CN110254706A - It is a kind of can VTOL aircraft - Google Patents
It is a kind of can VTOL aircraft Download PDFInfo
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- CN110254706A CN110254706A CN201910655990.5A CN201910655990A CN110254706A CN 110254706 A CN110254706 A CN 110254706A CN 201910655990 A CN201910655990 A CN 201910655990A CN 110254706 A CN110254706 A CN 110254706A
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/32—Wings specially adapted for mounting power plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
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Abstract
The present invention relates to it is a kind of can VTOL aircraft, which includes fuselage, wing and propulsion system；Wing includes the main wing of the front wing of two two sides for being symmetrically set in fuselage and two sides that two are symmetrically set in fuselage, and front wing is located at the front side of main wing；Propulsion system includes drive system and power packages, each main wing and front wing are respectively equipped with power packages, each power packages respectively include ducted fan, drive system includes battery system and motor compatible with each power packages, battery system is used to power for ducted fan and motor, and each power packages can be under the drive of the motor around the axial rotation of main wing or front wing.The aircraft can VTOL, low noise, flying speed are fast, electric energy utilization rate is high and has a safety feature.
Description
Technical field
The present invention relates to flight equipment technical fields, and in particular to it is a kind of can VTOL aircraft.
Background technique
In recent years along with the gradualling mature of fuel cell and lithium battery technology, battery energy density increases year by year, at present
All-electric automobile largely enters market, and all-electric aircraft (such as Air Passenger E-Fan) will enter marketing.Due to electronic
Aircraft has many characteristics, such as energy conservation and environmental protection, low noise, low vibration, highly reliable and high safety, therefore Electric aircraft will be future
One the main direction of development of green aviation.
Currently, aircraft can be there are many type according to structure, the differentiation of landing form, which be broadly divided into, needs runway (or water
Face) and two kinds of VTOL, high shutdown cost, limited runway resource and the high use cost on traditional airport limit winged
The fast development of row device.It there is no the civilian VTOL electric airplane to put into effect at present, and be based on multiaxis electric propeller
The VTOL craft of scheme there are high noise, flying speed is slow and safe margin is low the problems such as.
Therefore, how to provide one kind can VTOL, and low noise, flying speed be fast and the flight that has a safety feature
Device is those skilled in the art's technical issues that need to address.
Summary of the invention
The object of the present invention is to provide it is a kind of can VTOL aircraft, low noise, flying speed be fast and security performance
It is good.
In order to solve the above technical problems, the present invention provide it is a kind of can VTOL aircraft, the aircraft include fuselage,
Wing and propulsion system；The wing include the front wing of two two sides for being symmetrically set in the fuselage and two be symmetrically set in it is described
The main wing of the two sides of fuselage, the front wing are located at the front side of the main wing；The propulsion system includes drive system and power packages,
Each main wing and the front wing are respectively equipped with the power packages, and each power packages respectively include at least four ducted fans,
The drive system includes battery system and motor compatible with each power packages, and the battery system is used to be each described
Ducted fan and the motor power supply, each power packages can under the driving of the motor around the main wing or it is described before
The axial rotation of the wing.
The two sides of fuselage are symmetrically arranged with two main wings and two front wings, wherein each main wing and each front wing are mounted on power
Group, each power packages are made of multiple (at least four) ducted fans, wherein the power packages of main wing can be under the drive of the motor
Axial direction (length direction) around main wing rotates, and the power packages of front wing can be under the drive of the motor around axial direction (the length side of front wing
To) rotation.
There are three types of stage, stage of taking off vertically, efficient cruising phase and vertical landing stages for the flying instrument, wherein hangs down
Straight takeoff phase refers to that when taking off, each power packages turn to plumbness (the i.e. rotation of ducted fan under the drive of the motor
Shaft and horizontal plane), at this point, power packages to provide thrust as aircraft close to full power state rise, aircraft vertical
Fly；When aircraft flies to predetermined altitude, power packages gradually go to horizontality by upright position under the drive of the motor and (contain
The rotary shaft of road fan is parallel to the horizontal plane), the transition flown from taking off vertically to putting down is completed, is efficiently patrolled at this point, aircraft enters
The power packages small-power cruising condition of boat stage, main wing and front wing, aircraft lift are provided by main wing and front wing, the aircraft phase
Compared with its flying speed can be effectively improved for Multi-axis aircraft；The vertical landing stage refer to aircraft landing when, aircraft
Flying speed is gradually decreased, meanwhile, the power packages of main wing and front wing turn to vertical configuration by horizontality under the action of motor
State, and lift is provided to approach full power state work as aircraft to realize vertical landing.
The aircraft in the stage of taking off vertically, each power packages for its provide lift need to be greater than the self gravity of the aircraft with
It realizes and rises, and in efficient cruising phase and vertical landing stage, it is the requirement of lift provided by aircraft for power packages
It is relatively small, therefore, even in flight course, the case where single or several ducted fans, which are damaged, etc. leads to failure,
Also it can guarantee that the aircraft security lands, or in extreme circumstances, each power packages fail, which can also be by whole
Machine bales out, and security performance is good.
Since the thrust angle of each power packages is controllable, by the control of the thrust angle to power packages, can be realized winged
Row device is transitioned into another state from state automatic smoothing, is conducive to flexibly control state of flight, and aircraft
Homeostasis, it is highly-safe.Also, the longitudinal stability of the aircraft is the thrust by controlling wing the right and left power packages
What difference was realized；Aerial turn to is inclined by the differentiation thrust and main wing power packages thrust direction of the power packages of aircraft two sides
Turn, front wing power packages thrust direction deflection co- controlling, using no tail fin design, it is integrally-built can effectively to mitigate aircraft
Weight.The aircraft slow speed vertical can be moved as helicopter, be realized by the thrust direction variation of ducted fan aerial
Accurate pinpoint landing is realized in rotation in turn.
