CN113772104A - Oil-electricity hybrid power device capable of being used for medium-sized and large-sized unmanned aerial vehicles and unmanned aerial vehicle - Google Patents
Oil-electricity hybrid power device capable of being used for medium-sized and large-sized unmanned aerial vehicles and unmanned aerial vehicle Download PDFInfo
- Publication number
- CN113772104A CN113772104A CN202110886598.9A CN202110886598A CN113772104A CN 113772104 A CN113772104 A CN 113772104A CN 202110886598 A CN202110886598 A CN 202110886598A CN 113772104 A CN113772104 A CN 113772104A
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- engine
- electric
- hybrid power
- waste heat
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000002918 waste heat Substances 0.000 claims abstract description 35
- 238000004146 energy storage Methods 0.000 claims abstract description 26
- 238000011084 recovery Methods 0.000 claims abstract description 20
- 239000000446 fuel Substances 0.000 claims abstract description 19
- 238000012544 monitoring process Methods 0.000 claims abstract description 16
- 239000000295 fuel oil Substances 0.000 claims abstract description 9
- 239000007788 liquid Substances 0.000 claims description 14
- 239000000498 cooling water Substances 0.000 claims description 9
- 230000005611 electricity Effects 0.000 claims description 6
- 239000003921 oil Substances 0.000 claims description 4
- 238000004891 communication Methods 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- 239000010729 system oil Substances 0.000 claims 1
- 238000011161 development Methods 0.000 abstract description 4
- 238000005265 energy consumption Methods 0.000 abstract description 3
- 239000003344 environmental pollutant Substances 0.000 abstract description 3
- 231100000719 pollutant Toxicity 0.000 abstract description 3
- 230000002194 synthesizing effect Effects 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000010248 power generation Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- BASFCYQUMIYNBI-UHFFFAOYSA-N platinum Chemical compound [Pt] BASFCYQUMIYNBI-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052697 platinum Inorganic materials 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02G—HOT GAS OR COMBUSTION-PRODUCT POSITIVE-DISPLACEMENT ENGINE PLANTS; USE OF WASTE HEAT OF COMBUSTION ENGINES; NOT OTHERWISE PROVIDED FOR
- F02G5/00—Profiting from waste heat of combustion engines, not otherwise provided for
- F02G5/02—Profiting from waste heat of exhaust gases
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Hybrid Electric Vehicles (AREA)
Abstract
The invention discloses a gasoline-electricity hybrid power device for a medium-sized and large-sized unmanned aerial vehicle and the unmanned aerial vehicle, wherein the unmanned aerial vehicle is provided with an electric system and a fuel system, the electric system comprises a controller and a motor, the fuel system comprises an engine and a throttle, and the throttle is provided with a throttle steering engine and comprises: engine exhaust waste heat recovery system and energy storage charging system, engine exhaust waste heat recovery system is connected with fuel oil system, energy storage charging system is connected with electric system, hybrid power output system, acquisition control includes control structure and monitoring structure, this hybrid device is through synthesizing the optimal utilization to the energy, impel the engine and the effectual combination of electric propulsion is in the same place, and be used for the battery to charge with aviation piston engine exhaust waste heat high-efficient recovery, can effectively reduce energy consumption and reduce pollutant emission, good development prospect has, the time of endurance and the journey that also can greatly increase medium and large-scale unmanned aerial vehicle simultaneously.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicle power machinery, and particularly relates to a gasoline-electric hybrid power device for a medium-sized and large-sized unmanned aerial vehicle and the unmanned aerial vehicle.
Background
The aviation piston engine is favored by vast middle and large unmanned aerial vehicle manufacturers by virtue of the advantages of small volume, low cost, reliable work and the like. However, the thermal efficiency of the aviation piston engine is low, the oil consumption is generally high, the endurance time and range of the medium-and-large unmanned aerial vehicle are greatly limited, and therefore unmanned aerial vehicle manufacturers begin to search for new power schemes to improve tactical performance indexes of the medium-and-large unmanned aerial vehicle. With the development of science and technology, the oil-electricity hybrid power technology has been widely applied to automobiles and has entered the civil market. However, the technology of integrating hybrid power in the general aviation field is still in the test starting stage.
