CN106585964A - Aircraft and flying method thereof - Google Patents
Aircraft and flying method thereof Download PDFInfo
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- CN106585964A CN106585964A CN201610053378.7A CN201610053378A CN106585964A CN 106585964 A CN106585964 A CN 106585964A CN 201610053378 A CN201610053378 A CN 201610053378A CN 106585964 A CN106585964 A CN 106585964A
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- aircraft
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- fuel engine
- motor
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention provides an aircraft and a flying method thereof. The aircraft is provided with a plurality of power devices. The plurality of power devices comprise fuel power devices and electric power devices; the fuel power devices are driven by a fuel engine; the electric power devices comprise electric rotors driven by an electric motor; and the propelling directions of the fuel power devices are substantially vertical to rotation planes of the electric rotors so that the aircraft can vertically fly through simultaneous working of the fuel power devices and the electric power devices. As the aircraft simultaneously includes the fuel power devices and the electric rotors, the aircraft can bear heavy objects and can easily and accurately control the balance and posture of the aircraft. Optionally, the aircraft further comprises a fixed wing and the fixed wing is substantially parallel to the propelling directions of the plurality of power devices; therefore, at least partial power devices, including the fuel power devices, of the plurality of power devices can be matched with the fixed wing to realize flat flight of the aircraft.
Description
Technical field
The present invention relates to a kind of aircraft and its flying method.
Background technology
Current unmanned plane is generally flown using the rotor peace that carries out taking off vertically, and generally using motor drive
Dynamic rotor, electric power are provided by battery.Such unmanned plane presence is taken off, and load-carrying is little, and voyage is little, Yi Jiping
The shortcomings of rapidly spending slow.
The content of the invention
For the problems referred to above, the present invention provides the aircraft (example of a kind of fuel engine and motor combination drive
Such as, unmanned plane or small-sized manned aircraft).Further, the present invention also provide it is a kind of include simultaneously rotor and
The aircraft of fixed wing, this aircraft can not only the VTOL as common helicopter,
Can also put down as common fixed wing airplane and fly.Specifically, embodiments of the invention provide following skill
Art scheme.
According to an aspect of the present invention, there is provided a kind of aircraft, which has multiple power set.It is described
Multiple power set include fuel engine and electric power device, and the fuel engine is by fuel
Engine drives, and the electric power device is included by the electronic rotor of motor-driven；And the fuel
The Plane of rotation of the direction of propulsion of power set and the electronic rotor is substantially vertical so that the fuel is moved
Work while power apparatus and the electric power device can realize the vertical flight of the aircraft.Should
Aircraft due to including fuel engine and electronic rotor simultaneously, so heavier article can either be carried
Can be easier and accurately control the balance and posture of aircraft again.According to the present invention, by rotor
Lift offsets aircraft deadweight, and the hang time can be longer than the multi-rotor aerocraft that common batteries drive.
Alternatively, the aircraft also includes fixed wing, and the fixed wing is filled with the plurality of power
The direction of propulsion put is substantially parallel so that the plurality of power set include the fuel engine
At least partly with the cooperation of the fixed wing, power set can realize that the flat of the aircraft flies.Work as institute
When stating that aircraft is flat to fly, heading can be substantially parallel with the fixed wing.Due to this aircraft
Fixed wing is included simultaneously, therefore which can fly similar to the same quick flat of common fixed wing airplane.
As the flat power that flies can be provided by fuel engine, and lift, therefore this are provided by fixed wing
The speed and voyage for planting aircraft can be greatly increased.
Alternatively, when the aircraft is flat winged, power is provided or by described by the fuel engine
Fuel engine and the electric power device provide power simultaneously.This aircraft at least adopts fuel
Power set are provided puts down the power for flying, it is possible to increase the speed and voyage of aircraft.Furthermore, it is possible to
Select power to be provided simultaneously by the fuel engine and the electronic rotor, can so cause total dynamic
Power increases, and improves flight speed.
Alternatively, the electronic rotor has multiple, and multiple electronic rotors are distributed in the fixation
The both sides of wing so that change thrust ratio and/or the thrust side of the electronic rotor of the both sides of the fixed wing
To the flight attitude that can change the aircraft.It is possible thereby to the flight attitude of aircraft is flexibly controlled,
For example it is converted to from the posture that takes off vertically and equals winged posture, or on the contrary.
Alternatively, the fuel engine can be installed on the fixed wing so that aircraft hangs down
Easily balance when directly taking off, for example, when the fuel engine includes being driven by the fuel engine
Motor-driven rotor when, motor-driven rotor can be installed on the front end of the fixed wing.
Alternatively, at least one of described fuel engine includes the machine driven by the fuel engine
Dynamic rotor.Alternatively, the motor-driven rotor can be installed on the side of the fixed wing so that described
The wing tip of fixed wing is wrapped in the spiral air flow of the motor-driven rotor, when putting down winged so as to reduce aircraft
Energy consumption.
Alternatively, at least one of described fuel engine is also associated with electromotor, and the electromotor can
It is to charge to the battery of the powering electric motors, or is directly motor.So can be
Electronic rotor is needed when working, to ensure which has the supply of electric power of abundance.According to the embodiment, mechanical/electrical energy
The mode of conversion, with traditional register ratio, can allow the layout designs of many rotors more flexible changeable.
Alternatively, the electromotor is directly connected to corresponding fuel engine by the line shaft of coaxial line.Institute
State corresponding fuel engine and motor-driven rotor is directly connected to by the coaxial line line shaft also.Such design
The weight needed for actuating device is reduced, while the energy loss that actuating device brings is decreased, and
Improve reliability.
Alternatively, the electromotor is driven by clutch by corresponding fuel engine.
Alternatively, at least one of described fuel engine drives motor-driven rotor by clutch.
Alternatively, the balance of the aircraft, heading and/or flight attitude can be by the electronic rotations
The wing is controlled, or by the electronic rotor and the fuel engine co- controlling.The control of electronic rotor
System is more flexible, therefore balance, heading and/or the flight attitude of control aircraft are participated in by electronic rotor
The flight of aircraft can be made more stable and flexible.
