CN104234821A - Aviation supercharger control system and adjusting method thereof - Google Patents
Aviation supercharger control system and adjusting method thereof Download PDFInfo
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- CN104234821A CN104234821A CN201410479862.7A CN201410479862A CN104234821A CN 104234821 A CN104234821 A CN 104234821A CN 201410479862 A CN201410479862 A CN 201410479862A CN 104234821 A CN104234821 A CN 104234821A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention provides an aviation engine supercharger pressure closed-loop control system, and belongs to the field of adjusting of an aviation piston engine air inlet system. According to the invention, a motor-direct-driving position servo system is adopted to solve the coupling problem when a waste gate is adopted for controlling supercharge and the supercharge is utilized to adjust the waste gate coupling, the control is more direct, the adjusting range is wider, and the response speed is higher; meanwhile, the method adopted by the system is characterized in that transient correction is performed on the action of the waste gate according to the height of the atmosphere and the change rate of the position of a restrictor, and the transient fast control effect on supercharge pressure is ensured. The control system provided by the invention mainly comprises the position servo driving system consisting of a motor for direct driving and a reduction gear, an atmosphere pressure sensor, an atmosphere temperature sensor, a supercharge pressure sensor, a supercharge temperature sensor, a supercharger rotation speed sensor, an engine rotation speed sensor, a restrictor position sensor, a waste gate position sensor, and a controller consisting of a micro-computer provided with an adjusting algorithm and an interface circuit.
Description
Technical field
The present invention proposes a kind of aviation piston engine turbo-charger boost pressure closed loop control system and regulating method thereof, belong to piston engine air inlet adjustment and control field, may be used for General Aviation, unmanned plane and other aeroengine aspects, the High aititude power that also can be used in Ground Vehicle engine power recovers.This control system final controlling element adopts motor direct-drive, fast response time, and level of integration is high; The adjustment algorithm that this control system adopts considers atmospheric pressure and engine throttle position and both variance ratio simultaneously, is realizing, on the basis that boost pressure stable state controls, ensure that the transient control effect of boost pressure.
Background technique
Turbosupercharging puies forward high-power effective means as piston engine, is used widely in the engine power system of ground, comprises diesel engine and petrol engine.But in aerospace applications, now substantially still based on petrol engine, and fuel system major part is still in Carburetor mode, electronic fuel injection technology uses few.In the above conditions, to petrol engine carry out pressurization control realize power recover or improve ceiling more difficult, main cause one be existing pressurization control adopt be mechanical adjustment control mode, control range is very narrow, control dumb, also need the pressure protective device added; Two is in aviation piston engine running, and highly there is transient changing situation, external atmospheric pressure also exists transient changing, adopts mechanic adjustment unit to be difficult to realize supercharging fast transient and controls.
The pressurization system mechanical adjusting mechanism principle of existing use in enormous quantities as shown in Figure 1.Flexible sheet and spring form controlling mechanism, and before wherein an end receives the closure of supercharger air compressor outlet and engine charge part, an other end receives external pressure.The difference that what this kind of regulative mode regulated in fact is between boost pressure and external pressure, this difference determines the size of wastegate aperture.This uses on Surface power drive is out of question, because the change of Surface power drive Environmental Conditions pressure is not very greatly, such boost pressure can realize compared with stablizing within the scope of minor swing.But this kind of mode obviously can not solve the problem of aerospace applications environment, aeroengine is climbed in process and highly be there is sharply situation of change, can not keep constant according to the boost pressure of above-mentioned regulative mode, this, for the motor adopting supplying oil of carburetor mode, cannot work substantially.In addition, in the motor of existing ground, while adopting supercharging technology, substantially have employed electronic throttle, in order to ensure the mapping of motor, must avoid occurring the superpressure situation in closure transient state reduction situation, therefore additionally needing the safety valve increasing supercharger air compressor outlet, which increase the complexity of system, also do not meet the efficient and light weight requirement of aeroengine.Can say, existing pure mechanical adjustment mode can not meet aerospace applications requirement completely.
Except the regulative mode of above pure machinery, in order to improve degree of flexibility, another mode existed now is vacuum conditions mode, and it realizes principle as shown in Figure 2 substantially.This kind of mode is in fact in pure machinery type, adds automatically controlled regulating power, is realized by pneumatic adjustment module.Pneumatic adjustment module one termination air, one termination supercharger air compressor outlet, its working method realizes UNICOM of diaphragm chamber air or blower outlet by the switch of wherein solenoid valve, the proportion adjustment of both on times pressure of diaphragm chamber, thus can realize the adjustment of wastegate aperture.The pressure that this kind of mode can realize in certain limit regulates, but should be noted that the range regulation that can not realize outside boost pressure, and there is the circulatory problems adopting pressurization control wastegate and utilize wastegate adjustment supercharging in this kind of regulative mode, cannot apply in aviation piston engine.
