CN108945482A - A kind of aircraft for installing driving mechanism below the plate wing - Google Patents
A kind of aircraft for installing driving mechanism below the plate wing Download PDFInfo
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- CN108945482A CN108945482A CN201811081348.2A CN201811081348A CN108945482A CN 108945482 A CN108945482 A CN 108945482A CN 201811081348 A CN201811081348 A CN 201811081348A CN 108945482 A CN108945482 A CN 108945482A
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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Abstract
The present invention discloses a kind of aircraft that driving mechanism is installed below the plate wing, belongs to technical field of aerospace.The aircraft of large area plate wing is used for wing, in the forward lower part of plate nose of wing, driving device is set, aileron is arranged in the forward lower part of driving device, the plate wing is divided into four parts, front is fixed main wing, the left and right sides is can be anti-below and the winglet that levels off, and rear portion is can be anti-below and the negative dihedral wing that levels off, and tail portion is rectifying wings；The winglet of the left and right sides is pull-down, and the negative dihedral wing at rear portion is pull-down negative dihedral wing, divides formula negative dihedral wing, collapsible negative dihedral wing, sliding negative dihedral wing, any one in enclosure-type negative dihedral wing equally.The present invention allows bottom driving plate wing machine completely and two kinds of flight operating conditions of VTOL and high-speed flight, has many advantages, such as that mode conversion nature, flight efficiency is high, wing wing load is low, safety and stability, structure is simple, manipulation is easy, low in cost, is easy to universal.
Description
Technical field
The present invention relates to a kind of below the plate wing installs the aircraft of driving mechanism, belongs to technical field of aerospace.
Background technique
Man-carrying aircraft can be divided into fixed-wing and rotary wings two major classes, and fixed-wing is common in Horizontal Take-off and Landing aircraft (as sprayed
Gas formula passenger plane), and rotary wings are common in VTOL aircraft (such as helicopter).For state of the art, fixed-wing boat
Pocket can be easy to operate with high-speed flight, but need to rely on runway landing.Rotary wing aircraft can be not required to rely on VTOL
Runway landing, it is adaptable, but mechanism is lacked of proper care, manipulation is complicated, and flying speed is slow, and fuel efficiency is low.
Currently, there is also some inherent shortcomings that can not be overcome for VTOL aircraft.First is that low efficiency, uses now
VTOL aircraft thrust ratio is respectively less than 1, and flight efficiency is low, compared with Fixed-Wing is generally greater than 5 thrust ratio
Gap is fairly obvious；It is limited second is that being necessarily less than velocity of sound by wing tip absolute velocity, the theoretical velocity of rotary wing aircraft cannot
More than 420 kilometers/hour, flying speed has the limit；Third is that rotor blade waves generation mechanical oscillation, the mill of hinge is increased
Damage, reliability are low；It topples fourth is that two sides rotor lift unevenly will lead to rotary wing aircraft generation roll, roll stability
Difference；Fifth is that the rotor of helicopter had both provided the mobility of flight, while also resulting in the complexity of flight manipulation, manipulation is multiple
It is miscellaneous, so that manipulation load is far longer than fixed wing aircraft, increase the probability of human error；Sixth is that rotor diameter and revolving speed by
Tip velocity is no more than the limitation of velocity of sound, and the general maximum of rotor diameter is exactly more than ten meters, and aircraft is size-constrained, can not do
Greatly；Seventh is that in helicopter flight mechanism inaccurate coordination, be filled with geneogenous contradiction, flight mechanism imbalance；Eighth is that very much
Novel combined VTOL aircraft trial uses fixed-wing, and solid but face the limited large area of small area fixed-wing effect
Determine downwash flow of wing when can be to VTOL and causes the contradiction blocked.
In short, the drawbacks described above of VTOL aircraft from wing should take into account VTOL again satisfaction level fly
Two kinds of offline mode of row and the contradiction generated.Realize that VTOL can be compatible with vertically very well using the method for the tangential air blowing of aerofoil
Two kinds of offline mode of landing and horizontal flight, are the new developing direction of VTOL aircraft, and driving is installed below the plate wing
The aircraft of mechanism can be such that plate wing machine runs, and more efficient, flight is safer, structure is more reasonable, performance is more stable.
Summary of the invention
The technical problem to be solved by the present invention is to universal for existing VTOL aircraft inefficiency, thrust ratio
Less than 1, manipulation is complicated, safety is poor, horizontal flight mode and the conversion of VTOL mode are not enough smoothly naturally, and existing plate
The problems such as wing machine wing drag is excessive, vertical lift is insufficient and tangential inflatable gas stream dissipates proposes that one kind is installed below the plate wing
The aircraft of driving mechanism after increasing lift and realizing VTOL, and can reduce resistance and realize high-speed flight, makes the plate wing
Machine is more safe and efficient, compact, stable, reasonable.
In order to solve the above technical problems, the present invention provides a kind of aircraft for installing driving mechanism below the plate wing, in plate
Driving device is arranged in the forward lower part of nose of wing, high-speed flow is blowed along tangential past plate underwing by driving device, by driving
The air inlet of device forms negative pressuren zone, puff prot above the plate wing and forms zone of positive pressure in the lower section of the plate wing, above the plate wing
The pressure difference lift that negative pressuren zone and the zone of positive pressure of lower section are formed can greatly improve the flight efficiency and thrust ratio of plate wing machine.Driving
The forward lower part of device is arranged aileron, and the plate wing is combined type, anti-under the left and right sides and rear portion of the modular panel wing when VTOL
The airflow direction of propellerslip is changed into vertically downward by horizontal direction, plays the role of lift-rising drag reduction, further increases
The lift of VTOL and the ability of flight control；When horizontal flight, the fixation wing-like that the plate wing folds as resistance very little is being pressed
Other than poor lift, profile lift is further generated；The process of offline mode is mutually converted between VTOL and horizontal flight
In, naturally, operating parameter variation is smooth, manipulation effect does not generate mutation, has taken into account level for the control mode transition of operating mechanism
Flight and the different of VTOL require, and efficiently solve generally existing in existing mode conversion VTOL aircraft fly
The difficult problem of row mode conversion, greatly reduces the manipulation difficulty of VTOL aircraft.The plate wing is divided into four parts, and front is
Fixed main wing, at left and right sides of fixed main wing for can the anti-below and winglet leveled off and rear portion be can be anti-below and to level off down
The anti-wing, tail portion are fixed rectifying wings；Left and right sides winglet is pull-down, and hinge system is added between winglet and main wing
As pulling lower anti-and loosening upper anti-flexible or rigid shell structure, pass through the pulling or release of traction rope or traction mechanism