Two main wings and two front wings are respectively equipped with power packages, i.e., provide thrust by multiple groups power packages for aircraft, respectively
Power packages include at least four ducted fans, i.e. the quantity of ducted fan is more, wherein each ducted fan is multiple leaflet constructs
(blade of each ducted fan is at least ten) drives so that the bearing capacity of the power packages is strong relative to conventional piston engine
The aircraft that propeller promotes is more efficient, and dynamic population is distributed in the top rear portion of two main wings and two front wings, makes wing liter
Force coefficient is higher, which can be realized VTOL, without runway, expands the scope of application of the aircraft and uses ring
Border.Simultaneously as more ducted fans and mutliblade setting, so that the vibration of the propulsion system is compared with conventional piston engine and spiral shell
Rotation paddle is much smaller, and the cladding due to there is duct when ducted fan rotation, and the eddy current crack of fan blade tip will also drop significantly
While low, the safety of ground crew also will be high compared with traditional propeller aircraft, in addition, due to ducted fan be located at wing it
On, wing also has screening effect to ducted fan noise, can effectively reduce noise of the aircraft in lifting process.
In addition, battery system can be fuel cell and be also possible to lithium battery in the present embodiment, specific limit is not done herein
System, at this point, aircraft is to drive ducted fan to provide thrust for aircraft by battery system, therefore nothing is appointed in flight course
What pollutant emission, environment protecting is good, in addition, the battery system is high energy density cells system, can reduce use cost, by
Security performance therefore can be improved in no fuel oil and the component for generating high temperature.
The fuselage of the aircraft can be equipped with preceding freight house, aft hold and main cabin, can be suitable for short distance passenger traffic, public transport
The fields such as (such as aerial taxi), disaster area rescue, emergency medical, Private Flight.
Optionally, each power packages further include the shaft being axially arranged along the main wing or the front wing, the culvert
Road fan is fixed with the shaft, and the shaft being capable of being rotated by the motor.
Optionally, rudder face is equipped on rear side of each power packages.
Optionally, parachute is additionally provided at the top of the fuselage.
Optionally, the battery system includes main battery system and secondary cell system.
Optionally, the drive system further includes fuel oil power supply system, and the fuel oil power supply system includes fuel engines
And generator, the generator are used to power for each ducted fan and the motor.
Optionally, the height of the front wing is less than the height of the main wing.
Optionally, the aspect ratio of the main wing and the front wing is not less than 6.
Optionally, the junction smooth transition between the wing and the fuselage.
Optionally, the material of the fuselage, the main wing and the front wing is carbon fibre composite.
Optionally, the ducted fan includes the shell with air inlet and exhaust outlet, the air inlet and the exhaust
Mouth is connected to by the housing cavity, is provided with power motor in the middle part of the housing cavity, is provided with wind on the power motor
Fan leaf, the air inlet and the exhaust outlet are connected to by the housing cavity, and the vent position, which is provided with, laterally to be divided
The exhaust outlet is divided into first row port and second exhaust port by flowing plate, the transverse direction flow distribution plate, further includes actuator, for driving
Lateral one of the flow distribution plate or the Both are moved in longitudinal rotation in surface to change the first row port and described the
The scale and discharge directions of two exhaust outlets.
Optionally, the lateral flow distribution plate connect with housing into rotation, and the actuator drives the transverse direction flow distribution plate to right
The shell is swung to change the size of the first row port and the second exhaust port.
Optionally, the lateral flow distribution plate includes the first lateral flow distribution plate and the second lateral flow distribution plate, and described first laterally
The adjacent end portion of flow distribution plate and the second lateral flow distribution plate is rotatablely connected to the shell, and the described first lateral flow distribution plate is another
One end extends to the enclosure interior and the cross section outer profile of the described first lateral flow distribution plate is gradually increased from inside to outside,
The other end of the second lateral flow distribution plate extends to the hull outside and the second transverse direction flow distribution plate from inside to outside
Cross section outer profile size is gradually reduced；
The actuator includes the first actuator and the second actuator, and the first actuator driving described first laterally divides
Flowing plate inner end relatively rotates end reciprocally swinging；The described second lateral flow distribution plate of second actuator driving outer end is opposite to be turned
Moved end reciprocally swinging.
Optionally, each power packages are provided only with the lateral deflector, and the transverse direction deflector longitudinally prolongs
Stretch the exhaust outlet of all ducted fans in power packages described in this；Alternatively, the exhaust outlet of each ducted fan is provided with
One lateral deflector, each lateral deflector are relatively independent.
Optionally, the lateral flow distribution plate is fixedly connected with the power packages, and the actuator drives the shell opposite
The transverse direction flow distribution plate is rotated to change the size of the first row port and the second exhaust port.
Optionally, the shell further includes main body and at least two tailgates, and the main body surrounds the cavity, each tail
Plate is rotationally connected with the exhaust position of the main body and surrounds the exhaust outlet, and the outer end of each tailgate can opposing inner end turn
With relatively close or separate, the transverse direction flow distribution plate is set in the space that the tailgate surrounds dynamic point.
Optionally, the power motor shape is the spindle with predetermined longitudinal length, the air inlet and the row
The non-coaxial setting of port, the power motor are provided with diversion division close to the end outer surface of the exhaust outlet, are used for fan
The air-flow of blade sucking is guided to the exhaust outlet.
Optionally, each power packages further include the shaft being axially arranged along the main wing or the front wing, same dynamic
All ducted fans in power group are fixed with the shaft, and shaft described in the motor driven rotates.
Optionally, ducted fan is both secured to the corresponding power packages in each power packages, and the power packages are and institute
Main wing and front wing rotation connection are stated, rotation axis is along the main wing and the front wing length extending direction, described in the motor driven
Power packages are axially rotated around main wing and the front wing.
