CN109693796A - Aircraft oil electricity mixing energy supplying system, aircraft and its control method - Google Patents
Aircraft oil electricity mixing energy supplying system, aircraft and its control method Download PDFInfo
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- CN109693796A CN109693796A CN201811653822.4A CN201811653822A CN109693796A CN 109693796 A CN109693796 A CN 109693796A CN 201811653822 A CN201811653822 A CN 201811653822A CN 109693796 A CN109693796 A CN 109693796A
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- 230000005611 electricity Effects 0.000 title claims abstract description 50
- 238000000034 method Methods 0.000 title claims abstract description 33
- 238000005183 dynamical system Methods 0.000 claims abstract description 40
- 239000000446 fuel Substances 0.000 claims abstract description 31
- 239000007858 starting material Substances 0.000 claims description 12
- 238000012544 monitoring process Methods 0.000 claims description 5
- 230000008569 process Effects 0.000 abstract description 14
- 239000000126 substance Substances 0.000 abstract description 4
- 238000002485 combustion reaction Methods 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 40
- 239000000295 fuel oil Substances 0.000 description 8
- 239000002828 fuel tank Substances 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 230000007613 environmental effect Effects 0.000 description 4
- 238000005265 energy consumption Methods 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- -1 sounds an alarm Substances 0.000 description 1
- 239000013589 supplement Substances 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
- 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
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The present invention provides a kind of aircraft oil electricity mixing energy supplying system, aircraft and its control methods, including engine system, engine controller, dynamical system and fuel system, engine system includes engine and generator, fuel system is connect by oil circuit with engine, the power output end of engine is drivingly connected generator, generator connects engine controller, and engine controller controls connect dynamical system.By the mechanical energy for converting the chemical energy generated in fuel combustion process in engine, mechanical energy is passed to generator movement by engine, generator is set to convert electric energy for mechanical energy, engine controller distributes to dynamical system after rectifying electric energy, it is stronger compared to the aircraft cruising ability of pure electric vehicle, and engine does not directly drive power system operational, aircraft flight is more steady reliable in the process.
Description
Technical field
The present invention relates to aircraft field, in particular to a kind of aircraft oil electricity mixing energy supplying system, aircraft with
And its control method.
Background technique
In recent years with the development of automatic technology, the type of aircraft is also more cumulative more, and reliable and stable dynamical system is
The basis that aircraft can work normally.Battery or fuel oil is widely used as operation power source, by battery in aircraft at present
Energy density is low to be restricted with weak equal performance short slab of low temperature discharge ability itself, and pure electric vehicle aircraft flight endurance is shorter；It is another
There is operational reliability by fuel engines functional reliability and such environmental effects, using the aircraft of fuel engines in class
Limitation.
Inventor has found that the dynamical system of traditional aircraft at least has the following disadvantages: under study for action
One, the aircraft using battery as power are limited by battery performance itself, when aircraft use process is continued a journey
Between it is short；Constant with battery power consumption process battery itself weight, system output power is constant, reduces with cell voltage, causes
The case where battery discharge current increases, and battery discharge ability reduces；Cell discharge performance drastically reduces in low temperature environment, serious to make
About cruise duration and flight safety.
Secondly, use fuel engines as the aircraft of power, fuel engines is directly as power drive dynamical system
The process of system work, the vibration that aircraft is subject to is big, is unfavorable for the smooth flight of aircraft；In addition, fuel engines is exposed to
Outside aircraft body, operational process is easy situations such as being influenced and being stopped working by use environment.
Summary of the invention
The purpose of the present invention is to provide a kind of aircraft oil electricity mixing energy supplying systems, to improve traditional aircraft power
System has that battery energy density is low, cruising ability is weak and oil burning power system is larger by such environmental effects.
The object of the invention is also to provide a kind of aircraft, and to improve traditional Power System of Flight Vehicle, there are battery energy
The problem that metric density is low, cruising ability is weak and oil burning power system is larger by such environmental effects.
The object of the invention is also to provide a kind of flying vehicles control methods, are deposited with the Power System of Flight Vehicle for improving traditional
In the problem that battery energy density is low, cruising ability is weak and oil burning power system is larger by such environmental effects.
The embodiment of the present invention is achieved in that
Based on above-mentioned first purpose, the present invention provides a kind of aircraft oil electricity mixing energy supplying systems, including engine system
System, engine controller, dynamical system and fuel system, the engine system include engine and generator, described
Fuel system is connected with the engine by oil circuit, and the power output end of the engine is drivingly connected the generator, institute
It states generator and connects the engine controller, the engine controller controls connect the dynamical system.