Disclosure of Invention
The hybrid power device effectively combines engine propulsion and electric propulsion by comprehensively and optimally utilizing energy, efficiently recovers the exhaust waste heat of the aviation piston engine for charging the storage battery, can effectively reduce energy consumption and pollutant discharge, and has good development prospect. Compared with the traditional unmanned aerial vehicle power system, the novel oil-electricity hybrid power device can greatly reduce the flight cost, and greatly increase the endurance time and range of the medium-sized and large-sized unmanned aerial vehicles.
In order to achieve the above object, the present invention provides a hybrid power plant for a medium-large unmanned aerial vehicle, which has an electric system and a fuel system, wherein the electric system includes a controller and an electric motor, the fuel system includes an engine and a throttle, and the throttle is provided with a throttle steering engine, including:
the engine exhaust waste heat recovery system is connected with the fuel oil system, the energy storage charging system is connected with the electric system, the engine exhaust waste heat recovery system can utilize waste heat of the fuel oil system to generate waste heat power, and the energy storage charging system can store the waste heat power and supply power for the electric system;
the hybrid power output system is connected with the electric system and the fuel system and can control the electric system and/or the fuel system to output power;
the collection control system comprises a control structure and a monitoring structure and can control and monitor working parameters of the engine exhaust waste heat recovery system, the energy storage and charging system and the hybrid power output system.
Optionally, the monitoring structure includes collection module and a plurality of sensor, collection module with control structure communication is connected, and is a plurality of the sensor can monitor each part operation conditions that is used for medium and large-scale unmanned aerial vehicle's oil-electricity hybrid power device.
Optionally, the engine exhaust waste heat recovery system comprises an organic rankine cycle loop, the organic rankine cycle loop comprises an evaporator, an expander, a condenser, a flowmeter, a liquid storage tank, a working medium filter and a working medium pump which are connected end to end, and the evaporator is connected with the engine.
Optionally, the control structure comprises:
the control unit and the first electric valve are arranged on the water inlet of the condenser;
the second electric valve is arranged between the liquid storage tank and the working medium filter;
a control unit connected with the first electrically operated valve, the second electrically operated valve and the monitoring structure.
Optionally, the energy storage charging system comprises an energy storage charging loop, the energy storage charging loop comprises a generator, a rectifier, a charger, a switch relay and a storage battery which are connected end to end, and the storage battery is connected with the controller.
Optionally, the hybrid power output system comprises a torque combiner/divider, one end of which is provided with a gearbox connected to a propeller, and the other end of which is connected to both the engine and the electric motor.
Optionally, a plurality of the sensors comprises:
a pressure sensor disposed on a working medium pipe connected between the evaporator and the expander;
a flowmeter arranged on the working medium pipeline between the condenser and the liquid storage tank,
a first temperature sensor provided in an exhaust pipe connected between the engine and the evaporator;
a second temperature sensor provided on a working medium line connected between the evaporator and the expander;
the third temperature sensor is arranged on an exhaust pipeline on one side of the evaporator, which is far away from the expander;
a fourth temperature sensor disposed on a cooling water line connected between the first electric valve and the condenser;
the fifth temperature sensor is arranged on the cooling water pipeline on one side, away from the first electric valve, of the condenser;
a throttle position sensor provided on the throttle valve;
the propeller rotating speed sensor is arranged on the bracket at the side of the propeller;
and the engine rotating speed sensor is connected with the crankshaft of the engine.
Optionally, the monitoring structure further comprises a storage module, and the storage module can store monitoring data of a plurality of sensors.