It realizes the lower anti-or upper anti-of negative dihedral wing, needs that traction rope is directly used to pull down winglet lower inverse time anti-, need inverse time
Release traction rope keeps winglet upper anti-in the case where propellerslip pressure and/or profile lift push；Under the negative dihedral wing at rear portion is
Pull-type negative dihedral wing divides formula negative dihedral wing, collapsible negative dihedral wing, sliding negative dihedral wing, any one (tool in enclosure-type negative dihedral wing equally
Body can select according to actual needs)；Pull-down negative dihedral wing be added between negative dihedral wing and main wing shaft be made as it is anti-under pulling and
Loosen upper anti-flexible or rigid shell structure, is realized under negative dihedral wing by the pulling or release of traction rope or traction mechanism
It is anti-or upper anti-, it needs that traction rope is directly used to pull down negative dihedral wing lower inverse time anti-, needs inverse time release traction rope to make lower anti-
The wing is upper anti-under the promotion of propellerslip pressure；Dividing formula negative dihedral wing equally is that the plate wing is divided into two in the horizontal direction, is divided into upper plate
The wing and the lower plate wing, the upper plate wing is movable wing, and the lower plate wing is fixed-wing, is connected between the upper plate wing and fuselage by rocking bar, and machine is manipulated
Structure drive rocker makes the upper plate wing around the swing of the lower plate wing, when horizontal flight, swings before upper plate flapwise and merges into the lower plate wing
The plate wing of one complete convex lower flat aerofoil profile reduces resistance and realizes high-speed flight, and when VTOL, the upper plate wing is started backward
Lower section is significantly swung, and the upper plate wing and the lower plate wing is made to be staggered as the end to end lower counter plate wing；Collapsible negative dihedral wing is using flexible
Cloth production is collected negative dihedral wing into plate wing inside or expansion by fold mechanism；Sliding negative dihedral wing uses rigid material system
Make, negative dihedral wing is divided into can be overlapped several sections, several sections of negative dihedral wings are folded by slipping mechanism and are collected for one section into master
Wing inside or lower anti-expansion；Enclosure-type negative dihedral wing collects negative dihedral wing, the shaft position of negative dihedral wing using the left and right facade of sheet fuselage
In in the plane of sheet fuselage, negative dihedral wing is rearward flattened in the plane for collapsing in sheet fuselage and is reduced when horizontal flight or so
Resistance, negative dihedral wing is unfolded vertical with the plane of sheet fuselage forwards when VTOL or so, by horizontal gas flow enclosing downwards and
Play the role of increasing lift, enclosure-type negative dihedral wing also acts as the regulating and controlling effect of vertical tail.
The plate wing is shell structure, fabric plus nylon by high strength composite or high strength light metal framework
At, such as plus nylon cloth be made using carbon fiber cloth clamp honeycomb composite material or of aluminium alloy, titanium alloy frame；The plate wing
Contour line is the upper surface curve of Low Speed Airfoil, when horizontal flight, is washed in the case where plate wing upper surface is also by air draught by aerofoil profile
While generating lift, plate wing lower surface can also force down propellerslip to wash generation lift, therefore the liter that the plate wing generates
Power is bigger than general fixed-wing；The thrust ratio of VTOL is greater than 1, and thrust ratio when horizontal flight is greater than 5.
The winglet is aerofoil profile flat in thin plate aerofoil profile or evagination, the leading edge of winglet close to driving device,
The lower edge of winglet is more than the lower edge of driving device, rear of the rear of winglet near or above the plate wing, winglet
The width of trailing edge profile line be gradually decreased as zero according to streamline shape；When winglet is aerofoil profile flat in evagination, in the wing
Longitudinal hinge is arranged between tip winglet and fixed main wing to be connected, sagging winglet is enable to generate in horizontal flight air-flow
Profile lift pushes lower automatic anti-flattening, becomes convex lower flat aerofoil profile, the winglet leveled off can increase plate wing machine liter
Power increases wing light-receiving area, reduces wing load to greatest extent；Either level flight condition or VTOL state, work as a left side
When the winglet inverted diherdral difference of right two sides, a yawing, adjustment left and right sides winglet will be generated on the plate wing
Inverted diherdral yaw control can be realized；When the inverted diherdral of left side winglet is greater than the inverted diherdral of right side winglet, plate
Wing machine is to left drift；When the inverted diherdral of right side winglet is greater than the inverted diherdral of left side winglet, plate wing machine is yawed to the right；
The inverted diherdral deviation of left and right sides winglet is bigger, and the yawing of plate wing machine is bigger.
The aileron is convex lower flat aerofoil profile, is connected by the lateral hinge at aileron rear portion with fuselage, and aileron is around cross
It rotates to hinge to change the angle of attack；When horizontal flight, the aerofoil profile of aileron can generate profile lift, by changing attacking for aileron
Angle will cause the variation of the lift and resistance of the plate wing, thus the pitching of control panel wing machine；When aileron turns to positive incidence, aileron energy
Enough to generate impact lift, plate wing machine is faced upward, and positive incidence is bigger, and plate wing machine vertical angle is bigger；When aileron turns to negative angle of attack, aileron energy
Surge is enough generated, plate wing machine nutation, negative angle of attack is bigger, and the angle of depression is bigger under plate wing machine.In addition, the air inlet of driving device is inhaled
The air-flow generated when gas flows through the top airfoil of aileron, and the air velocity of aileron lower aerofoil is identical as aircraft speed, even if
When the air velocity for being aileron lower aerofoil in hang is zero, it still is able to form negative pressure lift on aileron.
The driving device is located among the cabinet that the plate wing, aileron and winglet surround, and forms ducted fan；Driving dress
Set is that any one of propeller, shrouded propeller, turbojet engine, fanjet, turbo oar engine (specifically can bases
Actual needs selection), the flow velocity for being blown into the air-flow on wing is directly proportional to the power of driving device.
The width of the fixed main wing is that all propellers (can root according to 1.1-1.5 times of the diameter D width enumerated in full detail side by side
Specifically determined according to actual conditions), the width that slightly larger than all propellers are enumerated in full detail side by side according to diameter D；The length of fixed main wing
Airscrew diameter D more than or equal to 3 times, the length of negative dihedral wing are greater than or equal to 2 times of airscrew diameter D.
The taking off of the plate wing machine is landed and forced landing is vertical mode, and suspension type cylinder spring can be directly used and rise
Fall frame.
The quantity of the plate wing can increase, and the quantity of the plate wing can be 1, constitute a width wing of a width overhead type,
It can be 2 multiple, constitute several wings of bilateral symmetry pressure-bearing type, for medium-sized or large-scale man-carrying aircraft, the plate wing
Quantity can increase in the way of pressure-bearing type wing or so wing in couples tandem.