Alternatively, at least one of described electronic rotor can change direction of rotation.
Alternatively, the side of the aircraft is equipped with undercarriage so that the aircraft can be on runway
It is sliding to run landing.
Alternatively, displacement slurry used in the fuel engine.
Alternatively, the maximum gross thrust of the electric power device is less than the fuel engine most
The 50% of big gross thrust.So, on the one hand, corresponding electromotor, battery and/or motor can be reduced
Capacity and volume, so as to reduce the weight of aircraft itself, on the other hand still ensure that the flat of aircraft
Weighing apparatus flight.
Alternatively, the motor is directly powered by the electromotor, and the work(consumed by the electromotor
Rate less than the output of correspondence fuel engine 50%.So, on the one hand, can reduce corresponding
The capacity and volume of electromotor and/or motor, so as to reduce the weight of aircraft itself, on the other hand exists
The balance land of aircraft are still ensured that under extreme case.
Alternatively, the motor-driven rotor is located at the rear of the electronic rotor；And in the motor-driven rotor
At least one have with least one of the electronic rotor it is Chong Die.Thus, electronic rotor is to pusher
The air force for going out can provide thrust to motor-driven rotor, reduce the resistance of motor-driven rotor.Especially, exist
In the case of the motor of electronic rotor is directly driven by the electromotor that fuel engine drives, above-mentioned arrangement can be with
Ensure the rotating speed of motor-driven rotor and fuel engine when the rotating speed of electronic rotor is increased suddenly, so as to ensure
Generator output voltage is stablized.
According to a further aspect in the invention, there is provided a kind of flying method of aircraft, the aircraft have
Multiple power set, the plurality of power set include fuel engine and electric power device, described
Fuel engine is driven by fuel engine, and the electric power device is included by the electronic of motor-driven
The Plane of rotation of rotor, the direction of propulsion of the fuel engine and the electronic rotor is substantially vertical.
The flying method includes：Run the fuel engine and the electric power device to realize simultaneously
The vertical flight of the aircraft, wherein the balance of the aircraft by the electronic rotor control or by
The electronic rotor and the fuel engine co- controlling.
Alternatively, the aircraft also includes fixed wing, and the fixed wing is filled with the plurality of power
The direction of propulsion put is substantially parallel, and the flying method also includes：Wrap in running the plurality of power set
At least part of fuel engine for including the fuel engine is realized with being coordinated with the fixed wing
The flat of the aircraft flies.
Alternatively, the flying method also includes：The thrust for changing the electronic rotor of the fixed wing is big
Little and/or thrust direction is changing the flight attitude of the aircraft.
Alternatively, the flying method also includes：The aircraft is flat along being located with the fixed wing
The parallel direction in face accelerates, to obtain the speed needed for flat flying.
Advantage above with respect to the technical scheme of aircraft is equally applicable to the technical scheme of flying method.
Description of the drawings
By description below in conjunction with the accompanying drawings to embodiment, the present invention these and/or other in terms of, it is special
Advantage of seeking peace will become clearer from it is easy to understand, wherein：
Fig. 1 is the structural representation of the aircraft of an embodiment of the invention.
Fig. 2 is the structural representation of aircraft according to another embodiment of the present invention.
Flight attitude schematic diagram when Fig. 3 is aircraft vertical flight according to embodiments of the present invention.
Fig. 4 is flight attitude schematic diagram when aircraft according to embodiments of the present invention puts down winged.
Fig. 5 is the structural representation that the fuel engine of aircraft according to embodiments of the present invention connects electromotor
Figure.
Fig. 6 is that another structure of the fuel engine connection electromotor of aircraft according to embodiments of the present invention is shown
It is intended to.
Fig. 7 is that another structure of the fuel engine connection electromotor of aircraft according to embodiments of the present invention is shown
It is intended to.
Fig. 8 is the structural representation of aircraft according to another embodiment of the present invention.
Fig. 9 is the structural representation of aircraft according to another embodiment of the present invention.
Figure 10 is the structural representation of aircraft according to another embodiment of the present invention.
Figure 11 is the structural representation of aircraft according to another embodiment of the present invention.
Figure 12 is the structural representation of aircraft according to another embodiment of the present invention.
Specific embodiment
Describe the present invention referring now to the exemplary embodiment of the present invention.However, this
Bright to be not limited to embodiment as described herein, which can be implemented in many different forms.Described
Embodiment is only used for making the disclosure thorough and complete, and comprehensively transmits this to those skilled in the art
Bright design.
Fig. 1 is the structural representation of the aircraft 100 of an embodiment of the invention.The aircraft 100
Can for example be unmanned plane, or manned vehicle.In the embodiment shown in fig. 1, aircraft
100 include six power set, and two of which power set are fuel engines, four power set
It is electric power device.Two fuel engines are respectively by motor-driven rotor 102a and 102b and driving machine
The fuel engine 103a and 103b of dynamic rotor 102a and 102b is constituted.Four electric power device difference
It is made up of with the motor 103c-103f for driving electronic rotor 102c-102f electronic rotor 102c-102f.
As shown in figure 1, aircraft 100 includes fuselage 101, six rotor 102a-102f are housed on fuselage 101.
