CN207843317U - A kind of short takeoff vertical landing aircraft - Google Patents

Abstract

A kind of short takeoff vertical landing aircraft, including fuselage, sustainer, vertical fin and the main wing, upper limb, the end wing and the canard that are separately positioned on fuselage both sides；It is held at two on the outside of the wing and is both provided with extension wing, aileron is both provided on two extension wings, elevator is both provided on two upper limbs；The tail portion of two end wings is both provided with rudder；To support construction is stretched out before holding the lower part of the wing to be respectively equipped at two, a sustainer, sustainer propeller and propeller inclination angle driving device are set in stretching support construction in each of front；In the lower part of each end wing, deployable and collapsible main landing gear is set；At vertical fin rear portion, support construction is stretched out in setting backward, stretches out in support construction be equipped with posture adjustment engine prop backward at this.This aircraft not only has short takeoff, vertical landing performance, while having taken into account the flying qualitys such as high speed, long endurance, big voyage.

Description

A kind of short takeoff vertical landing aircraft

Technical field

The utility model belongs to field of flight vehicle design, and in particular to a kind of connection wing canard with excellent aeroperformance Aerodynamic arrangement, can realize short takeoff, vertical landing aircraft.

Background technology

Aircraft has the characteristics that speed is fast, mobility is high, is not obstructed by high mountain, river, desert, ocean, without as vapour The highway or railway of vehicle and train build expensive necessary like that.But aircraft also has the limitation of itself, especially landing site It is restricted, aircraft, especially large-scale fixed wing aircraft, it is necessary to airfield runway landing is depended on, the construction scale of airfield runway is big, More than generally up to 2 kms, and occupied space is big, in the tens of kilometer ranges of airfield runway, is not allow for high-rise Or non-aviation management airflight object, so the at most several airports in a city, and airport is distributed in outer suburbs more.

Current aircraft is only applicable to light-weight, and time requirement is urgent, the transport that voyage again cannot be too close.However, high speed The development of railway, or even serious challenge also is had issued to this function of aircraft.So from the point of view of the long term growth of aircraft, Need the critical issue solved is so that aircraft is mitigated, even break away from the degree of dependence for airfield runway.

Connection wing canard configuration aircraft, pneumatic/structure-integrated designing technique of integrated use, big with useful lift, Full machine cruise lift resistance ratio is high, body weight is light, agent structure is strong, payload space is big in machine, airborne period is long, low latitude/low The features such as fast performance is good, takeoff and landing performance is excellent.

Normal arrangement aircraft relies primarily on wing and generates lift needed for the flight of full machine, wing while generating lift, It can also add and generate certain bending and torsional moment, it is necessary to be carried using stronger, heavier wing structure, it is therefore desirable to pay Larger construction weight.And use and be coupled wing canard configuration, it is coupled the wing itself, is both the lifting surface and lifting surface of aircraft Load frame can convert the tension and compression stress for holding the wing and vertical fin, greatly optimize machine moment of flexure caused by wing and torque to The wing is extended to be distributed to load, to significantly reduce the construction weight and whole machine weight of wing.

Normal arrangement aircraft realizes longitudinal trimming control of full machine using wing and empennage cooperation, therefore different Under the conditions of center of gravity, to reach the trim of full machine longitudinal direction, need to pay certain loss of lift.And it uses and is coupled the flight of wing canard configuration Device participates in longitudinal trimming control using three groups of lifting surfaces, is advantageous to reduce longitudinal trim loss of lift, it might even be possible to real Existing forward direction trimming control function.

Normal arrangement aircraft, using vertical tail as main course stabilization, rudder is located on vertical fin, improves boat The vertical fin and rudder that bigger is just needed to stability and maneuverability, cause vertical fin weight big, complicated.And it uses and is coupled the wing Canard configuration aircraft, can comprehensively utilize the end wing and the rudder on the wing of end realizes aircraft course control and stability control System.

The aileron of normal arrangement aircraft is arranged on main wing, closer apart from fuselage, must to improve roll guidance efficiency Larger aileron rudder face must be used.And use be coupled wing canard configuration aircraft, using sweepforward extension wing install aileron, can compared with Under the conditions of small aileron control area, realize that the efficient roll of full machine manipulates.

