CN109204844B - Near space unmanned aerial vehicle power system and hybrid power method - Google Patents
Near space unmanned aerial vehicle power system and hybrid power method Download PDFInfo
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- 238000010248 power generation Methods 0.000 claims abstract description 82
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- 238000004146 energy storage Methods 0.000 claims abstract description 36
- 239000000295 fuel oil Substances 0.000 claims abstract description 15
- 230000007613 environmental effect Effects 0.000 claims abstract description 8
- 230000005611 electricity Effects 0.000 claims description 34
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 15
- 238000002485 combustion reaction Methods 0.000 claims description 12
- MHAJPDPJQMAIIY-UHFFFAOYSA-N Hydrogen peroxide Chemical compound OO MHAJPDPJQMAIIY-UHFFFAOYSA-N 0.000 claims description 6
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- 229910001218 Gallium arsenide Inorganic materials 0.000 claims description 5
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- 239000003350 kerosene Substances 0.000 description 3
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- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
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- 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
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- 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
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Abstract
The invention discloses a near space unmanned aerial vehicle power system, which comprises a near space unmanned aerial vehicle hybrid power subsystem, a near space unmanned aerial vehicle hybrid power subsystem and an environmental information acquisition subsystem, and is characterized in that: the hybrid power subsystem comprises a hybrid power device, and the hybrid power device comprises a solar power generation device and a fuel oil power generation device; also disclosed is a method: when the flying height of the airplane reaches more than 11000 meters, solar photovoltaic power generation is used as flying power in the daytime, and meanwhile, charging electric energy is provided for an onboard storage battery, and main power at night comes from an onboard fuel oil power generation system. The invention utilizes solar power generation and solar energy storage to the maximum extent and uses fuel oil to generate power to the minimum extent, thereby reducing fuel consumption, prolonging the air-leaving time of the airplane and solving the problems of flight power and energy of the unmanned aerial vehicle in the adjacent space.
Description
Technical Field
The invention belongs to the field of super-altitude unmanned aerial vehicles, and particularly relates to a near space unmanned aerial vehicle power system.
Background
An atmospheric range of 20 km to 100 km above the surface of the earth is called the near space. The near space vehicle refers to a vehicle which can carry out long-term and continuous flight in the near space, and compared with a satellite, the near space vehicle has the advantages that: high cost-effectiveness ratio, good maneuverability and easy updating and maintenance. The distance between the aircraft and the target is only 1/10-1/20 of that of a low-orbit satellite generally, low-power transmission signals which cannot be monitored by the satellite can be received, and high-resolution earth observation is easy to realize. Therefore, the critical space has great utilization value for both military and civil use.
The adjacent space has four prominent features:
the air is very thin and the air density is only 1/30 of the ground density at altitude of about 24 km.
The critical space temperature is very low, from 20 km to 25 km the temperature is only around-55 ℃ to 58 ℃, and any heat conduction is extremely low due to the rarefied air.
The sunlight is sufficient, and because of the high and thin air, the time of direct sunlight is longer than that of the ground.
High radiation.
There have been decades of domestic development of near space vehicle research, and it has been reported that models and approaches are largely similar to the light structural solutions employed in some of the united states and united kingdom: there are normal layout double tail-boom layout and flying wing mode, but up to now there is no aircraft that can be used overnight, and there is no demonstration that can actually fly at a height of more than 12000 m. The reason is that the energy is provided by only using large-area solar photovoltaic power generation, the wingspan reaches about 40-50 meters, the wing area is about 50-100 square meters, and the possibility that the light structure aircraft with the weight of only 200-500 kilograms (including 3-10 kilogram load) tries to keep the whole day flat flying in the adjacent space is very small.
It is possible to utilize the unmanned aerial vehicle aircraft to keep flying all day long at the space flight that closes on, but it is very obvious, and the flight power, the energy of the unmanned aerial vehicle that close on the space are extremely important links, solve the flight power, the energy problem of the unmanned aerial vehicle that close on the space, still are blank at present domestically.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a near space unmanned aerial vehicle power system and a hybrid power method, which are used for solving the power and energy problems of the near space unmanned aerial vehicle for keeping large height and flying all day round and filling the domestic blank.
