CN108528735A - Serial mixed power aircraft and its control method - Google Patents
Serial mixed power aircraft and its control method Download PDFInfo
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- CN108528735A CN108528735A CN201810336908.8A CN201810336908A CN108528735A CN 108528735 A CN108528735 A CN 108528735A CN 201810336908 A CN201810336908 A CN 201810336908A CN 108528735 A CN108528735 A CN 108528735A
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 230000005611 electricity Effects 0.000 claims abstract description 31
- 238000003860 storage Methods 0.000 claims description 36
- 238000005183 dynamical system Methods 0.000 claims description 18
- 239000000203 mixture Substances 0.000 claims description 18
- 238000002156 mixing Methods 0.000 claims description 8
- 238000010248 power generation Methods 0.000 claims description 7
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical group [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 5
- 229910052744 lithium Inorganic materials 0.000 claims description 5
- 230000001360 synchronised effect Effects 0.000 claims description 3
- 230000005389 magnetism Effects 0.000 claims 1
- 238000011217 control strategy Methods 0.000 abstract description 10
- 238000013461 design Methods 0.000 abstract description 7
- 230000007613 environmental effect Effects 0.000 abstract description 4
- 238000004134 energy conservation Methods 0.000 abstract description 2
- 238000003912 environmental pollution Methods 0.000 abstract description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 125
- 239000002826 coolant Substances 0.000 description 70
- 239000007788 liquid Substances 0.000 description 61
- 238000001816 cooling Methods 0.000 description 47
- 230000033228 biological regulation Effects 0.000 description 10
- 238000012544 monitoring process Methods 0.000 description 9
- 230000006641 stabilisation Effects 0.000 description 6
- 238000011105 stabilization Methods 0.000 description 6
- 238000009826 distribution Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 239000000047 product Substances 0.000 description 4
- 238000004364 calculation method Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 239000013589 supplement Substances 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- 238000003745 diagnosis Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000003306 harvesting Methods 0.000 description 1
- 230000020169 heat generation Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000178 monomer Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000008961 swelling Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention discloses a kind of serial mixed power aircraft and its control methods, serial mixed power aircraft includes hybrid power system, hybrid power system includes power battery, increases journey system and power drive system, increase the rotary engine that journey system includes generator and connect with generator and generator is driven to generate electricity, power drive system includes propeller and provides the driving motor of driving force for propeller, and power battery provides electric energy for driving motor.The serial mixed power aircraft of the present invention; using series connection type hybrid power system; realize with energy conservation and environmental protection in order to control tactful design concept, with machine system power, parameter switches complete machine control strategy in real time in order to control; improve energy requirement allocation situation of the hybrid power system under different working modes and operating mode; energy saving consumption; reduce environmental pollution, alleviating energy crisis.
Description
Technical field
The invention belongs to aircraft technology fields, specifically, the present invention relates to a kind of serial mixed power aircraft and its
Control method.
Background technology
With the fast development of New-energy electric vehicle, electric bicycle, electric airplane etc. electric product, to electronic production
The research of product control strategy also gradually moves to maturity, but is limited to the development of power battery technology, charging pile fast charge technology, electronic
The cruising ability of product is difficult to be greatly improved, thus the control model of hybrid power become improve electric product continuation of the journey must
Through road, while in view of control strategy simple type, hybrid power system use tandem.In conjunction with current hybrid power aeroplane
Fast development, under the theory of national energy-saving environmental protection, consider serial mixed power aircraft complete machine control strategy.
In conjunction with the dynamic mode of hybrid power aeroplane, i.e., automatically controlled pattern and oily control pattern, by the work of hybrid power aeroplane
Pattern is divided into：The electric mixed mode of electric-only mode, conventional internal combustion oil control pattern, oil.The control of existing serial mixed power aircraft
Method processed, it is poor for the energy requirement distribution effects under complete machine different working modes, under operating mode, it can not achieve machine system work(
The optimal allocation of rate.
Invention content
The present invention is directed at least solve one of the technical problems existing in the prior art.For this purpose, the present invention provides a kind of string
Connection formula hybrid power aeroplane and its control method, it is therefore an objective to improve energy of the hybrid power system under different working modes and operating mode
Measure demand assignment situation.
To achieve the goals above, the technical solution that the present invention takes is：Serial mixed power aircraft, including mixing are dynamic
Force system, the hybrid power system include power battery, increase journey system and power drive system, increase journey system include generator and
The rotary engine for being connect with generator and generator being driven to generate electricity, power drive system include propeller and are carried for propeller
For the driving motor of driving force, power battery provides electric energy for driving motor.
The hybrid power system further includes integrated manipulator and drive motor controller, integrated manipulator and the power
Battery, drive motor controller and the power generation mechatronics, the driving motor are electrically connected with drive motor controller.
The driving motor is permanent magnet synchronous AC machine.
The power battery is lithium battery.
The three-phase alternating current that the generator generates is rectified into direct current by the integrated manipulator, is the driving motor
Power supply.
The serial mixed power aircraft further includes power management control module, and power management control module is according to dynamic
The storing electricity of power battery or the current aircraft altitude data acquired by height sensor are judged, are controlled described integrated
Controller starts the rotary engine.
