CN208021738U - It is a kind of to realize the dumping tower tray formula aircraft of VTOL and flight using tangential blow of aerofoil - Google Patents

Abstract

The utility model discloses a kind of dumping tower tray formula aircraft using the tangential realization VTOL and flight of blowing of aerofoil, belongs to technical field of aerospace.Including supporting mechanism, fuselage, wing, driving device and operating-controlling mechanism, several driving devices are arranged above the leading edge of a wing, driving device is hingedly fixed on wing and can longitudinally vert, and towards upper surface of the airfoil, wing is directly anchored on fuselage the puff prot of driving device；High-speed flow is blown into upper surface of the airfoil along tangential by driving device, the air for flowing quickly through wing upper table and following table forms current difference and generates airfoil lift, change the air blowing angle [alpha] that driving device is blown to aerofoil surface by manipulating driving device, change blowing direction of the high-speed flow with respect to fuselage, coordinate the increase and decrease of driving device power, realizes VTOL, hovering, forward or backward flight etc. of aircraft.With two kinds of operating modes of compatible VTOL and high-speed flight, flight efficiency is high, it is simple in structure, manipulation is intuitive, safe and reliable the advantages that.

Description

It is a kind of to realize the dumping tower tray formula aircraft of VTOL and flight using tangential blow of aerofoil

Technical field

It is especially a kind of to realize VTOL and flight using the tangential air blowing of aerofoil the utility model is related to a kind of aircraft Dumping tower tray formula aircraft, belong to aircraft technical field.

Background technology

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（Such as spray 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 the inherent shortcomings that some can not overcome for VTOL aircraft.First, efficiency is too low, use now VTOL aircraft thrust-weight ratio generally be equal to even greater than 1, flight efficiency is low, is generally less than with Fixed-Wing 0.5 thrust-weight ratio is fairly obvious compared to gap；It is limited second is that being necessarily less than velocity of sound by wing tip absolute velocity, rotary wing aircraft Theoretical velocity no more than 420 kilometers/hour, flying speed has the limit；Third, rotor blade waves generation mechanical oscillation, Increasing the abrasion of hinge makes reliability always be not so good as Fixed-Wing, and reliability is low；Fourth, both sides rotor lift is uneven It can cause rotary wing aircraft that roll occurs, will topple in seconds out of control, roll stability is poor；Fifth, the rotation of helicopter The wing had both provided the mobility of flight, while also resulting in the complexity of flight manipulation, and manipulation is complicated so that manipulation load is much More than fixed wing aircraft, the probability of human error is increased；Sixth, rotor diameter and rotating speed by tip velocity no more than sound The limitation of speed, the general maximum of rotor diameter is exactly more than ten meters, and aircraft is size-constrained, can not be done big；Seventh, although helicopter is sent out Opened up nearly 70 years, but in flight mechanism inaccurate coordination, be filled with geneogenous contradiction, flight mechanism imbalance；Eigth, 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.And the slip-stream lift of aerofoil is utilized to realize that VTOL can be compatible with vertical rise very well Drop and two kinds of offline mode of horizontal flight, are the new developing direction of VTOL aircraft.

Invention content

The technical problems to be solved in the utility model be in order to overcome existing VTOL aircraft it is inefficient and The complicated drawback of flight manipulation proposes a kind of dumping tower tray formula aircraft for realizing VTOL and flight using the tangential air blowing of aerofoil, So that aircraft is compatible with two kinds of flight operating modes of VTOL and high-speed flight, simplifies flight manipulation, improve the flight of aircraft The thrust-weight ratio of efficiency, aircraft can be reduced to 0.2 hereinafter, improving 5 times or more than existing VTOL aircraft.

It realizing VTOL in order to solve the above technical problems, the utility model offer is a kind of using the tangential air blowing of aerofoil and flies Capable dumping tower tray formula aircraft, including supporting mechanism 1, seat 2, fuselage 3, wing 5, driving device 6, hinge mount 7 and control stick 8, Several driving devices 6 are arranged above 5 leading edge of aircraft wing, and driving device 6 is hingedly fixed in wing by hinge mount 7 It can realize around hinge axis 4 on 5 and longitudinally vert, the puff prot of driving device 6 incites somebody to action high speed towards upper surface of the airfoil Air-flow is blown into upper surface of the airfoil along tangential, and wing 5 is directly anchored on fuselage 3；By driving device 6 by high-speed flow along tangential It is blown into upper surface of the airfoil, is allowed to flow quickly through upper surface of the airfoil, utilizes the stream for the air for flowing through upper surface of the airfoil and lower surface Speed difference forms airfoil lift；The air blowing angle [alpha] blown to aerofoil surface by changing driving device, to change high-speed flow The flow direction of opposite fuselage, coordinates the increase and decrease of 6 power of driving device, makes airfoil lift S and the pulling force F of driving device in level The resultant force in direction cancel out each other and the resultant force of vertical direction greater than, equal to or less than aircraft the sum of gravity W and resistance Z from And realize the VTOL or hovering of aircraft, make airfoil lift S and the pulling force F of driving device in the resultant force etc. of vertical direction In aircraft gravity W and resultant force in the horizontal direction be more than or less than aircraft resistance Z to realize aircraft forward Flight is flown backward.