Two 102a and 102b in this six rotors are motor-driven rotor, its respectively by fuel engine 103a and
103b drives.Fuel engine 103a and 103b can for example be internal combustion engine or turbogenerator, and which can
To provide the energy by any petrochemical industry fuel or hydrogen fuel etc..Remaining four 102c-102f of six rotors
Driven by motor 103c-103f respectively, motor can provide energy by rechargeable battery or non-charging battery
Source, it is also possible to directly provide the energy by the electromotor that fuel engine drives, or by battery and fuel engine
The grid-connected power supply together of the electromotor of driving.The advantage of grid-connected power supply is to provide extra power,
There is more abundant power when aircraft takeoff or flight maneuver, and also may be used when fuel engine power is more than needed
Think that battery charges, be to need to prepare during extra power in the future.In this embodiment, motor-driven rotor
102a-102b is substantially parallel or consistent with the Plane of rotation of electronic rotor 102c-102f, i.e. fuels and energy dress
The direction of propulsion put and the Plane of rotation of the electronic rotor are substantially vertical, such that it is able to pass through motor-driven rotor
The VTOL of the aircraft is realized with working while electronic rotor, for example, is taken off vertically.When winged
When row device 100 takes off, motor-driven rotor and electronic rotor are rotated, and its Plane of rotation is substantially at level
Direction, causes aircraft 100 to be raised above so as to rotor produces downward thrust.Those skilled in the art
Member is it should be understood that in order to offset the counteracting force produced by rotor wing rotation, motor-driven rotor 102a and 102b
Direction of rotation can be with conversely, the different rotor number in direction of rotation can phase in electronic rotor 102c-102f
Together.The power of the flight of aircraft 100 can be by motor-driven rotor 102a-102b and electronic rotor 102c-102f
There is provided together；Or, the power of the flight of aircraft 100 mainly can be carried by motor-driven rotor 102a-102b
For, and the electronic rotor 102c-102f of aircraft 100 can provide only balanced action.
When electronic rotor 102c-102f provides only balanced action, the power of the motor of aircraft 100
Can be less, the capacity and volume of corresponding electromotor or battery can also be less, such that it is able to reduce
Aircraft 100 weight of itself.The power of motor can depend on the motor-driven rotor of batch production in phase
It is poor with the thrust under power, for example, if the maximum thrust difference of the motor-driven rotor of batch production is 5%, that
As long as the maximum gross thrust of electronic rotor is higher than 5% (that is, all motor-driven rotations of the motor-driven Rotor thrust in side
Wing thrust 2.5%), it is possible to the balance of basic guarantee aircraft.Embodiments of the invention can be with electricity consumption
The mode of magnetic energy transmission simplifies equilibrium problem when fuels and energy aircraft vertical takes off, and can subtract
The power of small generators and motor, so as to reduce the volume and weight of the fuselage, and then increases effectively load
Lotus.In extreme situations, for example, in the embodiment of two motor-driven rotors, a motor-driven rotor goes out
Existing failure stalling, it is 0 that the thrust difference of motor-driven rotor can reach the thrust of the motor-driven rotor of 100%, i.e.,
Another is 100%, and in the case of other, the thrust difference of motor-driven rotor can be less than 100%.So, go out
As long as the maximum gross thrust of the electronic rotor of existing failure side reaches what the fuel engine being currently running was driven
The gross thrust (the electronic rotor of non-faulting side can be closed) of motor-driven rotor, i.e., the maximum of electronic rotor are total
Thrust reaches the 50% of two motor-driven rotor maximum gross thrusts, then aircraft balance can be allowed to fly.So,
When electronic rotor only provides balanced action, the maximum gross thrust of electronic rotor can be less than motor-driven rotor
The 50% of maximum gross thrust, in other words, the maximum gross thrust of electric power device is filled less than fuels and energy
The 50% of the maximum gross thrust put.The actual most high percentage for adopting can be with raw according to motor-driven rotor batch
The level of difference of product and the factor decision such as extra power required for holding aircraft mobility.As another
Embodiment, when the motor for driving electronic rotor is directly powered by the electromotor that fuel engine drives,
Can by the power setting consumed by electromotor be less than correspondence fuel engine output 50%,
It is arranged such the balance land that can ensure that aircraft in extreme circumstances.For example, with two fuel
In the embodiment of engine, if a fuel engine breaks down, as long as by the one of another fuel engine
Half power is used to drive electromotor and then drives the electric engine of side of breaking down, it is possible to so that aircraft
Balance land.
Balance of the aircraft 100 in vertical flight can be realized by adjusting the thrust of different rotors,
For example, when certain part for needing to raise aircraft 100, increase by the part or near which
Or the thrust of multiple rotors；When needing to reduce certain part of aircraft 100, then reduce the part
Place or the thrust of one or more rotor near which.The thrust for changing electronic rotor can be by adjusting
The rotating speed of motor is realizing；Change motor-driven rotor thrust can by adjust throttle, and/or by using
Displacement slurry adjusts the pitch of motor-driven rotor (propeller) to realize.Alternatively, the balance of aircraft 100
Only can be controlled by electronic rotor, it is also possible to by the electronic rotor and the motor-driven rotor co- controlling.
Generally, the control of the control ratio fuel engine rotating speed of motor speed is easier and accurate, therefore electronic rotation
The control of the wing is more flexible, so as to the balance that control aircraft is participated in by electronic rotor can make flying for aircraft
Row is more stable.Motor can be set to change direction of rotation, so as to can both produce thrust,
Pressure can also be produced.Maximum thrust needed for balance aircraft is poor, determines the size and weight of motor
Amount, also determines the size and weight of battery and electromotor.Motor can change direction of rotation, effectively
Increase thrust in ground is poor, reduces the weight of motor, battery and electromotor.
According to this embodiment of the invention, on the one hand, as aircraft 100 includes fuel engine,
Allow aircraft 100 to carry the higher fuel of energy density, there can be bigger load-carrying of taking off, i.e.,
Heavier article can be carried；On the other hand, as aircraft 100 includes electronic rotor, can cause
The design of aircraft is more succinct, and can be easier and accurately control the balance of aircraft 100 so that
The flight of aircraft 100 is more stable.
In the above-described embodiments, optionally, at least one of fuel engine of aircraft 100 can be with
Electromotor (not shown) is connected with, the electromotor can be to fill to the battery of powering electric motors
Electricity, or be directly motor.As such, it is possible to ensure which has when needing electronic rotor to work fill
The supply of electric power of foot.