Because existing pressurized machine final controlling element is all above-mentioned two kinds of modes, therefore regulating and controlling algorithm also all realizes based on above final controlling element.CN101082318B patent proposes a kind of control system controlling turbocharging internal-combustion engines suction pressure for different altitude height, but the engine boost pressure that this patent mainly solves high altitude localities controls, and does not consider the transient changing of altitude; And namely the final controlling element of this patent employing is the pneumatic actuator of the electrical adjustment discussed above, the power resources of pneumatic actuator are in boost pressure and external pressure, existing utilizes wastegate to control supercharging and to utilize supercharging to drive the Recycling of wastegate, and wastegate runs and is difficult to ensure ideal movements situation.The shortcoming of this kind of driving mode also has discussion in patent CN102191999A.CN101994594A patent regulates from throttle valve and pressurized machine Comprehensive Control, realize comprehensively taking into account of power character and Economy, this regulating method requires that motor must with electronic throttle and pressurized machine adjusting device (wastegate, variable-geometry, variable-nozzle etc.), obviously this kind of mode is in the aeroengine still adopting supplying oil of carburetor mode, cannot use.CN102297015A patent is then that emphasis solves the situation of pressurized machine adjusting actuator beyond control range, regulating algorithm by limiting according to engine operating condition pressurized machine final controlling element regulation range, adopting the adjustment different disposal of integration item being realized to control range simultaneously; This patent mainly concentrates on the pressurization control on Surface power drive, is not suitable for the aviation piston engine of variable height.Therefore, the state of the art of comprehensive existing supercharger systems and unique Environmental Conditions of aviation piston engine, the present invention proposes a kind of boost pressure closed loop control system based on motor direct-drive, and the free adjusting on a large scale that can realize boost pressure also can realize the quick control effects of transient state of boost pressure.
Summary of the invention
The present invention proposes a kind of aviation piston engine Pressure control system and regulating method thereof, stable gas handling system is provided for adopting the aviation piston engine of supplying oil of carburetor mode, its regulating and controlling method emphasis solves two problems, and one is that existing control system actuator response speed is slow, regulation range is narrow; Two is in motor height and throttle position transient changing situation, the transient state quick adjustment of boost pressure.The present invention can ensure that aviation piston engine meets starting, climbs, cruises and stable boost pressure requirement in descent.
The control system that the present invention proposes comprises sensor, controller and final controlling element three part, and wherein key core is the final controlling element of electric-machine directly-driven and corresponding control algorithm.Sensor section according to motor, pressurized machine and atmosphere environment three aspect divide, engine sensor comprises engine speed, throttle opening; Pressurized machine sensor comprises supercharger speed, boost pressure, wastegate aperture; Atmosphere environment comprises atmospheric temperature and pressure.Controller is the microcomputer and relevant sensor, the final controlling element interface circuit etc. that comprise regulating and controlling algorithm.Final controlling element is then the wastegate position servo drive unit of motor direct-drive.
The motor direct-drive final controlling element that the present invention adopts mainly solves the shortcoming proposition of mechanical adjustment or indirect pneumatic adjustment in existing pressurization system, avoid the Recycling of boost pressure and wastegate driving, also namely no longer there is coupled relation with control objectives boost pressure in final controlling element, under electric drive, directly realize the control of wastegate aperture.Because this final controlling element directly adopts electric drive, speed of response is faster than the actuator response speed of pure machinery or indirect pneumatic adjustment, and this requires extremely important for the transient control in aviation pressurization system.In addition, this final controlling element solves the coupled problem of control objectives boost pressure and wastegate, and control more direct, control range is also wider, can realize the boost pressure curve of more complicated, and this cannot realize in original final controlling element mode.