In the present invention, the fuselage of plate wing machine is sheet fuselage, and the plate wing, aileron and winglet define a biggish case
Body, when horizontal flight, can increase stability, and the VTOL plate wing anti-at present and the cabinet form an airflow duct will
Downwards, effect effect in ground is obvious, and the elasticity of air can be increased in takeoff and landing for the Jet Stream guidance of driving device, mitigates
The impact of takeoff and landing；The cabinet that the plate wing surrounds when fault forced landing is like a parachute, it is ensured that plate wing machine, which can delay, to drop
Land.In addition, forward air inlet, the VTOL mode of rear exhaust has made the motion path of air-flow in order, compared with being vented vertically downward
The landing mode of (such as helicopter), the motion path of air-flow is more scientific and reasonable, avoids screening of the ground wind-drifting sand to sight
Gear and the damage to machine.The flight control of plate wing machine is inverted diherdral, the winglet that negative dihedral wing is adjusted by operating-controlling mechanism
The power of inverted diherdral, the angle of attack of aileron and driving device is realized；When horizontal flight, pitching the attacking by adjusting aileron of plate wing machine
Angle is realized, or is realized by adjusting the inverted diherdral of rear portion negative dihedral wing, and the yaw of plate wing machine passes through wingtip at left and right sides of differential adjustment
The inverted diherdral of winglet is realized, is deviateed the slightly lower anti-negative dihedral wing of right side simultaneously in midpoint to left side negative dihedral wing when left drift and is deviateed midpoint
Slightly upper anti-, the slightly lower anti-negative dihedral wing deviation of the left side simultaneously midpoint in right side negative dihedral wing deviation midpoint is slightly upper anti-when yawing to the right
It can；When VTOL, the up and down motion of plate wing machine is regulated and controled by watt level, and travelling forward for plate wing machine is reduced by negative dihedral wing
Inverted diherdral realizes, the movement backward of plate wing machine by negative dihedral wing increase inverted diherdral to 100-120 ° (about 110 ° or so) can be real
Existing, the yaw of plate wing machine is then realized by the inverted diherdral of winglet at left and right sides of differential adjustment；Due to plate wing machine center of gravity compared with
Low, VTOL pitching moment in-flight and rolling moment are compensated by the drift angle autobalance of plate wing machine center of gravity, are not needed
Special mechanism controls.
The present invention allows bottom driving plate wing machine completely and two kinds of flight operating conditions of VTOL and high-speed flight, has mode
Conversion nature, flight efficiency are high, wing wing load is low, safety and stability, structure is simple, manipulation is easy, low in cost, are easy to universal etc.
Advantage.
Detailed description of the invention
Fig. 1 is bottom driving plate wing machine level flight condition schematic side view of the present invention.
Fig. 2 is bottom driving plate wing machine level flight condition schematic top plan view of the present invention.
Fig. 3 is bottom driving plate wing machine level flight condition schematic rear view of the present invention.
Fig. 4 is bottom driving plate wing machine VTOL state schematic side view of the present invention.
Fig. 5 is bottom driving plate wing machine VTOL state schematic top plan view of the present invention.
Fig. 6 is bottom driving plate wing machine VTOL state schematic rear view of the present invention.
Fig. 7 is bottom driving plate wing machine shell structure plate wing schematic diagram of the present invention.
Fig. 8 is the relation schematic diagram of the bottom driving plate wing machine airscrew diameter D and plate chord degree and negative dihedral wing length of the present invention.
Fig. 9 is that bottom driving plate wing machine horizontal flight of the present invention moves upwards control principle schematic diagram.
Figure 10 is that bottom driving plate wing machine horizontal flight of the present invention moves downward control principle schematic diagram.
Figure 11 is that bottom driving plate wing machine horizontal flight of the present invention moves right control principle schematic diagram.
Figure 12 is that bottom driving plate wing machine horizontal flight of the present invention moves downward control principle schematic diagram.
Figure 13 is that bottom driving plate wing machine VTOL of the present invention travels forward control principle schematic diagram.
Figure 14 is bottom driving plate wing machine VTOL of the present invention motion control schematic illustration backward.
Figure 15 is that bottom driving plate wing machine VTOL of the present invention moves right control principle schematic diagram.
Figure 16 is that bottom driving plate wing machine VTOL of the present invention moves downward control principle schematic diagram.
Figure 17 is bottom driving plate wing machine suspension type cylinder spring undercarriage landing schematic illustration of the present invention.
Figure 18 is that bottom driving plate wing machine suspension type cylinder spring undercarriage of the present invention takes off schematic illustration.
In figure: 1- aileron, 2- transverse direction hinge, 3- driving device, the 4- plate wing, 5- winglet, reverse drawing under 6- winglet
It restricts, reverse drawing sling under 7- winglet, 8- negative dihedral wing hinge, 9- negative dihedral wing, 10- negative dihedral wing drawstring, 11- negative dihedral wing stay cord button,
12- rectifying wings, 13- fuselage, the differential lower revertive control bar of 14- or so winglet, 15- cockpit, 16- undercarriage, 17- winglet
Hinge, 18-NACA4412 aerofoil profile horizontal stretch aerofoil profile parameter.
Specific embodiment
A specific embodiment of the invention is further described in detail with reference to the accompanying drawing, the skill being not specified in embodiment
The conventional products that art or product are the prior art or can be obtained by purchase.
Embodiment 1: as shown in Fig. 1-18, this installs the aircraft of driving mechanism below the plate wing, in fixed main wing leading edge
Forward lower part be arranged driving device, high-speed flow is blowed along tangential past plate underwing by driving device, by driving device
Air inlet forms negative pressuren zone, puff prot above the plate wing and forms zone of positive pressure in the lower section of the plate wing, make negative pressuren zone above the plate wing and
The zone of positive pressure of lower section forms pressure difference lift；Meanwhile the plate wing is set as combined type, and when VTOL, the left and right two of the modular panel wing
The airflow direction of propellerslip is instead changed into the work for playing lift-rising drag reduction vertically downward under side and rear portion by horizontal direction
With the ability that the lift and flight for further increasing VTOL control；When horizontal flight, the plate wing folds consolidating for resistance very little
Determine wing-like, other than pressure difference lift, also generates profile lift；Flight mould is mutually converted between VTOL and horizontal flight
During formula, naturally, operating parameter variation is smooth, manipulation effect does not generate mutation, simultaneous for the control mode transition of operating mechanism
It has cared for horizontal flight and the different of VTOL requires, efficiently solved universal in existing mode conversion VTOL aircraft
The difficult problem of existing offline mode conversion, greatly reduces the manipulation difficulty of VTOL aircraft.
Aileron is arranged in the forward lower part of driving device, and anti-winglet, the plate wing are group under the wingtip setting of fixed main wing
It is box-like, it is divided into four parts, front is fixed-wing, and the left and right sides is the winglet can be anti-below and leveled off, and rear portion is can be following
Negative dihedral wing that is anti-and leveling off, tail portion is rectifying wings；The winglet of the left and right sides is pull-down, and pull-down winglet is in the wing
Hinge is added between tip winglet and fixed main wing to be made as pulling lower anti-and loosen upper anti-flexible or rigid shell structure, is needed
It lower inverse time will directly use traction rope to pull down winglet anti-, and will need inverse time, release traction rope makes winglet in spiral
Paddle slip-stream pressure and/or profile lift push lower anti-；Rear portion negative dihedral wing be pull-down, pull-down negative dihedral wing be negative dihedral wing with
Shaft is added between main wing to be made as pulling lower anti-and loosen upper anti-flexible or rigid shell structure, needs lower inverse time, directly
Negative dihedral wing pulled down using traction rope anti-, needs inverse time, release traction rope make negative dihedral wing in propellerslip pressure and/or
Profile lift pushes lower anti-.