Optionally, a bypass valve is further included, the bypass valve being connected in parallel with the evaporator, the bypass valve being connected to the control unit.
An unmanned aerial vehicle, includes the foretell oily electric hybrid device who is used for medium and large-scale unmanned aerial vehicle of basis.
The invention provides a gasoline-electricity hybrid power device for a medium-large unmanned aerial vehicle, which has the beneficial effects that:
1. the hybrid power device effectively combines engine propulsion and electric propulsion together by comprehensively optimizing and utilizing energy, and effectively recovers the exhaust waste heat of the aviation piston engine for charging the storage battery, so that the energy consumption can be effectively reduced, the pollutant emission can be reduced, and the hybrid power device has a good development prospect. Compared with the traditional unmanned aerial vehicle power system, the novel oil-electricity hybrid power device can greatly reduce the flight cost, and greatly increase the endurance time and range of the medium-sized and large-sized unmanned aerial vehicles.
2. This hybrid power device passes through organic rankine cycle system and retrieves aviation piston engine exhaust waste heat for the battery charges, can improve energy utilization rate, very big improvement unmanned aerial vehicle duration and voyage.
3. This hybrid power device utilizes torque synthesizer/separator with fuel power output line and electric energy output line coupling, and two power output lines both can the autonomous working, can the collaborative work again, make unmanned aerial vehicle's driving system more nimble, can satisfy different flight operating mode demands, reach tactics performance index.
4. The organic Rankine cycle system for recovering the exhaust waste heat of the engine by the hybrid power device has a simple structure and high recovery efficiency, and can realize industrialization; a transmission mechanism (torque synthesizer/separator, etc.) as a key component is a well-established technique. The device has the advantages of high reliability, less energy loss, simple structure, compact structure, and convenient realization of standardization and productization.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout.
Fig. 1 shows a schematic diagram of a hybrid power plant for medium and large unmanned aerial vehicles according to an embodiment of the invention.
Description of reference numerals:
1. an electronic control unit; 2. an acquisition module; 3. an engine; 4. a throttle position sensor; 5. A throttle valve; 6. an engine speed sensor; 7. a torque synthesizer/separator; 8. a gearbox; 9. a propeller; 10. a condenser; 11. an electric motor; 12. a controller; 13. a storage battery; 14. a first temperature sensor; 15. a bypass valve; 16. an expander; 17. a generator; 18. a rectifier; 19. a first electrically operated valve; 20. a working medium flow meter; 21. a liquid storage tank; 22. a second electrically operated valve; 23. a working medium filter; 24. a working medium pump; 25. a pressure sensor; 26. a second temperature sensor; 27. an evaporator; 28. a third temperature sensor; 29. a throttle valve steering engine; 30. a charger; 31. a fourth temperature sensor; 32. a fifth temperature sensor; 33. a switching relay; 34. and a propeller rotating speed sensor.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the following describes preferred embodiments of the present invention, it should be understood that the present invention may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
Fig. 1 shows a schematic diagram of a hybrid power plant for medium and large unmanned aerial vehicles according to an embodiment of the invention.
As shown in fig. 1, a hybrid power plant for medium-large unmanned aerial vehicle has an electric system and a fuel system, the electric system includes a controller 12 and an electric motor 11, the fuel system includes an engine 3 and a throttle valve 5, the throttle valve 5 is provided with a throttle steering engine 29, including:
the engine 3 exhausts the waste heat recovery system and the energy storage charging system, the engine 3 exhausts the waste heat recovery system and is connected with the fuel oil system, the energy storage charging system is connected with the electric system, the engine 3 exhausts the waste heat recovery system and can utilize the waste heat of the fuel oil system to carry out waste heat power generation, and the energy storage charging system can store the waste heat power generation and supply power for the electric system.
The hybrid power output system can be connected with the electric system and the fuel system and can control the electric system and/or the fuel system to output power;
and the acquisition control system comprises a control structure and a monitoring structure and can control and monitor the working parameters of the exhaust waste heat recovery system, the energy storage charging system and the hybrid power output system of the engine 3.