The wing 5 is the overhead type wing positioned at body upper, either positioned at the pressure-bearing type wing of fuselage both sides or Bottom type wing below fuselage.The quantity of the wing can increase, for unmanned plane or light passenger's aircraft, One width overhead type wing can be met the requirements；And for medium-sized or large-scale man-carrying aircraft, the quantity of the wing can be by Increase according to the mode of pressure-bearing type wing or so wing tandem in couples, to generate enough lift in VTOL.

The wing 5 is wide string wing, and wing aspect ratio can be less than 2, even less than 1；Generally it is the big of low wing load Area continuous surface wing enables aircraft to realize slow drop forced landing as descending slowly and lightly leaf when failure occurs, when left and right machine When the wing is installed as aircraft can also being enable to descend slowly and lightly in the air after the aerodynamic configurations such as V-arrangement, Y shape or T shapes with certain upper counterangle Enough to become a full member automatically, the upper counterangle can specifically determine size according to actual needs.

Large-scale winglet should be arranged in the wingtip of the wing 5, to improve lift when aircraft VTOL and reduce induction Resistance, the minimum constructive height h and wingspan length l of winglet and the relationship of chord length b should meet following condition：Work as l/b>When=2, h=b ×(b/l)；Work as l/b<When=2, h=b × (1-0.25 × l/b）.

The shape of the wing 5 is diamond shape, triangle, rectangle, any one of trapezoidal or other shapes, wing shapes Limiting factor is reduced, and specifically can carry out adaptive change according to different actual demands with flexible design；The wing of wing 5 Type is lower flat any one of convex aerofoil profile or recessed convex aerofoil profile, symmetrical airfoil, S aerofoil profiles or flat profile, can be with Carry out adaptive change according to different needs, that is, after using upper surface of the airfoil air blowing lift-rising, the requirement for profile lift It substantially reduces, the thickness of wing substantially reduces therewith, it might even be possible to use flat profile so that the flight resistance of wing drops significantly It is low, and the use of flat profile can make wing area be made very big, and enough spaces are provided for the installation of photovoltaic cell.

The wing 5 divides for left and right wing, and several driving devices 6 are divided to left and right two groups of symmetric arrays in left and right wing 5 Above leading edge, specific number can determine according to actual needs, and 1-10 small drive device can generally be arranged on each wing, The number of driving device is more, and air-flow is more flat, and more close to aerofoil, the effect of lift-rising is better.

The driving device 6 is propeller, shrouded propeller, turbojet engine, fanjet, turbo oar engine, blows Any one of gas jets or leading edge blown flap, the air inlet or propeller of driving device 6 are located above the leading edge of a wing Rear portion, distance away from the leading edge of a wing are more than the diameter of air inlet or propeller and are less than 1/5th chord lengths, driving device 6 into The lower edge of gas port or propeller is close to aerofoil.

The driving device 6 is preferably in flat to the tangential air-flow blowed of wing 5, and is close to the wing of wing 5 as possible Face, it may be necessary to install cowling panel additional in driving device to improve blowing effect, the i.e. flowing by controlling tangential air blowing air-flow Form is allowed to blow to upper surface of the airfoil in flat, and flat air-flow is made close to aerofoil, to be obtained most from raising lift as possible Good lift-rising effect, the speed that air-flow flows through aerofoil is higher, and the chord length that air-flow flows through aerofoil is longer, and the lift of generation is bigger；Wing Chord length it is longer, the lift-rising effect of tangential air blowing is better.

After tangential air blowing lift-rising, the VTOL efficiency of driving device 6 greatly improves, and the thrust-weight ratio of aircraft can To be reduced to K=0.05, hence it is evident that be better than existing VTOL aircraft.The driving device 6 is blown into the gas of upper surface of the airfoil The flow direction of the opposite fuselage of stream can be adjusted by changing the air blowing angle [alpha] that driving device is blown to aerofoil surface, be led to It crosses adjustment α angles and changes the flow direction of driving device blow flow and reach balance to manipulate the power of all directions, while by aviation Device wake flow blows off VTOL region, reaches the good result for the security context for improving VTOL.