The plate wing is shell structure, is made of carbon fiber cloth clamp cellular composite material；The contour line of the plate wing is Low Speed Airfoil
Upper surface curve, when horizontal flight, washed under propellerslip is forced in plate wing lower surface generate lift while, table on the plate wing
Also by air draught by washing generation lift under aerofoil profile, the lift of the plate wing is bigger than general fixed-wing in face；VTOL pushes away
Again than being greater than 1, thrust ratio when horizontal flight reaches 5 or more.
Aileron is convex lower flat aerofoil profile, is connected by the lateral hinge at aileron rear portion with fuselage, and aileron is around laterally hinge
Chain is rotated to change the angle of attack；When horizontal flight, the aerofoil profile of aileron can generate profile lift, will by changing the angle of attack of aileron
Cause the variation of lift and resistance, thus the pitching of control panel wing machine；When aileron turns to positive incidence, aileron can generate impact and rise
Power, plate wing machine are faced upward, and positive incidence is bigger, and plate wing machine vertical angle is bigger；When aileron turns to negative angle of attack, aileron can generate percussive pressure
Power, plate wing machine nutation, negative angle of attack is bigger, and the angle of depression is bigger under plate wing machine；In addition, the gas generated when the air inlet air-breathing of driving device
Stream flows through the top airfoil of aileron, and the air velocity of aileron lower aerofoil is identical as aircraft speed, and when VTOL is zero, because
Even flying speed is equal to zero in this hang, it still is able to form negative pressure lift on aileron.
Winglet is thin plate aerofoil profile, and for the leading edge of winglet close to driving device, the lower edge of winglet is more than driving
The lower edge of device, the rear of winglet is close to the rear of the plate wing, and the width of the trailing edge profile line of winglet is according to streamlined
Shape is gradually decreased as zero；Either level flight condition or VTOL state, when the winglet inverted diherdral of the left and right sides
When different, a yawing will be generated on the plate wing, control the winglet inverted diherdral control yaw of the left and right sides；Work as left side
When the inverted diherdral of winglet is greater than the inverted diherdral of right side winglet, plate wing machine is to left drift；When under the winglet of right side
When dihedral is greater than the inverted diherdral of left side winglet, plate wing machine is yawed to the right；The inverted diherdral deviation of left and right sides winglet is got over
Greatly, the yawing of plate wing machine is bigger；Upper anti-winglet, which also has, to be increased plate wing machine lift, increases wing light-receiving area
The effect that the wing carries is reduced to greatest extent.
Driving device is propeller, among the cabinet that the plate wing, aileron and winglet surround, forms ducted fan,
The flow velocity for being blown into the air-flow on wing is directly proportional to the power of driving device.
The width of the plate wing is slightly larger than all propellers and enumerates in full detail width side by side according to diameter D, for all propellers according to
Diameter D enumerates in full detail 1.1 times of width side by side；The length of fixed main wing is 3 times of airscrew diameter D, and the length of negative dihedral wing is spiral
2 times of paddle diameter D.
The taking off of plate wing machine is landed and forced landing is vertical mode, using suspension type cylinder spring undercarriage.
The quantity of the plate wing can increase, and for medium-sized or large-scale man-carrying aircraft, the quantity of wing can be according to horizontal
The mode of formula wing or so wing tandem in couples increases.
Embodiment 2: as shown in Fig. 1-18, this installs the aircraft of driving mechanism below the plate wing, in fixed main wing leading edge
Forward lower part be arranged driving device, high-speed flow is blowed along tangential past plate underwing by driving device, by driving device
Air inlet forms negative pressuren zone, puff prot above the plate wing and forms zone of positive pressure in the lower section of the plate wing, utilizes the negative pressuren zone above the plate wing
The pressure difference lift formed with the zone of positive pressure of lower section；Meanwhile the plate wing is set as combined type, and when VTOL, a left side for the modular panel wing
Anti- the airflow direction of propellerslip is changed into vertically downward by horizontal direction under right two sides and rear portion, plays lift-rising drag reduction
Effect further increases the lift of VTOL and the ability of flight control；When horizontal flight, the plate wing is folded as resistance very little
Fixed wing-like also generates profile lift other than pressure difference lift；The mutually conversion flight between VTOL and horizontal flight
During mode, naturally, operating parameter variation is smooth, manipulation effect does not generate mutation for the control mode transition of operating mechanism,
It has taken into account horizontal flight and the different of VTOL requires, efficiently solved general in existing mode conversion VTOL aircraft
The problem difficult all over the conversion of existing offline mode, greatly reduces the manipulation difficulty of VTOL aircraft.
Aileron is arranged in the forward lower part of driving device, and anti-winglet, the plate wing are group under the wingtip setting of fixed main wing
It is box-like, it is divided into four parts, front is fixed-wing, and the left and right sides is the winglet can be anti-below and leveled off, and rear portion is can be following
Negative dihedral wing that is anti-and leveling off, tail portion is rectifying wings；The winglet of the left and right sides is pull-down, and pull-down winglet is in the wing
Hinge is added between tip winglet and fixed main wing to be made as pulling lower anti-and loosen upper anti-flexible or rigid shell structure, is needed
It lower inverse time will directly use traction rope to pull down winglet anti-, and will need inverse time, release traction rope makes winglet in spiral
Paddle slip-stream pressure and/or profile lift push lower anti-；Rear portion negative dihedral wing is to divide formula equally, and dividing formula negative dihedral wing equally is in the horizontal direction
Main wing is divided into two, the upper plate wing and the lower plate wing are divided into, the upper plate wing is movable wing, and the lower plate wing is fixed-wing, the upper plate wing and fuselage
Between connected by rocking bar, operating mechanism drive rocker makes the upper plate wing around the swing of the lower plate wing, when horizontal flight, the upper plate wing
The plate wing for merging into a complete convex lower flat aerofoil profile with the lower plate wing is swung forward reduces resistance realization high-speed flight, it is vertical to rise
When drop, the upper plate wing is started to the back lower place and is significantly swung, the upper plate wing and the lower plate wing is made to be staggered as end to end negative dihedral wing.
The plate wing is shell structure, is made of aluminum alloy frame plus nylon cloth；The contour line of the plate wing is the upper of Low Speed Airfoil
Surface curve, when horizontal flight, washed under propellerslip is forced in plate wing lower surface generate lift while, plate wing upper surface
Also by air draught by washing generation lift under aerofoil profile, the lift of the plate wing is bigger than general fixed-wing；VTOL is had an high regard for
Than being greater than 1, thrust ratio when horizontal flight reaches 5 or more.