The aircraft of normal arrangement relies primarily on the lifting surfaces such as wing, empennage to generate lift needed for flight, is only flying When speed reaches larger, the lift for being enough to support aircraft weight could be generated, as a result, necessarily leading to rising, dropping sliding run for aircraft Distance is longer.Using the aircraft of this layout, can be verted control technology using engine, be verted by power certain to generate Lift is equivalent to the landing weight for alleviating aircraft, can substantially reduce depart speed or the touchdown speed of aircraft, Greatly shorten the landing ground roll-out distance of aircraft.

When landing, longitudinally controlled torque is generated mainly by the pneumatic efficiency of rudder face for the aircraft of normal arrangement.And use this The aircraft of layout, can but be verted using engine and control technology, the control moments such as generation pitching, roll especially exist The takeoff and landing stage is verted and is controlled using the power of engine, can generate big nose-up pitching moment so that aircraft is playing reduction Under the conditions of speed, it can also reach the larger controllable angle of attack, it is liftoff in the lift of takeoff phase to be advantageous to aircraft；Or Aircraft realizes that High Angle of Attack (closing on stalling angle), small speed (even vertically downward) touchdown create item in landing period Part.

Good aircraft is paid with minimum energy, and maximum possible is efficiently securely and reliably flown using air force And it is good at " art work ".If the engine prop installed before the wing of end has enough pulling force, it is sufficient to " pull out in nonirrigated farmland aircraft Green onion " formula is departed, then can make aircraft that there is very outstanding VTOL ability, such aircraft even can complete class The various flights of helicopter are similar to, but will certainly be caused in long-time cruising flight phase, thus power bulk redundancy must The bulk redundancy of structural strength and aircraft weight can be so brought, therefore the aircraft of short takeoff/vertical landing is perhaps best Selection.

Utility model content

The purpose of this utility model is in view of the shortcomings of the prior art and defect, it is vertical to provide a kind of short takeoff Land aircraft makes it that can not only realize short takeoff, can on the runway of relatively short distance, even without suitable in special runway Profit is completed to take off, and also can allow aircraft under no runway conditions, safe landing be completed on arbitrary smooth, while taking into account height The flying qualitys such as fast, long endurance, big voyage.

In order to achieve the above objectives, the technical solution of the utility model is as follows：

A kind of short takeoff vertical landing aircraft, including fuselage, sustainer, vertical fin and it is separately positioned on fuselage two Main wing, upper limb, the end wing and the canard of side；The top of two end wings is respectively by being arranged upper limb and vertical fin company in body upper It connects；It is held at two on the outside of the wing and is both provided with the extension wing being connected with upper limb；It is both provided with elevator, feature on two upper limbs It is：It holds the lower part of the wing to be equipped at two preceding to support construction is stretched out, a master is set in stretching support construction in each of front Engine, sustainer propeller and propeller inclination angle driving device, and deployable and collapsible master is set in the lower part of each end wing Undercarriage；The vertical fin rear portion setting stretch out support construction backward, this stretches out in support construction backward be equipped with posture adjustment send out Motivation propeller.Preferably, in above-mentioned technical proposal, aileron is both provided on described two extension wings；Described two end wings Tail portion is both provided with rudder.

Preferably, the main wing, canard, upper limb and extension wing use buzzard-type wing, swept-back wing or the straight wing.

Preferably, the main wing uses swept-back wing, upper limb to use buzzard-type wing.The main wing slightly upper counterangle；The upper limb Slightly inverted diherdral.

Preferably, propeller inclination angle driving device uses ball screw drive mechanism.

Preferably, the end wing and extension wing are all made of conventional aerofoil profile, laminar flow airfoil, high-lift airfoil or super critical aerofoil Type.The leading edge of the end wing carries angle of sweep, and the rear of the wing is held to carry sweepforward angle.

Preferably, the blade of the sustainer propeller and posture adjustment engine prop is two leaf paddles, three leaf paddles, four leaves Paddle, five leaf paddles or six leaf paddles.