The present invention also provides a kind of control methods of serial mixed power aircraft, pass through the control to hybrid power system
System, according to power battery storage power, increase journey system generated output and power drive system output power, control mixing is dynamic
Power aircraft switches between pure electric mode, the electric blend modes of operation of oil and oil control operating mode.
When the storage power of power battery is more than the output power of propeller, hybrid power aeroplane is in pure electric vehicle work
Pattern；Hybrid power aeroplane is at the takeoff and landing stage, if the storage power of power battery is deposited less than the safety of power battery
The setting value of power is stored up, then hybrid power aeroplane is in oil control operating mode；Hybrid power aeroplane is in cruising phase, if power
The storage power of battery is more than the setting value of the secure storage power of power battery, then hybrid power aeroplane is in oil control Working mould
Formula or the electric blend modes of operation of oil.
When hybrid power aeroplane is in oil electricity blend modes of operation, if the generated output for increasing journey system is greater than or equal to spiral shell
The output power for revolving paddle, then increase journey system and charge to power battery, until the storage power of power battery reaches setting value,
Then hybrid power aeroplane switches to pure electric mode.
When hybrid power aeroplane is in oil electricity blend modes of operation, after drive motor controller receives enabled instruction,
Power battery is powered for driving motor, and driving motor is made to operate, and driving motor drives propeller rotational, drive motor controller to drive
The output power of dynamic motor matching propeller, output of the battery management system according to the output power matching power battery of propeller
Electricity ultimately forms closed loop pure electric vehicle system.
The serial mixed power aircraft of the present invention realizes that with energy conservation and environmental protection be control using series connection type hybrid power system
The design concept of system strategy, with machine system power, parameter switches complete machine control strategy in real time in order to control, improves hybrid power system
Energy requirement allocation situation of the system under different working modes and operating mode, energy saving consumption reduce environmental pollution, alleviate the energy
Crisis.The control method of the present invention controls plan using pure electric vehicle, oil control closed-loop control system as serial mixed power airplane complete machine
The basis slightly designed, with the power of complete machine subsystem tactful controling parameter in order to control, not according to serial mixed power aircraft
With under operating mode subsystem power demand it is different, switch the operating mode of complete machine control system, improve the power of machine system
Distribution improves the ability of complete machine real-time response.
Description of the drawings
This specification includes the following drawings, and shown content is respectively：
Fig. 1 is the structural schematic diagram of serial mixed power aircraft of the present invention；
Fig. 2 is the principle schematic of serial mixed power aircraft of the present invention；
Fig. 3 is serial mixed power aircraft power system control block diagram of the present invention；
Fig. 4 is serial mixed power aircraft pure electric vehicle state control policy flow chart of the present invention；
Fig. 5 is serial mixed power aircraft oil electricity admixture control strategy flow chart of the present invention；
Fig. 6 is the principle schematic of the cooling system of serial mixed power aircraft of the present invention；
Fig. 7 is the design frame chart of the cooling controller of serial mixed power aircraft of the present invention；
In figure label for：1, generator；2, radome fairing；3, rotary engine；4, power battery；5, propeller；6, battery
Management system；7, power management control module；8, integrated manipulator；9, drive motor controller；10, driving motor；11, start
Machine controller；12, the first water pump；13, the second water pump；14, third water pump；15, the 4th water pump；16, radiator；17, swelling water
Pot.
Specific implementation mode
Below against attached drawing, by the description of the embodiment, making to the specific implementation mode of the present invention further details of
Explanation, it is therefore an objective to those skilled in the art be helped to have more complete, accurate and deep reason to the design of the present invention, technical solution
Solution, and contribute to its implementation.
As shown in figures 1 and 3, the present invention provides a kind of serial mixed power aircrafts, including hybrid power system, mix
It closes dynamical system to include power battery, increase journey system and power drive system, increases journey system and include generator and connect with generator
And the rotary engine for driving generator to generate electricity, power drive system include propeller and provide the drive of driving force for propeller
Dynamic motor, power battery provide electric energy for driving motor.Increase the conversion that journey system realizes chemical energy to electrical energy, is carried for complete machine continuation of the journey
For energy.
Specifically, as shown in figure 3, hybrid power system further includes integrated manipulator, drive motor controller and power
Management control module, integrated manipulator and power battery, drive motor controller and power generation mechatronics, driving motor and driving
Electric machine controller is electrically connected.The three-phase alternating current that generator generates is rectified into direct current by integrated manipulator, is supplied for driving motor
Electricity.Propeller passes through integrated manipulator to drive motor controller, driving with driving motor by being driven axis connection, power battery
The DC inverter that electric machine controller provides power battery is powered at alternating current for driving motor.Rotary engine drives power generation
Machine generates electricity, and electric energy is driving motor power supply by integrated manipulator and is that power battery supplements energy, and power battery can also lead to
External equipment charger is crossed to charge for it.
