouth 22 be sent to the outlet 40.The valve location of servomotor 34 control rotary control valves 32.The valve location of closing fully can force more fuel from 22 secondary fluid path 26 of flowing through that enter the mouth.On the other hand, the valve location of opening fully can force still less fuel to flow through secondary fluid path and make the more fuel main fluid path 24 of flowing through.According to embodiments of the invention, the valve location of rotary control valve can by servomotor 34 adopt linear method open entirely and complete closure between regulate.
As will be explained, fuel enters secondary fluid path 26, and beginning rotary turbine machine 28 and alternator 30.Along with turbo machine rotates, two velocity transducers 36 and 38 (Prox1 and Prox2 as shown in FIG.) send a signal to FPGA control (PLC) 52.Prox2 detects turbo machine 28 and is rotating.Prox1 detects the rotating speed of turbo machine 28 or the rotating cycle (RPM) of per minute, provides the input signal of simulation RPM value as PLC52 by frequency converter 46 then.
These sensors may be inductance near switch, such as, by Turck (parts No.BIl, 5-G08-AP6X-H1341) or Pepperl+fuchs (parts No.NBB240-E2-V1) produce.
Servo driver 54 is the Interface Modules between PLC52 and the servomotor 34, and it provides positioning control to servomotor 34, and then the valve location of control rotary control valve 32.The example of rotary control valve can be the eccentric plug by the model No.35x12 of Masonellan production.This valve can be controlled pressure well in required dynamic range.It is enough powerful to it should be understood that servomotor needs, so that can be with the valve location of the Torque Control rotary control valve of 100 foot-pounds.
Exemplary servomotor can be the Exlar SLG90 that is produced by Exlars, or the another kind of similar servomotor of being produced by Bayside Motion Control.This servomotor can turn 90 degrees (from the fully open position to complete closed position) less than 1 second inward turning.This rotation allows in less than 1 second the valve location of rotary control valve to be closed from opening fully to move to fully.This servomotor can be spent in less than 50 milliseconds at least in (approximately) rotation 5.As will be discussed, control loop of the present invention was operated with about 50 milliseconds cycle.This servomotor is fit to this uniqueness and situation of difficult, allows moment with about 100 foot-pounds valve location to be moved at least 5 degree in less than 50 milliseconds.
The inventor finds that the servomotor 34 (or servomotor among Fig. 5 1034) of Fig. 1 can (0.9 second) rotate about 90 degree in less than 1 second, perhaps in less than 50 milliseconds, move about 5 degree (preferably), so that control the uniqueness and the situation of difficult of above-mentioned fuel delivery system fully.The slower rotating speed of rotary control valve also can be suitable for this fuel delivery system.For example, servomotor can be spent in less than 2 seconds in (1.8 seconds) rotation about 90, perhaps rotates about 2.5 degree and still be suitable for this fuel delivery system (being more preferably) in less than 50 milliseconds.As another embodiment, servomotor can rotate about 90 degree and still be suitable for this fuel delivery system in 3 seconds.Any rotating speed that turn 90 degrees about 3 seconds inward turnings that is slower than may not be used for the control algorithm that PLC52 carries out.As will be described, turbo machine is set to desired speed, such as 2200RPM.Under this rotating speed of turbo machine, turbo machine is no problem usually.Yet on this speed of turbo machine, turbo machine will have problems and can work the mischief (for example) to hearing.If preferred servomotor rotate about 90 degree in less than 1 second, then turbo machine can be set to 2200RPM and not need the speed of oblique line speed-raising (ramp up) turbo machine lentamente and at the rotating speed of each some place inspection turbo machine of oblique line speed-raising.For example, if servomotor is rotated with the low speed that turn 90 degrees 3 to 5 seconds (approximately) inward turnings, then the speed-raising of the oblique line of speed need be realized by PLC52.The speed-raising of this oblique line for example can be included in 700RPM, 1500RPM and final 2200RPM place and stop and check rotating speed.Similarly, if the desired speed of turbo machine be 700RPM and turbo machine with the 2400RPM rotation, then need oblique line reduction of speed (ramp down) process, stop when described oblique line reduction of speed process is included in the oblique line reduction of speed and check rotating speed.On the other hand, turn 90 degrees, then do not need oblique line speed-raising point and oblique line reduction of speed point if servomotor is controlled at less than 1 second inward turning.This has simplified the performed algorithm of PLC52.