The utility model provides a near space unmanned aerial vehicle driving system, includes near space unmanned aerial vehicle hybrid power subsystem, environmental information collection subsystem, hybrid power subsystem receive the information that environmental information collection subsystem sent and to hybrid power consumption subsystem output hybrid electric energy, its characterized in that: the hybrid power subsystem comprises a hybrid power device, the hybrid power device comprises a solar power generation device and a fuel oil power generation device, the solar power generation device is used for generating solar power generation electric energy, and the fuel oil power generation device generates electric energy by using a fuel oil engine.
The hybrid power subsystem comprises a fuel power generation module, a solar power generation module, a flight control system, an energy storage control module and a battery module; the flight control system respectively controls the fuel engine power generation module and the solar power generation module, the energy storage control and battery module respectively controls and receives power generation and energy storage of the fuel engine and solar energy storage, and sends the received energy storage to the unmanned aerial vehicle power and electronic system in the near space.
The fuel engine power generation module comprises a fuel engine, a three-phase generator, a restarting module and an energy storage module; the fuel engine drives the three-phase generator, the energy storage module receives instructions of the energy storage control and battery module to rectify three-phase electricity generated by the three-phase generator into single-phase electricity, and the single-phase electricity is subjected to balance charging and storage battery charging; and the restarting module receives an instruction of the flight control system to restart the fuel engine.
The solar power generation module comprises a solar photoelectric film and an energy storage module, and after the solar photoelectric film generates single-phase electricity, the energy storage module carries out balance charging and storage battery charging on the single-phase electricity.
The energy storage control and battery module charges the storage battery of the fuel power generation module and the storage battery of the solar power generation module, the energy storage control and battery module rectifies the single-phase electricity of the fuel power generation storage battery and the single-phase electricity of the solar power generation storage battery into three-phase electricity again, and provides the rectified three-phase electricity for propelling the propeller three-phase motor.
The solar photoelectric film is formed by covering gallium arsenide photoelectric generating films on the upper surface of the wing, the upper surface of the horizontal tail wing and the surfaces of the two sides of the vertical tail wing, and the solar photoelectric generating film is used for generating electricity by utilizing solar light and is used as flight power.
When the flying height of the aircraft is higher than 4500 m and lower than 11000 m, the compressed air provided by an air supercharger is used as the combustion improver; when the flying height of the airplane is higher than 11000 m, hydrogen peroxide is adopted as a combustion improver.
The near space unmanned aerial vehicle hybrid power and electronic system comprises a temperature control and heating electric module, a three-phase permanent magnet motor driving propeller propelling electric module, airborne equipment and a flight control electric module; the hybrid power utilization comprises single-phase power utilization and three-phase power utilization, the propeller power utilization is three-phase power utilization, and the temperature control and heating and airborne equipment and flight control power utilization is single-phase power utilization.
The environment information acquisition subsystem comprises a flight ground station instruction module, an airborne atmospheric equipment information module, a flight condition information module and an airborne computer module; the flight ground station instruction module, the airborne atmospheric equipment information module and the flight condition information module respectively provide information for the airborne computer, and the airborne computer processes the information and feeds the processed information back to the hybrid power subsystem of the unmanned aerial vehicle in the adjacent space.
A hybrid power method for an adjacent space unmanned aerial vehicle power system is characterized in that: the method comprises the following steps:
step one, the flying height of the airplane reaches more than 20,000 meters;
step two, utilizing solar photovoltaic power generation as flight power in daytime and providing charging electric energy for an onboard storage battery;
and step three, the main power at night comes from an onboard fuel power generation system.
Advantageous effects of the invention
The invention uses solar energy photoelectric power generation as flight power in the daytime at the high altitude of more than 20,000 meters, and provides charging electric energy for an onboard storage battery, main power at night comes from an onboard fuel oil power generation system, and the electric energy at night comes from solar energy and a small amount of residual energy except for flat flight. The problem of the unmanned aerial vehicle aircraft that can fly for a long time in near space is solved.