Optionally, the aircraft, the outer profile substantially aerofoil profile of the vertical centre section of fuselage along its length.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of aircraft provided by the embodiment of the present invention；
Fig. 2 is structural schematic diagram when power packages are located at plumbness in Fig. 1；
Fig. 3 is structural schematic diagram when power packages are located at horizontality in Fig. 1；
Fig. 4 is the schematic diagram of another angle of Fig. 3；
Fig. 5 is structural schematic diagram when power packages when motor can drive wing to rotate are located at plumbness；
Fig. 6 is structural schematic diagram when power packages when motor can drive wing to rotate are located at horizontality；
Fig. 7 is the structural schematic diagram of another wing and power packages；
The structural schematic diagram of aircraft when Fig. 8 is deployment；
Fig. 9 is that aircraft is in low cruise state power packages internal structure side, sectional and shows in an embodiment of the present invention
It is intended to；
Figure 10 is that aircraft is in high speed cruise conditions power packages internal structure side, sectional in an embodiment of the present invention
Schematic diagram；
Figure 11 is that aircraft low cruise state thrust vectoring deflects down schematic diagram in an embodiment of the present invention；
Figure 12 is that power packages overlook partial schematic diagram in an embodiment of the present invention；
Figure 13 is a kind of power packages schematic rear view of the present invention；
Figure 14 is another power packages --- tail portion is without thrust vectoring mode external structure schematic diagram；
Figure 15 is power packages schematic diagram of internal structure in another embodiment of the present invention；
Figure 16 is the backsight structural representation of power packages shown in Figure 15；
Figure 17 is that ducted fan internal cross section air flow field shows when transverse direction splitter is in horizontal position when high speed is flat winged
It is intended to；
Figure 18 is that transverse direction splitter deflects down ducted fan internal cross section air flow field schematic diagram when high speed is flat winged；
In attached drawing 1-18, the reference numerals are as follows:
1- fuselage, 11- fore hold, 12- aft hold, the main cabin 13-；2- main wing；3- front wing；4- power packages, 41- duct wind
Fan, 411- power motor；42- rudder face group；421- tailgate；43- fan blade；44- diversion division；45- power packages rotary shaft；46-
First lateral splitter；The lateral splitter of 47- second；48- shaft；49- transverse direction splitter；4a- first row port；4b- second
Exhaust outlet；5- parachute；6- main battery system；7- secondary cell system.
Specific embodiment
It is with reference to the accompanying drawing and specific real in order to make those skilled in the art more fully understand technical solution of the present invention
Applying example, the present invention is described in further detail.
Fig. 1-8 is please referred to, Fig. 1 is the structural schematic diagram of aircraft provided by the embodiment of the present invention；Fig. 2 is moved in Fig. 1
Power group is located at structural schematic diagram when plumbness；Fig. 3 is structural schematic diagram when power packages are located at horizontality in Fig. 1；Fig. 4
It is the schematic diagram of another angle of Fig. 3；Fig. 5 is structure when power packages when motor can drive wing to rotate are located at plumbness
Schematic diagram；Fig. 6 is structural schematic diagram when power packages when motor can drive wing to rotate are located at horizontality；Fig. 7 is another
The structural schematic diagram of kind wing and power packages；The structural schematic diagram of aircraft when Fig. 8 is deployment.
The embodiment of the invention provides it is a kind of can VTOL aircraft, as shown in Figure 1, the aircraft include fuselage 1,
Wing and propulsion system, wherein wing includes that the front wing 3 of two two sides for being symmetrically set in fuselage 1 and two are symmetrically set in fuselage 1
Two sides main wing 2, front wing 3 is located at the front side of main wing 2；Propulsion system includes drive system and power packages 4, and each main wing 2 is with before
The wing 3 is respectively equipped with power packages 4, and each power packages 4 respectively include at least four ducted fans 41, drive system include battery system and
Motor compatible with each power packages 4, wherein battery system is used to power for each ducted fan 41 and motor, and each power packages 4 are
It can be under the drive of the motor around the axial rotation of main wing 2 or front wing 3.
That is, two sides of fuselage 1 are symmetrically arranged with two main wings 2 and two front wings 3, wherein each main wing 2 and it is each before
The wing 3 is mounted on power packages 4, and each power packages 4 are made of multiple ducted fans 41, wherein the power packages 4 of main wing 2 can be
It is rotated under the driving of motor around the axial direction (length direction) of main wing 2, the power packages 4 of front wing 3 can be under the drive of the motor around preceding
The axial direction (length direction) of the wing 3 rotates.
Power packages 4 can be four or four or more or other quantity, and preferably power packages 4 are at least 4 herein.
It is well known that ducted fan 41 is a kind of propulsion device, that is to say, that each power packages 4 includes four ducts
The propulsion device that fan 41 is formed.For those skilled in that art, ducted fan necessarily includes with air inlet and row
The shell of port, air inlet and exhaust outlet are connected to by the inner cavity of shell, and power motor and fan blade are additionally provided in inner cavity,
When power motor drives fan blade rotation, exhaust outlet can produce motive force.
Flying instrument provided by the present embodiment is there are three types of the stage, stage of taking off vertically, efficient cruising phase and vertical drop
Fall the stage, wherein the stage of taking off vertically refers to that when taking off, each power packages 4 turn to plumbness under the drive of the motor
(i.e. the rotary shaft and horizontal plane of ducted fan 41), at this time the thrust direction of all ducted fans in each power packages 4 with
Horizontal plane, i.e., straight up, as shown in Fig. 2, at this point, power packages 4 to provide thrust as aircraft close to full power state,
Aircraft vertical is set to take off；When aircraft flies to predetermined altitude, power packages 4 are gradually turned by upright position under the drive of the motor
To horizontality (i.e. the rotary shaft of ducted fan 41 is parallel to the horizontal plane), since ducted fan group produces in conversion process
Ramp up aircraft to the thrust component at aircraft rear, while main wing 2 and front wing 3 gradually generate lift instead of duct wind
The down thrust that fan group generates provides lift for aircraft, when the thrust of all ducted fans of conversion end, that is, each power packages 4
When direction is parallel to the horizontal plane, i.e., in the horizontal direction, it is flat winged that aircraft is transitioned into high speed to thrust direction；As shown in Figure 3 and Figure 4,
Aircraft completes the transition flown from taking off vertically put down, at this point, aircraft enters efficient cruising phase, main wing 2 and front wing 3 are moved
Power group 4 because only need to provide for aircraft forward thrust without for aircraft provides upward lift due to enter small-power cruise
State, the aircraft compared to can be effectively improved for Multi-axis aircraft its flying speed, reduce energy consumption and increase course continuation mileage.
The vertical landing stage refers to aircraft in landing, and aircraft gradually decreases flying speed, meanwhile, main wing 2 is with before
The power packages 4 of the wing 3 turn to plumbness by horizontality under the action of motor, and aircraft gradually slows down in the process,
The required lift of aircraft is gradually transitioned into power packages 4 by main wing 2 and front wing 3 in conversion process and provides simultaneously, and each dynamic
Power group is to approach full power state work to realize vertical landing.