It further include battery pack in preferred embodiments of the present invention, the engine controller controls connect the battery
Group.
In preferred embodiments of the present invention, the battery pack is set as rechargeable battery pack.
In preferred embodiments of the present invention, the engine system further includes starter, the starter control connection
The engine, the engine controller connect the starter.
In preferred embodiments of the present invention, the fuel system is provided with the sensor for monitoring oil mass, the biography
Sensor is connect with the engine controller.
It further include automatic pilot in preferred embodiments of the present invention, the engine controller is driven automatically with described
Sail instrument connection.
Based on above-mentioned second purpose, the present invention provides a kind of aircraft, including body and the aircraft oil electricity
Energy supplying system is mixed, the aircraft oil electricity mixing energy supplying system is installed in the body.
In preferred embodiments of the present invention, the body is unmanned plane body.
Based on above-mentioned third purpose, the present invention provides a kind of flying vehicles control methods should suitable for the aircraft
Control method includes:
Starting engine, the driven by engine generator moves so that the electrical power generators,
The electricity that the generator issues is delivered to engine controller, and the engine controller is defeated by the electric energy after rectification
Out to dynamical system so that the dynamical system operation.
In preferred embodiments of the present invention, the control method further include:
When the engine system operation exception, the engine system is switched to battery by the engine controller
Group is dynamical system energy supply by the battery pack,
Alternatively, it is defeated that the engine controller controls battery pack participates in power when the engine system energizes insufficient
It out, is jointly the dynamical system energy supply with the engine system.
The beneficial effect of the embodiment of the present invention is:
In conclusion the embodiment of the invention provides a kind of aircraft oil electricity mixing energy supplying system, by by fuel burning
The chemical energy generated in the process is converted into the mechanical energy of engine, and mechanical energy is passed to generator and moved, makes to generate electricity by engine
Mechanical energy is converted electric energy by machine, and engine controller distributes to dynamical system after rectifying electric energy, compared to the flight of pure electric vehicle
Device cruising ability is stronger, and engine does not directly drive power system operational, and aircraft flight is more steady reliable in the process.Tool
Body is as follows:
Aircraft oil electricity mixing energy supplying system provided in this embodiment, includes engine system, engine controller, moves
Force system and fuel system, engine system include engine and generator, and engine passes through oil circuit and fuel system
Connection, fuel system provide necessary fuel oil for engine operation, and engine driving is connected to generator, engine working process
In, converting mechanical energy to the electric energy of generator sending, generator is connect with engine controller, meanwhile, engine controller
Control connection dynamical system is in this way, the electricity that generator issues distributes after being rectified by engine controller to dynamical system
The work of Force system provides electric energy.Oil electricity mixing energy supplying system provided in this embodiment can be completely disposed at the inside of aircraft,
Engine operating environment is stablized, and will not be influenced to cause engine failure by aircraft local environment.Meanwhile according in aircraft
Portion's space allocation engine mounting means can be very good to eliminate, reduce for aircraft to the vibration of engine operation
The influence of itself.
Aircraft provided in this embodiment includes above-mentioned aircraft oil electricity mixing energy supplying system, has above-mentioned aircraft oil
All advantages of electricity mixing energy supplying system.
Flying vehicles control method provided in this embodiment is suitable for above-mentioned aircraft oil electricity mixing energy supplying system, has upper
State all advantages of aircraft oil electricity mixing energy supplying system.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, below will be to needed in the embodiment attached
Figure is briefly described, it should be understood that the following drawings illustrates only certain embodiments of the present invention, therefore is not construed as pair
The restriction of range for those of ordinary skill in the art without creative efforts, can also be according to this
A little attached drawings obtain other relevant attached drawings.
Fig. 1 is the schematic diagram of the aircraft oil electricity mixing energy supplying system of the embodiment of the present invention 1；
Fig. 2 is the schematic diagram of a distressed structure of the aircraft oil electricity mixing energy supplying system of the embodiment of the present invention 1；
Fig. 3 is the schematic diagram of another distressed structure of the aircraft oil electricity mixing energy supplying system of the embodiment of the present invention 1；
Fig. 4 is the schematic diagram of the aircraft oil electricity mixing energy supplying system of the embodiment of the present invention 2；
Fig. 5 is the flow chart of the control method of the aircraft of the embodiment of the present invention 4.