Drawings
FIG. 1 is an overall view of subsystems and modules of the present invention;
FIG. 2 is a system framework diagram of the present invention;
FIG. 3 is a schematic diagram of a hybrid power generation subsystem of the present invention;
FIG. 4 is a schematic view of a fuel oil power generation module of the present invention;
FIG. 5 is a schematic view of a solar power module of the present invention;
FIG. 6 is a schematic diagram of a hybrid electronic system of the present invention;
FIG. 7 is a schematic diagram of an environmental information collection subsystem according to the present invention;
FIG. 8 is a schematic diagram of the power generation of the fuel generator of the present invention;
fig. 9 is a schematic view of solar power generation according to the present invention.
Detailed Description
The power matching design principle of the invention is as follows:
1. near space unmanned vehicles typically have two flight modes:
first, during the day, the solar energy is used to generate electric energy to maintain the flat flight at 24000 m height, and meanwhile, the surplus electric energy is accumulated to be used for night flight. At night, the flying height is reduced due to the limited energy. This may allow longer flight airtime, but has the disadvantage that the flight altitude varies greatly, up to several kilometers, with day and night.
Second, the aircraft maintains a 24,000 meter level flight using its own energy during the day and night, and is generally an airplane with an internal combustion engine, but has a short idle time due to fuel consumption. The advantage is that a specified design time can be run at a predetermined height.
2. The flight mode adopted by the invention is the combination of the two modes:
in order to achieve the purposes that the solar energy is utilized for flying in the daytime and the electric energy generated by the internal combustion engine is utilized for flying at night, and simultaneously, the problem that the air-remaining time is short because the consumption of electric energy and fuel is high due to the adoption of the internal combustion engine is solved, when a small amount of residual solar energy is left besides the flat flying, a charger and a small amount of lithium batteries are arranged on the airplane, and the electric energy is supplemented or accumulated in the night flying.
In the daytime, except the electric energy consumed by keeping the plane flight, part of the electric energy is stored in a small battery pack for night flight, when the electric energy is consumed to the lowest value, the internal combustion engine is automatically started, and the generated electric energy keeps the plane flight at night. To keep the overall power system efficient.
Based on the principle, the invention designs the near space unmanned aerial vehicle power system.
The utility model provides a close on space unmanned aerial vehicle driving system is as shown in fig. 2, including close on space unmanned aerial vehicle hybrid power subsystem, close on the mixed electronic system that uses of space unmanned aerial vehicle, environmental information collection subsystem, hybrid power subsystem receive the information that environmental information collection subsystem sent and to mix with electronic system output hybrid electric energy, its characterized in that: the hybrid power subsystem comprises a hybrid power device, the hybrid power device comprises a solar power generation device and a fuel power generation device, the solar power generation device is used for generating solar power generation electric energy, and the fuel power generation device is used for generating fuel power generation electric energy.
The hybrid power subsystem is shown in fig. 3 and comprises a fuel power generation module, a solar power generation module, a flight control system, an energy storage control module and a battery module; the flight control system controls fuel power generation module and solar energy power generation module respectively, energy storage control and battery module control respectively and receive fuel energy storage and solar energy storage to send the energy storage of receiving for close on the hybrid power consumption system of space unmanned aerial vehicle.
The fuel power generation module is shown in fig. 4 and comprises a fuel engine, a three-phase generator, a restarting module and an energy storage module; the fuel engine drives the three-phase generator, the energy storage module receives instructions of the energy storage control and battery module to rectify three-phase electricity generated by the three-phase generator into single-phase electricity, and the single-phase electricity is subjected to balance charging and storage battery charging; and the restarting module receives an instruction of the flight control system to restart the fuel engine.
The solar power generation module comprises a solar photoelectric film and an energy storage module as shown in fig. 5, wherein after the solar photoelectric film generates single-phase electricity, the energy storage module carries out balance charging and storage battery charging on the single-phase electricity.
The energy storage control and battery module is shown in fig. 6, the battery charges the storage battery of the fuel power generation module and the storage battery of the solar power generation module, the energy storage control and battery module rectifies the single-phase electricity of the fuel power generation storage battery and the single-phase electricity of the solar power generation storage battery into three-phase electricity again, and provides the rectified three-phase electricity for propelling the propeller three-phase motor.