Turbocharger control systems of the present invention, is primarily characterized in that, is provided with:
Sensor section:
Engine rotation speed sensor, throttle position sensor, for determining engine behavior (accelerate, slow down and stable state);
Turbocharger speed sensor, boost-pressure sensor, wastegate position transducer, for determining pressurized machine working state (normal, hypervelocity) and wastegate location status;
Atmospheric pressure, temperature transducer, for determining that motor runs ambient conditions (take off-climb-cruise-land);
Final controlling element part:
The Positioning Servo System of motor direct-drive, can be realized by motor acceleration and deceleration gear-box, motor also can be adopted to add worm-and-wheel gear and realize.Final controlling element exports by connecting rod Direct driver wastegate, realizes position closed loop feedback by wastegate position transducer.
Controller part:
Controller portion is divided into the microcomputer and corresponding sensor, final controlling element interface circuit that are integrated with regulating and controlling algorithm, and sensor interface part is analog sensor signal conditioning and the conversion of digital transducer pulse signal mainly; Final controlling element interface section mainly realizes the H-bridge circuit of the positive and negative bidirectional-movement of motor.Controller inputs according to sensor signal, determines boost pressure target, according to current exhaust gas door position, exports control signal, realizes wastegate positioning control by pressure feedback.
Pressurization control regulating method of the present invention, is characterized in that:
Use the electric-machine directly-driven position servo drive system of the invention described above as final controlling element;
Tabled look-up by throttle position and atmospheric pressure and determine steady-state target supercharging value;
Determine whether to need transient state supercharging compensate by throttle position and atmospheric pressure change rate;
Throttle position variance ratio is timing, and motor belongs to acceleration mode, and wastegate final controlling element closes offset forward to be increased, otherwise, then oppositely reduce;
When atmospheric pressure change rate increases, engine operation is in landing state, and wastegate final controlling element opens offset forward to be increased, otherwise, then oppositely reduce.
The invention has the advantages that:
1. adopt Direct driver final controlling element, isolated the contact between boost pressure and wastegate driving, drive more direct, speed of response is faster, and Stress control is also more accurate; Pressure control range regulation is more flexible simultaneously, and Applicable scope is wider.
2. adopt atmospheric pressure to judge variable height, determine whether to add transient control, avoid pressurized machine positive feedback event to occur, transient pressure controls more steady.
3. adopt throttle opening rate variation, determine pressurized machine wastegate action speed, boost pressure transient response characteristic is better.
4. do not need supercharger air compressor outlet end to add transient pressure limiting valve, system complexity reduces, and overall weight alleviates.
5. transient state regulates algorithm to determine according to engine flight situation, and pressurization system realtime control is stronger, and engine performance characteristics is better.
Accompanying drawing explanation
Fig. 1 is existing pressurized machine mechanical adjustment mode figure; ;
Fig. 2 is existing pressurized machine electrical adjustment mode figure;
Fig. 3 is the first mode of execution of the present invention figure;
Fig. 4 is the second mode of execution figure of the present invention;
Fig. 5 is that the second mode of execution positional servosystem of the present invention realizes schematic diagram;
Fig. 6 is Pressure control logic diagram of the present invention;
In figure:
101-air, 102-mechanically-operated controller, 103-wastegate, 104-turbine, 105-motor, 106-closure, 107-gas compressor, 108-impulse pipeline, 201-electrical adjustment module, 202-control system ECU, 301-atmospheric temperature, 302-atmospheric pressure, 303-boosted temperature, 304-boost pressure, 305-supercharger speed, 306-engine speed, 307-throttle opening, 308-wastegate position, 309-atmospheric conditions, 310-turbocharger condition, 311-engine condition, 312-controller, 313-wastegate driver, 314-pressurized machine, 401-engine controller, 402-communication interface, 403-pressurized machine Position Servo, 404-wastegate position, 405-positioning control, 406-pressurized machine, 501-power supply, 502-PWM interface, 503-CAN interface, 504-microcontroller, 505-position transducer, 506-H bridge, 507-motor, 508-gear-box.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
The first mode of execution of the present invention is that Single Controller completes wastegate position and pressure closed loop controls, and specific implementation as shown in Figure 3.This system comprises the sensors such as atmospheric pressure 301, atmospheric temperature 302, boost pressure 303, boosted temperature 304, supercharger speed 305, engine speed 306, closure 307, wastegate position 308, controller 312 is for being integrated with microcomputer and the associated interface circuitry of control algorithm, and exporting final controlling element 313 is the servo-system that drive motor and reduction gear are formed.