Icon: 100- engine system；110- engine；120- generator；130- starter；200- engine
Controller；300- dynamical system；400- fuel system；410- sensor；500- battery pack；600- automatic pilot.
Specific embodiment
Currently, aircraft mainly uses battery or fuel oil to be independently used as the energy for dynamical system energy supply.Made using battery
It is limited for the aircraft of power by battery performance itself, aircraft use process is short cruise duration；Battery power consumption process electricity
Pond own wt is constant, and system output power is constant, reduces with cell voltage, and battery discharge current is caused to increase, battery discharge
The case where ability reduces.Cell discharge performance drastically reduces in low temperature environment, serious to restrict cruise duration and flight safety.Using
Aircraft of the fuel engines as direct driving force, operational process are easy situations such as being influenced and being stopped working by use environment.
In consideration of it, inventor devises, a kind of aircraft oil is electric to mix energy supplying system, aircraft and its control method, leads to
The mechanical energy that the chemical energy that will be generated in fuel combustion process is converted into engine is crossed, the mechanical energy of engine directly drives power generation
Machine operation, makes generator convert electric energy for mechanical energy, engine controller is distributed to dynamical system after rectifying electric energy, compared
The aircraft cruising ability of pure electric vehicle is stronger, and engine does not directly drive power system operational, during aircraft flight more
Add steady reliable.
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.The present invention being usually described and illustrated herein in the accompanying drawings is implemented
The component of example can be arranged and be designed with a variety of different configurations.
Therefore, the detailed description of the embodiment of the present invention provided in the accompanying drawings is not intended to limit below claimed
The scope of the present invention, but be merely representative of selected embodiment of the invention.Based on the embodiments of the present invention, this field is common
Technical staff's every other embodiment obtained without creative efforts belongs to the model that the present invention protects
It encloses.
It should also be noted that similar label and letter indicate similar terms in following attached drawing, therefore, once a certain Xiang Yi
It is defined in a attached drawing, does not then need that it is further defined and explained in subsequent attached drawing.
In the description of the present invention, it should be noted that the orientation or position of the instructions such as term " on ", "lower", "inner", "outside"
Set relationship be based on the orientation or positional relationship shown in the drawings or the invention product using when the orientation or position usually put
Relationship is set, is merely for convenience of description of the present invention and simplification of the description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.
In the description of the present invention, it is also necessary to which explanation is unless specifically defined or limited otherwise, term " setting ",
" installation ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integrally connect
It connects；It can be mechanical connection, be also possible to be electrically connected；It can be directly connected, can also indirectly connected through an intermediary, it can
To be the connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood with concrete condition
Concrete meaning in the present invention.
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the present invention can phase
Mutually combination.
Embodiment 1
Referring to Fig. 1, a kind of aircraft oil electricity mixing energy supplying system is present embodiments provided, suitable for the power to aircraft
The energy of the offer need of work of system 300, wherein aircraft for example can be but be not limited to unmanned plane.
Referring to Fig. 2, aircraft oil electricity mixing energy supplying system provided in this embodiment includes engine system 100, starts
Machine controller 200, dynamical system 300 and fuel system 400, engine system 100 include engine 110 and generator
120, fuel system 400 is connect by oil circuit with engine 110, and the power output end of engine 110 is drivingly connected generator
120, generator 120 connects engine controller 200, the control connection dynamical system 300 of engine controller 200.
Aircraft oil electricity mixing energy supplying system provided in this embodiment, includes engine system 100, engine controller
200, dynamical system 300 and fuel system 400, engine system 100 include engine 110 and generator 120, are started
Machine 110 is connect by oil circuit with fuel system 400, and fuel system 400 provides necessary fuel oil for the work of engine 110, is started
Machine 110 is drivingly connected in generator 120,110 course of work of engine, converts the electricity that generator 120 issues for mechanical energy
Can, generator 120 is connect with engine controller 200, meanwhile, the control connection dynamical system 300 of engine controller 200, this
Sample, distribution is dynamical system 300 to dynamical system 300 after the electricity that generator 120 issues is rectified by engine controller 200
Work provide electric energy.Oil electricity mixing energy supplying system provided in this embodiment can be completely disposed at the inside of aircraft, engine
110 running environment are stablized, and will not be influenced to cause 110 failure of engine by aircraft local environment.Meanwhile according in aircraft
110 mounting means of portion's space allocation engine, to engine 110 run vibration can be very good to eliminate, reduce for
The influence of aircraft itself.In aircraft operational process, with the reduction of fuel oil, the weight saving of aircraft, energy consumption is reduced,
Enhance cruising ability.