It should be noted that, although the concrete structure of aircraft 100 is given in the above-described embodiments, but
The present invention is not limited to the concrete structure.Especially, rotor is not necessarily straight by motor or fuel engine
Driving is connect, but by motor or the gear train or belt transmission of fuel engine driving.This area
Technical staff should be understood that each motor or fuel engine can drive a rotor incessantly, can be with
By gear train or the multiple rotors of belt drives.The quantity of rotor is not necessarily six, for example, can be
Three, four, five or more, wherein the quantity of motor-driven rotor is not limited to two, can be one
Or more, the quantity of electronic rotor is also not necessarily limited to four, and can be one, two, three or more
It is multiple.It will be apparent to those skilled in the art that when the quantity of any rotor is odd number, it is single
The counteracting force for corresponding to the rotor of derotation can be supported by adjusting the angle or thrust of other rotors
Disappear.Additionally, in the example of fig. 1, electronic rotor is symmetrically distributed in around fuselage, but the present invention is not
It is limited to this mounting means.The shape of fuselage is also not necessarily limited to the shape shown in Fig. 1, and which can be any suitable
Shape.Those skilled in the art according to actual needs, can with the quantity of the above-mentioned rotor of specific design and
Distribution and the shape of fuselage.Additionally, the concrete principle and necessary design with regard to aircraft vertical flight can
With identical with pure helicopter or unmanned plane, no longer illustrate here.
Fig. 2 is the structural representation of aircraft 200 according to another embodiment of the present invention.With Fig. 1's
Embodiment is compared, and aircraft 200 also includes fixed airfoil member 204, and fixed airfoil member 204 includes
Two fixed wing 204a and 204b, are separately mounted to the both sides of fuselage 201.In fig. 2, aircraft
200 equally include six rotor 202a-202f.In this six rotors, rotor 202a and 202b are difference
The motor-driven rotor driven by fuel engine 203a and 203b, rotor 202c-202f are respectively by motor
The electronic rotor that 203c-203f drives.In fig. 2, electronic rotor 202c-202f is symmetrical respectively in fuselage
Around 201, and wherein electronic rotor 202c and 202d and electronic rotor 202e and 202f is located at respectively
The both sides of fixed wing 204.Motor-driven rotor 202a and 202b is arranged on the front end of fixed wing 204,
And be located on fixed wing 204a and 204b respectively.The Plane of rotation of all rotor 202a-202f and fixation
Wing 204 is substantially vertical, i.e. substantially vertical with the plane that the long cross direction of wing is constituted, in other words,
Fixed wing is substantially parallel with the direction of propulsion of power set.This form Design of rotor and fixed wing
It is similar with the form Design of the propeller of conventional fixed-wing aircraft and wing.Additionally, the fixed machine of the present invention
The shape design of the wing can also refer to the wing shapes of conventional fixed-wing aircraft, such as, can be all-wing aircraft
Layout.Two aerofoils of fixed wing 204 need to meet aerodynamic principle so that aircraft 200
When flat winged, fixed wing 204 can hold up aircraft upwards.It should be noted that here " basic
The Plane of rotation of rotor 202a-202f vertically " is represented with fixed wing 204 and absolute upright is not needed, " base
This is parallel " represent that the direction of propulsion of power set need not be absolute parallel with fixed wing, as long as in flight
When device 200 is flat winged, the rotation of rotor disclosure satisfy that above-mentioned aerodynamic principle with the cooperation of fixed wing
So that aircraft 200 obtains towing force upwards while thrust forward is obtained.
Can realize taking off similar to the static vertical of helicopter according to the aircraft 200 of Fig. 2 and similar to
The quick flat of common fixed wing airplane flies.Fig. 3 shows that aircraft 200 according to embodiments of the present invention exists
The schematic diagram of flight attitude during vertical flight.As shown in figure 3, when taking off vertically, aircraft 200
Flight attitude be：The direction of rotation of rotor 202a-202f is basically parallel to ground, and fixes wing 204
It is basically perpendicular to ground.Now, aircraft 200 starts the rotation of rotor 202a-202f, and air is produced
Aircraft 200 is boosted by downward thrust, the counteracting force of air upwards, and is flown vertically upward.Such as
It is mentioned above, the balance of aircraft 200 can be controlled by the thrust size of control rotor 202a-202f,
The rotary speed for especially controlling electronic rotor 202c-202f (is for example input to by increase or reduction electronic
The voltage/current of machine 203c-203f is controlled, and/or changes the alternating current or arteries and veins for being input to motor
The frequency of punching) or direction of rotation controlling the balance of aircraft 200.For example, when aircraft 200 to
When electronic rotor 202c and 202d sides incline, can pass through to increase electronic rotor 202c's and 202d
Rotary speed and/or reduce the rotary speed of electronic rotor 202e and 202f to adjust flight attitude and control
System balance.The rotating speed that some rotors should be increased still reduces the rotating speed of some rotors, depending on change or
Person keeps the needs of aircraft altitude.Need to change into flat flying from vertical flight after aircraft 200 goes up to the air
When, aircraft 200 needs change of flight posture, as shown in Figure 4.Fig. 4 is according to embodiments of the present invention
The schematic diagram of flight attitude of the aircraft 200 in flat flying (schematic diagram is from the front upper place of aircraft
The perspective view for looking over).In flat flying, the direction of fixed wing 204 is consistent with heading, and which can be with
Be basically parallel to ground, it is also possible to there is angle with ground in order to the reason such as turn, the flight attitude with
The flight attitude of conventional fixed-wing aircraft is the same.Aircraft 200 is from vertical flight to the flat flight attitude for flying
Change can be by controlling the thrust size and/or thrust direction of rotor realizing.For example, will be multiple
In the case that electronic rotor 202c-202f is distributed in the both sides of fixed wing, can be by changing fixed wing
Both sides electronic rotor thrust ratio and/or thrust direction changing the flight appearance of the aircraft 200
Gesture.In the aircraft 200 shown in Fig. 2, electronic rotor 202c and 202d and electronic rotor 202e and
202f is located at the both sides of fixed wing 204 respectively.It is assumed that electronic rotor 202c and 202d
The downside when side at place is flat flying, when the side that electronic rotor 202e and 202f is located is flat flying
Upside, then aircraft 200 is in the flat winged shape being changed into from the state of taking off vertically shown in Fig. 3 shown in Fig. 4
During state, can pass through to increase the rotary speed of electronic rotor 202e and 202f, and/or reduce electricity
The direction of rotation of the rotary speed or the electronic rotor 202c and 202d of reversion of dynamic rotor 202c and 202d.