PLC compares RPM (being detected by Prox1) with the set point RPM (variate-value that can set for example is worth 2000RPM) that is scheduled in program.Predetermined set point will be provided to PID subroutine (will introduce after a while), and this PID subroutine is calculated simulation output (being depicted as the analog position of Fig. 2).Should simulate output provides to servo driver 54, servo driver 54 and then control servomotor 34.If the RPM of turbo machine 28 is too low, then Spin Control is driven 32 valve and be placed on position towards closure.Yet,, valve is placed on towards the position of opening if RPM is too high.Along with the variation of valve location, the speed of turbo machine changes thereupon, and then can be detected and feed back to PLC52 by Prox1.
It should be understood that the waveform that speed produced (speed and time) by turbo machine comprises the vibration that is weakening.When turbine speed departed from predetermined set point, the feedback signal that is sent to valve was proofreaied and correct the RPM of turbo machine towards predetermined set-points.Along with oscillation amplitude decrescence, feedback signal in time continues.The speed of turbo machine is carried out timing, oscillation amplitude all can descend, and is stabilized in predetermined set-point value up to the RPM of turbo machine at every turn.The present invention advantageously keeps the RPM of approximately constant under the situation of the load variations of inlet fuel pressures and alternator.The present invention with the speed controlling of turbo machine near constant speed, thereby make it be independent of its dependent variable of native system.To such an extent as to (exception to this is that the too low servomotor of fuel flow pressure has cut out changeover valve fully, causes all the flow through situation of secondary fluid path of all fuel.)
Continue the description of Fig. 2, fork arm (deadman) switch 42, fork arm control 56, voltage regulator enable 50, recloser 44 and hand switch 48 are arranged shown in the figure.Cross-bar switch 42 is activated by the operator, so that the fork arm input signal to be provided to PLC52.As long as the operator supresses cross-bar switch, the fork arm input signal just will exist always.And then when safety condition can satisfy, PLC provided the fork arm output signal.This fork arm output is sent to fork arm control module 56.The fork arm control module provides actuating signal so that fuel can flow into inlet 22 from holding oil sump 2 (Fig. 1).
Hand switch 48 provides power by the command signal from PLC52 and servo driver 54, and the valve of rotary driving control valve 32 is to the fully open position.This is the consideration in the Security, guarantees in system's 8 initialization start-up courses the most inlet fuel main fluid path 24 of flowing through.It should be understood that hand switch 48 can be omitted, and whole system can be moved under automatic mode.
As shown in the figure, automatic mode is started by recloser 44.When automatic mode started, the control loop between turbo machine 28, PLC52, servo driver 54, servomotor 34 and the rotary control valve 32 was born the control to system's 8 operations.Algorithm of the present invention (will explain after a while) is effective for the near constant RPM that keeps turbo machine.The approaching constant rotation of turbo machine provides about 56 volts constant charging voltage to the battery with 48 volts of specified output (not shown).
Finish the description to Fig. 2, voltage regulator enable module 50 is by starting the magnetic field of alternator 30 from the control signal of PLC52.This makes alternator begin rotation.To such an extent as to dropping in the fuel pressures at inlet 22 places enough does not lowly have under the case conditions that enough moment starts turbo machine rotation, this to begin to rotate be useful.
The performed various algorithms of PLC52 will be described now.As shown in Figure 3A, one of these algorithms are that PID calculates.PID calculates control output signal, described control output signal are provided is ratio (P), integration (I) and the differential term sum of the institute's error of calculations in single counter circuit.In each calculating of pid loop, all receive same error signal value for every.
P, the I in PID calculates and the role of D item are as follows respectively:
(1) ratio one ratio (or oblique line) item is corresponding pari passu with the current size of error.The value of the proportional of each PID calculating is calculated in this loop control unit.When error was zero, proportional also was zero.
(2) integration-integration (or reseting) item carries out integration (summation) to error amount.The PID first time after entering automatic mode calculates, and integrator constantly calculates the operation summation to error amount.In the PID equation, when the loop reached balance and do not have error, described operation summation just expression kept the necessary constant output of process variables (PV) current location.