As shown in figure 3, the energy harvesting of driving motor can directly be powered by power battery, another kind is rotary engine band
Dynamic generator electricity.Driving motor provides power source for hybrid power aeroplane, and driving motor drives propeller to generate pulling force,
The kinetic energy of advance is provided for hybrid power aeroplane；Driving motor is preferably the permanent magnet synchronous AC machine of high power to weight ratio, reaches boat
Sky requires.The high efficiency range of propeller overlaps that (efficiency of propeller is by stages, propeller with the high efficiency range of driving motor
Efficiency under different rotating speeds is different, the general efficiency highest when determining cruise, is more than 0.8；Driving motor also has
Efficiency section, when aircraft cruises, the rotating speed of driving motor is kept constant, at this time by the high efficient area of driving motor and propeller
Between overlap, improve capacity usage ratio, reduce idle work), to improve the utilization rate of energy to the greatest extent, matching is to meet cruise
Demand is basic principle.
Preferably, power battery is lithium battery and is high-energy density lithium battery, power battery is by monomer lithium electricity
Pond is made up of series-parallel form and wraps, then several packets are carried out being composed in series power battery pack, and power battery passes through battery
Management system is managed it, and battery management system monitors voltage, electric current, temperature liter of power battery etc. in real time.Power battery
Energy supplement can be carried out to it by charger, carry out being reverse into alternating current by integrated manipulator to drive motor controller.
Battery management system is managed power battery, and power management control module can be according to the judgement of the storing electricity of power battery
It is no to start rotary engine.
As shown in figure 3, generator is generated electricity by rotary engine drive, integrated manipulator control rotary engine opens
Dynamic and electronic damper aperture, to ensure that output that the power of rotary engine can be stablized, control unit of engine control turn
The igniting and oil spout of sub- engine, and acquire in engine speed information sharing to CAN network.
Power management control module carries out power-distribution management to entire dynamical system, and monitoring and fault diagnosis passes through oil
The output power of the situation of change control driving motor of door push rod.Power management control module can be according to the residue electricity of power battery
Amount or the current aircraft altitude data acquired by height sensor are judged that control integrated manipulator starts rotor and starts
Machine.Integrated manipulator adjusts the size of electronic damper according to the conditions of demand of load, to control the output power of generator.Power
Management control module carries out power-distribution management according to the situation of change of throttle push rod to each system.
Power management control module controls drive motor controller by integrated manipulator, to adjust the output of driving motor
Rotating speed and power.Power management control module adjusts control strategy, it is ensured that each in time by monitoring each system working condition
System is safe and reliable, and when being higher than setting value such as the temperature of drive motor controller, power management control module passes through integrated control
Device starts to limit output power, to reduce the kinetic energy of driving motor, to reduce the flying speed of hybrid power aeroplane.
Hybrid power aeroplane is taking off and landing phases, is individually for driving motor power supply by power battery, realizes environmental protection
Demand reduces airport periphery noise and tail gas pollution；Start to cruise when hybrid power aeroplane reaches predetermined altitude, integrates control
Device processed starts rotary engine, drives generator to start to generate electricity, electric energy is provided for driving motor and power battery, effective to increase
The course continuation mileage of hybrid power aeroplane and cruise duration.Mixed dynamic control module control rotary engine always works in efficiently
Fuel consumption has been saved in section.
As shown in fig. 6, the serial mixed power aircraft of the present invention further includes cooling system, which includes heat dissipation
Device 16, control device, the coolant liquid in radiator 16 is delivered to that rotary engine cools down for rotary engine first
Cooling circuit, the coolant liquid in radiator 16 is delivered to the second cooling circuit that power battery cools down for power battery with
And the coolant liquid in radiator 16 is delivered to generator, hybrid power integrated manipulator, driving motor and driving motor and is controlled
The third cooling circuit that device cools down for generator, integrated manipulator 8, driving motor and drive motor controller.First is cold
But circuit, the second cooling circuit and third cooling circuit are to be arranged in parallel, and the first cooling circuit, the second cooling circuit and third are cold
But circuit matches, and carries out cooling down to each component of the dynamical system of serial mixed power aircraft, ensures dynamical system
All parts be in best working environment, maintain the high efficiency of dynamical system to export, improve serial mixed power aircraft
Adaptive capacity.Rotary engine operating temperature is relatively high, and the operating temperature of power battery is relatively low, therefore needs to be arranged
Two individual cooling circuits are that rotary engine and power battery provide coolant liquid respectively.Integrated manipulator 8, generator, drive
The operating temperature of dynamic motor and drive motor controller will be very close to therefore closing Integrated power controller, generator, driving motor
It is arranged in the same cooling circuit with drive motor controller.First cooling circuit, the second cooling circuit and third cool back
Road uses parallel setting, avoids pipeline from arranging the complexity brought, facilitates arrangement.