The utility model compared with prior art, has the following advantages and advantageous effect：

This aircraft can realize short takeoff, can on the runway of relatively short distance, even without suitable in special runway Profit is completed to take off；Can realize vertical landing, allow aircraft can under no runway conditions, on arbitrary smooth complete safety Land.This aircraft not only has short takeoff/vertical landing performance, while having taken into account the flight of high speed, long endurance, big voyage Can, the characteristic with larger mission payload.It is in particular in following several respects：

1. using wing canard is coupled (i.e.：The synthesis shape of main wing+upper limb+canard) distribution form, it is coupled the wing itself, is both The lifting surface of aircraft, and be the load frame of lifting surface, moment of flexure caused by wing and torque can be converted to for the end wing and The tension and compression stress of vertical fin, greatly optimizes wing and extends and be distributed to load, to significantly reduce the construction weight of wing and complete Machine weight.2. using wing canard configuration aircraft is coupled, longitudinal trimming control is participated in using three groups of lifting surfaces, is advantageous to Reduce the loss of lift of longitudinal trim, it might even be possible to realize positive trimming control function.3. the end wing can be comprehensively utilized and be mounted on The rudder on the wing is held to realize the control of aircraft course control and stability.4. using the technical solution of the utility model, can utilize Sustainer propeller inclination angle driving device, is verted by power to generate certain lift, is equivalent to and is alleviated rising for aircraft Weight is dropped, depart speed or the touchdown speed of aircraft can be substantially reduced, the landing ground for greatly shortening aircraft is slided Run distance.5. the utility model can utilize sustainer propeller inclination angle driving device to generate the control moments such as pitching, roll, Big nose-up pitching moment especially can be generated using sustainer propeller inclination angle driving device in the takeoff and landing stage so that Aircraft can also reach the larger controllable angle of attack under landing low-speed conditions, be advantageous to aircraft takeoff phase lift It is liftoff；Or aircraft realizes that High Angle of Attack (closing on stalling angle), small speed (even vertically downward) in landing period Land ground connection creates conditions.

Description of the drawings

Fig. 1 is that a kind of external structure schematic diagram of short takeoff vertical landing aircraft provided by the utility model (is risen and fallen Frame puts down, engine prop vertically upward).

Fig. 2 be a kind of short takeoff vertical landing aircraft provided by the utility model gear down, engine spiral shell Rotation paddle verts 45 ° of oblique vertical views upwards.

Fig. 3 is a kind of gear up of short takeoff vertical landing aircraft provided by the utility model, engine spiral shell Rotation paddle vertically tilts forward oblique vertical view.

Fig. 4 be a kind of short takeoff vertical landing aircraft provided by the utility model gear down, engine spiral shell Rotation paddle verts side view vertically upward.

Fig. 5 is a kind of gear up of short takeoff vertical landing aircraft provided by the utility model, engine spiral shell Rotation paddle verts 45 ° of side views upwards.

Fig. 6 is a kind of gear up of short takeoff vertical landing aircraft provided by the utility model, engine spiral shell Rotation paddle vertically tilts forward side view.

In figure, 1- fuselages；2- canards；3- main wings；4- upper limbs；5- extension wings；The ends the 6- wing；7- elevators；8- ailerons；The side 9- To rudder；10- vertical fins；11- propellers inclination angle driving device；12- sustainer propellers；To stretching support construction after 13-；14- Posture adjustment engine prop；15- deployable and collapsible main landing gears；16- deployable and collapsible nose-gears；To stretching support construction before 17-.

Specific implementation mode

The utility model is described in detail with reference to the accompanying drawings and detailed description.

As shown in Figure 1, a kind of short takeoff vertical landing aircraft provided by the utility model includes：Fuselage 1 is actively sent out Canard 2 in 1 front end both sides of fuselage is arranged in motivation, is separately positioned on the main wings 3 of 1 both sides of fuselage, upper limb 4, the end wing 6 and sets Set the vertical fin 10 in 1 upper rear of fuselage；The end wing 6 is arranged in the end of the main wing 3 of fuselage both sides, and two are held the upper of the wing 6 Portion is connect by the vertical fin 10 that upper limb 4 square on the fuselage 1 is arranged and is arranged in 1 tail portion of fuselage respectively, equal on two upper limbs 4 It is provided with elevator 7；The outside of described two end wings 6 is provided with the extension wing 5 being connected with upper limb, is all provided on two extension wings 5 It is equipped with aileron 8；The tail portion of described two end wings 6 is both provided with rudder 9.Support is stretched out before holding 6 lower part of the wing to be provided at two A sustainer and propeller inclination angle driving device 11 is arranged in stretching support construction 17 in each of front in structure 17, Sustainer propeller 12 is installed on sustainer；The forward direction, which stretches out in support construction 17, is equipped with the drive of ball-screw inclination angle Dynamic device 11, can be adjusted the angle of sustainer propeller 12.