In the present embodiment, it should be noted that fuel system 400 includes fuel tank and oil circuit, and oil circuit is connected to fuel tank,
Oil circuit is directly connected on engine 110, converts power generation for the chemical energy that fuel burning generates in 110 course of work of engine
Machine 120 works required mechanical energy, and generator 120 converts electric energy for mechanical energy again, in this way, engine system 100 will generate electricity
The dynamical system 300 of aircraft is distributed to after the electric rectification that machine 120 issues, the work for the dynamical system 300 of aircraft provides
The energy.
Optionally, the dynamical system 300 of aircraft includes motor and propeller, and propeller is mounted on the output of motor
On axis, electrical energy transportation to the motor for controlling propeller rotational rotates motor and then drives rotation by engine controller 200
Wing rotation.
It should be appreciated that the fuel tank size of fuel system 400 is arranged on demand, size and shape is herein without specifically limiting
It is fixed.
Referring to Fig. 3, it is optional, the sensor 410 for monitoring oil mass is installed in the fuel tank of fuel system 400,
The sensor 410 can be liquid level sensor, buoyancy sensor or pressure sensor, for detecting the height of oil mass, in turn
The number of oil mass in fuel tank judged.It in fuel tank when low on fuel, sounds an alarm, fuel oil or emergency operation can be added in time
(for example, if flight course will make a return voyage landing immediately without fuel oil, avoiding empty that accident occurs).
In the present embodiment, the dynamical system 300 that engine controller 200 can also monitor aircraft works required power,
Then it generates electricity in the engine 110 of Reverse Turning Control engine system 100 according to actually required Power operation.
Optional in the present embodiment, engine system 100 further includes having starter 130, and the work of starter 130 drives hair
Motivation 110 works.In 110 course of work of engine, engine controller 200 can monitor the work of engine system 100
State, if monitoring engine 110 is flame-out, engine controller 200 controls starter 130 and is again started up engine 110, works
Securely and reliably.
Referring to Fig. 3, aircraft oil electricity mixing energy supplying system further includes automatic pilot 600, engine in the present embodiment
Controller 200 is connect with automatic pilot 600.Engine controller 200 can be carried out by data-interface and automatic pilot 600
The working condition of entire energy supplying system is fed back to automatic pilot 600 by connection, while automatic pilot 600 can be according to negative
Demand control engine operating state is carried, and then entire energy supplying system is controlled.
It should be noted that automatic pilot 600 can be the automatic pilot of AP series.
Embodiment 2
Referring to Fig. 4, the present embodiment also provides a kind of aircraft oil electricity mixing energy supplying system, including above-described embodiment 1
The aircraft oil electricity of offer mixes energy supplying system, and technical solution disclosed in above-described embodiment 1 is equally applicable to the present embodiment, in order to
Narration is avoided to repeat burden, the technical solution that above-described embodiment 1 has been described is not repeated to illustrate, in the present embodiment, aircraft
Oily electricity mixing energy supplying system further includes battery pack 500.
Engine controller 200 connects battery pack 500, and battery pack 500 connects dynamical system 300.Aircraft operational process
In, if 100 operation irregularity of engine system, engine controller 200 can be smoothly switched battery pack 500 directly as dynamic
The drive energy of Force system 300.
Alternatively, the energy consumption as needed for conventional aircraft landing process is maximum, if in aircraft landing stage dynamical system
Power needed for system 300 exceeds 100 peak power output of engine system, then it is same will to control battery pack 500 for engine controller 200
When participate in power output, guarantee aircraft landing safety.
Further, rechargeable battery pack is set by battery pack 500.Battery pack 500 is electrically connected generator 120.Start
Machine controller 200 charges the battery the power output after rectification to battery pack 500.Further, engine controller
The voltage value of 200 monitoring battery packs 500 is filled battery pack 500 using setting power after cell voltage is lower than setting value
Electricity；It after cell voltage is not less than setting value, will not charge to battery pack 500, and save the energy.By the way that battery pack 500 is arranged
Supplement for rechargeable battery pack, electric energy is more convenient, provides better guarantee for the flight of aircraft.