As shown in fig. 6, the first cooling circuit includes being delivered to rotor for the coolant liquid in connecting radiator 16 to start
First temperature sensor of the first water pump 12 of machine and the coolant temperature of the water outlet for detecting rotary engine.First
Cooling circuit is by rotary engine, in the first cooling circuit, the first water pump 12 be located at radiator 16 and rotary engine it
Between, the water inlet of the first water pump 12 is connect by pipeline with the water outlet of radiator 16, and the water outlet of the first water pump 12 passes through pipe
The water inlet of road and rotary engine connects, and the water outlet of rotary engine is connect by pipeline with the water inlet of radiator 16,
Coolant liquid after cooling is carried out to rotary engine to be back in radiator 16, realizes the cycle of coolant liquid.Control device acquires
The data of first temperature sensor detection, the first temperature sensor and the first water pump 12 are to be electrically connected with control device, the first water
Pump 12 is controlled the control of device.First temperature sensor detects the temperature of the coolant liquid of the water outlet of rotary engine in real time
Degree, rotating speed of the control device according to the first water pump of coolant temperature real-time monitoring 12 by the acquisition of the first temperature sensor, in turn
The regulation and control for realizing the flow velocity of the coolant liquid of the water outlet of the first water pump 12, ensure the coolant liquid of the water outlet of rotary engine
Temperature stablize setting temperature value so that rotary engine is in best effort environment.If the water outlet of rotary engine
The temperature of coolant liquid at mouthful is more than the temperature value of setting, and control device sends out the instruction for the rotating speed for increasing the first water pump 12, water
The voltage that drive module regulates and controls the first water pump 12 is pumped, to increase the flow velocity of the coolant liquid of the water outlet of the first water pump 12, in turn
The flow velocity that cooling coolant liquid is carried out to rotary engine is increased, the flow velocity of real-time control coolant liquid maintains the stabilization of temperature.
As shown in fig. 6, the second cooling circuit includes being delivered to power battery for the coolant liquid in connecting radiator 16
The second water pump 13 and the water outlet for detecting power battery coolant temperature second temperature sensor.Second cooling
Circuit is by power battery, and in the second cooling circuit, the second water pump 13 is between radiator 16 and power battery, the second water
The water inlet of pump 13 is connect by pipeline with the water outlet of radiator 16, and the water outlet of the second water pump 13 passes through pipeline and power electric
The water inlet in pond connects, and the water outlet of power battery is connect by pipeline with the water inlet of radiator 16, is carried out to power battery
Coolant liquid after cooling is back in radiator 16, realizes the cycle of coolant liquid.Control device acquires second temperature sensor inspection
The data of survey, second temperature sensor and the second water pump 13 are to be electrically connected with control device, and the second water pump 13 is controlled device
Control.Second temperature sensor detects the temperature of the coolant liquid of the water outlet of power battery in real time, control device according to by
The rotating speed of the second water pump of coolant temperature real-time monitoring 13 of second temperature sensor acquisition, and then realize going out for the second water pump 13
The regulation and control of the flow velocity of coolant liquid at the mouth of a river ensure that the temperature of the coolant liquid of the water outlet of power battery stablizes the temperature in setting
Angle value so that power battery is in best effort environment.It is set if the temperature of the coolant liquid of the water outlet of power battery is more than
Fixed temperature value, control device send out the instruction for the rotating speed for increasing the second water pump 13, and water pump drive module regulates and controls the second water pump 13
Voltage and then increase and power battery cooled down to increase the flow velocity of the coolant liquid of the water outlet of the second water pump 13
Coolant liquid flow velocity, the flow velocity of real-time control coolant liquid maintains the stabilization of temperature.
As shown in fig. 6, third cooling circuit include third water pump 3 and the 4th water pump 4, for will by third water pump 14 and/
Or the 4th the coolant liquid that conveys of water pump 15 guide to the first solenoid valve of generator, for will be by third water pump 14 and/or the 4th
The coolant liquid that water pump 15 conveys is guided to the second solenoid valve of integrated manipulator 8, for will be by third water pump 14 and/or the 4th water
The coolant liquid of 15 conveying of pump guides to the third solenoid valve of drive motor controller and for will be by third water pump 14 and/or the
The coolant liquid of four water pumps 15 conveying is guided to the 4th solenoid valve of driving motor.Two water pumps are set in the third cooling circuit,
Allowing for hybrid power aeroplane takeoff phase needs high-power output, and system heat generation amount is larger, by open two water pumps come
Increase the flow velocity of coolant liquid, and then improves the effect of cooling system cooling；Hybrid power aeroplane cruising phase output power is opposite
Smaller, a water pump can meet the cooling effect of cooling system, open one of water pump at this time, another water pump is made
For backup, the safety issue for avoiding mechanical water pump, electric fault from bringing, and then improve the safety of cooling system, redundancy.
First solenoid valve, second solenoid valve, third solenoid valve and the 4th solenoid valve are to be electrically connected with control device, the first electricity
Magnet valve, second solenoid valve, third solenoid valve and the 4th solenoid valve are controlled the control of device, and control device controls the first electromagnetism
Valve, second solenoid valve, third solenoid valve and the first solenoid valve of opening and closing and adjusting of the 4th solenoid valve, second solenoid valve, third
The opening size of solenoid valve and the 4th solenoid valve, and then can control respectively to generator, integrated manipulator, driving motor control
Device and driving motor carry out the flow velocity of cooling coolant liquid, realize to generator, integrated manipulator, drive motor controller and drive
The control respectively of the temperature of dynamic motor maintains dynamical system power to ensure that all parts can be in best working condition
Stablize output.The setting of solenoid valve in third cooling circuit may be implemented the micro-control of the temperature of each component of dynamical system, make
Obtain temperature control precision, stability higher.