Aileron is convex lower flat aerofoil profile, is connected by the lateral hinge at aileron rear portion with fuselage, and aileron is around laterally hinge
Chain is rotated to change the angle of attack；When horizontal flight, the aerofoil profile of aileron can generate profile lift, will by changing the angle of attack of aileron
Cause the variation of the lift and resistance of the plate wing, thus the pitching of control panel wing machine；When aileron turns to positive incidence, aileron can be generated
Lift is impacted, plate wing machine is faced upward, and positive incidence is bigger, and plate wing machine vertical angle is bigger；When aileron turns to negative angle of attack, aileron can be generated
Surge, plate wing machine nutation, negative angle of attack is bigger, and the angle of depression is bigger under plate wing machine；In addition, being produced when the air inlet air-breathing of driving device
Raw air-flow flows through the top airfoil of aileron, and the air velocity of aileron lower aerofoil is identical as aircraft speed, when VTOL
Be zero, even therefore in hang flying speed be equal to zero when, still be able to form negative pressure lift on aileron.
Winglet is aerofoil profile flat in evagination, and for the leading edge of winglet close to driving device, the lower edge of winglet is super
The lower edge of over-driving device, the rear of winglet are more than the rear of the plate wing, the width of the trailing edge profile line of winglet according to
Streamline shape is gradually decreased as zero, and longitudinal hinge is arranged between winglet and the plate wing and is connected, enables sagging winglet
Enough anti-flattenings upper in the case where the profile lift that horizontal flight air-flow generates pushes, become convex lower flat aerofoil profile；It is either horizontal to fly
Row state or VTOL state will generate one partially when the winglet inverted diherdral difference of the left and right sides on the plate wing
Boat torque controls the winglet inverted diherdral control yaw of the left and right sides；When the inverted diherdral of left side winglet is greater than right side flap
When the inverted diherdral of tip winglet, plate wing machine is to left drift；When the inverted diherdral of right side winglet is greater than the lower anti-of left side winglet
When angle, plate wing machine is yawed to the right；The inverted diherdral deviation of left and right sides winglet is bigger, and the yawing of plate wing machine is bigger；
Upper anti-winglet also has the effect of increasing plate wing machine lift, increase wing light-receiving area and reducing the wing to greatest extent carrying.
Driving device is shrouded propeller, among the cabinet that the plate wing, aileron and winglet surround, forms duct wind
Fan, the flow velocity for being blown into the air-flow on wing are directly proportional to the power of driving device.
The width of the plate wing is slightly larger than all propellers and enumerates in full detail width side by side according to diameter D, for all propellers according to
Diameter D enumerates in full detail 1.25 times of width side by side；The length of fixed main wing is 3.5 times of airscrew diameter D, and the length of negative dihedral wing is spiral shell
Revolve 3 times of paddle diameter D.
The taking off of plate wing machine is landed and forced landing is vertical mode, using suspension type cylinder spring undercarriage.
The quantity of the plate wing can increase, and for medium-sized or large-scale man-carrying aircraft, the quantity of wing can be according to horizontal
The mode of formula wing or so wing tandem in couples increases.
Embodiment 3: as shown in Fig. 1-18, this installs the aircraft of driving mechanism below the plate wing, before plate nose of wing
Driving device is arranged in square lower part, high-speed flow is blowed along tangential past plate underwing by driving device, by the air inlet of driving device
Mouth forms negative pressuren zone, puff prot above the plate wing and forms zone of positive pressure in the lower section of the plate wing, using the negative pressuren zone above the plate wing under
The pressure difference lift that the zone of positive pressure of side is formed；Meanwhile the plate wing is set as combined type, and when VTOL, the left and right two of the modular panel wing
The airflow direction of propellerslip is instead changed into the work for playing lift-rising drag reduction vertically downward under side and rear portion by horizontal direction
With the ability that the lift and flight for further increasing VTOL control；When horizontal flight, the plate wing folds consolidating for resistance very little
Determine wing-like, other than pressure difference lift, also generates profile lift；Flight mould is mutually converted between VTOL and horizontal flight
During formula, naturally, operating parameter variation is smooth, manipulation effect does not generate mutation, simultaneous for the control mode transition of operating mechanism
It has cared for horizontal flight and the different of VTOL requires, efficiently solved universal in existing mode conversion VTOL aircraft
The difficult problem of existing offline mode conversion, greatly reduces the manipulation difficulty of VTOL aircraft.
Aileron is arranged in the forward lower part of driving device, and anti-winglet, the plate wing are group under the wingtip setting of fixed main wing
It is box-like, it is divided into four parts, front is fixed-wing, and the left and right sides is the winglet can be anti-below and leveled off, and rear portion is can be following
Negative dihedral wing that is anti-and leveling off, tail portion is rectifying wings；The winglet of the left and right sides is pull-down, and pull-down winglet is in the wing
Hinge is added between tip winglet and fixed main wing to be made as pulling lower anti-and loosen upper anti-flexible or rigid shell structure, is needed
It lower inverse time will directly use traction rope to pull down winglet anti-, and will need inverse time, release traction rope makes winglet in spiral
Paddle slip-stream pressure and/or profile lift push lower anti-；Rear portion negative dihedral wing is collapsible；Collapsible negative dihedral wing uses flexible cloth
Production, is collected negative dihedral wing into inside the plate wing by fold mechanism.
The plate wing is shell structure, is made of titanium alloy frame plus nylon cloth；The contour line of the plate wing is the upper of Low Speed Airfoil
Surface curve, when horizontal flight, washed under propellerslip is forced in plate wing lower surface generate lift while, plate wing upper surface
Also by air draught by washing generation lift under aerofoil profile, the lift of the plate wing is bigger than general fixed-wing；VTOL is had an high regard for
Than being greater than 1, thrust ratio when horizontal flight reaches 5 or more.
Aileron is convex lower flat aerofoil profile, is connected by the lateral hinge at aileron rear portion with fuselage, and aileron is around laterally hinge
Chain is rotated to change the angle of attack；When horizontal flight, the aerofoil profile of aileron can generate profile lift, will by changing the angle of attack of aileron
Cause the variation of the lift and resistance of the plate wing, thus the pitching of control panel wing machine；When aileron turns to positive incidence, aileron can be generated
Lift is impacted, plate wing machine is faced upward, and positive incidence is bigger, and plate wing machine vertical angle is bigger；When aileron turns to negative angle of attack, aileron can be generated
Surge, plate wing machine nutation, negative angle of attack is bigger, and the angle of depression is bigger under plate wing machine；In addition, being produced when the air inlet air-breathing of driving device
Raw air-flow flows through the top airfoil of aileron, and the air velocity of aileron lower aerofoil is identical as aircraft speed, when VTOL
Be zero, even therefore in hang flying speed be equal to zero when, still be able to form negative pressure lift on aileron.
Winglet is thin plate aerofoil profile, and for the leading edge of winglet close to driving device, the lower edge of winglet is more than driving
The lower edge of device, the rear of winglet is close to the rear of the plate wing, and the width of the trailing edge profile line of winglet is according to streamlined
Shape is gradually decreased as zero；Either level flight condition or VTOL state, when the winglet inverted diherdral of the left and right sides
When different, a yawing will be generated on the plate wing, control the winglet inverted diherdral control yaw of the left and right sides；Work as left side
When the inverted diherdral of winglet is greater than the inverted diherdral of right side winglet, plate wing machine is to left drift；When under the winglet of right side
When dihedral is greater than the inverted diherdral of left side winglet, plate wing machine is yawed to the right；The inverted diherdral deviation of left and right sides winglet is got over
Greatly, the yawing of plate wing machine is bigger；Upper anti-winglet, which also has, to be increased plate wing machine lift, increases wing light-receiving area
The effect that the wing carries is reduced to greatest extent.