Specifically, the throttle valve steering engine 29 controls the opening of the throttle valve 5 through a pull wire, so as to adjust the operation condition of the engine 3, the waste heat of the fuel system is recovered through the exhaust waste heat recovery system of the engine 3 to generate electricity, the energy storage charging system can supplement electric energy to improve endurance, meanwhile, the fuel system and the electric system work or work independently through the hybrid power output system according to different flight conditions, the acquisition control system monitors the working state of each system in real time, and the acquisition control system regulates and controls according to the flight state, so as to ensure stable flight.
Further, when the unmanned aerial vehicle is in a take-off working condition, a climbing working condition or needs high-power propulsion, the engine 3 and the motor 11 work cooperatively, and the torque of the engine 3 and the torque of the motor 11 are synthesized through a hybrid power output system and then transmitted to the propeller 9, so that the unmanned aerial vehicle is ensured to obtain the maximum thrust; when the unmanned aerial vehicle is under the long-time cruising working condition, the fuel power output route is adopted to work independently, and the waste heat power generation of the fuel system is recovered by the exhaust waste heat recovery system of the engine 3 and is used for power output again; when the unmanned aerial vehicle needs to fly quietly or is in the gliding operating mode, through the control structure, the switching is the electric system, and engine 3 is in the parking state this moment, is driven screw 9 by motor 11 and works.
In this embodiment, the monitoring structure includes collection module 2 and a plurality of sensor, collection module 2 with control structure communication be connected, a plurality of sensors can monitor each part operation conditions that is used for large-scale unmanned aerial vehicle's oil electricity hybrid power device.
Specifically, the acquisition module 2 monitors main working parameters in the exhaust waste heat recovery system, the energy storage and charging system and the hybrid power output system of the engine 3 in real time through various sensors, contains data such as the rotating speed of the engine 3, the rotating speed of the propeller 9, the flow rate of organic working media, the temperature and the pressure, has a storage and recording function, and is convenient for flight data analysis.
In the present embodiment, the engine 3 exhaust gas waste heat recovery system includes an organic rankine cycle loop, the organic rankine cycle loop includes an evaporator 27, an expander 16, a condenser 10, a flow meter 20, a liquid storage tank 21, a working medium filter 23 and a working medium pump 24 connected end to end, and the evaporator 27 is connected with the engine 3.
Specifically, the high temperature tail gas of engine 3 gets into evaporimeter 27 through exhaust pipe, high temperature tail gas gives organic working medium with heat transfer in evaporimeter 27, make liquid organic working medium become high temperature high pressure gaseous state organic working medium, do work in getting into expander 16, drive engine 3 work electricity generation, thereby turn into the electric energy with the energy that high temperature high pressure gaseous state organic working medium carried, charge for battery 13 through energy storage charging system, reuse in power output, retrieve aviation piston engine 3 exhaust waste heat through organic rankine cycle return circuit, be used for battery 13 to charge, can improve energy utilization, very big improvement unmanned aerial vehicle duration and voyage.
Further, the outlet of the evaporator 27, the expansion machine 16, the condenser 10, the flow meter 20, the liquid storage tank 21, the second electric valve 22, the working medium filter 23, the working medium pump 24 and the inlet of the evaporator 27 are sequentially connected to form an organic Rankine cycle loop, and the connection is a pipeline connection.
In this embodiment, the control structure includes:
the control unit 1 and the first electric valve 19, wherein the first electric valve 19 is arranged on a water inlet of the condenser 10;
the second electric valve 22, the second electric valve 22 is arranged between the liquid storage tank 21 and the working medium filter 23;
the control unit 1, the control unit 1 is connected with the first electric valve 19, the second electric valve 22 and the monitoring structure.