As shown in fig. 6, third cooling circuit is by generator, integrated manipulator, drive motor controller and driving motor,
In third cooling circuit, third water pump 14 and the 4th water pump 15 are between radiator 16 and current divider, 14 He of third water pump
The water inlet of 4th water pump 15 is connect by pipeline with the water outlet of radiator 16, the water outlet of third water pump 14 and the 4th water pump 15
It mouthful is connected by the water inlet of pipeline and current divider, the water outlet of current divider passes through four pipelines and the first solenoid valve, the respectively
The water inlet of two solenoid valves, third solenoid valve and the 4th solenoid valve connects, and the water outlet of the first solenoid valve passes through pipeline and power generation
The water inlet of machine connects, and the water outlet of second solenoid valve is connect by pipeline with the water inlet of integrated manipulator 8, third solenoid valve
Water outlet connected by pipeline and the water inlet of drive motor controller, the water outlet of the 4th solenoid valve passes through pipeline and driving
The water inlet of motor connects, the first solenoid valve, second solenoid valve, third solenoid valve and the 4th solenoid valve water outlet pass through pipeline
It is connect with the water inlet of current collector, the water outlet of current collector is connect by pipeline with the water inlet of radiator 16, to generator, collection
Coolant liquid after cooling is carried out at controller, drive motor controller and driving motor, and radiator 16 is back to by current collector
In, realize the cycle of coolant liquid.
As shown in fig. 6, third cooling circuit further includes the third temperature sensor of the temperature for detecting generator, first
Solenoid valve is connect by pipeline with third water pump 14 and the 4th water pump 15.Third cooling circuit further includes for detecting integrated control
4th temperature sensor of the temperature of device 8, second solenoid valve are connect by pipeline with third water pump 14 and the 4th water pump 15.Third
Cooling circuit further includes the 5th temperature sensor of the temperature for detecting drive motor controller, and third solenoid valve passes through pipeline
It is connect with third water pump 14 and the 4th water pump 15.Third cooling circuit further includes the 6th temperature of the temperature for detecting driving motor
Sensor is spent, the 4th solenoid valve is connect by pipeline with third water pump 14 and the 4th water pump 15.
Third temperature sensor is the coolant temperature of the water outlet for detecting generator, and the 4th temperature sensor is
Coolant temperature for the water outlet for detecting integrated manipulator 8, the 5th temperature sensor are for detecting driving motor control
The coolant temperature of the water outlet of device processed, the 6th temperature sensor are the coolant liquids of the water outlet for detecting driving motor
Temperature, control device acquire third temperature sensor, the 4th temperature sensor, the 5th temperature sensor and the 6th temperature sensor
The data of detection, third temperature sensor, the 4th temperature sensor, the 5th temperature sensor, the 6th temperature sensor, third water
To be electrically connected, third water pump 14 and the 4th water pump 15 are controlled the control of device for pump 14 and the 4th water pump 15 and control device.
Third temperature sensor detects the temperature of the coolant liquid of the water outlet of generator in real time, and control device is according to by the
The aperture of the first solenoid valve of coolant temperature real-time monitoring of three-temperature sensor acquisition, and then realize the cooling for flowing into generator
The regulation and control of the flow velocity of liquid ensure that the temperature of the coolant liquid of the water outlet of generator stablizes the temperature value in setting, realize power generation
The regulation and control of machine temperature so that generator is in best effort environment, and maintain dynamical system power stablizes output.If generator
Water outlet coolant liquid temperature be more than setting temperature value, control device send out increase the first solenoid valve aperture finger
It enables, to increase the flow velocity for the coolant liquid for flowing into generator, and then increases the flow velocity for carrying out cooling coolant liquid to generator, it is real
The flow velocity of time control coolant liquid maintains the stabilization of temperature.
4th temperature sensor detects the temperature of the coolant liquid of the water outlet of integrated manipulator 8 in real time, control device according to
According to the aperture of the coolant temperature real-time monitoring second solenoid valve acquired by the 4th temperature sensor, and then realizes and flow into integrated control
The regulation and control of the flow velocity of the coolant liquid of device 8 processed ensure that the temperature of the coolant liquid of the water outlet of integrated manipulator 8 is stablized in setting
Temperature value realizes the regulation and control of 8 temperature of integrated manipulator so that integrated manipulator 8 is in best effort environment, maintains dynamical system
Power stablizes output.If the temperature of the coolant liquid of the water outlet of integrated manipulator 8 is more than the temperature value of setting, control dress
The instruction for sending out the aperture for increasing second solenoid valve is set, to increase the flow velocity for the coolant liquid for flowing into integrated manipulator 8, and then is increased
The flow velocity of cooling coolant liquid is carried out to integrated manipulator 8, the flow velocity of real-time control coolant liquid maintains the stabilization of temperature.
5th temperature sensor detects the temperature of the coolant liquid of the water outlet of drive motor controller, control device in real time
According to the aperture of the coolant temperature real-time monitoring third solenoid valve by the acquisition of the 5th temperature sensor, and then realizes and flow into driving
The regulation and control of the flow velocity of the coolant liquid of electric machine controller ensure that the temperature of the coolant liquid of the water outlet of drive motor controller is stablized
In the temperature value of setting, the regulation and control of drive motor controller temperature are realized so that drive motor controller is in best effort ring
Border, maintain dynamical system power stablizes output.If the temperature of the coolant liquid of the water outlet of drive motor controller is more than
The temperature value of setting, control device sends out the instruction for the aperture for increasing third solenoid valve, to increase inflow drive motor controller
Coolant liquid flow velocity, and then increase the flow velocity that cooling coolant liquid is carried out to drive motor controller, real-time control cooling
The flow velocity of liquid maintains the stabilization of temperature.