Before aircraft 200 is changed to level-flight attitude by the attitude that takes off vertically, aircraft 200 generally can be first allowed to add
Speed however adjust the rotation of corresponding rotor again, to ensure that aircraft 200 can have enough speed after flat flying
Fixed wing is allowed to produce enough lift.
Alternatively, aircraft can also change of flight posture in the following manner.For example, in aircraft 200
It is changed to before level-flight attitude by the attitude that takes off vertically, first allows aircraft 200 upwards or accelerate flight to certain side,
To ensure that aircraft 200 can have enough speed to allow fixed wing to produce enough lift after flat flying.Allow
Aircraft flies to certain side, it is desirable to reduce the thrust of the side, or increases the thrust of opposite side, so
The direction of propulsion of all power set and the angle of horizontal direction can be allowed not to be right angle, and then make aircraft
200 power for obtaining horizontal direction movement.Opposite side is to increase also as the thrust that should reduce certain side
Thrust, depending on the needs for changing or keeping aircraft altitude.The direction for putting down the acceleration flight before flying can
With substantially vertical with fixed-wing plane.Alternatively, in order that putting down the acceleration flight before flying more effectively, plus
The direction of speed flight can also be almost parallel with fixed wingpiston, to reduce the resistance that fixed wing brings.
For example, can pass through to increase the rotary speed of electronic rotor 202c and 202e, and/or reduce electronic rotor
The rotary speed of 202d and 202f, allows aircraft to accelerate flight to electronic rotor 202d and 202f sides,
After aircraft has enough speed, can pass through further to increase the rotation of electronic rotor 202c and 202e
Speed, and/or reduce electronic rotor 202d and 202f rotary speed or invert electronic rotor 202d and
The direction of rotation of 202f, and allowed by the angle of the aileron (not shown) of the fixed wing of adjustment in time
The fuselage of aircraft makes the attitude almost parallel with ground into.Now, by adjusting the aileron for fixing wing
Angle allow the aileron of aircraft both sides to deflect to different direction, can allow the aircraft 200 with fuselage to be
Axis is rotated, and so as to make fixed wingpiston and ground almost parallel, and produces lift.Need
It is bright, in this example, wing is fixed comprising aileron, but for this disclosure, and not all is realized
The fixed wing of mode is required for comprising aileron.
Alternatively, the take-off process of aircraft 200 for example can be by the rudder face (not shown) of aircraft empennage
To control.Concrete mode can be that aircraft 200 accelerates to fly away from ground (heading after taking off vertically
It is not necessarily required to and ground exact vertical, aircraft can be ensured by way of above-mentioned control rotor
Heading), after aircraft has enough speed, the rudder face of aircraft tailplane is by the appearance of aircraft
State is changed to flat flying or other flight attitudes.Those skilled in the art should be understood that attitude of flight vehicle
Change and can also combine by way of swinging the rudder face of aircraft tailplane and adjusting aircraft rotor
Realize.It should be noted that in this example, aircraft includes empennage and its rudder face, but with regard to the disclosure
For, and the aircraft of not all implementation is required for comprising empennage or empennage and its rudder face.
The descent of aircraft is contrary with take-off process.By the rotor and/or the flight that control aircraft
The rudder face of device, allow aircraft pose adjustment be vertical attitude, then by adjust aircraft rotor turn
The pitch of speed or displacement slurry, allows aircraft slowly land.
It is alternatively possible to undercarriage is installed in the side of fixed-wing, so in the place being adapted to, aircraft
Can be with rolling start, or sliding race is landed, the electricity ratio of fuel and/or battery that cunning has run consumption reduction is vertical
Landing is few, can increase the voyage of aircraft, or the expense for saving fuel.
Alternatively, the rotor of power is not provided for all rotors or when putting down and flying, can be using folding automatically
Stacked rotor.This rotor when not rotating, by spring or wind-force affected can with auto-folder, from
And reduce resistance.Additionally, the design and installation of undercarriage can be facilitated using automatic collapsible type rotor.
Additionally, can be with change of flight device 200 by the thrust size and/or thrust direction that change rotor
The balance of heading or control aircraft 200.For example, can when aircraft 200 needs to turn round to the left
With the thrust for increasing the rotor on right side or the thrust of the rotor for reducing left side.Aircraft 200 in flat flying,
Thrust backward can be provided by motor-driven rotor 202a and 202b, with the wing by means of fixed wing 204
The aerodynamic design in face and the lift to aircraft is provided, its principle and common fixed wing airplane phase
Together, those skilled in the art can be designed to fixed wing 204 according to specific needs.Fly flat
During, the dynamical system of electronic rotor can be closed, it is also possible to electronic rotor be opened with provided auxiliary
The balance and/or adjustment heading and/or flight attitude of power and/or control aircraft.When the motor-driven rotation
When the wing and the electronic rotor are worked simultaneously, total output on the one hand can be caused to increase, on the other hand can be with
The precise control that flexible advantage realizes flight speed, direction and posture is controlled using electronic rotor.
Alternatively, the flight attitude of aircraft can also be controlled by the rudder face on fixed wing.Rudder face control
System is similar with conventional aircraft, can pass through wing flap, aileron, tailplane rudder face, vertical tail rudder face
Interact to control attitude Deng rudder face with air-flow.
According to the aircraft 200 of the embodiment of Fig. 2 can not only realize similar to helicopter VTOL but also
Can realize that the quick flat for being similar to common fixed wing airplane flies.Also, as aircraft 200 can pass through
The motor-driven rotor that the energy is provided by fuel engine provides flat fly power, therefore the speed and boat of this aircraft
Journey can be greatly increased.
In the above-described embodiments, optionally, at least one of fuel engine of aircraft 200 equally may be used
To be connected with electromotor (not shown), the electromotor can be the battery to powering electric motors
Charge, or be directly motor.As such, it is possible to ensure which has when needing electronic rotor to work
Sufficient supply of electric power.