Specifically, the control unit 1 controls the first motor-operated valve 19 and the second motor-operated valve 22, the second motor-operated valve 22 controls the opening and closing of the orc circuit, and the first motor-operated valve 19 controls the condenser 10.
In the embodiment, the energy storage charging system comprises an energy storage charging circuit, the energy storage charging circuit comprises a generator 17, a rectifier 18, a charger 30, a switch relay 33 and a storage battery 13 which are connected end to end, and the storage battery 13 is connected with the controller 12.
Specifically, the generator 17 is coaxially connected with the expander 16, the expander 16 rotor rotates at a high speed to drive the generator 17 to work and generate electricity, the generator 17 is sequentially connected with the rectifier 18, the charger 30, the switch relay 33 and the storage battery 13 to form an energy storage charging loop, and the connection is a circuit connection.
In the present embodiment, the hybrid power output system includes a torque combiner/divider 7, one end of the torque combiner/divider 7 is provided with a transmission 8, the transmission 8 is connected to a propeller 9, and the other end of the torque combiner/divider 7 is connected to both the engine 3 and the motor 11.
Specifically, a storage battery 13, a controller 12, a motor 11, a torque synthesizer/separator 7, a gearbox 8 and a propeller 9 are connected in sequence to form an electric energy power output route; the throttle valve steering engine 29, the throttle valve 5, the engine 3, the torque synthesizer/separator 7, the gearbox 8 and the propeller 9 are sequentially connected to form a fuel power output route; according to the unmanned aerial vehicle operating mode difference, can take two power take off routes and work alone or the mode of collaborative work, rely on torque synthesizer/separator 7 to realize that engine 3 and motor 11 drive screw 9 respectively or jointly.
In the present embodiment, the plurality of sensors includes:
a pressure sensor 25 provided on a working fluid line connected between the evaporator 27 and the expander 16;
a flow meter 20 arranged on the working medium pipeline between the condenser 10 and the liquid storage tank 21,
a first temperature sensor 14 provided on an exhaust pipe connected between the engine 3 and the evaporator 27;
a second temperature sensor 26 provided on a working fluid line connected between the evaporator 27 and the expander 16;
a third temperature sensor 28 provided on the exhaust line on the side of the evaporator 27 remote from the expander 16;
a fourth temperature sensor 31 provided on a cooling water line connected between the first motor-operated valve 19 and the condenser 10;
a fifth temperature sensor 32 provided on the cooling water line on the side of the condenser 10 remote from the first motor-operated valve 19;
a throttle valve 5 position sensor 4 provided on the throttle valve 5;
a propeller rotation speed sensor 34 provided on a bracket on the side of the propeller 9;
the engine speed sensor 346 is connected to a crankshaft of the engine 3.
Specifically, one end of an engine speed sensor 346 is connected with a crankshaft of the engine 3, and the other end of the engine speed sensor 346 is connected with the acquisition module 2; one end of the pressure sensor 25 is arranged on a working medium pipeline connected with the evaporator 27 and the expansion machine 16, and the other end of the pressure sensor is connected with the acquisition module 2; the flowmeter 20 is arranged on a working medium pipeline connected with the condenser 10 and the liquid storage tank 21 and is connected with the acquisition module 2; the throttle valve 5 position sensor 4 is arranged on the throttle valve 5, and the other end of the throttle valve 5 position sensor is connected with the acquisition module 2; one end of a propeller rotating speed sensor 34 is arranged on a bracket at the side of the propeller 9, and the other end of the propeller rotating speed sensor is connected with the acquisition module 2; one end of the first temperature sensor 14 is arranged on an exhaust pipeline connected with the engine 3 and the evaporator 27, and the other end of the first temperature sensor is connected with the acquisition module 2; one end of a second temperature sensor 26 is arranged on a working medium pipeline connected with the evaporator 27 and the expansion machine 16, and the other end of the second temperature sensor is connected with the acquisition module 2; one end of a third temperature sensor 28 is arranged on the exhaust pipeline on the other side of the evaporator 27, and the other end of the third temperature sensor is