6th temperature sensor detects the temperature of the coolant liquid of the water outlet of driving motor in real time, control device according to by
The aperture of the 4th solenoid valve of coolant temperature real-time monitoring of 6th temperature sensor acquisition, and then realize and flow into driving motor
The regulation and control of the flow velocity of coolant liquid ensure that the temperature of the coolant liquid of the water outlet of driving motor stablizes the temperature value in setting, real
The regulation and control of existing driving motor temperature so that driving motor is in best effort environment, and maintain dynamical system power stablizes output.
If the temperature of the coolant liquid of the water outlet of driving motor is more than the temperature value of setting, control device, which is sent out, increases the 4th electromagnetism
The instruction of the aperture of valve to increase the flow velocity for the coolant liquid for flowing into driving motor, and then is increased and is cooled down to driving motor
Coolant liquid flow velocity, the flow velocity of real-time control coolant liquid maintains the stabilization of temperature.
As shown in fig. 7, the control device that the cooling system of serial mixed power aircraft of the present invention uses includes mainly temperature
The hardware modules such as acquisition module, water pump drive module and solenoid valve driving module and control chip are spent, the model of chip is controlled
For TMS320C5000, temperature collecting module, water pump drive module and solenoid valve driving module are electrically connected with control chip, temperature
Acquisition module and the first temperature sensor, second temperature sensor, third stability sensor, the 4th stability sensor, the 5th temperature
Sensor and the electrical connection of the 6th temperature sensor are spent, the temperature and optimum operating condition of control chip comparison temperature acquisition module acquisition are set
Fixed temperature controls the input voltage of major loop water pump, the aperture of cooling liquid speed and each solenoid valve, real-time monitoring subsystem
Temperature, maintain dynamical system power stablize output.The control strategy of entire dynamical system is all by controlling chip
TMS320C5000 is completed, and control algolithm fully takes into account in the design according to temperature auto-control temperature of dynamical system
The heat dissipation performance of each subsystem, the water pump of designing backup and the solenoid valve etc. of high-accuracy water flow control improve dynamical system
The intelligentized control method of serial mixed power aircraft cooling system is realized in the precise and stable control for temperature of uniting.
For above-mentioned serial mixed power aircraft, the present invention also provides a kind of controls of serial mixed power aircraft
Method, by the control to hybrid power system, (storage power of power battery is set as P to the storage power of foundation power battery
It is dynamic), increase journey system generated output (generated output for increasing journey system is set as P oil) and power drive system output power (electricity drive
The output power of dynamic system namely the output power of propeller, are set as P paddles), control hybrid power aeroplane is in pure electric vehicle Working mould
It is switched between the electric blend modes of operation of formula, oil and oil control operating mode.
The control method of the present invention is according to the energy-saving and environment-friendly theory design work pattern of serial mixed power aircraft, i.e., mixed
It closes motor plane and uses pure electric mode in the takeoff and landing stage, hybrid power aeroplane is in the cruise high-altitude stage using oil
Electricity mixing or oil control operating mode, the length of each stage work mode time are the storage powers of foundation power battery, increase journey
The numbers of other power such as the generated output of system, the output power of power drive system considers.
When the dynamic output power P paddles for being more than propeller of the storage power P of power battery, hybrid power aeroplane is in pure electricity
It starts building operation mode, driving motor power supply is individually for by power battery at this time.Hybrid power aeroplane at the takeoff and landing stage, if
The storage power of power battery is in oil control work less than the setting value of the secure storage power of power battery, then hybrid power aeroplane
Operation mode；Hybrid power aeroplane is in cruising phase, if the storage power of power battery is more than the secure storage work(of power battery
The setting value of rate, then hybrid power aeroplane is in oil control operating mode or the electric blend modes of operation of oil.At hybrid power aeroplane
When oily electric blend modes of operation, if the generated output for increasing journey system is greater than or equal to the output power of propeller, increase journey system
System charges to power battery, until the storage power of power battery reaches setting value, then hybrid power aeroplane switches to
Pure electric mode.When hybrid power aeroplane is in oil electricity blend modes of operation, drive motor controller receives startup
After instruction, power battery is powered for driving motor, and driving motor is made to operate, and driving motor drives propeller rotational, driving motor
Controller driving motor matches the output power of propeller, and battery management system matches power electric according to the output power of propeller
The output electricity in pond ultimately forms closed loop pure electric vehicle system.
When the dynamic output power P paddles for being more than power drive system of the storage power P of power battery, hybrid power aeroplane is in
Pure electric mode, the formation such as power battery, driving motor, drive motor controller, power management control module, propeller
Closed loop pure electric vehicle system, and integrated manipulator monitors the dynamic sizes of P in real time.It is in take-off climb and drop in hybrid power aeroplane
When during falling, if P moves storage power safety value (the storage power safety value is set as P and sets) less than power battery, mixing
Motor plane need to switch to oil control operating mode.After hybrid power aeroplane reaches Cruising Altitude, if P is moved more than power battery
Storage power safety value P is set, and hybrid power aeroplane need to switch to the electric blend modes of operation of oil control operating mode oil.