The flow velocity that the driving device 6 is blown into the air-flow of 5 upper surface of wing is directly proportional to the power of driving device, and machine The air velocity of 5 lower surface of the wing is identical as the flying speed of aircraft, the gas velocity of 5 lower surface of wing when aircraft VTOL Degree can be zero（The tangential air blowing air-flow of upper surface of the airfoil still can form enough airfoil lifts at this time）.

When the utility model controls lift by left and right aerofoil flow, it left and right can both link and form pitching moment, It can be with left and right differential formation rolling moment.

The utility model manipulates driving device 6 by control stick 8 and exists in fuselage or wing longitudinally opposed around hinge axis 4 Rotation, can be realized by the control of conventional mechanical formula control stick or electronic corner control mechanism, to change in certain angle The air blowing angle [alpha] that driving device is blown to aerofoil surface.

The quantity of the utility model wing 5 can increase；For unmanned plane or light passenger's aircraft, a width overhead type Wing can be met the requirements；And for medium-sized or large-scale man-carrying aircraft, the quantity of the wing can be according to pressure-bearing type machine The mode of wing or so wing tandem in couples increases, to generate enough lift in VTOL.

When utility model works, even if aircraft is static, top airfoil of the aircraft by driving device in wing pushes High-speed flow, using bernoulli principle, the current difference that the air by flowing through upper surface of the airfoil and lower surface is formed, in aircraft Wing on the adjustment of air blowing angle [alpha] that generates lift, while being blown to aerofoil surface using driving device, and coordinate driving dress Set the increase and decrease of power, you can the balance for realizing pulling force F, lift S, gravity W and resistance Z, to realize that the preceding of aircraft flies, Winged, VTOL and hovering.

When the air-flow wind speed difference that the upper and lower surface of wing generates is 90km/h, airfoil lift calculates as follows：

By Bernoulli equation：Kinetic energy+gravitional force+pressure potential=constant,

Appoint in the perfect gas flowed in gravitational field and takes one section of flow tube with difference in height：

In formula：P- pressure, ρ-density, v- flow velocitys, g- acceleration of gravity, h- flow tube height differences.

For horizontal flow tube, h=0, therefore：

From the relationship of wind pressure and wind speed：When wind speed is 90km/h, wind pressure is：400 N/m2, therefore, according to above formula The aerofoil lift that can be obtained is 40 kilograms every square metre, even flat profile can also meet boat of the wing load less than 40 kilograms Pocket takes off.For 200 kilograms of the weight that takes off vertically, 5 square metres of wing is only needed.If using curved surface aerofoil profile, Lift can also further increase.

When VTOL, the physical relationship of each component is：

W+Z=F×sinθ+S×cosθ

F×cosθ=S×sinθ

When hovering, the physical relationship of each component is：

The events of Z=0：

W=F×sinθ+S×cosθ

F×cosθ=S×sinθ

When flying with inverted flight before at the uniform velocity, the physical relationship of each component is：

F=Z, S=W

Therefore, as long as by controlling throttle（That is driving device power）Pulling force F and adjustment driving device are adjusted to wing table The air blowing angle [alpha] that face is blown, you can realize preceding winged, inverted flight, VTOL and the hovering of aircraft.

The utility model relies on the aerodynamic characteristic of wing using slip-stream lift-rising principle（Lift resistance ratio）Improve driving device Working efficiency, while pulling force F, lift S, gravity W are realized in the adjustment for the air blowing angle [alpha] blown to aerofoil surface using driving device With the balance of resistance Z, you can preceding winged, inverted flight, VTOL and the hovering for realizing aircraft realize VTOL and high speed fly Two kinds of flight operating modes of row it is completely compatible.

Compared with prior art, have can completely and VTOL and high-speed flight two kinds of flight works for the utility model Condition, flight efficiency are high（Five times or more are improved than existing VTOL aircraft）, manipulation is easy, feedback is intuitive, simple in structure, at The advantages that this is cheap can apply in VTOL aircraft especially popular style, lightweight aircraft, while also have extensively There are the potentiality of the large-scale VTOL aircraft of structure.Since this new configuration aircraft can be tablet in wing（Do not have and appoints What curved surface aerofoil profile）In the case of, it realizes the VTOL of aircraft using the lift that air-flow velocity difference above and below aerofoil generates and flies Row, therefore plate wing machine can also be referred to as.In addition, the utility model also overcome existing rotor class aircraft by space layout and The limitation of wing tip velocity of sound, may be used multiple rotors or multiple rows of rotor improves lift so that VTOL aircraft can be broken through The limitation of size and load, it is more enlarged.

Description of the drawings

Fig. 1 is the utility model aircraft principle schematic.

Fig. 2 is the utility model tilting drive operating-controlling mechanism schematic diagram.

Fig. 3 is the utility model aircraft pullover flight principle schematic.