The control algorithm of the first mode of execution is by following process implementation.Controller 312 gathers 301-308 sensor information, first according to engine speed 306 and throttle position 307 sensor determination preliminary aim supercharging value according to certain frequency (interruption); Then determine whether to add transient state correction value by barometric pressure sensor 301 and throttle position sensor 307 change, both sums are as final target supercharge value; Then according to current booster pressure 303 numerical value, determine that wastegate final controlling element 313 is opened or closing motion, this process is realized by pid control algorithm.In order to prevent pid algorithm from occurring oscillatory occurences in transient state large-signal transient process, avoiding pressurized machine to occur surge, adding feedforward control adjustment, ensureing transient control effect.
The second mode of execution of the present invention is that pressurized machine and independent position controller are integrated into one, and independently become a system, specific implementation principle as shown in Figure 4.Position Servo 403 itself completes the closed loop control of wastegate position feedback, and the interface in the external world is realized by communication interface 402 or other modes.Position controller receives the control command signal of extraneous (being generally engine control system 401), this control signal represents the target location that wastegate needs reach, and Position Servo 403 self realizes wastegate by closed loop control and reaches target corresponding position.In other words, Position Servo 403 itself is position feedback closed loop controller, and the closed loop control of pressure is realized by engine control system 401.The benefit of this kind of implementation is, pressurized machine and regulon are integrated, can make supercharger systems module, is convenient to carry out integrated with other engine control systems, and interface is simple.
The implementation of Position Servo 403 as shown in Figure 5.This system and extraneous interface seldom, only have power supply 501, PWM communication interface 502, CAN interface 503.Power supply 501 provides electric power for whole control system.PWM communication interface 502 provides command information and diagnostic message for control system, and command information is represented by the dutycycle of signal, and diagnostic message was represented by low and high level and endurance.CAN interface 503 is the interface between control system and other control system, and relevant command information is formulated by agreement and realized.Above-mentioned communication interface also can adopt other modes to realize in fact, and this kind of communication mode can make Position Servo 403 can as independently position actuator, with in other respects, and such as otherwise position servo control.Microcontroller 504 carries out bi-directional drive by H bridge 506 pairs of motors 507, and motor movement carries out slowing down through reduction gear box 508 and finally realizes the driving of wastegate position, realizes position-force control by wastegate position transducer 505.
The control algorithm of the second mode of execution is by following process implementation.In this kind of implementation, Position Servo 403 is by receiving the positioning control instruction of engine control system 401, and self realizes the closed loop control of wastegate position by the position servo drive system be made up of microcontroller 504, H bridge 506, motor 507, gear-box 508 and wastegate position transducer 505.
Regulating and controlling algorithm logic of the present invention as shown in Figure 6.This algorithm is compared with Surface power drive, add the transient state correction of air height, simultaneously according to the feature of aviation piston engine own, directly adopt pid algorithm when wastegate is opened, and when wastegate cuts out in order to prevent pressurized machine from occurring surge and pressure surge, adopt the mode of first feed forward open loop progressively to close exhaust gas valve, reach in 90% scope of desired value at boost pressure, in order to reduce steady-state error, now adopting pid algorithm adjustment, ensureing the accuracy of desired value.
Whole algorithm, based on engine operating condition, is determined present engine state, is tabled look-up and determine preliminary aim supercharging value based on engine speed 306, throttle position 307 sensor; Then determine whether to add transient state correction according to the height of atmospheric pressure 301 representative and the change of throttle position 307, table look-up and determine relevant correction factor; After preliminary aim supercharging value and correction factor are determined, three is multiplied and obtains final realistic objective supercharging value; Then whether be greater than current booster force value according to realistic objective supercharging value to determine, determine that wastegate cuts out and opens algorithm, adopt the mode of partial open loop and stable state PID closed-loop adjustment to realize when wastegate cuts out, wastegate is opened, and the mode directly adopting stable state PID to regulate realizes.
Claims (4)
1. an aviation piston engine turbocharger pressure control system, is characterized in that: the position servo drive system comprising Direct driver, and the positional servosystem of described Direct driver adopts motor to drive and reduction gear coordinates realization; Described control system also comprises barometric pressure sensor, atmosphere temperature transducer, boost-pressure sensor, charge temperature sensor, turbocharger speed sensor, engine rotation speed sensor, throttle position sensor and wastegate position transducer; Described control system is also provided with the controller of microcomputer and the interface circuit composition possessing and regulate algorithm.
2. control system as claimed in claim 1, is characterized in that: described set-up of control system is undertaken integrated by the position servo drive system of described controller and described Direct driver, becomes independent Positioning Servo System.Described Positioning Servo System is connected with engine control system by communication interface, and engine control system is according to sensor signal and regulate algorithm, sends the order that Positioning Servo System reaches target location.Positioning Servo System realizes the interior location closed loop control of wastegate position, and the external closed-loop that engine control system realizes boost pressure controls.