Hybrid power aeroplane is in climb and takes off or when landing phases, set less than P if the storage power P of power battery is dynamic,
Hybrid power aeroplane is in oil control operating mode, increases journey system and is worked with maximum generating watt, increases the generated energy directly quilt of journey system
Power drive system consumes, and rotary engine drives electrical power generators at this time, and electric energy, power are provided for driving motor and power battery
Battery charges.It is set more than P if the storage power P of power battery is dynamic, after hybrid power aeroplane reaches Cruising Altitude, mixing
For motor plane all in oil control or the electric blend modes of operation of oil, pure electric vehicle closed-loop control, which is added, increases journey system, driving motor, drive
Dynamic electric machine controller, power management control module, propeller shape at oil control closed-loop control system.If increasing the power generation of journey system
Power P oil is more than the output power P paddles of power drive system, and rotary engine drives electrical power generators, a part of electric energy to be provided to
Driving motor, another part electric energy are provided to power battery, charge to power battery；If increasing the generated output of journey system
P oil is less than the output power P paddles of power drive system, is powered jointly to driving motor by increasing journey system and power battery at this time.
In the case where hybrid power aeroplane is in the electric blend modes of operation of oil, the generated output P oil for only increasing journey system meets electricity
Under the premise of the output power P paddles of drive system, increasing journey system can just charge to power battery, until power battery fills
Electricity reaches charging safety value (the charging safety value is set as P peaces), and hybrid power aeroplane switches to pure electric mode, power
The dynamic output power P paddles for being electrically driven system of the storage power P of battery are consumed, and P is dynamic to be set less than P, and hybrid power aeroplane enters
Mixed dynamic state, foundation detection quantity of power, the difference of the operating mode operating mode that switching pure electric vehicles, oily control, oil electricity mixing control in real time,
So cycle.
It is pure that power battery, driving motor, drive motor controller, power management control module, propeller etc. form closed loop
Power driven system, according to the rotary speed instruction that throttle push rod provides, power management control module detects the output power of propeller, in turn
The discharge capacity of power battery is controlled, driving motor controls rotating speed size using two close cycles vector control strategy.According to power battery
Storage power, propeller output power size, adjust the aperture of the electronic damper of rotary engine, adjustment increases journey system
Generated energy, form the throttle opening of rotary engine and the closed-loop control system of generated energy, wherein：
Calculation formula dynamic the storage power P of power battery is：P moves=power battery voltage (V) * battery capacities (Ah)；
The calculation formula of generated output P oil for increasing journey system is：Rotating speed (n1) * generators of P oil=rotary engine
Generated energy conversion constant (K)；
The calculation formula of the output power P paddles of power drive system is：Rotating speed (n2) * propellers of P paddles=driving motor
It loads (Tn)/9550.
When serial mixed power aircraft switches to pure electric mode, control process flow chart as shown in figure 4,
Airplane throttle push rod sends out driving motor rotary speed instruction, and drive motor controller receives driving motor rotary speed instruction, driving motor
Output power of the controller according to driving motor matching propeller, controls opening for the power line of power battery and driving motor
Logical, power battery is powered for driving motor, output of the battery management system according to the output power matching power battery of propeller
Power, ultimately forms closed loop pure electric vehicle system, and with the storage power of power battery in order to control parameter switching pure electric vehicle state or
Oily electricity admixture S37.
When serial mixed power aircraft switches to oily electric blend modes of operation, flow chart such as Fig. 5 institutes of process are controlled
Show, throttle push rod sends out driving motor rotary speed instruction, and integrated manipulator detects that the storage power P of power battery is dynamic and is difficult to maintain
The output power P paddles of propeller, under the premise of not changing rotating speed, distribution increases the generated output of journey system, increases unification side of journey system
Face maintains generating state, on the other hand regulates and controls the electronic damper aperture and generated output of rotary engine, increases journey system and enters oil
Closed-loop control state is controlled, control system foundation increases the generated output P oil of journey system, the storage power P of power battery is moved, propeller
Output power P paddle threes relationship, regulate and control control model (automatically controlled pattern, oily control pattern or the electric hybrid guided mode of oil of whole system
Formula).