Aircraft in the present invention has front wing, main wing, and the ducted fan being set on front wing and main wing；This frame
Structure design makes upper surface of the airfoil air velocity be greater than conventional airfoil, and wing lower surface is made to upward pressure more compared with conventional airfoil generation
Keep airfoil lift bigger greatly, and each ducted fan of power packages can also generate lift in flat fly；Therefore wing be located at
The power packages of wing upper rear constitute high coefficient of lift combined aerofoil system, can effectively reduce wing area, reduce wing structure weight
It measures and reduces air drag.
The aircraft provides the self gravity that lift need to be greater than the aircraft for it in the stage of taking off vertically, each power packages 4
Risen with realizing, and in efficient cruising phase and vertical landing stage, it is wanting for lift provided by aircraft for power packages 4
Ask relatively small, therefore, even in flight course, the case where individual ducted fans 41, which are damaged, etc. leads to failure,
It can guarantee that the aircraft security lands, or in extreme circumstances, each power packages 4 fail, which can also be by whole
Machine bales out, and security performance is good.
Each power packages 4 can turn around its axial direction for being mounted on corresponding main wing 2 or front wing 3 under the drive of the motor in the present invention
Dynamic, the exhaust outlet of ducted fan 41 can be in any angle between 0-90 degree with horizontal direction, make to be applied to carry-on
Thrust direction can change, to meet the smooth transition of aircraft flight control and three kinds of stages of aircraft, i.e., due to each power
The thrust size and angle of group 4 are controllable, and by the control of thrust size and angle to power packages 4, aircraft can be realized
Be transitioned into another state from state automatic smoothing, be conducive to flexibly control state of flight, and aircraft from
Body is stablized, highly-safe.Also, the longitudinal stability of the aircraft is poor by controlling the thrust of wing the right and left power packages 4
Different realization, aerial turn to is realized by differentiation thrust and the thrust direction variation of the power packages 4 of aircraft two sides, adopts
With no tail fin design, it can effectively mitigate the integrally-built weight of aircraft.The aircraft can as helicopter slow speed vertical
Movement realizes rotating in air by the thrust direction variation of ducted fan 41, realizes accurate pinpoint landing.
Two main wings 2 and two front wings 3 are respectively equipped with power packages 4, i.e., provide thrust by each power packages 4 for aircraft,
Each power packages 4 include at least four ducted fans 41, i.e. the quantity of ducted fan 41 is more, wherein each ducted fan 41 is
Multiple leaflet constructs (in the present embodiment, the blade of each ducted fan 41 is at least ten), so that the bearing capacity of the power packages 4 is strong,
The aircraft promoted relative to conventional piston engine driving propeller is more efficient, and power packages 4 are distributed in two main wings 2 and two
On rear side of the top of a front wing 3, i.e., power packages 4 are distributed in two main wings 2 and the tail end top of two front wings 3 constitutes high coefficient of lift combined
Aerofoil system can reduce gross wing area to reduce wing structure weight and air drag；The aircraft can be realized vertical rise
Drop without runway, expands the scope of application and use environment of the aircraft.Simultaneously as more ducted fans 41 and multiple-blade
Setting so that the vibration of the propulsion system is much smaller compared with conventional piston engine and propeller, and due to ducted fan
There are the cladding of duct, while the eddy current crack of fan blade tip will also substantially reduce, the safety of ground crew when 41 rotation
Will be high compared with traditional propeller aircraft, in addition, wing is also to 41 noise of ducted fan since ducted fan 41 is located on wing
There is screening effect, can effectively reduce noise of the aircraft in lifting process.
In addition, battery system can be fuel cell and be also possible to lithium battery in the present embodiment, specific limit is not done herein
System, at this point, aircraft be by cell system power to provide power needed for it, therefore in flight course without any pollutant arrange
It puts, environment protecting is good, in addition, the battery system is high energy density cells system, use cost can be reduced, due to not generating
Therefore security performance can be improved in the component of high temperature.
The fuselage 1 of the aircraft can be equipped with preceding freight house 11, aft hold 12 and main cabin 13, can be suitable for short distance passenger traffic, public affairs
The fields such as traffic (such as aerial taxi), disaster area rescue, emergency medical, Private Flight altogether.
In the above-described embodiments, each main wing 2 and front wing 3 respectively include at least one power packages 4.And in each power packages 4
Ducted fan is mutually redundant, i.e., 41 single-point of ducted fan or multipoint fault in any power packages 4 do not influence the safety of complete machine
Flight guarantees the stability and safety of aircraft operation.
In the above-described embodiments, each power packages 4 further include the shaft being axially arranged along main wing 2 or front wing 3, ducted fan
41 fix with shaft, and shaft can rotate under the drive of the motor.Certainly, in the present embodiment, can also by wing (including
Main wing 2 and front wing 3) be set as structure as shown in Figure 5 and Figure 6, i.e. wing can be rotated axially around it under the drive of the motor,
And the structure that above-mentioned setting shaft is rotated relative to wing can reduce motor for the organization plan of wing unitary rotation
Driving force, reduce burden requirement to motor, and influenced more by the crosswind being mutated in the air in the air in each state of flight transition
It is small, and the rotation of ducted fan 41 is more flexible.
In addition, each power packages 4 are respectively equipped with shaft when main wing 2 and front wing 3 are respectively equipped with more than one set power packages 4, side
Just being operated alone for each power packages 4 is realized.
In the above-described embodiments, the rear side of each power packages 4 is equipped with rudder face group 42, as shown in figure 4, motor drives power packages
When 4 rotation, rudder face group 42 is also rotated with it, to realize to the airflow direction of each ducted fan 41 and the accurate control of throughput.
Certainly, in the present embodiment, each power packages 4 can also be set as split type structure, as shown in fig. 7, and each separate structure it is equal
By a corresponding motor control rotation, to realize the control to airflow direction, and the scheme that rudder face 42 is arranged can
Simplify overall structure, the quantity for reducing motor, reduce flight resistance, is easy to implement control, good economy performance.
In the above-described embodiments, as shown in Figure 1, the top of fuselage 1 is additionally provided with parachute 5, which is set to fuselage 1
Top, under the extreme case of drive system complete failure, as shown in figure 8, parachute 5 can guarantee the aircraft security drop
It falls, and then improves the safety coefficient of the aircraft.