connected with the acquisition module 2; one end of a fourth temperature sensor 31 is arranged on a cooling water pipeline connected with the first electric valve 19 and the condenser 10, and the other end of the fourth temperature sensor is connected with the acquisition module 2; one end of a fifth temperature sensor 32 is arranged on the cooling water pipeline on the other side of the condenser 10, and the other end of the fifth temperature sensor is connected with the acquisition module 2; the acquisition module 2 is connected with the electronic control unit 1 through a circuit; the throttle valve steering engine 29 is arranged at the front end of the throttle valve 5, controls the throttle valve 5 through a pull wire, and is connected with the electronic control unit 1 at the other end; the bypass valve 15 is arranged on the exhaust pipeline, and the other end of the bypass valve is connected with the electronic control unit 1; the first electric valve 19 is arranged on a working medium pipeline connected with the liquid storage tank 21 and the working medium filter 23, and the other end of the first electric valve is connected with the electronic control unit 1; the second electric valve 22 is arranged on the cooling water pipeline at the front end of the condenser 10 and is positioned in front of the fifth temperature sensor 32, and the other end of the second electric valve is connected with the electronic control unit 1; one end of the switching relay 33 is provided on the circuit between the charger 30 and the secondary battery 13, and the other end is connected to the electronic control unit 1.
Further, the first temperature sensor 14 and the third temperature sensor 28 are K-couple temperature sensors, the total length is 100mm, the sensors are packaged by metal shells, the measuring range is 0-1000 ℃, and the measuring precision is +/-1 ℃;
the second temperature sensor 26, the fourth temperature sensor 31 and the fifth temperature sensor 32 are platinum resistance temperature sensors, the total length is 28mm, the sensors are packaged by metal shells, the measuring range is-50-220 ℃, and the measuring precision is +/-0.3 ℃;
the pressure sensor 25 is a CYB-20S pressure sensor and is of a cylindrical structure, the diameter of the cylinder is 28mm, the height of the cylinder is 115mm, the measuring range is 0 bar-10 bar, and the measuring precision can reach +/-0.02 bar
In this embodiment, the monitoring structure further includes a storage module, and the storage module is capable of storing the monitoring data of the plurality of sensors.
In the present embodiment, a bypass valve 15 is further included, the bypass valve 15 being connected in parallel with the evaporator 27, the bypass valve 15 being connected to the control unit 1.
Specifically, evaporator 27 is protected by bypass valve 15 to prevent damage to evaporator 27 due to excessive air pressure.
An unmanned aerial vehicle, includes foretell a hybrid power device of oil electricity that is used for medium and large-scale unmanned aerial vehicle.
When this embodiment hybrid power device used to there is oily electric hybrid unmanned aerial vehicle as an example, when unmanned aerial vehicle was in the operating mode of taking off, climbed the operating mode or need high-power to impel, engine 3 and 11 collaborative work of motor, synthesize engine 3 and 11 moments of torsion of motor and then transmit for screw 9 through moment of torsion synthesizer/separator 7, guarantee that unmanned aerial vehicle obtains maximum thrust. At this time, the electronic control unit 1 closes the second motor-operated valve 22, disconnects the orc circuit, and opens the bypass valve 15 to prevent the engine 3 from suffering an excessive exhaust back pressure and affecting the normal operation of the engine 3. When the unmanned aerial vehicle is under the long-time cruising working condition, the fuel power output route independent working scheme is adopted. The high-temperature tail gas of the engine 3 enters an evaporator 27 in the organic Rankine cycle loop through an exhaust pipeline, heat carried by the high-temperature tail gas is transferred to the organic working medium in the evaporator 27 to be changed into high-temperature high-pressure gaseous organic working medium, the high-temperature high-pressure gaseous organic working medium enters the expansion machine 16 to work, the engine 3 is driven to work and generate power, and therefore energy carried by the high-temperature high-pressure gaseous organic working medium is converted into electric energy, the electric energy is charged to the storage battery 13 through the energy storage charging system, and the electric energy is used for power output again. When the unmanned aerial vehicle needs to fly quietly or is in a gliding working condition, the unmanned aerial vehicle is switched to an electric energy power output route to work through the electronic control unit 1 and the torque separator 7, the engine 3 is in a parking state at the moment, and the motor 11 drives the propeller 9 to work.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (10)