Driving device is turbojet engine, among the cabinet that the plate wing, aileron and winglet surround, forms duct wind
Fan, the flow velocity for being blown into the air-flow on wing are directly proportional to the power of driving device.
The width of the plate wing is slightly larger than all propellers and enumerates in full detail width side by side according to diameter D, for all propellers according to
Diameter D enumerates in full detail 1.1 times of width side by side；The length of fixed main wing is 4 times of airscrew diameter D, and the length of negative dihedral wing is spiral
2.5 times of paddle diameter D.
The taking off of plate wing machine is landed and forced landing is vertical mode, using suspension type cylinder spring undercarriage.
The quantity of the plate wing can increase, and for medium-sized or large-scale man-carrying aircraft, the quantity of wing can be according to horizontal
The mode of formula wing or so wing tandem in couples increases.
Embodiment 4: as shown in Fig. 1-18, this installs the aircraft of driving mechanism below the plate wing, in fixed main wing leading edge
Forward lower part be arranged driving device, high-speed flow is blowed along tangential past plate underwing by driving device, by driving device
Air inlet forms negative pressuren zone, puff prot above the plate wing and forms zone of positive pressure in the lower section of the plate wing, utilizes the negative pressuren zone above the plate wing
The pressure difference lift formed with the zone of positive pressure of lower section；Meanwhile the plate wing is set as combined type, and when VTOL, a left side for the modular panel wing
Anti- the airflow direction of propellerslip is changed into vertically downward by horizontal direction under right two sides and rear portion, plays lift-rising drag reduction
Effect further increases the lift of VTOL and the ability of flight control；When horizontal flight, the plate wing is folded as resistance very little
Fixed wing-like also generates profile lift other than pressure difference lift；The mutually conversion flight between VTOL and horizontal flight
During mode, naturally, operating parameter variation is smooth, manipulation effect does not generate mutation for the control mode transition of operating mechanism,
It has taken into account horizontal flight and the different of VTOL requires, efficiently solved general in existing mode conversion VTOL aircraft
The problem difficult all over the conversion of existing offline mode, greatly reduces the manipulation difficulty of VTOL aircraft.
Aileron is arranged in the forward lower part of driving device, and anti-winglet, the plate wing are group under the wingtip setting of fixed main wing
It is box-like, it is divided into four parts, front is fixed main wing, and the left and right sides is can be anti-below and the winglet that levels off, and rear portion is for can
Negative dihedral wing that is anti-below and leveling off, tail portion is rectifying wings；The winglet of the left and right sides is pull-down, and pull-down winglet is
It is added between winglet and fixed main wing anti-under hinge is made as pulling and loosens upper anti-flexible or rigid shell structure,
Lower inverse time is needed, directly uses traction rope to pull down winglet anti-, needs inverse time, release traction rope makes winglet exist
Propellerslip pressure and/or profile lift push lower anti-；Rear portion negative dihedral wing is sliding；Sliding negative dihedral wing is using rigidity
Negative dihedral wing is divided into can be overlapped several sections, folds several sections of negative dihedral wings by slipping mechanism and receive for one section by material production
It hides into inside main wing.
The plate wing is shell structure, is made of carbon fiber cloth clamp cellular composite material；The contour line of the plate wing is Low Speed Airfoil
Upper surface curve, when horizontal flight, washed under propellerslip is forced in plate wing lower surface generate lift while, table on the plate wing
Also by air draught by washing generation lift under aerofoil profile, the lift of the plate wing is bigger than general fixed-wing in face；VTOL pushes away
Again than being greater than 1, thrust ratio when horizontal flight reaches 5 or more.
Aileron is convex lower flat aerofoil profile, is connected by the lateral hinge at aileron rear portion with fuselage, and aileron is around laterally hinge
Chain is rotated to change the angle of attack；When horizontal flight, the aerofoil profile of aileron can generate profile lift, will by changing the angle of attack of aileron
Cause the variation of the lift and resistance of the plate wing, thus the pitching of control panel wing machine；When aileron turns to positive incidence, aileron can be generated
Lift is impacted, plate wing machine is faced upward, and positive incidence is bigger, and plate wing machine vertical angle is bigger；When aileron turns to negative angle of attack, aileron can be generated
Surge, plate wing machine nutation, negative angle of attack is bigger, and the angle of depression is bigger under plate wing machine；In addition, being produced when the air inlet air-breathing of driving device
Raw air-flow flows through the top airfoil of aileron, and the air velocity of aileron lower aerofoil is identical as aircraft speed, when VTOL
Be zero, even therefore in hang flying speed be equal to zero when, still be able to form negative pressure lift on aileron.
Winglet is aerofoil profile flat in evagination, and for the leading edge of winglet close to driving device, the lower edge of winglet is super
The lower edge of over-driving device, the rear of winglet are more than the rear of the plate wing, the width of the trailing edge profile line of winglet according to
Streamline shape is gradually decreased as zero, and longitudinal hinge is arranged between winglet and the plate wing and is connected, enables sagging winglet
Enough anti-flattenings upper in the case where the profile lift that horizontal flight air-flow generates pushes, become convex lower flat aerofoil profile；It is either horizontal to fly
Row state or VTOL state will generate one partially when the winglet inverted diherdral difference of the left and right sides on the plate wing
Boat torque controls the winglet inverted diherdral control yaw of the left and right sides；When the inverted diherdral of left side winglet is greater than right side flap
When the inverted diherdral of tip winglet, plate wing machine is to left drift；When the inverted diherdral of right side winglet is greater than the lower anti-of left side winglet
When angle, plate wing machine is yawed to the right；The inverted diherdral deviation of left and right sides winglet is bigger, and the yawing of plate wing machine is bigger；
Upper anti-winglet also has the effect of increasing plate wing machine lift, increase wing light-receiving area and reducing the wing to greatest extent carrying.
Driving device is fanjet, among the cabinet that the plate wing, aileron and winglet surround, forms duct wind
Fan, the flow velocity for being blown into the air-flow on wing are directly proportional to the power of driving device.
The width of the plate wing is slightly larger than all propellers and enumerates in full detail width side by side according to diameter D, for all propellers according to
Diameter D enumerates in full detail 1.15 times of width side by side；The length of fixed main wing is 3.5 times of airscrew diameter D, and the length of negative dihedral wing is spiral shell
Revolve 3.5 times of paddle diameter D.
The taking off of plate wing machine is landed and forced landing is vertical mode, using suspension type cylinder spring undercarriage.