In the above-described embodiments, battery system includes main battery system 6 and secondary cell system 7, wherein main battery system 6
It is mutually redundant with secondary cell system 7, i.e., when in use, secondary cell system 7 can guarantee as spare main battery system 6
The whole cruising ability of the battery system is easy to implement long-distance flight while guaranteeing safe flight.
In the above-described embodiments, drive system further includes fuel oil power supply system, wherein fuel oil power supply system includes fuel oil hair
Motivation and generator, generator are used to power for each ducted fan 41 and the motor；That is, in the present embodiment,
The aircraft can be pure electric vehicle driving, i.e., drive system only includes the case where battery system, be also possible to hybrid power driving,
I.e. drive system includes the case where battery system and fuel oil power supply system.When being driven by hybrid power, drive system includes electricity
Cell system and fuel system can promote the cruising ability of drive system, be suitable for oceangoing voyage.It specifically can be according to service condition (such as fuselage
Interior memory space, distance to go etc.) it is configured.
In the above-described embodiments, the height of front wing 3 is less than the height of main wing 2, i.e. the aircraft is wing in low early and high after
Tandem wing layout aircraft, main wing can be made to avoid the influence of the bad downwash flow of front wing, avoided between front wing 3 and main wing 2
Reciprocation.
In the above-described embodiments, the aspect ratio of main wing 2 and front wing 3 is not less than 6, that is to say, that the aircraft uses exhibition
The bigger wing of string can reduce resistance of the aircraft in flight course, more energy efficient, so that the structural strength of aircraft is gentle
Efficiency of movement is higher.Certainly, in the present embodiment, the aspect ratio of wing might be less that 6, and the situation identical in power demand
Under, can have smaller air drag and bigger fuselage 1 using the biggish aircraft of aspect ratio, and then there is bigger visitor
The volume of cabin 13 or freight house (including preceding freight house 11 and aft hold 12).
In the above-described embodiments, the material of fuselage 1, main wing 2 and front wing 3 is carbon fibre composite, certainly, fuselage 1,
Main wing 2 and front wing 3 can also select glass fibre or other materials and multiple material to be used in mixed way, and multiple with carbon fiber
While can reduce the overall structure weight of the aircraft based on condensation material, payload is improved, i.e. electric energy utilization rate is high.
In the above-described embodiments, as shown in Figure 1, without relatively rotating between wing and fuselage 1, and wing and fuselage
Junction smooth transition between 1, improves the bonding strength between wing and fuselage 1, reduces the shadow of connection internal volume
It rings, while reducing the induced drag between wing and fuselage 1.
In addition, specific requirement is not done in the setting position of the components such as structure setting and battery system for fuselage 1, this
In embodiment, it is even variation that the shape of the fuselage 1 of the aircraft, which prolongs its axis direction, and the leading portion of fuselage 1 can be equipped with sky
Adjusting system and battery thermal management system, it is main battery system 6, machine that 1 middle section major part space of fuselage, which is load zones, 1 bottom of fuselage,
The aft hold 12 of 1 tail portion of body can be luggage compartment, lower part is secondary cell system 7, and entire fuselage 1 is that airflow design reduces flight
Resistance.
In a specific embodiment, ducted fan 41 includes the shell with air inlet and exhaust outlet, air inlet and
The air outlet is connected to by housing cavity, and housing cavity is provided with power motor 411, is provided with fan on power motor 411
Blade, inner cavity from fan blade rear portion circular cross-section be transitioned into two exhaust outlets before square-section, vent position is provided with
Exhaust outlet is divided into first row port 4a and second exhaust port 4b, by taking Figure 13 as an example, first row by lateral flow distribution plate, lateral flow distribution plate
Port 4a and second exhaust port 4b or more arrangement.
Aircraft further includes actuator, for driving one of lateral flow distribution plate or Both in longitudinal rotation in surface to change
Become the scale of first row port 4a and second exhaust port 4b.That is, actuator can drive lateral flow distribution plate to rotate,
To change the size of first row port 4a and second exhaust port 4b, actuator can be rotated with the relatively transverse flow distribution plate of drive shell,
To change size and the discharge directions of first row port 4a and second exhaust port 4b to be formed along vertical stabilizer surface up and down direction
Two-dimensional vector propulsion system, that is, thrust direction can dynamically be adjusted up and down in exhaust outlet.
In above-described embodiment, exhaust outlet is divided by first row port 4a and the second air outlet 4b by lateral flow distribution plate, and
And the external surface shape by the way that beam wind flowing plate is arranged may be implemented to change first row port 4a and second exhaust port 4b exhaust stream
Amount and discharge directions, control of the ducted fan available in this way to the different thrust angles along vertical stabilizer up and down direction, with
Meets the needs of aircraft flight control.
In one embodiment, lateral flow distribution plate is connect with housing into rotation, and actuator drives lateral flow distribution plate to shell
It swings to change the size of first row port 4a and second exhaust port 4b and then control thrust direction.
Specifically, lateral flow distribution plate may include the first lateral flow distribution plate 46 and the second lateral flow distribution plate 47, and first laterally
The adjacent end portion of flow distribution plate 46 and the second lateral flow distribution plate 47 is rotatablely connected shell, and Fig. 9 to Figure 11 shows two flow distribution plates
Shaft 48, shaft 48 are longitudinally arranged.First lateral 46 the other end of flow distribution plate extends and from inside to outside the to enclosure interior
The longitudinal cross-section outer profile of one lateral flow distribution plate 46 is gradually increased, and the cross section outer profile of the first beam wind flowing plate 46 can be spinning
Capitate structure.The other end of second lateral flow distribution plate 47 extends to hull outside and the second lateral flow distribution plate 47 from inside to outside
Cross section outer profile size is gradually reduced.The outer profile of the cross section of second lateral flow distribution plate 47 can be triangle.It needs
Bright, cross section refers to the section perpendicular to wing width direction herein.
In above-described embodiment, actuator also further comprises the first actuator and the second actuator, the driving of the first actuator
First lateral flow distribution plate inner end relatively rotates end reciprocally swinging；The second lateral flow distribution plate of second actuator driving outer end is opposite
Turning end reciprocally swinging.