The solar photoelectric film is formed by covering gallium arsenide photoelectric generating films on the upper surface of the wing, the upper surface of the horizontal tail wing and the surfaces of the two sides of the vertical tail wing, and the solar photoelectric generating film is used for generating electricity by utilizing solar light and is used as flight power.
When the flying height of the aircraft is higher than 4500 m and lower than 11000 m, the compressed air provided by an air supercharger is used as the combustion improver; when the flying height of the airplane is higher than 11000 m, hydrogen peroxide is adopted as a combustion improver.
The near space unmanned aerial vehicle hybrid power utilization system comprises a temperature control and heating power utilization module, a three-phase permanent magnet motor driving propeller power utilization module, airborne equipment and a flight control power utilization module; the hybrid power utilization comprises single-phase power utilization and three-phase power utilization, the propeller power utilization is three-phase power utilization, and the temperature control and heating and airborne equipment and flight control power utilization is single-phase power utilization.
The environment information acquisition subsystem is shown in fig. 7 and comprises a flying ground station instruction module, an airborne atmospheric equipment information module, a flying condition information module and an airborne computer module; the flight ground station instruction module, the airborne atmospheric equipment information module and the flight condition information module respectively provide information for the airborne computer, and the airborne computer processes the information and feeds the processed information back to the hybrid power subsystem of the unmanned aerial vehicle in the adjacent space.
Supplementary explanation:
the environment information acquisition subsystem is an integrated system of all flight attitude, distance and surrounding environment measurement perception sensors carried by the airplane. The information and data acquired and sensed by all the sensors are integrated on the airborne computer, are comprehensively described and displayed on one display screen or a plurality of display screens, so that an unmanned aerial vehicle operator can make a flight task real-time decision instruction through comprehensive evaluation, send unmanned aerial vehicle information and data receivers, and command all airborne execution equipment to operate through the airborne computer.
The airborne atmosphere equipment information module includes a sensory information sensor that collects conditions around the aircraft. Such as airspeed, heading, altitude, acceleration, temperature, humidity, and engine operating conditions, speed, temperature, power usage, and the aircraft's own state; oil mass, consumption speed, residual oil, battery voltage and electric quantity allowance.
The flight condition information module comprises a flight sensor, the flight sensor senses the attitude of the airplane, the temperature of a steering engine, the motion angles of various movable surfaces, the pressure of a pressure storage bottle and the like, and the information is gathered to an onboard computer. The onboard computer synthesizes the data to instruct the airplane to fly, namely the attitude and the heading, generate a current flight map and the like. Some information is transmitted by the data transmission system to ground stations, such as course deviation, GPS fault maintenance, camera systems, tracking systems. And the real-time operation is judged and decided by a ground unmanned aerial vehicle operator.
A hybrid power method for an adjacent space unmanned aerial vehicle power system is characterized in that: the method comprises the following steps:
step one, the flying height of the airplane reaches more than 20,000 meters;
step two, utilizing solar photovoltaic power generation as flight power in daytime and providing charging electric energy for an onboard storage battery;
and step three, the main power at night comes from an onboard fuel power generation system.
The specific implementation scheme is as follows:
1. the controllable power sports car takes off or takes off in a traction manner.
2. The kerosene engine and the electric energy climb automatically, the climbing rate is not less than 2 m/s, and the height is increased to about 24,000 m in 3-4 hours.
3. Carrying about 120 kg of hydrogen (160 atmospheric pressure), 60-80 kg of oxygen-containing combustion improver or 150 kg of aviation kerosene and liquid oxygen, and working for about 120-150 hours, about 15-18 nights and 8-10 hours in average at night.
4. The gallium arsenide photoelectric film of about 60 square meters of Han energy company of China is used for generating electricity. The power generation efficiency is 0.28-0.31%; the solar energy power generation can provide about 11000 watt-12700 watt for flying in the daytime and about 14-17 horsepower, can keep flying flat for 220-250 kilometers/hour, and can save partial electric energy. Therefore, the total empty time can reach 15 to 20 days.
5. A small kerosene compression-ignition engine with 18 horsepower and a permanent magnet generator with an engine restart module.