1. The utility model provides a hybrid power device of oil electricity for medium and large-scale unmanned aerial vehicle has electric system and fuel oil system, electric system includes controller and motor, fuel oil system includes engine and throttle valve, the throttle valve is provided with the throttle valve steering wheel, its characterized in that includes:
the engine exhaust waste heat recovery system is connected with the fuel oil system, the energy storage charging system is connected with the electric system, the engine exhaust waste heat recovery system can utilize waste heat of the fuel oil system to generate waste heat power, and the energy storage charging system can store the waste heat power and supply power for the electric system;
the hybrid power output system is connected with the electric system and the fuel system and can control the electric system and/or the fuel system to output power;
the collection control system comprises a control structure and a monitoring structure and can control and monitor working parameters of the engine exhaust waste heat recovery system, the energy storage and charging system and the hybrid power output system.
2. The hybrid power plant of claim 1, wherein the monitoring structure comprises an acquisition module and a plurality of sensors, the acquisition module is in communication connection with the control structure, and the plurality of sensors can monitor the operation conditions of the components of the hybrid power plant for the medium-large unmanned aerial vehicle.
3. The hybrid power plant of claim 2, wherein the engine exhaust waste heat recovery system comprises an organic Rankine cycle loop, the organic Rankine cycle loop comprises an evaporator, an expander, a condenser, a flow meter, a liquid storage tank, a working medium filter and a working medium pump which are connected end to end, and the evaporator is connected with the engine.
4. A gasoline-electric hybrid power plant for medium-and-large unmanned aerial vehicles according to claim 3, characterized in that the control structure comprises:
the control unit and the first electric valve are arranged on the water inlet of the condenser;
the second electric valve is arranged between the liquid storage tank and the working medium filter;
a control unit connected with the first electrically operated valve, the second electrically operated valve and the monitoring structure.
5. The hybrid power plant of claim 4, wherein the energy storage and charging system comprises an energy storage and charging circuit, the energy storage and charging circuit comprises an end-to-end connected generator, a rectifier, a charger, a switching relay and a storage battery, and the storage battery is connected with the controller.
6. A gasoline-electric hybrid for medium-and-large unmanned aerial vehicles according to claim 4, characterized in that the hybrid power output system comprises a torque synthesizer/splitter, one end of which is provided with a gearbox connected with a propeller, and the other end of which is connected with the engine and the motor simultaneously.
7. A gasoline-electric hybrid power plant for medium-and-large unmanned aerial vehicles according to claim 4, characterized in that a plurality of said sensors comprise:
a pressure sensor disposed on a working medium pipe connected between the evaporator and the expander;
a flowmeter arranged on the working medium pipeline between the condenser and the liquid storage tank,
a first temperature sensor provided in an exhaust pipe connected between the engine and the evaporator;
a second temperature sensor provided on a working medium line connected between the evaporator and the expander;
the third temperature sensor is arranged on an exhaust pipeline on one side of the evaporator, which is far away from the expander;
a fourth temperature sensor disposed on a cooling water line connected between the first electric valve and the condenser;
the fifth temperature sensor is arranged on the cooling water pipeline on one side, away from the first electric valve, of the condenser;
a throttle position sensor provided on the throttle valve;
the propeller rotating speed sensor is arranged on the bracket at the side of the propeller;
and the engine rotating speed sensor is connected with the crankshaft of the engine.