(3) response was made in the variation of institute's use error during differential one differential (or ratio) item calculated with respect to previous PID the error current value.Its task is may increasing of predicated error, and in advance output is produced contribution.
P, I and the collaborative work of D item, any one can be set to zero.
Fig. 3 B shows the schematic block diagram of the PID calculating of being carried out by PLC, usually this figure is appointed as 70.As shown in the figure, process PID calculates and comprises set point and process variables (PV), and it is as the input signal of two separation.Set point is that the user is adjustable, for example, can be set as 2000RPM.Process variables (PV) is the actual RPM by the current measurement of the turbo machine of proximity detector 1 (Prox1) detection.The generated error item is subtracted each other in these two inputs mutually.Error term is handled by P, I and D, and it is sued for peace produces the control output signal.As shown in the figure, this control output signal sends to servo driver 54 from PLC52 (Fig. 2).Then this signal is sent to servomotor 34, the valve location of servomotor 34 and then control rotary control valve 32.
Next with reference to figure 4A-4G, as shown in the figure, method 400 is used as exemplary embodiment of the present invention.At first with reference to figure 4A, the method is from step 410.The used variable of method of the present invention is initialised in step 411.In step 412, come it is carried out initialization by servomotor being set to original position.The method enters step 413 then, and in step 413, treatment of simulated is to the conversion of numeral and digital to analogy.
Next method is calculated at the velocity process PID of step 414 with 50 milliseconds.Carry out the second speed monitoring circuit in step 415 with 1 millisecond speed.Speed and Fault Control algorithm are carried out in step 416.Then, step 413 is got back to by method branch, repeats this process.
Below with reference to Fig. 4 B-4G each step of being mentioned among Fig. 4 A is described in detail.With reference to figure 4B,, in this step, be its initial value with the PID specification of variables in the initialization of step 420 beginning variable.The PID variable comprises set point, gains, resets, ratio, sample rate and manual position.For example, set point is set as 2000RPM.Gain is the proportionality constant that is used for the oblique line of Fig. 3 A, and it is set to tilting value 2.3.Reset the integral loop calculation that is used for Fig. 3 A.The value of reseting was set to 0.04 minute.So, carry out integration according to 0.04 minute the time lag.Ratio, or differential are set to 0.001 (but also can be made as 0) in present embodiment of the present invention.Sample rate is set to 50 milliseconds.Therefore, in 50 milliseconds the time lag, carry out PID and calculate, and per 50 milliseconds of time lags repeat once.Manual position is set to 0.When manual position was false (0), pid loop was activated.Yet working as manual position is true time, and pid loop may be closed.
After setting the PID variable, method branches to step 421, sets second speed monitor unit sample rate.In exemplary embodiment of the present invention, the second speed sample rate is set to 1 millisecond of time lag.Step 422 resets speed and Fault Control is set, as the part of initialize process.
Next with reference to figure 4C, for security consideration, method 400 is set at original position (home) with servo position.By step 430 beginning, method provides and starts servo output (as directed 54 startup drives from PLC52 to servo driver).Step 431 control servomotor 34 is to original position.Method verifies that by judgement frame 432 servomotor is in original position really.Method continues to check by cycling back to step 431 whether servo driver is in original position.After judgement frame 432 drew the conclusion that servomotor is in original position, method branched to step 433, and notice PLC52 servomotor has been ready to controlled.
Next with reference to figure 4D, method 400 provide analogue signal to digital signal conversion and opposite digital signal to the conversion of analogue signal.By step 440 beginning, method inputs to the PLC algorithm with analogue signal from frequency converter 46 (being appointed as simulation RPM Fig. 2).Step 441 with analog input signal divided by its resolution.Then, step 442 multiplies each other signal and its full scale RPM value of step 441 output.In step 443 the result of calculation value is stored as RPM-IN.
In step 444 the PID output signal is offered algorithm.Step 445 multiplies each other PID output with its full scale valve location.Step 446 is stored as output signal with the PID output value.