Fig. 4 is the utility model aircraft nutation flight theory schematic diagram.

Fig. 5 is the utility model aircraft horizontal flight principle schematic.

Fig. 6 is the utility model embodiment dumping tower tray formula aircraft series winding principle schematic.

Fig. 7 is the aircraft schematic diagram that the utility model wing wingtip is equipped with winglet.

In figure：1- supporting mechanisms, 2- seats, 3- fuselages, 4- hinge axis, 5- wings, 6- driving devices, 7- hinge mounts, 8- Control stick, the air blowing angle that α-driving device is blown to aerofoil surface, F- pulling force, S- lift, W- gravity, Z- resistances, h- winglets Highly, l- wingspan lengths, b- wing chord lengths.

Specific implementation mode

Below in conjunction with the accompanying drawings, specific embodiment of the present utility model is further described in detail.It is not noted in embodiment Bright technology or product is the prior art or can be by buying the conventional products obtained.

Embodiment 1：As shown in figs. 1-7, this realizes the dumping tower tray formula aviation of VTOL and flight using tangential blow of aerofoil Device, including 8,10 supporting mechanism 1, fuselage 3, wing 5, driving device 6 and control stick propeller type driving devices 6 are arranged Above 5 leading edge of aircraft wing, propeller is located at the rear portion above the leading edge of a wing, the distance away from the leading edge of a wing is more than propeller Diameter and be less than 1/5th chord lengths, the lower edge of propeller is close to aerofoil；Driving device 6 is fixed on wing 5 by hinge mount 7 Upper and can realize around hinge axis 4 and longitudinally vert, the puff prot of driving device 6 is towards upper surface of the airfoil so as to by high speed gas Stream is blown into upper surface of the airfoil along tangential, and wing 5 is directly anchored on fuselage 3 and is divided into left and right wing, 10 driving devices 6 It is divided to left and right two groups of symmetric arrays above the leading edge of left and right wing 5（5 driving devices are set on each wing）；It is filled by driving It sets 6 and high-speed flow is blown into upper surface of the airfoil along tangential, be allowed to flow quickly through upper surface of the airfoil, using flowing through upper surface of the airfoil With the current difference of the air of lower surface, airfoil lift is formed；After tangential air blowing lift-rising, the efficiency of driving device 6 is significantly It improves, the thrust-weight ratio of aircraft can be reduced to K=0.2, hence it is evident that be better than existing VTOL aircraft.It is driven by changing The air blowing angle [alpha] that device is blown to aerofoil surface coordinates driving device to change blowing direction of the high-speed flow with respect to fuselage The increase and decrease of power makes the pulling force F of airfoil lift S and driving device resultant forces in the horizontal direction cancel out each other and in vertical direction Resultant force greater than, equal to or less than aircraft the sum of gravity W and resistance Z to realize the VTOL or hovering of aircraft, Make airfoil lift S and the pulling force F of driving device vertical direction resultant force equal to aircraft gravity W and conjunction in the horizontal direction Power is more than or less than the resistance Z of aircraft to realize the flight forward of aircraft or fly backward.In control aerofoil air-flow When, it can both control linkage and form pitching moment, it can also the differential formation rolling moment in left and right.

Wing 5 is the pressure-bearing type positioned at fuselage both sides, and wing 5 is that the low wing carries large area continuous surface wing, and wing opens up string Than being 2.4, aircraft is set to realize slow drop forced landing as descending slowly and lightly leaf when failure occurs, when left and right wing is with 10 ° The upper counterangle is installed as V-arrangement aerodynamic configuration so as to can become a full member automatically when aircraft descends slowly and lightly in the air.The wingtip of wing 5 is provided with small The wing, to improve lift when aircraft VTOL and reduce induced drag, the pass of winglet height h and wingspan length l and chord length b System meets following condition：Work as l/b>When=2, h=b × (b/l)；Work as l/b<When=2, h=b × (1-0.25 × l/b）. The shape of wing 5 is rectangle, aerofoil profile is lower flat upper convex.Driving device 6 is in flat to the tangential air-flow blowed of wing 5, and It is close to the aerofoil of wing 5 as possible, the nowed forming of tangential air blowing air-flow can be controlled by installing cowling panel additional, is allowed in flat Shape blows to wing upper table, and flat air-flow is made to improve lift close to aerofoil to obtain best lift-rising effect as possible.Pass through Control stick 8 controls the driving device 6 flow directions of the air-flow with respect to fuselage for being blown into upper surface of the airfoil, and control stick is using conventional machine Tool formula controls, longitudinal air blowing angle [alpha] for changing driving device and blowing to aerofoil surface, to meet the change of aircraft operating mode It is required that.The flow velocity that driving device 6 is blown into the air-flow of 5 upper surface of wing is directly proportional to the power of driving device, and 5 following table of wing The air velocity in face is identical as the flying speed of aircraft, and the air velocity of 5 lower surface of wing can be with when aircraft VTOL It is zero（The tangential air blowing air-flow of upper surface of the airfoil still can form enough airfoil lifts at this time）.