6 lower part of the wing is held to be mounted on deployable and collapsible main landing gear 15 at two, the medium position installation under fuselage can receive Put formula nose-gear 16；The rear upper of the vertical fin 10 stretches out support construction 13 after being provided with, in the stretching support construction 13 Top posture adjustment engine prop 14, the blade of the sustainer propeller 12 and posture adjustment engine prop 14 are installed For two leaf paddles, three leaf paddles, four leaf paddles, five leaf paddles or six leaf paddles.

The main wing 3, canard 2, upper limb 4 and extension wing 5 are using buzzard-type wing, swept-back wing or the straight wing.3 sweepback of main wing, on 4 sweepforward of the wing forms wing configurations form one in front and one in back, and pneumatic efficiency is high, can give full play to the lift-rising effect of two groups of aerofoils.Prolong The useful lift area that the wing 5 increases full machine is stretched, the useful lift of aircraft is greatly improved.Sustainer is under the wing of end In the preceding stretching support construction 17 in portion, in preceding stretching support construction 17, engine prop is realized using ball-screw It verts control.When sustainer propeller 12 verts upwards, works in lift conditions, on its purling direction, Ji Huwei Have it is any block, the lift-rising pneumatic efficiency of rotor can be given full play to, effective powered lift is provided in the landing stage for full machine, Without causing powered lift to lose because purling blocks.When sustainer propeller 12 vertically upward, lift-rising maximum shape When state, since propeller is sufficiently close together ground, has effects that the ground effect hovering class similar to helicopter, spiral shell can be greatly enhanced Paddle is revolved in the lift-rising efficiency of Near Ground, and being advantageous to the takeoff and landing performance of aircraft improves.Aircraft is in cruising flight phase, main hair Slip-stream caused by motivation propeller 12 will not generate unfavorable aerodynamic interference to wing 3；At this point, propellerslip flows aft through The wing 6 and main wing 3 are held, favourable aerodynamic interference can be generated with the opposite end wing 6 and main wing 3, increase the side of the lift resistance ratio and the end wing 6 of main wing 3 To stability.Deployable and collapsible main landing gear 15 is mounted on the lower section of the end wing 6, is conducive to make full use of the structure of the aircraft excellent Gesture, increase inside fuselage 1 and wing 3 using space.

This aircraft is designed according to aerodynamic principle, has the spies such as resistance is small, useful lift face is big, lift resistance ratio is high Point, it is to allow the end wing 6 far as possible from the center of gravity of airplane that main wing 3, which uses angle of sweep, main purpose, enhances 6 fixed fin of the end wing Directional yaw stability.Upper limb 4 uses buzzard-type wing, buzzard-type wing to have superior aeroperformance, be greatly improved the low-speed control of aircraft Performance is substantially reduced resistance when transonic speed flight, has good stalling characteristics under High Angle of Attack.The main wing 3 of aircraft omits The band upper counterangle, the slightly inverted diherdral of upper limb 4 so that the shape of the vertical view and front view of aircraft wing (including 4 main wing 3 of upper limb) All close to diamond shape, aircraft overall stiffness is good, and structure-bearing characteristic is good.In this Flight Vehicle Design, between main wing 3,4 aerofoil of upper limb Away from enough, interfering with each other between main wing 3 and upper limb 4 is smaller, therefore can give full play to the aerodynamic characteristic of two groups of aerofoils. The head of aircraft is nearby provided with canard 2, improves the total life of full machine, greatly improves the longitudinally controlled energy of full machine Power, the leading vortex hauled out by canard 2 (mainly under flat winged status condition), can stablize the top of main wing 3 under certain condition Interlayer, to postpone air-flow separation so that the useful lift and stalling angle of main wing 3 increase.Extension wing 5 increases having for full machine Lifting area is imitated, because extension wing 5 is located exactly at full machine immediate vicinity, the lift for being almost not necessarily to trim, institute can be provided for full machine With with prodigious lift-rising efficiency.

