CN208855877U - A kind of aircraft for installing driving mechanism below the plate wing - Google Patents

Abstract

The utility model 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 utility model 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

A kind of aircraft for installing driving mechanism below the plate wing

Technical field

The utility model 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.

Utility model content

The technical problems to be solved in the utility model is for existing VTOL aircraft inefficiency, thrust ratio Generally less than 1, manipulation is complicated, safety is poor, horizontal flight mode and the conversion of VTOL mode are not smooth enough naturally, and now There is the problems such as plate wing machine wing drag is excessive, vertical lift is insufficient and tangential inflatable gas stream dissipates, proposes one kind below the plate wing The aircraft for installing driving mechanism after increasing lift and realizing VTOL, and can reduce resistance and realize high-speed flight, makes Plate wing machine is more safe and efficient, compact, stable, reasonable.

In order to solve the above technical problems, the utility model provides a kind of aircraft that driving mechanism is installed below the plate wing, Driving device is set in the forward lower part of plate nose of wing, high-speed flow is blowed along tangential past plate underwing by driving device, by The air inlet of driving 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, using on the plate wing The pressure difference lift that the negative pressuren zone of side and the zone of positive pressure of lower section are formed can greatly improve the flight efficiency and thrust ratio of plate wing machine. The forward lower part of driving device is arranged aileron, and the plate wing is combined type, when VTOL, the left and right sides and rear portion of the modular panel wing Anti- the airflow direction of propellerslip is changed into vertically downward by horizontal direction down, plays the role of lift-rising drag reduction, further Improve 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, Other than pressure difference lift, profile lift is further generated；Offline mode is mutually converted between VTOL and horizontal flight In the process, naturally, operating parameter variation is smooth, manipulation effect does not generate mutation, takes into account for the control mode transition of operating mechanism Horizontal flight and the different of VTOL require, and efficiently solve generally existing in existing mode conversion VTOL aircraft The difficult problem of offline mode conversion, greatly reduce the manipulation difficulty of VTOL aircraft.The plate wing is divided into four parts, preceding Portion 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 Negative dihedral wing, tail portion is fixed rectifying wings；Left and right sides winglet is pull-down, and hinge is added between winglet and main wing Chain is made as pulling lower anti-and loosens upper anti-flexible or rigid shell structure, by the pulling of traction rope or traction mechanism or The lower anti-or upper anti-of negative dihedral wing is realized in release, needs that traction rope is directly used to pull down winglet lower inverse time anti-, needs Inverse time release traction rope keeps winglet upper anti-in the case where propellerslip pressure and/or profile lift push；The negative dihedral wing at rear portion For pull-down negative dihedral wing, divide formula negative dihedral wing equally, collapsible negative dihedral wing, sliding negative dihedral wing, any one in enclosure-type negative dihedral wing Kind (can specifically select according to actual needs)；Pull-down negative dihedral wing is to add shaft between negative dihedral wing and main wing to be made as under pulling Instead and loosen upper anti-flexible or rigid shell structure, negative dihedral wing is realized by the pulling or release of traction rope or traction mechanism It is lower anti-or upper anti-, need that traction rope is directly used to pull down negative dihedral wing lower inverse time anti-, inverse time release traction rope needed to make Negative dihedral 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 The upper plate 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, behaviour Vertical mechanism drive rocker makes the upper plate wing around the swing of the lower plate wing, when horizontal flight, swings before upper plate flapwise and closes with the lower plate wing And reduce resistance realization high-speed flight for the plate wing of complete convex lower flat aerofoil profile, when VTOL, the upper plate wing is started It is significantly swung to the back lower place, 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 uses Flexible cloth production is collected negative dihedral wing into plate wing inside or expansion by fold mechanism；Sliding negative dihedral wing is using rigid material Negative dihedral wing is divided into can be overlapped several sections, folds several sections of negative dihedral wings by slipping mechanism and collect for one section by material production Into main wing inside or lower anti-expansion；Enclosure-type negative dihedral wing collects negative dihedral wing using the left and right facade of sheet fuselage, and negative dihedral wing turns Axle position in the plane of sheet fuselage, when horizontal flight or so negative dihedral wing rearward flatten in the plane for collapsing in sheet fuselage and Reduce resistance, negative dihedral wing is unfolded vertical with the plane of sheet fuselage forwards when VTOL or so, by horizontal gas flow enclosing to Play the role of down 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 utility model, the fuselage of plate wing machine is sheet fuselage, the plate wing, aileron and winglet define one it is larger Cabinet, when horizontal flight can increase stability, and the VTOL plate wing anti-at present and the cabinet form an air-flow and contain Road guides the Jet Stream of driving device downwards, and effect effect in ground is obvious, and the elasticity of air can be increased in takeoff and landing, Mitigate 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 can delay Drop is landed.In addition, forward air inlet, the VTOL mode of rear exhaust, have made the motion path of air-flow in order, compared with vertically downward It is vented the landing mode of (such as helicopter), the motion path of air-flow is more scientific and reasonable, avoids ground wind-drifting sand to sight Block and the damage to machine.The flight control of plate wing machine is small by the inverted diherdral of operating-controlling mechanism adjustment negative dihedral wing, wingtip The power of the inverted diherdral of the wing, the angle of attack of aileron and driving device is realized；When horizontal flight, the pitching of plate wing machine is by adjusting aileron The angle of attack realize that or realize by adjusting the inverted diherdral of rear portion negative dihedral wing, the yaw of plate wing machine passes through the differential adjustment left and right sides 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 is slightly upper anti-, when yawing to the right right side negative dihedral wing deviate the slightly lower anti-negative dihedral wing of left side simultaneously in midpoint deviate midpoint slightly on It is anti-；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 passes through negative dihedral wing Reduce inverted diherdral to realize, the movement backward of plate wing machine by negative dihedral wing increase inverted diherdral to 100-120 ° (about 110 ° or so) i.e. It can be achieved, 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 weight The heart is lower, and VTOL pitching moment in-flight and rolling moment are compensated by the drift angle autobalance of plate wing machine center of gravity, no Need special mechanism controls.