Embodiment 2：As shown in figs. 1-7, this realizes the dumping tower tray formula aviation of VTOL and flight using tangential blow of aerofoil Device, including 8,12 supporting mechanism 1, fuselage 3, wing 5, driving device 6 and control stick turbojet engine driving devices 6 are arranged and are set It is placed in above aircraft wing 5 leading edge, the air inlet of turbojet engine is located at rear portion above the leading edge of a wing, away from the leading edge of a wing Distance is more than the diameter of air inlet and is less than 1/5th chord lengths, and the lower edge of the air inlet of turbojet engine is close to aerofoil；Driving Device 6 by hinge mount 7 is hinged on wing 5 can be realized around hinge axis 4 it is longitudinal vert, the puff prot of driving device 6 Towards upper surface of the airfoil so as to which high-speed flow is blown into upper surface of the airfoil along tangential, wing 5 be directly anchored on fuselage 3 and It is divided into left and right wing, 12 driving devices 6 are divided to left and right two groups of symmetric arrays above the leading edge of left and right wing 5（Each wing 6 driving devices of upper setting）；High-speed flow is blown into upper surface of the airfoil along tangential by driving device 6, is allowed to flow quickly through machine Wing upper surface forms airfoil lift using the current difference for the air for flowing through upper surface of the airfoil and lower surface；Increased using tangential air blowing After rising, the efficiency of driving device 6 greatly improves, and the thrust-weight ratio of aircraft can be reduced to K=0.2, hence it is evident that hangs down better than existing Straight landing aircraft.The air blowing angle [alpha] blown to aerofoil surface by changing driving device, to change high-speed flow with respect to machine The blowing direction of body coordinates the increase and decrease of driving device power, keeps the pulling force F of airfoil lift S and driving device in the horizontal direction Resultant force cancel out each other and the resultant force of vertical direction greater than, equal to or less than aircraft the sum of gravity W and resistance Z to realize The VTOL or hovering of aircraft make airfoil lift S and the pulling force F of driving device be equal to aviation in the resultant force of vertical direction The gravity W of device and resultant force in the horizontal direction be more than or less than the resistance Z of aircraft to realize aircraft flight forward or Person flies backward.In control aerofoil air-flow, it can both control linkage and form pitching moment, it can also the differential formation rolling in left and right Torque.

Wing 5 is the overhead type positioned at body upper, and wing 5 is that the low wing carries large area continuous surface wing, and wing opens up string Than being 1.2, aircraft is enable to realize slow drop forced landing as descending slowly and lightly leaf when failure occurs, when left and right wing is upper with 0 ° Dihedral is installed as T shapes aerodynamic configuration so as to can become a full member automatically when aircraft descends slowly and lightly in the air.The wingtip of wing 5 is provided with small The wing, to improve lift when aircraft VTOL and reduce induced drag, the pass of winglet height h and wingspan length l and chord length b System meets following condition：Work as l/b>When=2, h=b × (b/l)；Work as l/b<When=2, h=b × (1-0.25 × l/b）. The shape of wing 5 is trapezoidal, aerofoil profile is recessed upper convex.Driving device 6 is in flat to the tangential air-flow blowed of wing 5, and It is close to the aerofoil of wing 5 as possible, i.e., controls the nowed forming of tangential air blowing air-flow by cowling panel, is allowed to blow in flat Wing upper table, and flat air-flow is made to improve lift close to aerofoil to obtain best lift-rising effect as possible.Pass through control stick 6 flow directions of the air-flow with respect to fuselage for being blown into 5 upper surface of wing are controlled the driving device, control stick is using conventional electronic corner The control of control mechanism, the air blowing angle [alpha] that longitudinal change driving device is blown to aerofoil surface is adjusted, to meet aircraft The requirement that flight operating mode changes.Driving device 6 is blown into the flow velocity of the air-flow of 5 upper surface of wing and the power of driving device at just Than and the air velocity of 5 lower surface of wing is identical as the flying speed of aircraft, 5 lower surface of wing when aircraft VTOL Air velocity can be zero（The tangential air blowing air-flow of upper surface of the airfoil still can form enough airfoil lifts at this time）.Control When aerofoil flow processed, it can both control linkage and form pitching moment, it can also the differential formation rolling moment in left and right.