It should be noted that, although the concrete structure of aircraft 200 is given in the above-described embodiments, but
The present invention is not limited to the concrete structure.Especially, fixed wing is not limited to the installation relation of fuselage
Shown in Fig. 2, and can be using any appropriate design, for example, fuselage can be arranged on fixed wing
Side, now fix wing two parts can not be divided into but an entirety by fuselage.Motor-driven rotor
It is also not necessarily limited to be centrally mounted to fix the front end of wing by motor-driven rotor with the position relationship of fixed wing,
And can be the lower section for being for example arranged on fixed wing, as long as these position relationships meet aircraft 200 and fly
Capable principle of dynamics.Furthermore, such as described in Figure 1, the quantity of rotor is not necessarily six
It is individual, can for example be three, four, five or more, wherein the quantity of motor-driven rotor is not limited to two
It is individual, can be one or more, the quantity of electronic rotor is also not necessarily limited to four, and can be one,
Two, three or more.Electronic rotor is not limited to be symmetrically distributed in around fuselage.The shape of fuselage
The shape being not limited to shown in Fig. 2, and can be any suitable shape.Additionally, with regard to aircraft 200
The concrete principle and necessary design that vertical flight peace flies can be with pure helicopter or unmanned plane and fixation
Wing aircraft is identical, and those skilled in the art can carry out specific design according to principles well-known.
Those skilled in the art should be understood that each fuel engine or motor can drive one incessantly
Rotor, can pass through gear train or the multiple rotors of belt drives.For example, aircraft can be with only one of which
Fuel engine, the mode being driven with umbrella shape/ring gear and axle drive two positioned at two fixed tip extensions
The contrary rotor in direction of rotation.
Optionally, embodiments in accordance with the present invention, fuel engine can drive electromotor simultaneously, be electronic
The battery of rotor charges or directly powers for electronic rotor.When fuel engine drives electromotor simultaneously,
Fuel engine can directly drive itself rotor (or propeller, in the disclosure, rotor and propeller
Represent identical implication, i.e., the blade that can be rotated), and pass through belt, chain, and/or gear driving
Electromotor.Or, fuel engine can also direct drive generator, and pass through belt, chain, and/or
Gear drives rotor.Or, fuel engine can drive rotation respectively by belt, chain, and/or gear
The wing and electromotor.However, it is contemplated that aircraft is higher to the weight and reliability requirement of all component, most
The type of drive of suitable aircraft is that fuel engine passes through the line shaft of coaxial line while driving rotor and generating
Machine.The line shaft of the coaxial line can be the axle of an entirety, it is also possible to the coaxial line being connected together
Multiple axles, it will be apparent to those skilled in the art the mode of the multiple axles connection of coaxial line is had a lot
(for example, by various shaft couplings).Each line shaft of coaxial line can be connected with each other by clutch, led to
Cross the power supply that clutch can selectively cut off electromotor or rotor.Clutch is also applied for leading to
Cross belt, chain, and/or gear-driven mode.Fuel engine can effectively be distributed using clutch
Power.Fig. 5-Fig. 7 is schematically illustrated piston type by a line shaft 504,604,704
Electromotor 501,601,701 is direct with electromotor 503,603,703 and rotor 502,602,702
The schematic diagram of connection.In Fig. 5-Fig. 7, electromotor is located at the diverse location of electromotor and rotor respectively.So
Design reduce weight needed for actuating device, while decrease the energy loss that actuating device brings,
And improve reliability.Certainly, the concrete structure of Fig. 5-Fig. 7 should not be construed a kind of restriction.Send out
Motivation can be any fuel engine, for example, it may be turbogenerator or jet engine.
When fuel engine is jet engine, only it is directly connected to electromotor and is not connected to rotor (spiral shell on the line shaft
Rotation oar).Additionally, more than one electromotor can also be connected on line shaft.
Fig. 8-11 schematically shows the structural representation of the aircraft of other embodiments of the invention
Figure.In the embodiment in fig. 8, aircraft 800 includes fuselage 801, equipped with fixed machine on fuselage 801
The wing 804, the rear end of fixed wing 804 are equipped with two empennages 805a and 805b, fix the two of wing 804
Two fuel powered systems are housed on the end of side, which is drawn by motor-driven rotor 802a, 802b and fuel respectively
Hold up 803a, 803b composition.Four are provided with the direction of fixed wing 804 on fixed wing 804
Individual support member 806a-806d, is separately installed with two electronic rotor 802c-802j in each support member, often
Individual electronic rotor can be by independent motor-driven, it is also possible to will be several or all electric by actuating device
, by a motor-driven, for example, two electronic rotors of same support member one end are by same for dynamic rotor
Individual motor-driven.These motor are may be located in the end of support member.The embodiment and Fig. 8 of Fig. 9
The difference of embodiment be that motor-driven rotor is different with the setting of the position of electronic rotor.In the embodiment of Fig. 9
In, support two support members of electronic rotor to be located at the end of fixed wing both sides respectively, and two are motor-driven
Rotor 902a, 902b are located at the front end of fuselage.The two coaxial motor-driven rotors can be by a fuel engine
Drive, the fuel engine drives the two coaxial motor-driven rotors to carry out rightabout rotation by gear train.
The embodiment of Figure 10 and the difference of the embodiment of Fig. 8 are that the quantity of electronic rotor and position setting are different.