First actuator and the second actuator can be hydraulic-driven, or power drive system.Drive is not shown herein
The structure of moving part has no effect on understanding and implementation of the those skilled in that art for technical solution.
The rear side of each power packages 4 is provided with the lateral flow distribution plate 46 of can act respectively first and the second lateral flow distribution plate 47,
Specifically the rotational angle range of the first lateral flow distribution plate 46 can be 15 degree of swings positive and negative on the basis of level, and second laterally shunts
The rotational angle of plate 47 can be 30 degree of swings positive and negative on the basis of level, and the such first lateral flow distribution plate 46 and second laterally divides
Both flowing plates 47 rotate positive and negative 30 degree of variations to realize power packages thrust direction in proportion in the same direction.
In above-described embodiment, the lateral flow distribution plate 46 of the first actuator driving first is rotated, and the second actuator driving second is horizontal
It is rotated to flow distribution plate, the first lateral flow distribution plate 46 and the second lateral flow distribution plate 47 rotate relatively independent, the such first laterally shunting
Both the both side surface up and down of plate 46, the surface of survey up and down of the second lateral flow distribution plate 47 are collectively formed first with respective housings inner wall
Exhaust outlet 4a and second exhaust port 4b can be such that ducted fan internal gas flow more smoothly flows and form low disturb at wing rear portion
Dynamic air flow field reduces the interference of front wing and main wing air flow field and reduces air drag.
Each power packages are provided only with a lateral deflector, and lateral deflector is longitudinally extended across the institute in the power packages
There is the exhaust outlet of ducted fan.That is, a lateral deflector, which is only arranged, realizes all duct wind in the same power packages
Fan exhaust outlet is divided into first row port and second exhaust port is uniformly controlled the thrust direction of entire power packages, and structure is simple, and
And it is easy to simplified control system.
Figure 15 and Figure 16 are please referred to, in another embodiment specific implementation mode, lateral flow distribution plate 49 and main wing 2 or front wing 3 are solid
Fixed connection, the relatively transverse flow distribution plate of actuator drive shell are rotated to change the size of first row port 4a and second exhaust port 4b
And discharge directions.
As shown in figure 11, the flow area of the exhaust outlet for controlling outlet air flow amount of the rear side of each power packages 4
It is variable, and then can change power packages muzzle velocity and thrust size, specific setting is as follows.
In the respective embodiments described above, shell further includes main body and at least two tailgates 421, and main body surrounds cavity, each tailgate
421 are rotationally connected with the outlet air position of main body and surround exhaust outlet, the outer end of each tailgate 421 can opposing inner end rotation point with phase
To close to or far from lateral flow distribution plate is set to the space that tailgate 421 surrounds.
Given in Figure 10 and Figure 11 main body exhaust position be arranged up and down two tailgates specific embodiment, upper and lower two
The inner end of tailgate is articulated with main body, the opposite expansion in the outer end of upper and lower two tailgate 421 and the close size to change exhaust outlet.
Upper and lower two tailgate 421 can open and close angle by equal proportion opposite direction separately as one group and control power packages air stream outlet sectional area
To change the exhaust velocity of power packages 4 to change thrust size.Wherein tailgate, the first lateral flow distribution plate 46, second laterally shunt
Plate 47 acts relatively independent.
Ducted fan inner duct cavity is that circle turns square structure, facilitates the lateral flow distribution plate 46, second of setting first horizontal
To flow distribution plate 47.
The exhaust outlet of power packages is improved to variable cross section to change exhaust velocity and then change thrust size and be arranged the
One lateral flow distribution plate 46 and the second lateral flow distribution plate 47 enable aircraft to change discharge directions and then change thrust direction in this way
It is enough that 4 air exit section of power packages is changed via winged control according to the variation and gesture stability demand of flying height and flying speed
Thrust size and thrust direction needed for long-pending and discharge directions facilitate adjustment aircraft, reduce the quantity of control rotary power group motor,
Simplified control mechanism.
Further, air inlet and the non-coaxial setting of exhaust outlet in the respective embodiments described above, 411 shape of power motor are tool
There is the spindle of predetermined longitudinal length, power motor is provided with diversion division close to the end outer surface of exhaust outlet, is used for fan
The air-flow of blade sucking is guided to exhaust outlet.
In the respective embodiments described above, each power packages 4 can also include the power packages rotation being axially arranged along main wing 2 or the wing 3
Shaft 45, all ducted fans 41 in same power packages are fixed with power packages rotary shaft 45, and motor driven power packages are revolved
Shaft 45 rotates.
In another embodiment, ducted fan is both secured to corresponding main wing 2 or the front wing 3 in each power packages, main wing and
Front wing is rotatablely connected with body, and rotation axis is along main wing and front wing length extending direction, and motor driven main wing and front wing are around axial direction
Rotation.