Embodiment 3：As shown in figs. 1-7, this realizes the dumping tower tray formula aviation of VTOL and flight using tangential blow of aerofoil Device, including 2,20 supporting mechanism 1, fuselage 3, wing 5, driving device 6 and operating-controlling mechanism fanjet driving devices 6 arrange It is set to above aircraft wing 5 leading edge, the air inlet of fanjet is located at rear portion above the leading edge of a wing, away from the leading edge of a wing Distance be more than the diameter of air inlet and be less than 1/5th chord lengths, the lower edge of the air inlet of fanjet is close to aerofoil；It drives Dynamic device 6 can be realized around hinge axis 4 and longitudinally verted by the way that hinge mount 7 is hinged on wing 5, the jet of driving device 6 Towards upper surface of the airfoil so as to which high-speed flow is blown into upper surface of the airfoil along tangential, wing 5 is directly anchored on fuselage 3 mouth And it is divided into left and right wing, 20 driving devices 6 are divided to left and right two groups of symmetric arrays above the leading edge of left and right wing 5（Each machine 10 driving devices are set on the wing）；High-speed flow is blown into upper surface of the airfoil along tangential by driving device 6, is allowed to quickly flow Through upper surface of the airfoil airfoil lift is formed using the current difference for the air for flowing through upper surface of the airfoil and lower surface；It is blown using tangential After gas lift-rising, the efficiency of driving device 6 greatly improves, and the thrust-weight ratio of aircraft can be reduced to K=0.15, hence it is evident that better than existing Some VTOL aircrafts.The air blowing angle [alpha] blown to aerofoil surface by changing driving device, to change high-speed flow The blowing direction of opposite fuselage, coordinates driving device power adjustment, makes airfoil lift S and the pulling force F of driving device in level side To resultant force cancel out each other and the resultant force of vertical direction greater than, equal to or less than aircraft the sum of gravity W and resistance Z to The VTOL or hovering for realizing aircraft, make airfoil lift S and the pulling force F of driving device be equal in the resultant force of vertical direction The gravity W of aircraft and resultant force in the horizontal direction is more than or less than the resistance Z of aircraft to realize flying forward for aircraft Row flies backward.In control aerofoil air-flow, it can both control linkage and form pitching moment, it can also the differential formation in left and right Rolling moment.

Wing 5 is the bottom type below fuselage, and wing 5 is that the low wing carries large area continuous surface wing, and wing opens up string Than being 2.2, aircraft is set to realize slow drop forced landing as descending slowly and lightly leaf when failure occurs, when left and right wing is with 20 ° The upper counterangle is installed as Y shape aerodynamic configuration so as to can become a full member automatically when aircraft descends slowly and lightly in the air.The wingtip of wing 5 is provided with small The wing, to improve lift when aircraft VTOL and reduce induced drag, the pass of winglet height h and wingspan length l and chord length b System meets following condition：Work as l/b>When=2, h=b × (b/l)；Work as l/b<When=2, h=b × (1-0.25 × l/b）. The shape of wing 5 is rectangle, aerofoil profile is symmetrical airfoil.Driving device 6 is to the tangential air-flow blowed of wing 5 in flat and most The aerofoil that amount is close to wing 5 controls the flowing shape of tangential air blowing air-flow that is, by using flat puff prot formula driving device State is allowed to blow to wing upper table in flat, and makes flat air-flow as possible close to aerofoil, to obtain best lift-rising effect, Improve lift.6 flow directions of the air-flow with respect to fuselage for being blown into upper surface of the airfoil can be controlled the driving device by control stick, The control of conventional mechanical formula may be used in control stick, and the air blowing angle [alpha] that longitudinal change driving device is blown to aerofoil surface is adjusted It is whole.The flow velocity that driving device 6 is blown into the air-flow of 5 upper surface of wing is directly proportional to the power of driving device, and 5 lower surface of wing Air velocity it is identical as the flying speed of aircraft, the air velocity of 5 lower surface of wing can be when aircraft VTOL Zero（The tangential air blowing air-flow of upper surface of the airfoil still can form enough airfoil lifts at this time）.