The quantity of the plate wing can increase, and for medium-sized or large-scale man-carrying aircraft, the quantity of wing can be according to horizontal
The mode of formula wing or so wing tandem in couples increases.
Embodiment 5: as shown in Fig. 1-18, this installs the aircraft of driving mechanism below the plate wing, in fixed main wing leading edge
Forward lower part be arranged driving device, high-speed flow is blowed along tangential past plate underwing by driving device, by driving device
Air inlet forms negative pressuren zone, puff prot above the plate wing and forms zone of positive pressure in the lower section of the plate wing, utilizes the negative pressuren zone above the plate wing
The pressure difference lift formed with the zone of positive pressure of lower section；Meanwhile the plate wing is set as combined type, and when VTOL, a left side for the modular panel wing
Anti- the airflow direction of propellerslip is changed into vertically downward by horizontal direction under right two sides and rear portion, plays lift-rising drag reduction
Effect further increases the lift of VTOL and the ability of flight control；When horizontal flight, the plate wing is folded as resistance very little
Fixed wing-like also generates profile lift other than pressure difference lift；The mutually conversion flight between VTOL and horizontal flight
During mode, naturally, operating parameter variation is smooth, manipulation effect does not generate mutation for the control mode transition of operating mechanism,
It has taken into account horizontal flight and the different of VTOL requires, efficiently solved general in existing mode conversion VTOL aircraft
The problem difficult all over the conversion of existing offline mode, greatly reduces the manipulation difficulty of VTOL aircraft.
Aileron is arranged in the forward lower part of driving device, and anti-winglet, the plate wing are group under the wingtip setting of fixed main wing
It is box-like, it is divided into four parts, front is fixed main wing, and the left and right sides is can be anti-below and the winglet that levels off, and rear portion is for can
Negative dihedral wing that is anti-below and leveling off, tail portion is rectifying wings；The winglet of the left and right sides is pull-down, and pull-down winglet is
It is added between winglet and fixed main wing anti-under hinge is made as pulling and loosens upper anti-flexible or rigid shell structure,
Lower inverse time is needed, directly uses traction rope to pull down winglet anti-, needs inverse time, release traction rope makes winglet exist
Propellerslip pressure and/or profile lift push lower anti-；Rear portion negative dihedral wing is enclosure-type；Enclosure-type negative dihedral wing utilizes sheet
The left and right facade of fuselage is collected, and the shaft of negative dihedral wing is located in the plane of sheet fuselage, and negative dihedral wing is backward when horizontal flight or so
Fang Zhanping is collapsed in the plane of sheet fuselage and is reduced resistance, and negative dihedral wing be unfolded and sheet machine forwards when VTOL or so
The plane of body is vertical, horizontal gas flow enclosing is played the role of increasing lift downwards, enclosure-type negative dihedral wing also acts as vertical end
The regulating and controlling effect of the wing.
The plate wing is shell structure, is made of titanium alloy frame plus nylon cloth；The contour line of the plate wing is the upper of Low Speed Airfoil
Surface curve, when horizontal flight, washed under propellerslip is forced in plate wing lower surface generate lift while, plate wing upper surface
Also by air draught by washing generation lift under aerofoil profile, the lift of the plate wing is bigger than general fixed-wing；VTOL is had an high regard for
Than being greater than 1, thrust ratio when horizontal flight reaches 5 or more.
Aileron is convex lower flat aerofoil profile, is connected by the lateral hinge at aileron rear portion with fuselage, and aileron is around laterally hinge
Chain is rotated to change the angle of attack；When horizontal flight, the aerofoil profile of aileron can generate profile lift, will by changing the angle of attack of aileron
Cause the variation of the lift and resistance of the plate wing, thus the pitching of control panel wing machine；When aileron turns to positive incidence, aileron can be generated
Lift is impacted, plate wing machine is faced upward, and positive incidence is bigger, and plate wing machine vertical angle is bigger；When aileron turns to negative angle of attack, aileron can be generated
Surge, plate wing machine nutation, negative angle of attack is bigger, and the angle of depression is bigger under plate wing machine；In addition, being produced when the air inlet air-breathing of driving device
Raw air-flow flows through the top airfoil of aileron, and the air velocity of aileron lower aerofoil is identical as aircraft speed, when VTOL
Be zero, even therefore in hang flying speed be equal to zero when, still be able to form negative pressure lift on aileron.
Winglet is aerofoil profile flat in evagination, and for the leading edge of winglet close to driving device, the lower edge of winglet is super
The lower edge of over-driving device, the rear of winglet close to the plate wing rear, the width of the trailing edge profile line of winglet according to
Streamline shape is gradually decreased as zero, and longitudinal hinge is arranged between winglet and the plate wing and is connected, enables sagging winglet
Enough anti-flattenings upper in the case where the profile lift that horizontal flight air-flow generates pushes, become convex lower flat aerofoil profile；It is either horizontal to fly
Row state or VTOL state will generate one partially when the winglet inverted diherdral difference of the left and right sides on the plate wing
Boat torque controls the winglet inverted diherdral control yaw of the left and right sides；When the inverted diherdral of left side winglet is greater than right side flap
When the inverted diherdral of tip winglet, plate wing machine is to left drift；When the inverted diherdral of right side winglet is greater than the lower anti-of left side winglet
When angle, plate wing machine is yawed to the right；The inverted diherdral deviation of left and right sides winglet is bigger, and the yawing of plate wing machine is bigger；
Upper anti-winglet also has the effect of increasing plate wing machine lift, increase wing light-receiving area and reducing the wing to greatest extent carrying.
Driving device is that turbo oar engine is located among the cabinet that the plate wing, aileron and winglet surround, and forms duct wind
Fan, the flow velocity for being blown into the air-flow on wing are directly proportional to the power of driving device.
The width of the plate wing is slightly larger than all propellers and enumerates in full detail width side by side according to diameter D, for all propellers according to
Diameter D enumerates in full detail 1.2 times of width side by side；The length of fixed main wing is 4 times of airscrew diameter D, and the length of negative dihedral wing is spiral
4 times of paddle diameter D.
The taking off of plate wing machine is landed and forced landing is vertical mode, using suspension type cylinder spring undercarriage.
The quantity of the plate wing can increase, and for medium-sized or large-scale man-carrying aircraft, the quantity of wing can be according to horizontal
The mode of formula wing or so wing tandem in couples increases.
Technology contents of the invention are described above in conjunction with attached drawing, but protection scope of the present invention be not limited to it is described
Content within the knowledge of one of ordinary skill in the art can also be in the premise for not departing from present inventive concept
Under technology contents of the invention are made a variety of changes, all within the spirits and principles of the present invention, any modification for being made, etc.
With replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of aircraft for installing driving mechanism below the plate wing, it is characterised in that: in the fixed up-front forward lower part of main wing
It is arranged driving device (3), aileron (1) is arranged in the forward lower part of driving device (3), and the plate wing (4) is divided into four parts, and front is to fix
The winglet (5) can be anti-below and leveled off is arranged in main wing, the left and right sides of fixed main wing, and the rear portion of fixed main wing is can be following
Negative dihedral wing (9) that is anti-and leveling off, tail portion are fixed rectifying wings (12).