To sum up compared with conventional aircraft, each power packages 4 in the present invention are two-dimensional vector propulsion systems, are flown below by flat
(shown in Fig. 3) and two stages of VTOL (shown in Fig. 2) tell about the flight control of aircraft.In the flat winged stage: on aircraft
All power packages 4 have gone to 0 degree of position of level (frame head and tail axis direction) around respective rotary shaft 45；Positioned at two, aircraft
The vectored thrust of the power packages 4 of front wing 3 is equivalent to the front wing elevator function of traditional aircraft, i.e., two power packages when flat winged
Aircraft comes back when 4 vectored thrusts deflect down simultaneously, upward deflects, aircraft is bowed；On each main wing 2 of aircraft
The thrust vectoring of two power packages 4 is equivalent to the high speed aileron (close to that group of inboard) and low speed aileron of traditional wing
(close to that group of the wing slightly), by taking low cruise as an example, 4 vectored thrust of power packages of the control right flank wing slightly side is deflected down, and is flown
Device prolongs along the rolling counterclockwise of frame head and tail axis, and 4 vectored thrust of power packages for controlling the right flank wing slightly side upward deflects then aircraft
Prolong along frame head and tail axis both clockwise rolling, can also reversely link realization according to demand and left side flap slightly power packages thrust vectoring
Same manipulation rolling；Aircraft or so yaw is realized by the total thrust difference of main wing power packages 4 before change of flight device two sides, i.e.,
All 4 gross thrusts of power packages are greater than all 4 gross thrust aircrafts of power packages in right side and yaw to the right on the left of fuselage, otherwise to left drift,
Aircraft is completed with 4 thrust vectoring of the power packages cooperation on main wing 2 to turn in the air.In the VTOL stage: owning on aircraft
Power packages 4 have gone to vertical 90 degree of positions around respective rotary shaft 45；The translation flight control of this stage is similar to Multi-axis aircraft,
Aircraft is realized along the left and right translation control of frame head and tail axis by the whole thrust differential at left and right sides of aircraft, that is, is reduced
On the left of aircraft thrust (reducing the thrust of the left front wing and all power packages 4 of left main wing) increase simultaneously on the right side of thrust (increase
The thrust of right front wing 3 and all power packages of right main wing 2) aircraft entirety down thrust is remained unchanged, aircraft is flat to the left
It moves；Reverse operating aircraft is to right translation.Aircraft passes through 3 He of aircraft front wing along the anterior-posterior translation control of frame head and tail axis
The whole thrust differential of 2 power packages of main wing 4 realizes that is, thrust (reduces all power packages 4 of left and right front wing on front side of reduction aircraft
Thrust), while increasing back pressure (i.e. increase all power packages 4 of left and right main wing) remains unchanged aircraft entirety down thrust,
Aircraft is translate forward；Reverse operating aircraft translates backward.Aircraft along frame head and tail axis to before left front, right, it is left back, right
After translate according to same control logic realize；Aerial rotate to the left along itself axis (direction perpendicular to the ground) of aircraft passes through control
Making two 2 wings of main wing slightly 4 deboost vector of side power packages, (and 4 thrust vectoring of left side power group is deflected on front side of aircraft, right side
Power packages 4 are deflected to airplane tail group, while it is constant to increase the two 4 thrusts of power packages whole thrust that keeps down) Lai Shixian, instead
Aircraft rotate to the right.By being precisely controlled to the rotation of power packages 4 and thrust vectoring direction, aircraft can be realized from one
A state automatic smoothing it is transitioned into another state, and entire flight control process is in any mission phase completely reversibility,
Be conducive to flexibly control state of flight, and the homeostasis of aircraft, it is highly-safe.Also, the aircraft is used without vertical
Straight tail design can effectively mitigate the integrally-built weight of aircraft that is, without erecting the tail of coming.The aircraft can be as straight
The same slow speed vertical movement of the machine of liter, realizes rotating in air, translation by each 4 thrust differential of power packages and thrust direction variation
Realize accurate pinpoint landing.
In the various embodiments described above, the fuselage of entire aircraft can be lifting body, from fuselage section in terms of the direction of wing two sides
It is the shape close to aerofoil profile, i.e. the outer profile substantially aerofoil profile of the vertical centre section of fuselage along its length can reduce wing
Total face reduces Flight Vehicle Structure weight.
The above is only the preferred embodiment of the present invention, it is noted that those skilled in the art are come
It says, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications also should be regarded as
Protection scope of the present invention.
Claims (13)
1. one kind can VTOL aircraft, which is characterized in that including fuselage (1), wing and propulsion system；
The wing includes that the front wing (3) of two two sides for being symmetrically set in the fuselage (1) and two are symmetrically set in the fuselage
(1) main wing (2) of two sides, the front wing (3) are located at the front side of the main wing (2)；
The propulsion system includes drive system and power packages (4), and each main wing (2) and the front wing (3) are equipped with described
Power packages (4), each power packages (4) respectively include four ducted fans (41), the drive system include battery system and
The compatible motor with each power packages (4), the battery system are used to be each ducted fan (41) and the motor
Power supply, each power packages (4) can be under the driving of the motor around the axial direction of the main wing (2) or the front wing (3)
Rotation.
2. aircraft according to claim 1, which is characterized in that each main wing (2) and the front wing (3) respectively include
At least one described power packages (4).
3. aircraft according to claim 1 or 2, which is characterized in that each power packages (4) further include along the main wing
(2) or the shaft of the front wing (3) being axially arranged, the ducted fan (41) is fixed with the shaft, and the shaft energy
Enough being rotated by the motor；
Alternatively, being equipped with rudder face (42) on rear side of each power packages (4)；
Alternatively, being additionally provided with parachute (5) at the top of the fuselage (1)；
Alternatively, the battery system includes main battery system (6) and secondary cell system (7)；
Alternatively, the drive system further includes fuel oil power supply system, the fuel oil power supply system includes fuel engines and power generation
Machine, the generator are used to power for each ducted fan (41) and the motor；
Alternatively, the height of the front wing (3) is less than the height of the main wing (2)；
Alternatively, the aspect ratio of the main wing (2) and the front wing (3) is not less than 6；
Alternatively, the junction between the wing and the fuselage (1) seamlessly transits；
Alternatively, the material of the fuselage (1), the main wing (2) and the front wing (3) is carbon fibre composite.
4. aircraft according to claim 1, which is characterized in that the ducted fan (41) includes having air inlet and row
The shell of port, the air inlet and the exhaust outlet are connected to by the housing cavity, are provided in the middle part of the housing cavity
Power motor is provided with fan blade on the power motor, and the vent position is provided with lateral flow distribution plate, the transverse direction
The exhaust outlet is divided into first row port (4a) and second exhaust port (4b) by flow distribution plate, further includes actuator, for driving
One of lateral flow distribution plate or the Both are stated in longitudinal rotation in surface to change the first row port (4a) and described
The scale and discharge directions of two exhaust outlets (4b).
5. aircraft according to claim 4, which is characterized in that the transverse direction flow distribution plate is connect with housing into rotation, described
The actuator driving lateral relatively described shell of flow distribution plate is swung up and down to change the first row port (4a) and described the
The size and discharge directions of two exhaust outlets (4b).
6. aircraft according to claim 5, which is characterized in that the transverse direction flow distribution plate includes the first lateral flow distribution plate
(46) and the second lateral flow distribution plate (47), the described first lateral flow distribution plate (46) and the second transverse direction flow distribution plate (47) is adjacent
End is rotationally connected with the shell, described first lateral flow distribution plate (46) the other end extend to the enclosure interior and
The cross section outer profile of the described first lateral flow distribution plate (46) is gradually increased from inside to outside, the described second lateral flow distribution plate (47)
The other end extends to the hull outside and the cross section outer profile size of the described second lateral flow distribution plate (47) from inside to outside
It is gradually reduced；
The actuator includes the first actuator and the second actuator, the lateral flow distribution plate of the first actuator driving described first
(46) inner end relatively rotates end reciprocally swinging；Described described second lateral flow distribution plate (47) outer end of second actuator driving phase
To turning end reciprocally swinging.
7. aircraft according to claim 6, which is characterized in that each power packages (4) are provided only with described in one
Lateral deflector, the transverse direction deflector are longitudinally extended across the exhaust outlet of all ducted fans in the power packages；Or
Person, the exhaust outlet of each ducted fan are provided with the lateral deflector, and each lateral deflector is relatively independent.
8. aircraft according to claim 4, which is characterized in that the transverse direction flow distribution plate and the main wing (2) or described
Front wing (3) is fixedly connected, and the actuator drives the shell relative to the lateral flow distribution plate rotation to change the first row
The size of port and the second exhaust port.
9. aircraft according to claim 4, which is characterized in that the shell further includes main body and at least two tailgates
(421), the main body surrounds the cavity, and each tailgate (421) is rotationally connected with the exhaust position of the main body and surrounds
The exhaust outlet, the outer end of each tailgate can the rotation of opposing inner end rotation axis with relatively close or separate, the transverse direction point
Flowing plate is set in the space that the tailgate (421) surrounds.
10. aircraft according to claim 9, which is characterized in that the power motor (411) is with predetermined longitudinal long
The spindle of degree, the air inlet and the non-coaxial setting of the exhaust outlet, the power motor is close to the end of the exhaust outlet
Outer surface is provided with diversion division, and the air-flow for sucking fan blade is guided to the exhaust outlet.
11. according to the described in any item aircraft of claim 4 to 10, which is characterized in that each power packages (4) further include edge
The power packages rotary shaft (45) of the main wing (2) or the front wing (3) being axially arranged, all culverts in same power packages
Road fan (41) is fixed with the power packages rotary shaft (45), and power packages rotary shaft (45) described in the motor driven turns
It is dynamic.
12. according to the described in any item aircraft of claim 4 to 10, which is characterized in that ducted fan in each power packages
It is both secured to the corresponding main wing (2) or the front wing (3), the main wing and the front wing are rotatablely connected with body, rotation
Axis is along the main wing and the front wing length extending direction, and main wing described in the motor driven and the front wing are around axial rotation.
13. aircraft according to claim 1, which is characterized in that the fuselage of entire aircraft is lifting body, and fuselage is along long
Spend the outer profile substantially aerofoil profile of the vertical centre section in direction.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2018108359400 | 2018-07-26 | ||
| CN201810835940.0A CN108688803A (en) | 2018-07-26 | 2018-07-26 | It is a kind of can VTOL aircraft |
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| Publication Number | Publication Date |
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| CN110254706A true CN110254706A (en) | 2019-09-20 |
| CN110254706B CN110254706B (en) | 2024-05-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810835940.0A Pending CN108688803A (en) | 2018-07-26 | 2018-07-26 | It is a kind of can VTOL aircraft |
| CN201910655990.5A Active CN110254706B (en) | 2018-07-26 | 2019-07-19 | Aircraft capable of taking off and landing vertically |
| CN201921147796.8U Active CN211033016U (en) | 2018-07-26 | 2019-07-19 | Aircraft capable of vertically taking off and landing |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810835940.0A Pending CN108688803A (en) | 2018-07-26 | 2018-07-26 | It is a kind of can VTOL aircraft |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921147796.8U Active CN211033016U (en) | 2018-07-26 | 2019-07-19 | Aircraft capable of vertically taking off and landing |
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| CN114771827A (en) * | 2022-05-27 | 2022-07-22 | 云翼航空科技(深圳)有限公司 | Aircraft capable of taking off and landing vertically and control method thereof |
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| EP3998200B1 (en) * | 2021-02-19 | 2024-04-24 | Lilium eAircraft GmbH | Fault tolerant aircraft flight control system |
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| EP4294719A1 (en) * | 2021-02-19 | 2023-12-27 | Lilium GmbH | Wing assembly for an aircraft |
| EP3998202B1 (en) * | 2021-02-19 | 2024-03-06 | Lilium eAircraft GmbH | Aircraft, comprising a battery assembly |
| EP3998195A1 (en) * | 2021-02-19 | 2022-05-18 | Lilium eAircraft GmbH | Aircraft flap-to-flap seal |
| EP3998197A1 (en) * | 2021-03-05 | 2022-05-18 | Lilium eAircraft GmbH | Engine comprising a movable aerodynamic component |
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| EP3998687B1 (en) * | 2021-05-19 | 2024-05-15 | Lilium eAircraft GmbH | Electrical fault isolation in a power distribution network of an aircraft |
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| CN102180258A (en) * | 2011-04-07 | 2011-09-14 | 龙川 | Duct aerofoil system and aerial craft applying duct aerofoil system |
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| CN105292444A (en) * | 2014-07-08 | 2016-02-03 | 吴建伟 | Vertical take-off and landing aircraft |
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| CN207417149U (en) * | 2017-09-29 | 2018-05-29 | 清华大学 | A kind of double lift culvert vertical take-off and landing aircrafts based on tilting duct |
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| CN112722263A (en) * | 2021-01-19 | 2021-04-30 | 西北工业大学 | Vertical/short-distance take-off and landing aircraft with distributed power coupling lift-increasing wing surfaces |
| US20220266979A1 (en) * | 2021-02-19 | 2022-08-25 | Lilium Eaircraft Gmbh | Wing assembly for an aircraft |
| CN113086184A (en) * | 2021-04-23 | 2021-07-09 | 北京航空航天大学 | Tandem distributed electric propulsion coaxial duct vertical take-off and landing aircraft |
| CN114771827A (en) * | 2022-05-27 | 2022-07-22 | 云翼航空科技(深圳)有限公司 | Aircraft capable of taking off and landing vertically and control method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN211033016U (en) | 2020-07-17 |
| CN110254706B (en) | 2024-05-31 |
| CN108688803A (en) | 2018-10-23 |
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