Further, engine controller 200 can control the charging voltage and output power of battery pack 500.
Further, power needed for engine controller 200 monitors battery pack 500 and dynamical system 300, Reverse Turning Control hair
Motivation system 100 generates electricity according to actually required Power operation.
Further, battery pack 500 is electrically connected starter 130, and the starting for starter 130 provides electric energy.
Embodiment 3
A kind of aircraft is present embodiments provided, is flown including what body and above-described embodiment 1 or embodiment 2 were mentioned
Row device oil electricity mixing energy supplying system, aircraft oil electricity mixing energy supplying system are installed in body.
Optionally, body is unmanned plane body.
Embodiment 4
Referring to Fig. 5, present embodiments providing a kind of flying vehicles control method, fly suitable for what above-described embodiment 3 was mentioned
Row device, the control method include:
Start engine 110, engine 110 drive generator 120 move so that generator 120 generate electricity,
The electricity that generator 120 issues is delivered to engine controller 200, and engine controller 200 is by the electric energy after rectification
Output is to dynamical system 300 so that 300 operation of dynamical system.
Optionally, this method further includes when 100 operation irregularity of engine system, and engine controller 200 is by engine
It is that dynamical system 300 energizes that system 100, which switches to battery pack 500 by battery pack 500,
Alternatively, engine controller 200 controls battery pack 500 and participates in power when engine system 100 energizes deficiency
Output energizes jointly for dynamical system 300 with engine system 100.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of aircraft oil electricity mixing energy supplying system, which is characterized in that including engine system, engine controller, power
System and fuel system, the engine system include engine and generator, and the fuel system passes through oil circuit and institute
Engine connection is stated, the power output end of the engine is drivingly connected the generator, starts described in the generator connection
Machine controller, the engine controller controls connect the dynamical system.
2. aircraft oil electricity mixing energy supplying system according to claim 1, which is characterized in that it further include battery pack, it is described
Engine controller controls connect the battery pack.
3. aircraft oil electricity mixing energy supplying system according to claim 2, which is characterized in that the battery pack is set as can
Rechargeable battery set.
4. according to the oil electricity mixing energy supplying system of aircraft described in claim 2 or 3, which is characterized in that the engine system
System further includes starter, and the starter control connects the engine, and the engine controller connects the starter.
5. aircraft oil electricity mixing energy supplying system according to claim 1, which is characterized in that the fuel system is provided with
For monitoring the sensor of oil mass, the sensor is connect with the engine controller.
6. aircraft oil electricity mixing energy supplying system according to claim 1, which is characterized in that it further include automatic pilot,
The engine controller is connect with the automatic pilot.
7. a kind of aircraft, which is characterized in that including body and aircraft according to claim 1 to 6
Oily electricity mixing energy supplying system, the aircraft oil electricity mixing energy supplying system are installed in the body.
8. aircraft according to claim 7, which is characterized in that the body is unmanned plane body.
9. a kind of flying vehicles control method, which is characterized in that suitable for flight described in any one of the claims 7-8
Device, the control method include:
Starting engine, the driven by engine generator moves so that the electrical power generators,
The electricity that the generator issues is delivered to engine controller, the engine controller by the power output after rectification extremely
Dynamical system is so that the dynamical system operation.
10. flying vehicles control method according to claim 9, which is characterized in that the control method further include:
When the engine system operation exception, the engine controller by the engine system switch to battery pack by
The battery pack is dynamical system energy supply,
Alternatively, the engine controller controls battery pack participates in power output when the engine system energizes insufficient, with
The engine system is the dynamical system energy supply jointly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201811653822.4A CN109693796A (en) | 2018-12-29 | 2018-12-29 | Aircraft oil electricity mixing energy supplying system, aircraft and its control method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811653822.4A CN109693796A (en) | 2018-12-29 | 2018-12-29 | Aircraft oil electricity mixing energy supplying system, aircraft and its control method |
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| CN109693796A true CN109693796A (en) | 2019-04-30 |
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| CN201811653822.4A Pending CN109693796A (en) | 2018-12-29 | 2018-12-29 | Aircraft oil electricity mixing energy supplying system, aircraft and its control method |
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| CN116902210A (en) * | 2023-09-13 | 2023-10-20 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Energy supply method and device for aircraft onboard system |
| CN116902210B (en) * | 2023-09-13 | 2023-12-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Energy supply method and device for aircraft onboard system |
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