The leading-edge sweep of the wing 6 is held, the rear sweepforward of the wing 6 is held, it can be between 6 fixed fin of the enlarged portion wing and the center of gravity of airplane Distance improves the directional yaw stability of aircraft.In front of 6 lower part of the left and right end wing, sustainer and the driving of propeller inclination angle are set Device, 6 lower middle position of the wing at left and right end, installation deployable and collapsible main landing gear 15；The tail portion installation direction of the wing 6 is held at two Rudder 9；The installation site of rudder 9 is located between 3 face of upper limb 4 and main wing so that upper limb 4 and main wing 3 are stronger to the generation of rudder 9 " end the wing effect ", it is possible to increase the pneumatic efficiency of rudder 9 is conducive to the rudder effectiveness for improving rudder；Due to 9 rudder of rudder Vertical center of gravity of the aerodynamic center in face close to full machine so that non-instruction rolling moment caused by rudder kick greatly reduces； The aileron 8 that is arranged on extension wing 5 simultaneously, due to the longitudinal center of gravity close to aircraft, the deflection of aileron 8 will not generate big non- The pitching moment of instruction, comprehensive function effect, by the roll angle control accuracy for greatly improving aircraft and anti-crosswind capability, This is highly beneficial for the handling quality for improving aircraft.

In takeoff phase, as long as the weight of aircraft is close to the powered lift of engine prop, so that it may to realize aircraft " pulling out green onion in nonirrigated farmland " formula take off vertically it is liftoff.Even if the powered lift of engine can be significantly if being not enough to directly lift aircraft Improve the takeoff data of aircraft, realizes short takeoff：Playing the aircraft stage, it is still desirable to which aircraft is in ground roll-out speedup, when winged When machine has had certain flying speed, sustainer propeller 12 is tilted a certain angle upwards, make engine generate to Certain powered lift is generated while preceding pulling force；Under powered lift effect, aircraft will generate nose-up pitching moment so that aircraft is Make at low speeds, to could be used that the prodigious take-off angle of attack, increase the useful lift of full machine lifting surface, with it is shorter it is sliding run away from From lifting off.Then, the lift for gradually increasing posture adjustment engine prop 14 is gradually reduced flying angle, reduces flight resistance Power, and the sustainer propeller 12 that gradually leans forward, increase propeller pulling force component, aircraft are made persistently to accelerate sporting flying, Full machine lift will increase with the increase of flying speed, and the lift caused by each lifting surface of aircraft is enough that full machine is supported to fly Row weight, you can be transferred to the efficient cruising flight phase of fixed-wing.

In landing period, as long as the weight of aircraft is close to engine power lift, so that it may to realize the vertical of aircraft Land.Even if powered lift caused by engine is not enough to support the landing weight of full machine, it is also possible that the landing speed of aircraft Degree substantially reduces：When landing glide closes on ground, Engine full load can be allowed to work, utilize propeller inclination angle driving device 11 so that most thrusts is equivalent to the landing weight for alleviating aircraft in lift direction, generated lift, To substantially reduce the touchdown speed of aircraft.In the later stage of landing, sustainer propeller 12 can be enabled to hang down fully upward Directly, and make maximum rating operating, at this time under the nose-up pitching moment effect caused by sustainer propeller 12, what can be made flies Machine is generated compared with High Angle of Attack and pitch angle, and sustainer propeller 12 and posture adjustment engine prop 14 is made to generate maximum power While lift, it can also generate prodigious propulsive thrust on its flying speed direction, aircraft enabled to slow down rapidly, and keep aircraft It is moved ahead with High Angle of Attack, big aerodynamic drag posture, even if 12 lift of sustainer propeller is not sufficient to ensure that aircraft vertical lands It can ensure that aircraft is grounded with extremely low speed, also ensure that aircraft is moved ahead with large pitching angle, big aerodynamic drag posture after ground connection, from And greatly shorten distance of landing run.