In the embodiment in figure 10, four electronic rotor 1002c-1002f are respectively arranged on two empennages, this
Four electronic rotors can be driven by four motor 1003c-1003f respectively.The enforcement of Figure 11 is exemplified
A kind of aircraft 1100 with three fixed wing 1104a-c.In two fixed wings of downside
The end of 1104a and 1104b is provided with fuel engine, and which is respectively by motor-driven rotor 1102a, 1102b
Constitute with fuel engine 1103a, 1103b.By perpendicular to fixation on the fixed wing 1104c of upside
The support member of wing 1104c installs two electric power devices, and which is respectively by electronic rotor 1102c, 1102d
Constitute with motor 1103c, 1103d.Support meanss are respectively provided with the rear end of three fixed wings, are used
In taking off vertically front support aircraft 1100 in aircraft 1100.Fix in wing in above three, it is fixed
Wing 1104a and 1104b are mainly provided and are put down the lift for flying, and fixed wing 1104c is electric except support two
The effect in stabilized flight direction outside dynamic power set, is also acted as, the vertical tail of conventional airplane is similar to.Machine
Dynamic rotor 1102a, 1102b can be starched using displacement, direction of rotation conversely, when taking off vertically,
The angular balance of Y direction is controlled by constantly correcting the pitch of the two rotors.Electronic rotor
The direction of rotation of 1102c, 1102d is conversely, by the rotating speed of control motor, can control aircraft X
Axial angular balance.Electronic rotor 1102c, 1102d can be shown in approximately the same plane (i.e.
Place left and right), or coaxial (placing before and after i.e.).After aircraft 1100 takes off vertically, can
With the rotating speed by increasing electronic rotor 1102c, 1102d, aircraft 1100 is allowed to be changed to by vertical attitude
Level-flight attitude.
Fuel engine in Fig. 1-4 and Fig. 8-11 all includes rotor (propeller), i.e., all pass through combustion
Material engine drives rotor to provide the power of aircraft, however, the invention is not restricted to this, fuel engine
It can be electromotor that turbofan or jet engine etc. do not drive propeller.In this feelings
Under condition, fuel powered systems only have engine without rotor.In the present invention, no matter what fuel engine is
Kind of engine, the direction of propulsion of fuel powered systems are all substantially vertical with the direction of rotation of electronic rotor, and solid
The plane for determining the wing is almost parallel.When aircraft vertical takes off, direction of propulsion and the ground of fuel powered systems
Face is substantially vertical.When aircraft is flat to fly, direction of propulsion and the heading of fuel powered systems are substantially put down
OK.
Additionally, in the disclosure, when fuel engine uses rotor, it is possible to use variable-distance rotor
(displacement oar).The pitch (propeller pitch angle) of displacement oar can be regulation, under identical rotating speed, pass through
Increase or reduce pitch, can increase or reduce thrust, while the power of the fuel engine for consuming
Can increase or reduce.Displacement oar is used in an embodiment of the present invention, except can conveniently control flight
The balance of device, also helps the power for effectively utilizing fuel engine.For example, when the embodiment of the present invention
Aircraft can cut out motor and reduce because of generator energy conversion brought energy loss when putting down winged, this
When can increase displacement slurry pitch, allow rotor more effectively using fuel engine output whole power.
When the aircraft is in vertical attitude, the power of motor can come from electromotor, at this moment can be with
Reduce the pitch of displacement slurry, can so increase the rotating speed of fuel engine, electromotor can be exported enough
Electric drive motor.
According to another embodiment of the present invention, motor-driven rotor may be located at the rear of electronic rotor；And extremely
A few motor-driven rotor has Chong Die with least one electronic rotor.As shown in figure 12, four electronic rotors
1202c-1202f is respectively arranged in the front side of aircraft 1200, and two motor-driven rotor 1202a-1202b are located at
Rear (posture when " front " and " afterwards " here puts down winged with aircraft of electronic rotor 1202c-1202f
It is determined that), and electronic rotor and motor-driven rotor have it is Chong Die.Thus, the air that electronic rotor is released backward
Power can provide thrust to motor-driven rotor, reduce the resistance of motor-driven rotor.Especially, drawn by fuel
In the case of holding up the motor of the electronic rotor of electromotor direct drive of drive, above-mentioned layout can increase suddenly
Ensure the rotating speed of motor-driven rotor and fuel engine during the rotating speed of big electronic rotor, so as to ensure that electromotor is defeated
Go out stablizing for voltage.The experiment of inventor shows, if not adopting above-mentioned layout, increases electronic when suddenly
During the rotating speed of rotor, as the load of electromotor increases, motor-driven rotor and generating that fuel engine is driven
The total load of machine increases therewith, so as to the rotating speed for causing fuel engine is reduced, so output voltage can be unexpected
Diminish；And when using after above-mentioned layout, the back pressure of electronic rotor by promote motor-driven rotor and one
Determine in degree, to compensate for the load of fuel engine increase suddenly, so as to ensure that the moment output work of electromotor
Rate is stable.
It should be appreciated by those skilled in the art that can be carried out to the present invention according to design requirement and other factorses
Various modifications, combination, part are combined and are replaced, as long as they are in claims or the model of its equivalent
In enclosing, that is, belong to claimed interest field of the invention.
Claims (24)
1. a kind of aircraft, with multiple power set, it is characterised in that：
The plurality of power set include fuel engine and electric power device, the fuels and energy dress
Put and driven by fuel engine, the electric power device is included by the electronic rotor of motor-driven；And
The Plane of rotation of the direction of propulsion of the fuel engine and the electronic rotor is substantially vertical.
2. aircraft as claimed in claim 1, it is characterised in that：
The aircraft also includes fixed wing, the propulsion of the fixed wing and the plurality of power set
Direction is substantially parallel.
3. aircraft as claimed in claim 2, it is characterised in that：
When the aircraft is flat winged, power is provided or by the fuels and energy by the fuel engine
Device and the electric power device provide power simultaneously.
4. aircraft as claimed in claim 2, it is characterised in that：
The electronic rotor has multiple, and multiple electronic rotors are distributed in the two of the fixed wing
Side.
5. aircraft as claimed in claim 2, it is characterised in that：
The fixed wing is multiple, is provided with the fuel engine at least two fixation wings,
And remaining fixes at least one of wing above or both sides are provided with the electronic rotor.
6. aircraft as claimed in claim 2, it is characterised in that：
At least one of described fuel engine includes the motor-driven rotor driven by the fuel engine.
7. aircraft as claimed in claim 1, it is characterised in that：
At least one of described fuel engine is also associated with electromotor, and the electromotor can be to described
The battery of powering electric motors charges and/or directly provides electric power to the motor.