6. A4-6 blade tail pushing type propeller with high rotating speed of carbon fiber is used as part of power for high altitude forward flight and take-off and landing.
7. During takeoff, part of electric energy is supplied by an onboard battery, the short-time power of the motor is 30 horsepower, and the power takeoff is assisted. The takeoff power is provided by an electrically driven controllable sports car, and the electric energy and the engine power only serve as the power of the ascending motor when the takeoff speed is 25-40 km/h.
8. A large-scale near space unmanned aerial vehicle is used for multiple times, wherein the wingspan is 38-40 meters, the takeoff weight is 450-550 kilograms, and the effective load is not less than 50 kilograms.
9. The upper surfaces of the wings and the horizontal tails and the surfaces of the vertical tails are respectively provided with a gallium arsenide photoelectric film with the weight of about 40-55 square meters and each square meter is about 1.0 kilogram, so that the wing power generation film weighs about 45-50 kilograms, the wings are composed of stress skins and composite material frameworks, and the total weight of the wings is about 120-140 kilograms. The fuselage and tail structure is about 60 kg and the total weight of the aircraft power system is only 10 kg (one engine + generator).
Fuel: 200-250 kg.
A load device: 50 kg.
It is emphasized that the embodiments described herein are illustrative and not restrictive, and thus the present invention includes, but is not limited to, the embodiments described in the detailed description.
Claims (5)
1. The utility model provides a close on space unmanned aerial vehicle driving system, includes close on space unmanned aerial vehicle hybrid subsystem, closes on space unmanned aerial vehicle hybrid power subsystem, environmental information collection subsystem, close on the information that space unmanned aerial vehicle hybrid power subsystem received environmental information collection subsystem and sent and to close on space unmanned aerial vehicle hybrid power subsystem output hybrid electric energy, its characterized in that: the near space unmanned aerial vehicle hybrid power subsystem comprises a hybrid power device, the hybrid power device comprises a solar power generation module and a fuel power generation module, the solar power generation module is used for generating solar power generation electric energy, and the fuel power generation module is used for generating fuel power generation electric energy;
the near space unmanned aerial vehicle hybrid power subsystem comprises a fuel power generation module, a solar power generation module, a flight control system, an energy storage control module and a battery module; the flight control system respectively controls the fuel oil power generation module and the solar power generation module, and the energy storage control and battery module respectively controls and receives fuel oil energy storage and solar energy storage and sends the received energy storage to the near space unmanned aerial vehicle hybrid power utilization system;
the solar power generation module comprises a solar photoelectric film and an energy storage module, and after the solar photoelectric film generates single-phase electricity, the energy storage module carries out balance charging on the single-phase electricity and charges a storage battery of the solar power generation module;
the fuel power generation module comprises a fuel engine, a three-phase generator, a restarting module and an energy storage module; the fuel engine drives a three-phase generator, the energy storage module receives the instruction of the energy storage control and battery module to rectify three-phase electricity generated by the three-phase generator into single-phase electricity, and the single-phase electricity is subjected to balance charging and storage battery charging of the fuel power generation module; the restarting module receives an instruction of the flight control system to restart the fuel engine;
the energy storage control and battery module charges a storage battery of the fuel power generation module and a storage battery of the solar power generation module, rectifies single-phase electricity of the storage battery of the fuel power generation module and the storage battery of the solar power generation module into three-phase electricity again, and provides the rectified three-phase electricity for propelling the propeller three-phase motor;
when the flying height of the unmanned aerial vehicle in the near space is lower than 4500 m, the fuel engine adopts air as a combustion improver, and when the flying height of the unmanned aerial vehicle in the near space is higher than 4500 m and lower than 11000 m, the fuel engine adopts compressed air provided by an air supercharger as the combustion improver; when the flying height of the unmanned aerial vehicle in the near space is higher than 11000 m, hydrogen peroxide is adopted as a combustion improver by the fuel engine;
when the flying height of the near space unmanned aerial vehicle reaches more than 20000 meters, solar photovoltaic power generation is used as flying power in the daytime, and meanwhile, charging electric energy is provided for a storage battery of the solar power generation module; the night power source comprises solar power generation electric energy stored in a storage battery of the solar power generation module and the fuel oil power generation module, when the solar power generation electric energy is consumed to the lowest value, the fuel oil engine is automatically started, and the generated electric energy continuously keeps the unmanned aerial vehicle flying at night in the adjacent space;
the controllable power sports car pulls the near space unmanned aerial vehicle to take off; the fuel engine and the electric energy realize the autonomous climbing of the unmanned aerial vehicle in the near space, the climbing rate is not less than 2 m/s, and the unmanned aerial vehicle rises to the height of 24,000 m within 3-4 hours; the fuel engine can work for 120-150 hours, the power supply power of the solar power generation module is 11000-12700 watts when the solar power generation module flies in the daytime, the unmanned aerial vehicle in the adjacent space can fly horizontally for 220-250 kilometers per hour, and partial electric energy can be stored, so that the total air remaining time of the unmanned aerial vehicle in the adjacent space can be as long as 15-20 days.