Embodiment 4：As shown in figs. 1-7, this realizes the dumping tower tray formula aviation of VTOL and flight using tangential blow of aerofoil Device, including 2,16 supporting mechanism 1, fuselage 3, wing 5, driving device 6 and operating-controlling mechanism shrouded propeller driving devices 6 arrange It is set to above aircraft wing 5 leading edge, it is big that shrouded propeller is located at the rear portion above the leading edge of a wing, the distance away from the leading edge of a wing In propeller diameter and be less than 1/5th chord lengths, the lower edge of shrouded propeller is close to aerofoil.Driving device 6 passes through hinge mount 7 be hinged on wing 5 and can be realized around hinge axis 4 it is longitudinal vert, the puff prot of driving device 6 towards upper surface of the airfoil from And high-speed flow can be blown into upper surface of the airfoil along tangential, and wing 5 is directly anchored on fuselage 3 and is divided into left and right wing, and 16 A driving device 6 is divided to left and right two groups of symmetric arrays above the leading edge of left and right wing 5（8 driving dresses of setting on each wing It sets）；High-speed flow is blown into upper surface of the airfoil along tangential by driving device 6, is allowed to flow quickly through upper surface of the airfoil, utilizes stream The current difference of upper surface of the airfoil and the air of lower surface is crossed, airfoil lift is formed；After tangential air blowing lift-rising, driving device 6 efficiency greatly improves, and the thrust-weight ratio of aircraft can be reduced to K=0.15, hence it is evident that is better than existing VTOL aircraft. The air blowing angle [alpha] blown to aerofoil surface by changing driving device, to change blowing direction of the high-speed flow with respect to fuselage, Coordinate driving device power increase and decrease, make the pulling force F of airfoil lift S and driving device resultant forces in the horizontal direction cancel out each other and The resultant force of vertical direction greater than, equal to or less than aircraft the sum of gravity W and resistance Z to realize the VTOL of aircraft Or hovering, make airfoil lift S and the pulling force F of driving device vertical direction resultant force equal to aircraft gravity W and in water Square to resultant force be more than or less than the resistance Z of aircraft to realize the flight forward of aircraft or fly backward.It is controlling When aerofoil flow processed, it can both control linkage and form pitching moment, it can also the differential formation rolling moment in left and right.

Wing 5 is the overhead type positioned at body upper, and wing 5 is that the low wing carries large area continuous surface wing, and wing opens up string Than being 1.8, aircraft is set to realize slow drop forced landing as descending slowly and lightly leaf when failure occurs, when left and right wing is with 15 ° The upper counterangle is installed as V-arrangement aerodynamic configuration so as to can become a full member automatically when aircraft descends slowly and lightly in the air.The wingtip of wing 5 is provided with small The wing, to improve lift when aircraft VTOL and reduce induced drag, the pass of winglet height h and wingspan length l and chord length b System meets following condition：Work as l/b>When=2, h=b × (b/l)；Work as l/b<When=2, h=b × (1-0.25 × l/b）. The shape of wing 5 is triangle, aerofoil profile is flat profile, and the use of flat profile can make wing area be made very big, be light The installation for lying prostrate battery provides enough spaces.Driving device 6 to the tangential air-flow blowed of wing 5 in flat, and as possible close to In the aerofoil of wing 5, i.e., the flow profile of tangential air blowing air-flow is controlled by cowling panel, be allowed to blow on wing in flat Table, and flat air-flow is made to improve lift close to aerofoil to obtain best lift-rising effect as possible.Control stick control can be passed through Driving device 6 processed is blown into flow direction of the air-flow with respect to fuselage of upper surface of the airfoil, and conventional electric rotating may be used in control stick Angle control mechanism control, the air blowing angle [alpha] that longitudinal change driving device is blown to aerofoil surface are adjusted.Driving device 6 is blown The flow velocity for being sent to the air-flow of 5 upper surface of wing is directly proportional to the power of driving device, and the air velocity and boat of 5 lower surface of wing The flying speed of pocket is identical, and the air velocity of 5 lower surface of wing can be zero when aircraft VTOL（Wing upper table at this time The tangential air blowing air-flow in face still can form enough airfoil lifts）.

The technology contents of the utility model are described above in conjunction with attached drawing, but the scope of protection of the utility model is not It is limited to the content, one skilled in the relevant art within the scope of knowledge, can also not depart from this practicality newly 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 realizing the dumping tower tray formula aircraft of VTOL and flight, including supporting mechanism using tangential blow of aerofoil（1）, seat Chair（2）, fuselage（3）, wing（5）, driving device（6）, hinge mount（7）And control stick（8）, it is characterised in that：Several driving dresses It sets（6）The wing in aircraft is arranged（5）Above leading edge, driving device（6）Pass through hinge mount（7）It is hingedly fixed in wing （5）On, control stick（8）Pass through hinge mount（7）Manipulate driving device（6）Around hinge axis（4）Longitudinal direction is verted, driving device（6） Puff prot high-speed flow is blown into upper surface of the airfoil, wing along tangential towards upper surface of the airfoil（5）It is directly fixed In fuselage（3）On；By driving device（6）High-speed flow is blown into upper surface of the airfoil along tangential, is allowed to flow quickly through on wing Surface forms airfoil lift using the current difference for the air for flowing through upper surface of the airfoil and lower surface；Pass through control stick（8）It manipulates Driving device（6）Longitudinal direction, which is verted, changes the air blowing angle [alpha] that driving device is blown to aerofoil surface, opposite to change high-speed flow The flow direction of fuselage coordinates driving device（6）The increase and decrease of power makes airfoil lift S and the pulling force F of driving device in level side To resultant force cancel out each other and the resultant force of vertical direction greater than, equal to or less than aircraft the sum of gravity W and resistance Z to The VTOL or hovering for realizing aircraft, make airfoil lift S and the pulling force F of driving device be equal in the resultant force of vertical direction The gravity W of aircraft and resultant force in the horizontal direction is more than or less than the resistance Z of aircraft to realize flying forward for aircraft Row flies backward.