8. The hybrid power plant of claim 2, wherein the monitoring structure further comprises a storage module capable of storing monitoring data of a plurality of the sensors.
9. The hybrid plant of claim 4, further comprising a bypass valve connected in parallel with the evaporator, the bypass valve being connected to the control unit.
10. An unmanned aerial vehicle, characterized in that, includes the oil-electric hybrid power device for medium-and-large-sized unmanned aerial vehicles based on claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110886598.9A CN113772104A (en) | 2021-08-03 | 2021-08-03 | Oil-electricity hybrid power device capable of being used for medium-sized and large-sized unmanned aerial vehicles and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110886598.9A CN113772104A (en) | 2021-08-03 | 2021-08-03 | Oil-electricity hybrid power device capable of being used for medium-sized and large-sized unmanned aerial vehicles and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113772104A true CN113772104A (en) | 2021-12-10 |
Family
ID=78836674
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110886598.9A Pending CN113772104A (en) | 2021-08-03 | 2021-08-03 | Oil-electricity hybrid power device capable of being used for medium-sized and large-sized unmanned aerial vehicles and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113772104A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115576257A (en) * | 2022-12-08 | 2023-01-06 | 北京航空航天大学 | Aeroengine high altitude bench test control system |
-
2021
- 2021-08-03 CN CN202110886598.9A patent/CN113772104A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115576257A (en) * | 2022-12-08 | 2023-01-06 | 北京航空航天大学 | Aeroengine high altitude bench test control system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104220715B (en) | Utilize the method for the CO2 compressor of the waste heat driven CO2 trapping systems from internal combustion engine | |
| CN102712355B (en) | The operating method of boats and ships and boats and ships | |
| CN101415908B (en) | Large-sized turbo-charging diesel motor with energy recovery apparatus | |
| US8141360B1 (en) | Hybrid gas turbine and internal combustion engine | |
| CN102971509B (en) | For the method and structure of recombinating to the power of turbo machine | |
| CN102003229B (en) | Control system and method for generating power by waste heat of diesel engine | |
| CN103052774A (en) | Marine denitration system, marine vessel equipped with same, and control method for marine denitration system | |
| CN101169067A (en) | Engine apparatus with heat recovery system and relative heat recovery method | |
| WO2007109414A2 (en) | Energy recovery system | |
| CN201049586Y (en) | Hybrid power driven system | |
| CN102628396A (en) | Regenerative assisted turbocharger system | |
| CN201963362U (en) | Automobile diesel engine afterheat power-generation control system | |
| CN113772104A (en) | Oil-electricity hybrid power device capable of being used for medium-sized and large-sized unmanned aerial vehicles and unmanned aerial vehicle | |
| CN201496168U (en) | Engine exhaust gas afterheat utilization device | |
| CN108457744A (en) | A kind of engine exhaust heat recovery system of equipment mechanical-electric coupling booster | |
| CN103410573B (en) | Vehicle exhaust comprehensive utilization energy conserving system | |
| CN108386271B (en) | Vehicle gas-electricity hybrid power system for generating electricity by utilizing residual pressure of compressed natural gas | |
| CN216102802U (en) | Oil-electricity hybrid power device capable of being used for medium-sized and large-sized unmanned aerial vehicles and unmanned aerial vehicle | |
| CN106285784A (en) | There is the compressed air engine of energy-storage system | |
| CN108643994B (en) | Multistage combined recovery device for exhaust energy of vehicle-mounted engine | |
| WO2023040191A1 (en) | Zero-carbon ship power system, and method for driving ship | |
| US6729136B2 (en) | Liquid metal/liquid nitrogen power plant for powering a turbine or any use device | |
| CN202266346U (en) | Engine exhaust afterheat recycling control system based on organic rankine cycle | |
| CN100430581C (en) | Method and equipment for reducing vehicle energy consumption | |
| KR20130106495A (en) | Turbo compound system with improved structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |