CN108045575A - A kind of short takeoff vertical landing aircraft - Google Patents
A kind of short takeoff vertical landing aircraft Download PDFInfo
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- CN108045575A CN108045575A CN201711364349.3A CN201711364349A CN108045575A CN 108045575 A CN108045575 A CN 108045575A CN 201711364349 A CN201711364349 A CN 201711364349A CN 108045575 A CN108045575 A CN 108045575A
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- 238000010276 construction Methods 0.000 claims abstract description 37
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- 230000006870 function Effects 0.000 description 6
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Classifications
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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
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
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- 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
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/12—Canard-type aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
Abstract
A kind of short takeoff vertical landing aircraft, including fuselage, sustainer, vertical fin and the main wing, upper limb, the end wing and the canard that are separately positioned on fuselage both sides；It is held at two on the outside of the wing and is both provided with extension wing, aileron is both provided on two extension wings, elevator is both provided on two upper limbs；The afterbody of two end wings is both provided with rudder；To support construction is stretched out before being respectively equipped in the lower part of two end wings, a sustainer, sustainer propeller and propeller inclination angle driving device are set in stretching support construction in each of front；In the lower part of each end wing, deployable and collapsible main landing gear is set；It is set at vertical fin rear portion and stretches out support construction backward, stretched out backward in support construction posture adjustment engine prop is installed at this.Aircraft of the present invention not only has short takeoff, vertical landing performance, while has taken into account the flying qualitys such as high speed, long endurance, big voyage.
Description
Technical field
The invention belongs to field of flight vehicle design, and in particular to a kind of connection wing canard with excellent aeroperformance is pneumatic
Layout, can realize short takeoff, the aircraft of vertical landing.
Background technology
Aircraft has the characteristics that speed is fast, mobility is high, from the barrier of high mountain, river, desert, ocean, without as vapour
The highway or railway of vehicle and train build expensive necessary like that.But aircraft also has the limitation of itself, is particularly landing site
It is restricted, aircraft, especially large-scale fixed wing aircraft, it is necessary to dependent on airfield runway landing, the construction scale of airfield runway is big,
More than generally up to 2 kms, and occupied space is big, in the tens of kilometer ranges of airfield runway, is not allow for high-rise
Or non-aviation management airflight object, so the at most several airports in a city, and airport is distributed in outer suburbs more.
Current aircraft is only applicable to light-weight, and time requirement is urgent, the transport that voyage again cannot be too near.However, at a high speed
The development of railway or even serious challenge also is had issued to this function of aircraft.So from the point of view of the long term growth of aircraft,
Need the key issue solved is to mitigate how aircraft, even break away from degree of dependence for airfield runway.
Be coupled wing canard configuration aircraft, pneumatic/structure-integrated designing technique of integrated use, have useful lift it is big,
Full machine cruise lift resistance ratio is high, body weight is light, agent structure is strong, payload space is big in machine, airborne period is long, low latitude/low
The features such as fast performance is good, takeoff and landing performance is excellent.
Normal arrangement aircraft relies primarily on wing and generates lift needed for the flight of full machine, wing while lift is generated,
It can also add and generate certain bending and torsional moment, it is necessary to be carried using stronger, heavier wing structure, it is therefore desirable to pay
Larger construction weight.And use and be coupled wing canard configuration, it is coupled the wing in itself, is both the lifting surface and lifting surface of aircraft
Moment of flexure caused by wing and torque can be converted into the tension and compression stress for the end wing and vertical fin, greatly optimize machine by load frame
The wing is extended to be distributed to load, so as to significantly reduce the construction weight of wing and whole machine weight.
Normal arrangement aircraft realizes longitudinal trimming control of full machine using wing and empennage cooperation, therefore different
Under the conditions of center of gravity, to reach the trim of full machine longitudinal direction, it is necessary to pay certain loss of lift.And it uses and is coupled the flight of wing canard configuration
Device participates in longitudinal trimming control using three groups of lifting surfaces, is advantageous to reduce longitudinal trim loss of lift, it might even be possible to real
Existing forward direction trimming control function.
Normal arrangement aircraft, using vertical tail as main course stabilization, rudder is located on vertical fin, improves boat
The vertical fin and rudder of bigger are just needed to stability and maneuverability, causes vertical fin weight big, complicated.And it uses and is coupled the wing
Canard configuration aircraft, can comprehensively utilize the end wing and the rudder on the wing of end realizes aircraft course control and stability control
System.
The aileron of normal arrangement aircraft is arranged on main wing, nearer apart from fuselage, must to improve roll guidance efficiency
Larger aileron rudder face must be used.And use be coupled wing canard configuration aircraft, using sweepforward extension wing install aileron, can compared with
Under the conditions of small aileron control area, realize that the efficient roll of full machine manipulates.
The aircraft of normal arrangement, rely primarily on the lifting surfaces such as wing, empennage generate flight needed for lift, only flying
When speed reaches larger, it could generate and be enough the lift for supporting aircraft weight, as a result, necessarily causing rising, dropping sliding run for aircraft
Distance is longer.Using the aircraft of this layout, can be verted control technology using engine, vert to generate by power certain
Lift is equivalent to the landing weight for alleviating aircraft, can substantially reduce depart speed or the touchdown speed of aircraft,
Greatly shorten the landing ground roll-out distance of aircraft.
During landing, longitudinally controlled torque is generated mainly by the pneumatic efficiency of rudder face for the aircraft of normal arrangement.And use this
The aircraft of layout, can but be verted using engine and control technology, the control moments such as generation pitching, roll particularly exist
The takeoff and landing stage is verted and is controlled using the power of engine, can generate big nose-up pitching moment so that aircraft is playing reduction
Under the conditions of speed, it can also reach the larger controllable angle of attack, the lift for being advantageous to aircraft in takeoff phase is liftoff；Or
Aircraft creates item in landing period, realization High Angle of Attack (closing on stalling angle), small speed (even vertically downward) touchdown
Part.
Good aircraft is paid with minimum energy, and maximum possible is efficiently securely and reliably flown using air force
And it is good at " art work ".If the engine prop installed before the wing of end has enough pulling force, it is sufficient to " pull out in nonirrigated farmland aircraft
Green onion " formula is departed, then aircraft can be made to have very outstanding VTOL ability, and such aircraft can even complete class
The various flights of helicopter are similar to, but will certainly be caused in long-time cruising flight phase, thus power bulk redundancy must
The bulk redundancy of structural strength and aircraft weight can be so brought, therefore the aircraft of short takeoff/vertical landing is perhaps optimal
Selection.
The content of the invention
The purpose of the present invention is in view of the shortcomings of the prior art and defect, provide a kind of short takeoff vertical landing and fly
Row device makes it that can not only realize short takeoff, can on the runway of relatively short distance, even without smoothly complete in special runway
Into taking off, aircraft can also be allowed to complete safe landing on arbitrary smooth under no runway conditions, while take into account high speed, length
The flying qualitys such as endurance, big voyage.
In order to achieve the above objectives, technical scheme is as follows：
A kind of short takeoff vertical landing aircraft including fuselage, sustainer, vertical fin and is separately positioned on fuselage two
Main wing, upper limb, the end wing and the canard of side；The top of two end wings is connected respectively by being arranged on the upper limb of body upper with vertical fin
It connects；The extension wing for being both provided on the outside of the wing and being connected with upper limb is held at two；Elevator, feature are both provided on two upper limbs
It is：The lower part of the wings is held to be equipped with preceding to support construction is stretched out at two, in each of front a master is set to stretching out in support construction
Engine, sustainer propeller and propeller inclination angle driving device, and deployable and collapsible master is set in the lower part of each end wing
Undercarriage；The vertical fin rear portion set stretch out support construction backward, this stretch out backward in support construction be equipped with posture adjustment hair
Motivation propeller.Preferably, in above-mentioned technical proposal, aileron is both provided on described two extension wings；Described two end wings
Afterbody is both provided with rudder.
Preferably, the main wing, canard, upper limb and extension wing use buzzard-type wing, swept-back wing or the straight wing.
Preferably, the main wing uses swept-back wing, and upper limb uses buzzard-type wing.The main wing slightly upper counterangle；The upper limb
Slightly inverted diherdral.
Preferably, propeller inclination angle driving device uses ball screw drive mechanism.
Preferably, the end wing and extension wing are using conventional aerofoil profile, laminar flow airfoil, high-lift airfoil or super critical aerofoil
Type.The leading edge of the end wing carries angle of sweep, and the trailing edge of the wing is held to carry sweepforward angle.
Preferably, the blade of the sustainer propeller and posture adjustment engine prop is two leaf paddles, three leaf paddles, four leaves
Paddle, five leaf paddles or six leaf paddles.
Compared with prior art, the present invention haing the following advantages and the technique effect of high-lighting：
The present invention can realize short takeoff, can on the runway of relatively short distance, even without smooth in special runway
Completion is taken off；It can realize vertical landing, allow aircraft that can complete safe landing on arbitrary smooth under no runway conditions.
Aircraft of the present invention not only has short takeoff/vertical landing performance, while has taken into account high speed, the flight of long endurance, big voyage
Performance has the characteristic of larger mission payload.It is in particular in following several respects：
1. using connection wing canard (i.e.：The synthesis shape of main wing+upper limb+canard) distribution form, it is coupled the wing in itself, is both
The lifting surface of aircraft, and be the load frame of lifting surface, moment of flexure caused by wing and torque can be converted into for the end wing and
The tension and compression stress of vertical fin, greatly optimizes wing and extends and be distributed to load, so as to significantly reduce the construction weight of wing and complete
Machine weight.
2. using wing canard configuration aircraft is coupled, longitudinal trimming control is participated in using three groups of lifting surfaces, it is highly beneficial
In the loss of lift for reducing longitudinal trim, it might even be possible to realize positive trimming control function.3. the present invention can comprehensively utilize the end wing
The control of aircraft course control and stability is realized with the rudder on the wing of end.4. using the present invention, master can be utilized to start
Machine propeller inclination angle driving device is verted to generate certain lift by power, is equivalent to the landing weight for alleviating aircraft,
Depart speed or the touchdown speed of aircraft can be substantially reduced, greatly shortens the landing ground roll-out distance of aircraft.
5. the present invention can utilize sustainer propeller inclination angle driving device to generate the control moments such as pitching, roll, particularly flying
The machine landing stage using sustainer propeller inclination angle driving device, can generate big nose-up pitching moment so that aircraft is in landing
Under low-speed conditions, it can also reach the larger controllable angle of attack, the lift for being advantageous to aircraft in takeoff phase is liftoff；It can also
Be aircraft in landing period, realize that High Angle of Attack (closing on stalling angle), small speed (even vertically downward) touchdown are created
Condition.
Description of the drawings
Fig. 1 for a kind of external structure schematic diagram of short takeoff vertical landing aircraft provided by the invention, (put by undercarriage
Under, engine prop vertically upward).
Fig. 2 be a kind of short takeoff vertical landing aircraft provided by the invention gear down, engine prop
Vert 45 ° of oblique top views upwards.
Fig. 3 is a kind of gear up, the engine prop of short takeoff vertical landing aircraft provided by the invention
Vertically tilt forward oblique top view.
Fig. 4 be a kind of short takeoff vertical landing aircraft provided by the invention gear down, engine prop
Vert side view vertically upward.
Fig. 5 is a kind of gear up, the engine prop of short takeoff vertical landing aircraft provided by the invention
Vert 45 ° of side views upwards.
Fig. 6 is a kind of gear up, the engine prop of short takeoff vertical landing aircraft provided by the invention
Vertically tilt forward side view.
In figure, 1- fuselages；2- canards；3- main wings；4- upper limbs；5- extension wings；The 6- ends wing；7- elevators；8- ailerons；9- side
To rudder；10- vertical fins；11- propellers inclination angle driving device；12- sustainer propellers；To stretching support construction after 13-；14-
Posture adjustment engine prop；15- deployable and collapsible main landing gears；16- deployable and collapsible nose-gears；To stretching support construction before 17-.
Specific embodiment
The present invention is described in detail with reference to the accompanying drawings and detailed description.
As shown in Figure 1, a kind of short takeoff vertical landing aircraft provided by the invention includes：Fuselage 1, actively starts
Machine, the canard 2 for being arranged on 1 front end both sides of fuselage are separately positioned on main wing 3, upper limb 4, the end wing 6 and the setting of 1 both sides of fuselage
In the vertical fin 10 of 1 upper rear of fuselage；The end wing 6 is arranged on the end of the main wing 3 of fuselage both sides, the top of two end wings 6
It is connected with being arranged on the vertical fin 10 of 1 afterbody of fuselage by being arranged on the upper limb 4 of 1 top of fuselage, is all provided on two upper limbs 4 respectively
It is equipped with elevator 7；The outside of described two end wings 6 is provided with the extension wing 5 being connected with upper limb, is respectively provided on two extension wings 5
There is aileron 8；The afterbody of described two end wings 6 is both provided with rudder 9.Support knot is stretched out before at two 6 lower part of the wing being held to be provided with
Structure 17, in each of front to one sustainer of setting and propeller inclination angle driving device 11 in support construction 17 is stretched out, in master
Sustainer propeller 12 is installed on engine；The forward direction, which is stretched out in support construction 17, is equipped with the driving of ball-screw inclination angle
The angle of sustainer propeller 12 can be adjusted in device 11.
At two 6 lower part of the wing is held to be mounted on deployable and collapsible main landing gear 15, the medium position installation under fuselage can receive
Put formula nose-gear 16；The rear upper of the vertical fin 10 stretches out support construction 13 after being provided with, in the stretching support construction 13
Top the blade of posture adjustment engine prop 14, the sustainer propeller 12 and posture adjustment engine prop 14 is installed
For two leaf paddles, three leaf paddles, four leaf paddles, five leaf paddles or six leaf paddles.
The main wing 3, canard 2, upper limb 4 and extension wing 5 are using buzzard-type wing, swept-back wing or the straight wing.3 sweepback of main wing, on
4 sweepforward of the wing forms wing configurations form one in front and one in back, and pneumatic efficiency is high, can give full play to the lift-rising effect of two groups of aerofoils.Prolong
The useful lift area that the wing 5 adds full machine is stretched, greatly improves the useful lift of aircraft.Sustainer is under the wing of end
In the preceding stretching support construction 17 in portion, in preceding stretching support construction 17, engine prop is realized using ball-screw
It verts control.When sustainer propeller 12 verts upwards, when working in lift conditions, on its purling direction, Ji Huwei
There is any lift-rising pneumatic efficiency for blocking, rotor being given full play to, effective powered lift provided in the landing stage for full machine,
Without because purling blocks powered lift being caused to lose.When sustainer propeller 12 vertically upward, lift-rising maximum shape
During state, since propeller is sufficiently close together ground, there is the ground effect hovering class similar to helicopter, spiral shell can be greatly enhanced
Lift-rising efficiency of the paddle in Near Ground is revolved, being advantageous to the takeoff and landing performance of aircraft improves.Aircraft is in cruising flight phase, main hair
Slip-stream caused by motivation propeller 12 will not generate unfavorable aerodynamic interference to wing 3；At this point, propellerslip flows aft through
The wing 6 and main wing 3 are held, can favourable aerodynamic interference be generated with the opposite end wing 6 and main wing 3, increase the lift resistance ratio of main wing 3 and the side of the end wing 6
To stability.Deployable and collapsible main landing gear 15 is mounted on the lower section of the end wing 6, and the structure for being conducive to make full use of the aircraft is excellent
Gesture, increase inside fuselage 1 and wing 3 using space.
Aircraft of the present invention is designed according to aerodynamic principle, has resistance is small, useful lift face is big, lift resistance ratio is high etc.
Feature, main wing 3 use angle of sweep, and main purpose is that the end wing 6 is allowed to enhance 6 fixed fin of the end wing far as possible from the center of gravity of airplane
Directional yaw stability.Upper limb 4 uses buzzard-type wing, and buzzard-type wing has superior aeroperformance, is greatly improved the low speed behaviour of aircraft
Vertical performance, is substantially reduced resistance during transonic speed flight, has good stalling characteristics under High Angle of Attack.The main wing 3 of aircraft
The slightly upper counterangle, the slightly inverted diherdral of upper limb 4 so that the top view of aircraft wing (including 4 main wing 3 of upper limb) and front view it is outer
For shape all close to diamond shape, aircraft overall stiffness is good, and structure-bearing characteristic is good.In this Flight Vehicle Design, main wing 3, upper limb 4 aerofoil
Spacing is enough, and interfering with each other between main wing 3 and upper limb 4 is smaller, therefore can give full play to the aerodynamic characteristic of two groups of aerofoils.
Canard 2 is provided near the head of aircraft, improves the total life of full machine, drastically increases the longitudinally controlled energy of full machine
Power, the leading vortex hauled out by canard 2 (mainly under flat winged status condition), can stablize the top of main wing 3 under certain condition
Interlayer, so as to postpone air-flow separation so that the useful lift and stalling angle of main wing 3 increase.Extension wing 5 adds having for full machine
Lifting area is imitated, because extension wing 5 is located exactly at full machine immediate vicinity, the almost lift without trim, institute can be provided for full machine
To have very big lift-rising efficiency.
The leading-edge sweep of the wing 6 is held, holds the trailing edge sweepforward of the wing 6, it can be between 6 fixed fin of the enlarged portion wing and the center of gravity of airplane
Distance improves the directional yaw stability of aircraft.In front of 6 lower part of the left and right end wing, sustainer and the driving of propeller inclination angle are set
Device, 6 lower middle position of the wing at left and right end, installation deployable and collapsible main landing gear 15；In the afterbody installation direction that two are held the wing 6
Rudder 9；The installation site of rudder 9 is located between 3 face of upper limb 4 and main wing so that upper limb 4 and main wing 3 generate rudder 9 relatively by force
" end the wing effect ", it is possible to increase the pneumatic efficiency of rudder 9 is conducive to improve the rudder effectiveness of rudder；Due to 9 rudder of rudder
The aerodynamic center in face is close to the vertical center of gravity of full machine so that non-instruction rolling moment greatly reduces caused by rudder kick；
Aileron 8 on extension wing 5 is arranged on simultaneously, and due to the longitudinal center of gravity close to aircraft, the deflection of aileron 8 will not generate big non-
The pitching moment of instruction, comprehensive function effect, by the roll angle control accuracy for greatly improving aircraft and anti-crosswind capability,
This is highly beneficial for the handling quality for improving aircraft.
In takeoff phase, as long as the weight of aircraft is close to the powered lift of engine prop, it is possible to realize aircraft
" pulling out green onion in nonirrigated farmland " formula take off vertically it is liftoff.Even if the powered lift of engine is not enough to directly lift aircraft, also can be significantly
Improve the takeoff data of aircraft, realize short takeoff：Playing an aircraft stage, it is still desirable to which aircraft is in ground roll-out speedup, when flying
When machine has had certain flying speed, sustainer propeller 12 is inclined upwardly certain angle, make engine generate to
Certain powered lift is generated while preceding pulling force；Under powered lift effect, aircraft will generate nose-up pitching moment so that aircraft is
Make at low speeds, to could be used that the very big take-off angle of attack, increase the useful lift of full machine lifting surface, with it is shorter it is sliding run away from
From lifting off.Then, gradually increase the lift of posture adjustment engine prop 14, be gradually reduced flying angle, reduce flight resistance
Power, and the sustainer propeller 12 that gradually leans forward, increase propeller pulling force component, aircraft are made persistently to accelerate sporting flying,
Full machine lift will increase with the increase of flying speed, until lift caused by each lifting surface of aircraft is enough full machine is supported to fly
Row weight, you can be transferred to the efficient cruising flight phase of fixed-wing.
In landing period, as long as the weight of aircraft is close to engine power lift, it is possible to realize the vertical of aircraft
Land.Even if powered lift caused by engine is not enough to support the landing weight of full machine, it is also possible that the landing speed of aircraft
Degree substantially reduces：When landing glide closes on ground, Engine full load can be allowed to work, utilize propeller inclination angle driving device
11 so that most thrusts is equivalent to the landing weight for alleviating aircraft in lift direction, generated lift,
So as to substantially reduce the touchdown speed of aircraft.In the later stage of landing, sustainer propeller 12 can be made to hang down fully upward
Directly, and maximum rating operating is made, at this time under nose-up pitching moment effect caused by sustainer propeller 12, what can be made flies
Machine, which is generated, compared with High Angle of Attack and pitch angle, makes sustainer propeller 12 and posture adjustment engine prop 14 generate maximum power
While lift, it can also generate very big propulsive thrust on its flying speed direction, aircraft made to slow down rapidly, and keeps aircraft
It is moved ahead with High Angle of Attack, big aerodynamic drag posture, even if 12 lift of sustainer propeller is not sufficient to ensure that aircraft vertical lands,
It can ensure that aircraft is grounded with extremely low speed, also ensure that aircraft is moved ahead with large pitching angle, big aerodynamic drag posture after ground connection, from
And greatly shorten distance of landing run.
Embodiment 1：
The embodiment of the present invention provides a kind of aircraft of short takeoff vertical landing, which includes：Fuselage 1 is set
Canard 2 in 1 front end both sides of fuselage is separately positioned on main wing 3, upper limb 4 and the end wing 6 of 1 both sides of fuselage and is arranged on fuselage 1
The vertical fin 10 of upper rear；The end wing 6 is arranged on the end of the main wing 3 of fuselage both sides, and the top of two end wings 6 passes through respectively
The upper limb 4 for being arranged on 1 top of fuselage is connected with being arranged on the vertical fin 10 of 1 afterbody of fuselage, and lifting is both provided on two upper limbs 4
Rudder 7；The outside of described two end wings 6 is provided with the extension wing 5 being connected with upper limb, and aileron 8 is both provided on two extension wings 5；
The afterbody of described two end wings 6 is both provided with rudder 9.Support construction 17 is stretched out before at two 6 lower part of the wing being held to be provided with, every
A forward direction, which stretches out, sets a sustainer and propeller inclination angle driving device 11 in support construction 17, propeller inclination angle driving dress
11 are put for adjusting the angle of inclination (referring to Fig. 2, Fig. 3, Fig. 4, Fig. 5, Fig. 6) of propeller, propeller inclination angle driving device 11 can
Using ball screw driving device.At two 6 lower part of the wing is held to be mounted on retractable landing gear 15；The rear portion of the vertical fin 10
Support construction 13 is stretched out in top after being provided with, and posture adjustment engine prop 14 is equipped in the top of the stretching support construction 13.
This aircraft is designed according to aerodynamic principle, due to resistance is small, useful lift face is big, lift resistance ratio is high
The features such as, main wing 3 uses swept-back wing, and upper limb 4 uses buzzard-type wing, and buzzard-type wing has superior aeroperformance, is greatly improved winged
The low-speed control performance of machine, is substantially reduced resistance during transonic speed following flight, has good stalling characteristics under High Angle of Attack.
The slightly upper counterangle of main wing 3 of aircraft, the slightly inverted diherdral of upper limb 4 so that the main wing 3 of aircraft machine and the top view of upper limb 4 and
For the shape of front view all close to diamond shape, aircraft overall stiffness is good, and structure-bearing characteristic is good.In this Flight Vehicle Design, 3 He of main wing
The spacing of 4 aerofoil of upper limb is enough, and interfering with each other between main wing 3 and upper limb 4 is smaller, therefore can give full play to two groups of aerofoils
Aerodynamic characteristic.Canard 2 is provided near the head of aircraft, improves full machine lift, drastically increases the vertical of full machine
To control ability；The leading vortex hauled out by canard 2 (mainly under flat winged status condition), can stablize main wing under certain condition
3 upper surface boundary layer, so as to postpone air-flow separation so that 3 useful lift of main wing and stalling angle increase.Extension wing 5 increases
The useful lift area of full machine, because extension wing 5 is located exactly near full machine longitudinal center of gravity, can provide for full machine and almost need not
The lift of trim, so with very big lift-rising efficiency.
In the present invention, hold 6 leading-edge sweep of the wing, hold the trailing edge sweepforward of the wing 6, be conducive to 6 fixed fin of the enlarged portion wing with it is complete
The distance of machine center of gravity improves the directional yaw stability of aircraft, sets a sustainer in stretching support construction 17 in each of front
And propeller inclination angle driving device 11；6 lower middle position of the wing at left and right end, installation deployable and collapsible main landing gear 15；It is holding
The afterbody of the wing 6, setting direction rudder 9, between the aerofoil of upper limb 4 and main wing 3 so that upper limb 4 and 3 aerofoil of main wing are to rudder
9 generate stronger " end wing effect ", it is possible to increase the pneumatic efficiency of rudder 9 is conducive to improve 9 rudder effectiveness of rudder.Due to
The aerodynamic center of 9 rudder face of rudder is close to the vertical center of gravity of full machine so that rudder 9 deflects generated non-instruction rolling moment
It greatly reduces；Aileron 8 is set on extended segment 5 simultaneously, and due to the longitudinal center of gravity close to full machine, the deflection of aileron 8 will not produce
The pitching moment of raw big non-instruction, comprehensive function effect will greatly improve the roll angle control accuracy of aircraft and anti-side wind
Throwing power, this is highly beneficial for the handling quality for improving aircraft.
The fuselage 1 and main wing 3 of aircraft of the present invention have carried out the warm processing of wing body, and fuselage 1 and canard 2 have carried out wing body and melted
And processing, so as on the premise of its pneumatic efficiency is improved, add the structural strength of 1 wing 3 of fuselage and 2 junction of canard；
The vertical fin 10 and fuselage 1 carry out fusion connection, increase intensity.The main wing 3, canard 2, upper limb 4, extension wing 5 and the end wing 6 are adopted
With conventional aerofoil profile, laminar flow airfoil, high-lift airfoil or supercritical airfoil.Canard 2 and extension wing 5 using buzzard-type wing, swept-back wing or
The straight wing.
Embodiment 2：
The embodiment of the present invention provides a kind of short takeoff aircraft, which includes：Fuselage 1 is arranged on 1 front end of fuselage
The canard 2 of both sides, main wing 3, the upper limb 4 for being arranged on 1 both sides of fuselage), the end wing 6, be arranged on the vertical fin 10 of 1 upper rear of fuselage；
The end wing 6 is respectively provided in the end of the main wing 3 of 1 both sides of fuselage, the top of described two end wings 6 is respectively by setting on the fuselage 1
The upper limb 4 of side is connected with being arranged on the vertical fin 10 of afterbody；The outside of described two end wings 6 is provided with prolonging of being connected with upper limb
Stretch the wing 5；Elevator 7 is both provided on described two upper limbs 4, aileron 8 is both provided on described two extension wings 5, it is described two
Hold the afterbody side of the being both provided with rudder 9 of the wing 6；Described two 6 lower parts of the end wing are stretched out before setting to stretching support construction 17, the forward direction
17 front end of support construction is provided with propeller inclination angle driving device 11；Master is installed to start in the driving device of the propeller inclination angle
Machine propeller 12；Described two 6 lower parts of the end wing are equipped with deployable and collapsible main landing gear 15；The rear upper of the vertical fin 10 is set
There is backward stretching support construction 13, the backward top for stretching out support construction 13 is equipped with posture adjustment engine prop 14.
In takeoff phase, as long as the weight of aircraft is close to sustainer propeller powered lift, it is possible to realize aircraft
Take off vertically it is liftoff.
Even if the powered lift of sustainer propeller 12 is not enough to directly lift aircraft, aircraft can be also substantially improved
Takeoff data realizes short takeoff：In takeoff phase, it is still desirable to which aircraft is in ground roll-out speedup, when aircraft has had one
During fixed flying speed, sustainer propeller 12 is inclined upwardly certain angle, will make sustainer propeller generate to
Certain powered lift is generated while preceding pulling force；12 powered lift of sustainer propeller can also generate larger new line power
Square is superimposed with the rudder effectiveness of canard 2 and elevator 7；Deployable and collapsible main landing gear 15 is provided below in the end wing 6, and aircraft is allowed to have
Sufficiently large grazing angle；The result of its comprehensive function：So that even if aircraft at low speeds, could be used that very big taking off is met
Angle increases full machine canard 2, the useful lift of 5 lifting surface of main wing 3, upper limb 4 and extension wing, with the shorter liftoff liter of ground run distance
It is empty.Then, gradually increase the lift of posture adjustment engine prop 14, be gradually reduced flying angle, reduce flight resistance, and gradually
Lean forward sustainer, and 12 pulling force component of increase sustainer propeller makes aircraft persistently accelerate sporting flying, each lift of aircraft
The lift in face will increase with the increase of flying speed, until lift caused by each lifting surface of aircraft is enough full machine is supported to fly
Row weight, you can be transferred to the efficient cruising flight phase of fixed-wing.
Embodiment 3
The embodiment of the present invention provides a kind of vertical (short distance) landing aircrafts, which includes：Fuselage 1 is arranged on machine
The canard 2 of body front end both sides, the main wing 3 for being arranged on 1 both sides of fuselage, upper limb 4, end and are arranged on above afterbody the wing 6
Vertical fin 10；The end of the main wing 3 for being arranged on fuselage both sides is respectively provided with the end wing 6, and the top of described two end wings 6 passes through respectively
The upper limb 4 for being arranged on body upper is connected with the vertical fin 10 for being arranged on afterbody；The outside of described two end wings 6 be provided with
The extension wing 5 that upper limb is connected；Elevator 7 is both provided on described two upper limbs 4, pair is both provided on described two extension wings 5
The wing 8, the afterbody side of the being both provided with rudder 9 of described two end wings 6；Described two 6 lower parts of the end wing set before to stretching out support construction 17,
The forward direction stretches out 17 front end of support construction and is provided with propeller inclination angle driving device 11；In the driving device of the propeller inclination angle
Airscrew engine is installed；Described two 6 lower parts of the end wing are equipped with deployable and collapsible main landing gear 15；The rear portion of the vertical fin 10
Top is provided with backward stretching support construction 13, and the backward top for stretching out support construction 13 is equipped with posture adjustment engine spiral
Paddle 14.
In landing period, as long as the weight of aircraft is close to 12 powered lift of sustainer propeller, it is possible to realize and fly
The vertical landing of machine.
Even if powered lift caused by sustainer propeller 12 is not enough to support the landing weight of full machine, can also make
The landing speed for obtaining aircraft substantially reduces.When landing glide closes on ground, the work at full capacity of sustainer propeller 12 can be allowed
Make, utilize propeller inclination angle driving device 11 so that most thrusts is in lift direction, sustainer propeller 12
Generated lift is equivalent to the landing weight for alleviating aircraft.In the later stage of landing, sustainer propeller 12 can be made complete
It is vertical in omnidirectional, and make maximum rating operating, at this time nose-up pitching moment caused by sustainer propeller 12 and canard 2,
Under the collective effect of elevator 7, it may be such that aircraft is generated compared with High Angle of Attack or pitch angle, at this point, sustainer propeller 12 and tune
Appearance engine prop 14 can also generate very big while maximum powered lift is generated on its flying speed direction
Propulsive thrust makes aircraft slow down rapidly；Simultaneously as used deployable and collapsible main landing gear 15 has almost unrestricted wiping
Ditch enables aircraft with High Angle of Attack/big aerodynamic drag posture ground connection, moves ahead, even if sustainer propeller lift is not enough to protect
It demonstrate,proves aircraft vertical to land, can also greatly shorten distance of landing run.
In addition, super large main wheel track possessed by deployable and collapsible main landing gear 15, it can be ensured that aircraft take off High Angle of Attack from
Problem does not occur for horizontal shipping-direction stability when ground, landing daying corner-of-delta grounding.
Conventional aerofoil profile, laminar flow airfoil, high lift hardware can be used in the canard 2, main wing 3, upper limb 4, the end wing 6 and extension wing 5
The blade of type or supercritical airfoil, sustainer propeller 12 and posture adjustment engine prop 14 is two leaf paddles, three leaf paddles, four leaves
Paddle, five leaf paddles or six leaf paddles.
Claims (9)
1. a kind of short takeoff vertical landing aircraft including fuselage (1), sustainer, vertical fin (10) and is separately positioned on
Main wing (3), upper limb (4), the end wing (6) and the canard (2) of fuselage both sides；The top of two end wings (6) is respectively by being arranged on machine
Square upper limb (4) is connected with vertical fin (10) with it；The extension for being both provided on the outside of the wing (6) and being connected with upper limb (4) is held at two
The wing (5)；Elevator (7) is both provided on two upper limbs (4), it is characterised in that：It is equipped in the lower part of two end wings preceding to stretching
Support construction (17), in each of front to stretch out support construction on set a sustainer, sustainer propeller (12) and
Propeller inclination angle driving device (11), and deployable and collapsible main landing gear (15) is set in the lower part of each end wing；In the vertical fin
(10) rear portion is set stretches out support construction (13) backward, stretches out backward in support construction at this and is equipped with posture adjustment engine prop
(14)。
2. a kind of short takeoff vertical landing aircraft as described in claim 1, it is characterised in that：On two extension wings
It is provided with aileron (8)；The afterbody of described two end wings is both provided with rudder (9).
3. a kind of short takeoff vertical landing aircraft as described in claim 1, it is characterised in that：The main wing, canard, on
The wing and extension wing use buzzard-type wing, swept-back wing or the straight wing.
4. a kind of short takeoff vertical landing aircraft as claimed in claim 3, it is characterised in that：The main wing uses sweepback
The wing, upper limb use buzzard-type wing.
5. a kind of short takeoff vertical landing aircraft stated such as claim 1, it is characterised in that：The propeller inclination angle driving
Device (11) uses ball screw drive mechanism.
6. a kind of short takeoff vertical landing aircraft as described in claim 1, it is characterised in that：The end wing (6) and prolong
The wing (5) is stretched using conventional aerofoil profile, laminar flow airfoil, high-lift airfoil or supercritical airfoil.
7. a kind of short takeoff vertical landing aircraft stated such as claim 6, it is characterised in that：The leading edge of the end wing carries
Angle of sweep holds the trailing edge of the wing to carry sweepforward angle.
8. a kind of short takeoff vertical landing aircraft as described in claim 1-7 any claims, it is characterised in that：Institute
State main wing (3) the slightly upper counterangle；The upper limb (4) slightly inverted diherdral.
9. a kind of short takeoff vertical landing aircraft as claimed in claim 8, it is characterised in that：The sustainer spiral
The blade of paddle (12) and posture adjustment engine prop (14) is two leaf paddles, three leaf paddles, four leaf paddles, five leaf paddles or six leaf paddles.
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| CN201711364349.3A CN108045575B (en) | 2017-12-18 | 2017-12-18 | Short-distance take-off vertical landing aircraft |
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|---|---|---|---|
| CN201711364349.3A CN108045575B (en) | 2017-12-18 | 2017-12-18 | Short-distance take-off vertical landing aircraft |
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| CN108045575B CN108045575B (en) | 2024-03-19 |
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| CN109774916A (en) * | 2019-01-14 | 2019-05-21 | 北京航空航天大学 | A kind of Helios using three-dimensional layout designs |
| CN109987223A (en) * | 2019-04-02 | 2019-07-09 | 夏季风 | A kind of new vertical landing unmanned plane coupling wing configuration |
| CN110775263A (en) * | 2019-10-22 | 2020-02-11 | 上海交通大学 | Tailstock type sea-air cross-region unmanned aerial vehicle and sea-air flight mode thereof |
| CN110871892A (en) * | 2018-09-01 | 2020-03-10 | 田瑜 | Aircraft vertical stabilizer with lift propeller and using method thereof |
| CN112027078A (en) * | 2020-09-16 | 2020-12-04 | 郑州航空工业管理学院 | Amphibious composite wing unmanned aerial vehicle and control method thereof |
| CN113911318A (en) * | 2021-09-22 | 2022-01-11 | 重庆理工大学 | Posture self-adaptive adjustment annular lift wing device for pneumatic suspension train |
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