8. aircraft as claimed in claim 7, it is characterised in that：
The motor is powered by the battery, the generator powered or by the battery and described
Generator connecting in parallel with system is powered.
9. aircraft as claimed in claim 7, it is characterised in that：
The electromotor is directly connected to corresponding fuel engine by the line shaft of coaxial line.
10. aircraft as claimed in claim 9, it is characterised in that：
The corresponding fuel engine is also directly connected to motor-driven rotor by the line shaft of the coaxial line.
11. aircraft as claimed in claim 7, it is characterised in that：
The electromotor is driven by clutch by corresponding fuel engine.
12. aircraft as claimed in claim 7, it is characterised in that：
At least one of described fuel engine drives motor-driven rotor by clutch.
13. aircraft as claimed in claim 1, it is characterised in that：
The balance of the aircraft, heading and/or flight attitude are controlled by the electronic rotor, or
By the electronic rotor and the fuel engine co- controlling.
14. aircraft as claimed in claim 1, it is characterised in that：
Maximum gross thrust of the maximum gross thrust of the electric power device less than the fuel engine
50%.
15. aircraft as claimed in claim 7, it is characterised in that：
The motor is directly powered by the electromotor, and the power consumed by the electromotor is less than
The 50% of the output of correspondence fuel engine.
16. aircraft as claimed in claim 1, it is characterised in that：
The side of the aircraft is equipped with undercarriage so that the aircraft can slide race landing on runway.
17. aircraft as claimed in claim 1, it is characterised in that：
At least one rotor of the aircraft is automatic collapsible type rotor.
18. aircraft as claimed in claim 1, it is characterised in that：
At least one of described electronic rotor can change direction of rotation.
19. aircraft as claimed in claim 1, it is characterised in that：
Displacement slurry used in the fuel engine.
20. aircraft as described in claim 1 or 8, it is characterised in that：
At least one of described fuel engine includes the motor-driven rotor driven by the fuel engine；
The motor-driven rotor is located at the rear of the electronic rotor；And
At least one of at least one of described motor-driven rotor and described electronic rotor have Chong Die.
A kind of 21. flying methods of aircraft, the aircraft have multiple power set, and its feature exists
In：The plurality of power set include fuel engine and electric power device, the fuels and energy dress
Put and driven by fuel engine, the electric power device is included by the electronic rotor of motor-driven, described
The Plane of rotation of the direction of propulsion of fuel engine and the electronic rotor is substantially vertical, and the flight
Method includes：
Run the fuel engine and the electric power device simultaneously to realize hanging down for the aircraft
Fly nonstop to row, wherein the balance of the aircraft by the electronic rotor control or by the electronic rotor and
The fuel engine co- controlling.
22. flying methods as claimed in claim 21, it is characterised in that：The aircraft also includes solid
Determine wing, the fixed wing is substantially parallel with the direction of propulsion of the plurality of power set, the flight
Method also includes：
Running the plurality of power set includes at least part of fuels and energy dress of the fuel engine
Put to coordinate with the fixed wing to realize that the flat of the aircraft flies.
23. flying methods as claimed in claim 21, it is characterised in that the flying method also includes：
Change the thrust size and/or thrust direction of the electronic rotor to change the flight of the aircraft
Posture.
24. flying methods as claimed in claim 21, it is characterised in that the flying method also includes：
The aircraft accelerates along the direction parallel with the fixed wing place plane, to obtain flat flying
Required speed.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510685169 | 2015-10-20 | ||
| CN201520815553 | 2015-10-20 | ||
| CN201510685169X | 2015-10-20 | ||
| CN2015208155532 | 2015-10-20 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106585964A true CN106585964A (en) | 2017-04-26 |
Family
ID=57413863
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620076951.1U Expired - Fee Related CN205770176U (en) | 2015-10-20 | 2016-01-26 | Aircraft |
| CN201610053378.7A Withdrawn CN106585964A (en) | 2015-10-20 | 2016-01-26 | Aircraft and flying method thereof |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620076951.1U Expired - Fee Related CN205770176U (en) | 2015-10-20 | 2016-01-26 | Aircraft |
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| Country | Link |
|---|---|
| CN (2) | CN205770176U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107499506A (en) * | 2017-07-07 | 2017-12-22 | 清华大学 | A kind of distributed propulsion tailstock formula VTOL Fixed Wing AirVehicle |
| CN110697056A (en) * | 2018-07-10 | 2020-01-17 | 劳斯莱斯有限公司 | Hybrid electric aircraft |
| CN110963052A (en) * | 2018-09-30 | 2020-04-07 | 中国航发商用航空发动机有限责任公司 | Distributed propulsion system, aircraft and propulsion method |
| CN113212745A (en) * | 2021-04-26 | 2021-08-06 | 南方科技大学 | Rotor unmanned aerial vehicle and endurance prolonging method thereof |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107215462B (en) * | 2017-07-01 | 2021-08-31 | 山东翔鸿电子科技有限公司 | Landing method and landing device for vertical take-off and landing fixed wing unmanned aerial vehicle |
-
2016
- 2016-01-26 CN CN201620076951.1U patent/CN205770176U/en not_active Expired - Fee Related
- 2016-01-26 CN CN201610053378.7A patent/CN106585964A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107499506A (en) * | 2017-07-07 | 2017-12-22 | 清华大学 | A kind of distributed propulsion tailstock formula VTOL Fixed Wing AirVehicle |
| CN110697056A (en) * | 2018-07-10 | 2020-01-17 | 劳斯莱斯有限公司 | Hybrid electric aircraft |
| CN110963052A (en) * | 2018-09-30 | 2020-04-07 | 中国航发商用航空发动机有限责任公司 | Distributed propulsion system, aircraft and propulsion method |
| CN113212745A (en) * | 2021-04-26 | 2021-08-06 | 南方科技大学 | Rotor unmanned aerial vehicle and endurance prolonging method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN205770176U (en) | 2016-12-07 |
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