2. The proximity space unmanned aerial vehicle power system of claim 1, wherein: the solar photoelectric film is formed by covering gallium arsenide photoelectric generating films on the upper surface of the wing, the upper surface of the horizontal tail and the surfaces of the two sides of the vertical tail, and the solar photoelectric generating film is used for generating electricity by utilizing solar energy and is used as flight power.
3. The proximity space unmanned aerial vehicle power system of claim 1, wherein: the near space unmanned aerial vehicle hybrid power utilization system comprises a temperature control and heating power utilization module, a three-phase permanent magnet motor driving propeller power utilization module, airborne equipment and a flight control power utilization module; the hybrid power consumption system uses both single-phase electricity and three-phase electricity, the three-phase permanent magnet motor drives the propeller power consumption module to use three-phase electricity, and the temperature control and heating power consumption module, the airborne equipment and the flight control power consumption module use the single-phase electricity.
4. The proximity space unmanned aerial vehicle power system of claim 1, wherein: the environment information acquisition subsystem comprises a flight ground station instruction module, an airborne atmospheric equipment information module, a flight condition information module and an airborne computer module; the flight ground station instruction module, the airborne atmospheric equipment information module and the flight condition information module respectively provide information for the airborne computer module, and the airborne computer module processes the information and feeds the processed information back to the near space unmanned aerial vehicle hybrid power subsystem.
5. A hybrid method for the near space unmanned aerial vehicle powered system of any one of claims 1-4, wherein: the method comprises the following steps:
firstly, the flying height of an unmanned aerial vehicle with the unmanned aerial vehicle power system in the near space of any one of claims 1 to 4 reaches more than 20000 meters and keeps flying in a flat way all day long;
step two, utilizing solar photovoltaic power generation as flight power in daytime and providing charging electric energy for an onboard storage battery;
and thirdly, the power source at night comprises solar power generation electric energy and the fuel oil power generation module which are stored in the onboard storage battery, when the solar power generation electric energy is consumed to the lowest value, the fuel oil engine in the fuel oil power generation module is automatically started, and the generated electric energy continuously keeps the unmanned aerial vehicle flying at night in the adjacent space.
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| CN110697058A (en) * | 2019-11-26 | 2020-01-17 | 复旦大学 | Hybrid unmanned aerial vehicle |
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| CN107878762A (en) * | 2017-11-28 | 2018-04-06 | 北京正兴弘业科技有限公司 | A kind of long endurance unmanned aircraft oil electric mixed dynamic system and control method |
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| CN102060107A (en) * | 2010-11-26 | 2011-05-18 | 北京航空航天大学 | Energy supply system for stratosphere electricity-electricity hybrid solar airship |
| CN103612768A (en) * | 2013-11-29 | 2014-03-05 | 无锡同春新能源科技有限公司 | Solar unmanned aerial vehicle for sowing chemical weeding fine particles at low altitude above rice field |
| CN205837209U (en) * | 2016-07-04 | 2016-12-28 | 深圳市龙云创新航空科技有限公司 | A kind of integrated form power multiaxis unmanned plane |
| CN107878762A (en) * | 2017-11-28 | 2018-04-06 | 北京正兴弘业科技有限公司 | A kind of long endurance unmanned aircraft oil electric mixed dynamic system and control method |
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