Next with reference to figure 4E, method 400 is carried out PID and is calculated.By 453 beginnings of judgement frame, method determines whether manual input opens.If manually input is opened, then method branches to step 457, PID output is set at equal manual position.If judgement frame 453 determines that manually input is closed, method branches to judgement frame 455, carries out PID and calculates.The output that step 456 provides PID to calculate.
It should be understood that the consideration for Security, only when method was not in manual position, method 400 was just carried out PID and is calculated.
Next with reference to figure 4F, method 400 is carried out second speed and is monitored.By step 460 beginning, input RPM2 signal (second speed of being undertaken by velocity transducer 2 monitors) is as the signal that inputs to PLC52.Step 461 beginning is counted the positive transfer (position transition) of RPM2 signal with 1 millisecond speed.This counting of step 462 storage, and when the positive transfer of RPM2 takes place once more, reset counter.Judgement frame 463 determines whether the Cumulative time is shorter than 2 seconds.If the Cumulative time, then step 461 was got back to by method branch less than 2 seconds, continue stored counts.Be longer than 2 seconds or equal 2 seconds (value is 2000) if the judgement frame is determined the Cumulative time, method branches to step 464, stops counting.
Below with reference to Fig. 4 G, this method provides speed and wrong control by step 470 beginning.Method 400 determines whether the Cumulative time equals 2 seconds.If it equals 2 seconds, the no_speed sign is set then.Step 471 determines that whether the Cumulative time is less than 2 seconds.If it was less than 2 seconds, then start the operation chronograph, close up to deadman_in.Step 472 determines whether this process is moved, and whether deadman_in be activated, and the RPM input is provided with the no_RPM sign then whether less than 100 or there is not speed.
Step 473 determines that whether the RPM input is more than or equal to 2500.If it is more than or equal to 2500, the high_high sign then is set, it shows that RPM is too high.Whether step 474 determines whether the fork arm input is activated, and whether LCR input (rice) open, and whether the high_high sign close, and open from the preparation input of servo driver, and whether no_RPM close, and sets fork arm then and exports.
Step 475 determines that when d/d the fork arm input is, if the fork arm input is released, then this method keeps deadman off to be masked as unlatching, and deadman off time-delay chronograph becomes very after 5 seconds.
Then, method 400 enters judgement frame 476.Judgement frame 476 determines whether hand switch is opened.If its unlatching, then step 477 is provided with manual door bolt and manual position is moved to output terminal.Close if judgement frame 476 is determined hand switch, then method enters judgement frame 478.
If judgement frame 478 is determined the RPM input less than 2350, then method enters judgement frame 479.Judgement frame 479 determines whether the no_RPM switch is opened.If this switch open, then this method branches to step 477, manual door bolt is set and manual position is moved to output terminal.
Close if judgement frame 479 is determined the no_RPM switch, then method branches to step 480 and enters the subroutine that analog to digital and digital to analogy conversion are provided.
Next forward another embodiment of the present invention to, with reference to figure 5.As shown in the figure, system 1300 comprises rotary control valve 1306, and rotary control valve 1306 is placed on the fluid flow path identical with turbo machine 1302.Thereby the embodiment's of system difference is shown in present embodiment and Fig. 2, and rotary control valve is arranged in the fluid flow path that parallels with the fluid flow path that is back to the driving turbo machine among Fig. 2.Servomotor 1304 uses the valve location from the command signal control rotary control valve of PLC.Element is similar shown in other elements among Fig. 5 and Fig. 2.
In the embodiment shown in fig. 5, the pilot-motor-operated of rotary control valve is opposite with operation described in Fig. 2 system.Rotary control valve is shifted to full open position so that allow more fuel inflow paths 1308, itself so turbo machine quickened.Rotary control valve is shifted to the contract fully position so that allow fuel inflow path 1308 still less, itself so turbo machine slowed down.
Detailed description at the employing ladder grid configuration of many subroutines shown in Fig. 2 and Fig. 5, that carried out by PLC is provided in appendix, has been used for its description this whole introducing.Although illustrate and describe with reference to specific embodiment at this, the present invention will limit details.Opposite, in the scope of the equivalent of claim and under the situation that does not deviate from spirit of the present invention, can carry out various modifications to details.