2. according to claim 1 realize the dumping tower tray formula aircraft of VTOL and flight using tangential blow of aerofoil, It is characterized in that：The wing（5）For the pressure-bearing type wing positioned at the overhead type wing of body upper, or positioned at fuselage both sides, Or the bottom type wing below fuselage.

3. according to claim 1 or 2 realize the dumping tower tray formula aircraft of VTOL and flight using tangential blow of aerofoil, It is characterized in that：The wing（5）For wide string wing, wing aspect ratio is less than 2；Generally it is the continuous table of large area that the low wing carries Face wing, aircraft can realize slow drop forced landing when failure occurs as descending slowly and lightly leaf, when left and right wing is with certain upper Dihedral is installed as automatically becoming a full member when also aircraft being enable to descend slowly and lightly in the air after the aerodynamic configurations such as V-arrangement, Y shape or T shapes.

4. according to claim 1 or 2 realize the dumping tower tray formula aircraft of VTOL and flight using tangential blow of aerofoil, It is characterized in that：The wing（5）Wingtip large-scale winglet, the minimum constructive height h and wingspan length l and chord length b of winglet should be set Relationship should meet following condition：Work as l/b>When=2, h=b × (b/l)；Work as l/b<When=2, h=b × (1-0.25 × l/b）.

5. according to claim 1 or 2 realize the dumping tower tray formula aircraft of VTOL and flight using tangential blow of aerofoil, It is characterized in that：The wing（5）Shape be diamond shape, triangle, rectangle or trapezoidal, wing（5）Aerofoil profile be lower flat convex Any one of aerofoil profile or recessed convex aerofoil profile, symmetrical airfoil, S aerofoil profiles or flat profile.

6. according to claim 1 realize the dumping tower tray formula aircraft of VTOL and flight using tangential blow of aerofoil, It is characterized in that：The wing（5）It is divided into left and right wing, several driving devices（6）It is divided to left and right two groups of symmetric arrays in left and right machine Above the leading edge of the wing；The driving device（6）It is propeller, shrouded propeller, turbojet engine, fanjet, whirlpool paddle hair Any one of motivation, blow-out nozzle either leading edge blown flap；Driving device（6）Air inlet or propeller be located at wing Rear portion above leading edge, the distance away from the leading edge of a wing are more than the diameter of air inlet or propeller and are less than 1/5th chord lengths, drive Dynamic device（6）Air inlet or propeller lower edge close to aerofoil.

7. according to claim 1 realize the dumping tower tray formula aircraft of VTOL and flight using tangential blow of aerofoil, It is characterized in that：The driving device（6）To wing（5）The tangential air-flow blowed is in flat, adds fairing and ensures air-flow It is close to wing as possible（5）Aerofoil；When by the gas flow optimized lift of left and right aerofoil, left and right linkage formed pitching moment or Left and right differential formation rolling moment.

8. according to claim 1 realize the dumping tower tray formula aircraft of VTOL and flight using tangential blow of aerofoil, It is characterized in that：The driving device（6）It is blown into wing（5）The air-flow of upper surface passes through manipulation with respect to the flow direction of fuselage Bar（8）Manipulate driving device（6）The air blowing angle [alpha] that change driving device is blown to aerofoil surface of longitudinally verting is adjusted；It is logical It crosses and changes the angles α and reach balance to manipulate the power of all directions, while aircraft wake flow being blown off VTOL region, improve vertically The security context of landing.

9. according to claim 1 realize the dumping tower tray formula aircraft of VTOL and flight using tangential blow of aerofoil, It is characterized in that：The driving device（6）It is blown into wing（5）The flow velocity and driving device of the air-flow of upper surface（6）Power at Direct ratio, and wing（5）The air velocity of lower surface is identical as the flying speed of aircraft, wing when aircraft VTOL（5） The air velocity of lower surface is zero.

10. according to claim 1 realize the dumping tower tray formula aircraft of VTOL and flight using tangential blow of aerofoil, It is characterized in that：The wing（5）Quantity increase；For unmanned plane or light passenger's aircraft, a width overhead type wing is It can meet the requirements；For medium-sized or large-scale man-carrying aircraft, the wing（5）Quantity according to pressure-bearing type wing or so wing The mode of tandem increases in couples.