Serial mixed power aircraft measures the control strategy for considering complete machine with the power of subsystem in order to control, controls plan in detail
It is slightly as described below：
(1) if P moves >=P paddles, i.e. the storage power of power battery maintains the output power of power drive system, control system enough
System enters automatically controlled state, enters oily control state in power points (P moves-P paddles), hybrid power aeroplane switches to oil control operating mode；
(2) if P moves ＜ P paddles, i.e. the storage power of power battery is not enough to maintain the output power of power drive system, mixing
Dynamical system needs rotary engine to provide power, and hybrid power aeroplane switches to oily electric blend modes of operation；
(3) if P moves ＜ P paddles and P oil >=(P paddles-P dynamic), output power (P oil-(P paddles-P is dynamic)) that oil control at this time has more to
Power battery charging；
(4) if P moves ＜ P paddles and P oil ＜ (P paddles-P is dynamic), P moves the maximum power that can be exported for power battery, collects at this time
Being sent out at controller reduces the instruction of driving motor rotating speed；
(5) if P oil >=P paddles, that is, the generated output P oil for increasing journey system maintains the output power P paddles of power drive system enough,
Hybrid power aeroplane switches to oil control operating mode, and the output power that oil control has more is moved to reach and be set to power battery charging, at this time P
Dingan County total power P pacifies, into automatically controlled state；
(6) if P oil ＜ P paddles, that is, increase journey system generated output P shortages of oil to maintain the output power of power drive system,
Dynamical system needs additional automatically controlled offer power, hybrid power aeroplane to switch to oily electric blend modes of operation；
(7) if P oil ＜ P paddles and P it is dynamic >=(P paddles-P oil), power battery power is consumed to lowest power point (P paddles-P
Oil), integrated manipulator sends out the instruction for the electronic damper aperture for improving rotary engine at this time, to improve turning for rotary engine
Speed；
(8) if P oil ＜ P paddles, and additional automatically controlled peak power output P moves ＜ (P paddles-P oil), and P oil is maximum power,
Integrated manipulator sends out the instruction for reducing driving motor rotating speed at this time；
(9) if P oil+P it is dynamic >=P paddles, not discuss P oil >=P paddles, P it is dynamic >=operating modes of P paddles, it is dynamic by reducing P oil or P
Power maintain power match, in the case where not changing the operating mode of rotating speed of propeller, reduce rotary engine electronic damper aperture and
The rotating speed of rotary engine and the output current of power battery etc.；
(10) if P oil+P moves ＜ P paddles, not in the operating mode for discussing the dynamic ＜ P paddles of P oil ＜ P paddles, P, do not changing turning for propeller
Under the operating mode of speed, the output current etc. of the electronic damper aperture and rotating speed and power battery of rotary engine is improved.
The present invention is exemplarily described above in association with attached drawing.Obviously, present invention specific implementation is not by above-mentioned side
The limitation of formula.As long as using the improvement of the various unsubstantialities of inventive concept and technical scheme of the present invention progress；Or not
It is improved, the above-mentioned design of the present invention and technical solution are directly applied into other occasions, in protection scope of the present invention
Within.
Claims (10)
1. serial mixed power aircraft, including hybrid power system, which is characterized in that the hybrid power system includes power
Battery increases journey system and power drive system, increases journey system and includes generator and connect with generator and generator is driven to be sent out
The rotary engine of electricity, power drive system include propeller and provide the driving motor of driving force for propeller, and power battery is
Driving motor provides electric energy.
2. serial mixed power aircraft according to claim 1, which is characterized in that the hybrid power system further includes
Integrated manipulator and drive motor controller, integrated manipulator and the power battery, drive motor controller and the power generation
Mechatronics, the driving motor are electrically connected with drive motor controller.
3. serial mixed power aircraft according to claim 1 or 2, which is characterized in that the driving motor is permanent magnetism
Synchronous AC motor.
4. serial mixed power aircraft according to any one of claims 1 to 3, which is characterized in that the power battery is
Lithium battery.
5. according to any serial mixed power aircraft of claim 2 to 4, which is characterized in that the integrated manipulator
The three-phase alternating current that the generator generates is rectified into direct current, is powered for the driving motor.
6. according to any serial mixed power aircraft of claim 2 to 5, which is characterized in that further include power management
Control module, power management control module fly according to the storing electricity of power battery or by the current aircraft of height sensor acquisition
Row altitude information is judged, is controlled the integrated manipulator and is started the rotary engine.
7. the control method of any serial mixed power aircraft of claim 1 to 7, which is characterized in that by mixed
Close the control of dynamical system, the output of the storage power of foundation power battery, the generated output and power drive system of increasing journey system
Power, control hybrid power aeroplane carry out between pure electric mode, the electric blend modes of operation of oil and oil control operating mode
Switching.
8. the control method of serial mixed power aircraft according to claim 7, which is characterized in that when power battery
When storage power is more than the output power of propeller, hybrid power aeroplane is in pure electric mode；Hybrid power aeroplane exists
When the takeoff and landing stage, if the storage power of power battery is mixed less than the setting value of the secure storage power of power battery
It closes motor plane and is in oil control operating mode；Hybrid power aeroplane is in cruising phase, if the storage power of power battery is more than
The setting value of the secure storage power of power battery, then hybrid power aeroplane is in oil control operating mode or the electric hybrid working mould of oil
Formula.
9. the control method of serial mixed power aircraft according to claim 7 or 8, which is characterized in that dynamic in mixing
When power aircraft is in oil electricity blend modes of operation, if the generated output for increasing journey system is greater than or equal to the output power of propeller,
Then increase journey system to charge to power battery, until the storage power of power battery reaches setting value, then hybrid power flies
Machine-cut changes pure electric mode into.
10. according to the control method of any serial mixed power aircraft of claim 7 to 9, which is characterized in that mixed
When closing motor plane in oil electricity blend modes of operation, after drive motor controller receives enabled instruction, power battery is to drive
Dynamic motor power supply, makes driving motor operate, and driving motor drives propeller rotational, drive motor controller driving motor to match spiral shell
Revolve the output power of paddle, output electricity of the battery management system according to the output power matching power battery of propeller, most end form
At closed loop pure electric vehicle system.
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