3. control system as claimed in claim 1, is characterized in that: described control system completes position servo and pressure closed loop function by single controller.Controller, according to sensor signal and regulating and controlling algorithm, directly exports the control signal of activation point servo-control system, the basis realizing wastegate position-force control realizes the closed loop control of engine boost pressure.
4., based on the regulating method of control system according to any one of claim 1-3, it is characterized in that:
Comprise the following steps:
Step 1: control system pick-up transducers information;
Control system is according to certain frequency collection atmospheric pressure, atmospheric temperature, boost pressure, boosted temperature, supercharger speed, engine speed, throttle position and wastegate position information.
Step 2: control system computation of table lookup preliminary aim supercharging value;
Control system according to engine speed and throttle position information, interpolation calculation of tabling look-up preliminary aim supercharging value.
Step 3: control system transient state correction;
Control system, according to the throttle position of current collection, compares with collection last time value, calculates throttle position variance ratio, and being divided by with throttle position variance ratio transient state correction threshold value obtains closure transient state correction factor; Control system, according to the atmospheric pressure value of current collection, is converted into air height value, compares, calculate air altitude rate with collection last time value, and being divided by with air altitude rate transient state correction threshold value obtains air height transient state correction factor.
Step 4: control system calculates final goal supercharging value;
Control system is according to preliminary aim supercharging value, closure transient state correction factor and air height transient state correction factor, and three is multiplied and determines final goal supercharging value.
Step 5: control system controls wastegate;
If target boost pressure value is greater than current booster force value, wastegate cuts out, in order to prevent turbocharger surge and pressure surge, closing wastegate makes current booster force value tend to target boost pressure value, when after both convergences to certain limit, adopt PID method to control the opening and closing of wastegate, make current booster force value consistent with target boost pressure value.Realistic objective boost pressure value is less than current booster force value, and wastegate is opened, and directly adopts PID closed loop control algorithm.
Step 6: control system exports driving pulse, completes driving function;
Control system exports driving pulse to the motor in the servo drive system of position, realizes wastegate motion control, reaches the requirement of boost pressure stability contorting.
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| CN201410479862.7A CN104234821A (en) | 2014-09-18 | 2014-09-18 | Aviation supercharger control system and adjusting method thereof |
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Cited By (6)
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| CN109113858A (en) * | 2017-06-22 | 2019-01-01 | 襄阳联航动力技术有限公司 | A kind of electric-control system unmanned plane petrol engine of band list ECU sub-control air throttle |
| CN110131193A (en) * | 2018-02-02 | 2019-08-16 | 中国航发商用航空发动机有限责任公司 | Aero-engine surge fault monitoring method and system |
| CN110284961A (en) * | 2019-07-09 | 2019-09-27 | 西安爱生技术集团公司 | Control system and control method for aviation piston engine pressurization |
| CN113250810A (en) * | 2021-06-29 | 2021-08-13 | 四川迅联达智能科技有限公司 | Method and system for stabilizing intake pressure of two-stroke engine |
| CN113250809A (en) * | 2021-05-11 | 2021-08-13 | 昆明云内动力股份有限公司 | WGT supercharger bypass valve actuator |
| CN113464271A (en) * | 2021-08-03 | 2021-10-01 | 航天时代飞鸿技术有限公司 | Closed-loop control method and system for pressure of supercharger for aviation two-stroke piston engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109113858A (en) * | 2017-06-22 | 2019-01-01 | 襄阳联航动力技术有限公司 | A kind of electric-control system unmanned plane petrol engine of band list ECU sub-control air throttle |
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| CN113250809A (en) * | 2021-05-11 | 2021-08-13 | 昆明云内动力股份有限公司 | WGT supercharger bypass valve actuator |
| CN113250810A (en) * | 2021-06-29 | 2021-08-13 | 四川迅联达智能科技有限公司 | Method and system for stabilizing intake pressure of two-stroke engine |
| CN113464271A (en) * | 2021-08-03 | 2021-10-01 | 航天时代飞鸿技术有限公司 | Closed-loop control method and system for pressure of supercharger for aviation two-stroke piston engine |
| CN113464271B (en) * | 2021-08-03 | 2023-01-06 | 航天时代飞鸿技术有限公司 | Booster pressure closed-loop control method and system for aviation two-stroke piston engine |
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Application publication date: 20141224 |