2. the aircraft according to claim 1 for installing driving mechanism below the plate wing, it is characterised in that: described fixed main
It can below instead be pull-down with the winglet (5) leveled off at left and right sides of the wing, the fixed main wing rear portion can be following anti-and be leveled off
Negative dihedral wing (9) be pull-down negative dihedral wing, divide formula negative dihedral wing, collapsible negative dihedral wing, sliding negative dihedral wing, enclosure-type negative dihedral wing equally
In any one.
3. the aircraft according to claim 2 for installing driving mechanism below the plate wing, it is characterised in that: the wingtip is small
The wing (5) be pull-down be added between winglet (5) and fixed main wing winglet hinge (17) be made as under pulling instead and
Loosen upper anti-flexible or rigid shell structure；The pull-down negative dihedral wing is added between negative dihedral wing (9) and fixed main wing
Negative dihedral wing hinge (8) is made as anti-under pulling and loosens upper anti-flexible or rigid shell structure；Dividing formula negative dihedral wing equally is edge
Main wing is divided into two by horizontal direction, is divided into the upper plate wing and the lower plate wing, and the upper plate wing is movable wing, and the lower plate wing is fixed-wing, upper plate
It is connected between the wing and fuselage by rocking bar, operating mechanism drive rocker makes the upper plate wing around the swing of the lower plate wing；Under collapsible
The anti-wing is made of flexible cloth, is collected by fold mechanism into plate wing inside or expansion；Sliding negative dihedral wing is using rigid material
Material production, is divided into can be overlapped several sections, folds several sections of negative dihedral wings by slipping mechanism and collect for one section into main wing
Portion or lower anti-expansion；Enclosure-type negative dihedral wing collects negative dihedral wing using the left and right facade of sheet fuselage, and the shaft of negative dihedral wing is located at piece
In the plane of shape fuselage.
4. the aircraft according to claim 1,2 or 3 for installing driving mechanism below the plate wing, it is characterised in that: described
The plate wing (4) is shell structure, is made of high strength composite or high strength light metal framework plus nylon cloth；The plate wing (4)
Contour line be Low Speed Airfoil upper surface curve, when horizontal flight, the plate wing (4) upper surface by air draught by aerofoil profile under
While washing generation lift, generation lift is washed in the case where propellerslip can also be forced in the plate wing (4) lower surface, is obtained than general
The bigger lift of fixed-wing, the thrust ratio of VTOL are greater than 1, and thrust ratio when horizontal flight is greater than 5.
5. the aircraft according to claim 1 or 2 for installing driving mechanism below the plate wing, it is characterised in that: the wing
Tip winglet (5) is aerofoil profile flat in thin plate aerofoil profile or evagination, and the leading edge of winglet (5) is super close to driving device (3), lower edge
Rear of the lower edge, rear of over-driving device (3) near or above the plate wing (4), the width of the trailing edge profile line of winglet (5)
Zero is gradually decreased as according to streamline shape.
6. the aircraft according to claim 1 for installing driving mechanism below the plate wing, it is characterised in that: the aileron
(1) it is convex lower flat aerofoil profile, is connected by the lateral hinge (2) at aileron (1) rear portion with fuselage, aileron (1) is around laterally hinge
Chain (2) is rotated to change the angle of attack.
7. the aircraft according to claim 1 for installing driving mechanism below the plate wing, it is characterised in that: the driving dress
(3) are set among the cabinet that fixed main wing, aileron (1) are surrounded with winglet (5), form ducted fan；Driving device (3)
It is any one of propeller, shrouded propeller, turbojet engine, fanjet, turbo oar engine, is blown into machine along tangential
The flow velocity of the air-flow of underwing and the power of driving device are directly proportional.
8. the aircraft according to claim 1 or 2 for installing driving mechanism below the plate wing, it is characterised in that: described solid
The width for determining main wing is all propellers according to 1.1-1.5 times of the diameter D width enumerated in full detail side by side, and the length of fixed main wing is greater than
Or it is equal to 3 times of airscrew diameter D, the length of negative dihedral wing (9) is greater than or equal to 2 times of airscrew diameter D.
9. the aircraft according to claim 1 for installing driving mechanism below the plate wing, it is characterised in that: the plate wing
(4) the taking off of aircraft that constitutes is landed and forced landing is vertical mode, using suspension type cylinder spring undercarriage.
10. the aircraft according to claim 1-3 for installing driving mechanism below the plate wing, it is characterised in that:
The quantity of the plate wing (4) can according to need increase, and the quantity of the plate wing (4) can be 1, constitute the wing of a width overhead type,
Or 2 multiple, constitute bilateral symmetry pressure-bearing type several wings, for medium-sized or large-scale man-carrying aircraft, the number of wing
Amount increases in the way of pressure-bearing type wing or so wing in couples tandem.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811081348.2A CN108945482A (en) | 2018-09-17 | 2018-09-17 | A kind of aircraft for installing driving mechanism below the plate wing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811081348.2A CN108945482A (en) | 2018-09-17 | 2018-09-17 | A kind of aircraft for installing driving mechanism below the plate wing |
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| CN108945482A true CN108945482A (en) | 2018-12-07 |
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| CN106741842A (en) * | 2016-12-30 | 2017-05-31 | 马晓辉 | A kind of three-stage fixed-wing unmanned plane for being provided with protection device |
| CN107244410A (en) * | 2017-06-13 | 2017-10-13 | 昆明鞘翼科技有限公司 | A kind of method of wing coordinated flight state using imitative beetle elytrum |
| CN108408044A (en) * | 2018-02-10 | 2018-08-17 | 昆明鞘翼科技有限公司 | Utilize the tangential method for realizing aircraft VTOL and flight of blowing of aerofoil |
| CN208855877U (en) * | 2018-09-17 | 2019-05-14 | 昆明鞘翼科技有限公司 | A kind of aircraft for installing driving mechanism below the plate wing |
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2018
- 2018-09-17 CN CN201811081348.2A patent/CN108945482A/en active Pending
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| CN205768418U (en) * | 2016-05-21 | 2016-12-07 | 龙川 | Modified model distributed electric ducted fan wing flap high-lift system and hovercar thereof |
| CN106741842A (en) * | 2016-12-30 | 2017-05-31 | 马晓辉 | A kind of three-stage fixed-wing unmanned plane for being provided with protection device |
| CN107244410A (en) * | 2017-06-13 | 2017-10-13 | 昆明鞘翼科技有限公司 | A kind of method of wing coordinated flight state using imitative beetle elytrum |
| CN108408044A (en) * | 2018-02-10 | 2018-08-17 | 昆明鞘翼科技有限公司 | Utilize the tangential method for realizing aircraft VTOL and flight of blowing of aerofoil |
| CN208855877U (en) * | 2018-09-17 | 2019-05-14 | 昆明鞘翼科技有限公司 | A kind of aircraft for installing driving mechanism below the plate wing |
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