The utility model 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 is high, wing wing load is low, safety and stability, structure is simple, manipulation is easy, low in cost, is easy to general And the advantages that.

Detailed description of the invention

Fig. 1 is the utility model bottom driving plate wing machine level flight condition schematic side view.

Fig. 2 is the utility model bottom driving plate wing machine level flight condition schematic top plan view.

Fig. 3 is the utility model bottom driving plate wing machine level flight condition schematic rear view.

Fig. 4 is the utility model bottom driving plate wing machine VTOL state schematic side view.

Fig. 5 is the utility model bottom driving plate wing machine VTOL state schematic top plan view.

Fig. 6 is the utility model bottom driving plate wing machine VTOL state schematic rear view.

Fig. 7 is the utility model bottom driving plate wing machine shell structure plate wing schematic diagram.

Fig. 8 is that the utility model bottom driving plate wing machine airscrew diameter D and the relationship of plate chord degree and negative dihedral wing length are shown It is intended to.

Fig. 9 is that the utility model bottom driving plate wing machine horizontal flight moves upwards control principle schematic diagram.

Figure 10 is that the utility model bottom driving plate wing machine horizontal flight moves downward control principle schematic diagram.

Figure 11 is that the utility model bottom driving plate wing machine horizontal flight moves right control principle schematic diagram.

Figure 12 is that the utility model bottom driving plate wing machine horizontal flight moves downward control principle schematic diagram.

Figure 13 is that the utility model bottom driving plate wing machine VTOL travels forward control principle schematic diagram.

Figure 14 is the utility model bottom driving plate wing machine VTOL motion control schematic illustration backward.

Figure 15 is that the utility model bottom driving plate wing machine VTOL moves right control principle schematic diagram.

Figure 16 is that the utility model bottom driving plate wing machine VTOL moves downward control principle schematic diagram.

Figure 17 is the utility model bottom driving plate wing machine suspension type cylinder spring undercarriage landing schematic illustration.

Figure 18 is that the utility model bottom driving plate wing machine suspension type cylinder spring undercarriage 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

Specific embodiment of the present utility model is further described in detail with reference to the accompanying drawing, is not specified in embodiment Technology or product, be the prior art or can by purchase obtain conventional products.

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 plate wing machine can increase, and for medium-sized or large-scale man-carrying aircraft, the quantity of wing can be according to cross The mode for setting 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.

It is described above in conjunction with technology contents of the attached drawing to the utility model, but the protection scope of the utility model is not It is limited to the content, it within the knowledge of one of ordinary skill in the art, can also be not depart from this practical new The technology contents of the utility model are made a variety of changes under the premise of type objective, it is all the spirit and principles of the utility model it Any modification, equivalent substitution, improvement and etc. that are interior, being done, should be included within the scope of protection of this utility model.

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.