Claims (21)
1, provide the mobile fuel transport vehicle of aircraft fuel in bulk to aircraft being used for holding oil sump from fuel under pressure, a kind of method that is used to regulate the electricity output of the turbine driven alternator that fuel under pressure drives comprises following steps:
(a) in fluid path, receive the aircraft fuel described in bulk that holds oil sump from described fuel under pressure;
(b) flow rate of the described in bulk aircraft fuel of control on the described fluid path;
(c) in response to step (b), the axle of the described alternator on the described fluid path of Flow Control ground rotation;
(d), detect the rotating speed of the axle of described alternator by measuring the rotating cycle of described axle in each time period;
(e) be the axle setting desired speed of described alternator;
(f) difference between the desired speed that sets of the rotating speed that detected of measurement procedure (d) and step (e); And
(g), change along the flow rate of the described fuel of described fluid path, and then change the electricity output of described alternator based on step (f).
2, the method for claim 1, wherein
The rotating speed that detects the axle of described alternator comprises, velocity transducer is coupled to described alternator, and
Directly detect the rotating cycle (RPM) of the per minute of described axle.
3, method as claimed in claim 2, wherein
Described velocity transducer is coupled to described alternator comprises, described velocity transducer is connected to described alternator, and described alternator is installed on the described vehicle.
4, the method for claim 1 comprises step:
To described vehicle, need the equipment of electrical input signal that electricity output is provided from described alternator.
5, the method for claim 1, wherein change along the flow rate of the described fuel of described fluid path and comprise:
On described fluid path, place valve, be used for being controlled at the flow rate of the described fuel of described fluid path, and
According to the described alternator that is detected the axle rotating speed and the difference between the described desired speed that sets, operate described valve electrically.
6, method as claimed in claim 5 comprises
With rotating speeds, dynamically move described valve 90 degree less than at least 5 degree in about 50 milliseconds.
7, method as claimed in claim 5 comprises
In less than about 1 second, dynamically described valve is moved to the contract fully position from full open position.
8, provide the mobile fuel transport vehicle of aircraft fuel in bulk to aircraft being used for holding oil sump from fuel under pressure, a kind of method that is used to regulate the electricity output of the turbine driven alternator that fuel under pressure drives comprises following steps:
(a) hold oil sump from described fuel under pressure and receive described aircraft fuel in bulk;
(b) described aircraft fuel in bulk is divided into along main fluid path flow and mobile along secondary fluid path;
(c) control is along the flow rate of the fuel in described main fluid path;
(d), be rotated in to Flow Control the described alternator in the described secondary fluid path in response to step (c);
(e), detect the rotating speed of the axle of described alternator by measuring the rotating cycle of described axle in each time period;
(f) be the axle setting desired speed of described alternator;
(g) difference between the desired speed that sets of the rotating speed that detected of measurement procedure (e) and step (f); And
(h), change along the flow rate of the described fuel in described main fluid path, and then change the electricity output of described alternator based on step (g).
9, method as claimed in claim 8, wherein
The rotating speed that detects the axle of described alternator comprises, velocity transducer is coupled to described alternator, and
Directly detect the rotating cycle (RPM) of the per minute of described axle.
10, method as claimed in claim 8 comprises step
To described vehicle, need the equipment of electrical input signal that electricity output is provided from described alternator.
11, method as claimed in claim 8, wherein, change comprises along the flow rate of the described fuel in described main fluid path:
On described main fluid path, place valve, be used for being controlled at the flow rate of the described fuel in described main fluid path, and
According to the described alternator that is detected the axle rotating speed and the difference between the described desired speed that sets, operate described valve electrically.
12, method as claimed in claim 11 comprises
With rotating speeds, dynamically move described valve 90 degree less than at least 5 degree in about 50 milliseconds.
13, method as claimed in claim 11 comprises
In less than about 1 second, dynamically described valve is moved to the contract fully position from full open position.
14, provide the mobile fuel transport vehicle of aircraft fuel in bulk to aircraft being used for holding oil sump from fuel under pressure, a kind of method that is used to regulate by the electricity output of turbine driven alternator, described turbo machine is driven by fuel under pressure, and described method comprises following steps:
(a) hold oil sump from described fuel under pressure and receive described aircraft fuel in bulk;
(b) described aircraft fuel in bulk is divided into along main fluid path flow and mobile along secondary fluid path;
(c) control is along the flow rate of the fuel in described main fluid path;
(d), be rotated in to Flow Control the axle of the described turbo machine in the described secondary fluid path in response to step (c);
(e) rotating speed of the axle of the described turbo machine of detection;
(f) be the axle setting desired speed of described turbo machine;
(g) difference between the desired speed that sets of the rotating speed that detected of measurement procedure (e) and step (f); And
(h), change along the flow rate of the described fuel in described main fluid path, and then change the electricity output of described alternator based on step (g).
15, method as claimed in claim 14, wherein, the rotating speed of controlling the axle of described turbo machine comprises
In FPGA control (PLC), carry out the control loop algorithm.
16, method as claimed in claim 14, wherein, the rotating speed of controlling the axle of described turbo machine comprises
Under the different pressure situations that fuel in described main fluid path and described secondary fluid path flows, the rotating speed of the axle of described turbo machine is controlled near constant speed.
17, method as claimed in claim 14, wherein, the rotating speed of controlling the axle of described turbo machine comprises
Under situation about changing, the rotating speed of the axle of described turbo machine is controlled near constant speed by the output loading of described turbine driven alternator.
18, method as claimed in claim 14, wherein,
The rotating speed that detects the axle of described turbo machine comprises, velocity transducer is coupled to described turbo machine, and
Directly detect the rotating cycle (RPM) of per minute of the axle of described turbo machine.
19, method as claimed in claim 14 comprises step
Provide electricity output from described alternator to battery, described battery needs the equipment of electrical input signal that electricity output is provided in described vehicle.
20, method as claimed in claim 14, wherein change along the flow rate of the described fuel in described main fluid path and comprise:
On described main fluid path, place valve, be used for being controlled at the flow rate of the described fuel in described main fluid path, and
According to the described turbo machine that is detected the axle rotating speed and the difference between the described desired speed that sets, operate described valve electrically.
21, a kind ofly be used for holding oil sump from fuel under pressure and provide the mobile fuel transport vehicle of aircraft fuel in bulk to aircraft, it comprises
Fluid path, it is used for holding oil sump from described fuel under pressure and receives described aircraft fuel in bulk;
Valve, it is placed in the described fluid path, in order to the flow rate of control along the described aircraft fuel in bulk of described fluid path;
Turbo machine, it is used to drive alternator and generates stable electrical power, is coupled to Flow Control the aircraft fuel described in bulk in the described fluid path;
Speed probe, it is used for detecting described turbine speeds by measuring the rotating cycle of each described turbo machine of time period;
Controller, it is coupled to described fluid path and described speed probe, is used to control the desired speed of described turbo machine;
Wherein, rotating speed and the difference desired speed of described turbo machine between the rotating speed of controlling described turbo machine of described controller by measuring the described turbo machine detected changed along the flow rate of the described fuel of described fluid path by the position that change is positioned at the described valve on the described fluid path then.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US57024304P | 2004-05-12 | 2004-05-12 | |
| US60/570,243 | 2004-05-12 | ||
| US11/124,720 | 2005-05-09 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101023252A CN101023252A (en) | 2007-08-22 |
| CN100580233C true CN100580233C (en) | 2010-01-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200580023439A Expired - Fee Related CN100580233C (en) | 2004-05-12 | 2005-05-10 | Fuel delivery system and method providing regulated electrical output |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100580233C (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110252130A1 (en) * | 2010-04-12 | 2011-10-13 | Jeyhan Karaoguz | System and method for managing a network of user-selectable devices |
| CN110262574B (en) * | 2019-06-19 | 2022-03-11 | 中丝营口化工品港储有限公司 | Tank car operation flow rate integrated monitoring system |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5028017A (en) * | 1989-08-08 | 1991-07-02 | Federal Express Corporation | Mobile system for deicing aircraft |
-
2005
- 2005-05-10 CN CN200580023439A patent/CN100580233C/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5028017A (en) * | 1989-08-08 | 1991-07-02 | Federal Express Corporation | Mobile system for deicing aircraft |
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| CN101023252A (en) | 2007-08-22 |
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