Embodiment 1：

The utility model embodiment provides a kind of aircraft of short takeoff vertical landing, which includes：Fuselage 1, Canard 2 in 1 front end both sides of fuselage is set, and main wing 3, upper limb 4 and the end wing 6 and setting for being separately positioned on 1 both sides of fuselage exist The vertical fin 10 of 1 upper rear of fuselage；The end wing 6 is arranged in the end of the main wing 3 of fuselage both sides, the upper part of two end wings 6 It is not connect with the vertical fin 10 for being arranged in 1 tail portion of fuselage by the way that upper limb 4 square on the fuselage 1 is arranged, is respectively provided on two upper limbs 4 There is elevator 7；The outside of described two end wings 6 is provided with the extension wing 5 being connected with upper limb, is both provided on two extension wings 5 Aileron 8；The tail portion of described two end wings 6 is both provided with rudder 9.Support construction is stretched out before holding 6 lower part of the wing to be provided at two 17, in each of front to one sustainer of setting and propeller inclination angle driving device 11 in support construction 17 is stretched out, propeller inclines Angle driving device 11 is used to adjust the angle of inclination (referring to Fig. 2, Fig. 3, Fig. 4, Fig. 5, Fig. 6) of propeller, the driving of propeller inclination angle Ball screw driving device can be used in device 11.6 lower part of the wing is held to be mounted on retractable landing gear 15 at two；The vertical fin 10 rear upper stretches out support construction 13 after being provided with, and posture adjustment engine spiral shell is equipped in the top of the stretching support construction 13 Revolve paddle 14.

This aircraft is designed according to aerodynamic principle, due to small with resistance, useful lift face is big, lift resistance ratio is high The features such as, main wing 3 uses swept-back wing, upper limb 4 that buzzard-type wing, buzzard-type wing is used to have superior aeroperformance, be greatly improved winged The low-speed control performance of machine, is substantially reduced resistance when transonic speed following flight, has good stalling characteristics under High Angle of Attack. The slightly upper counterangle of main wing 3 of aircraft, the slightly inverted diherdral of upper limb 4 so that the main wing 3 of aircraft machine and the vertical view of upper limb 4 and For the shape of front view all close to diamond shape, aircraft overall stiffness is good, and structure-bearing characteristic is good.In this Flight Vehicle Design, 3 He of main wing The spacing of 4 aerofoil of upper limb is enough, and interfering with each other between main wing 3 and upper limb 4 is smaller, therefore can give full play to two groups of aerofoils Aerodynamic characteristic.It is provided with canard 2 near the head of aircraft, improves full machine lift, greatly improves the vertical of full machine To control ability；The leading vortex hauled out by canard 2 (mainly under flat winged status condition), can stablize main wing under certain condition 3 upper surface boundary layer, to postpone air-flow separation so that 3 useful lift of main wing and stalling angle increase.Extension wing 5 increases The useful lift area of full machine because extension wing 5 is located exactly near full machine longitudinal center of gravity can be provided for full machine and be almost not necessarily to The lift of trim, so having prodigious lift-rising efficiency.

In the technical solution of the utility model, 6 leading-edge sweep of the wing is held, the rear sweepforward of the wing 6 is held, is conducive to the enlarged portion wing 6 Fixed fin improves the directional yaw stability of aircraft at a distance from full machine center of gravity, is set in each of front in stretching support construction 17 Set a sustainer and propeller inclination angle driving device 11；6 lower middle position of the wing at left and right end installs deployable and collapsible master Undercarriage 15；In the tail portion of the end wing 6, setting direction rudder 9, between upper limb 4 and the aerofoil of main wing 3 so that upper limb 4 and main wing 3 aerofoils generate stronger " end wing effect " rudder 9, it is possible to increase the pneumatic efficiency of rudder 9 is conducive to improve rudder 9 Rudder effectiveness.Due to 9 rudder face of rudder aerodynamic center close to full machine vertical center of gravity so that caused by rudder 9 deflects Non- instruction rolling moment greatly reduces；Aileron 8 is set on extended segment 5 simultaneously, due to the longitudinal center of gravity close to full machine, aileron 8 Deflection, the pitching moment of big non-instruction will not be generated, comprehensive function effect will greatly improve the roll angle control of aircraft Precision processed and anti-crosswind capability, this is highly beneficial for the handling quality for improving aircraft.

The fuselage 1 and main wing 3 of this aircraft have carried out the warm processing of wing body, and fuselage 1 and canard 2 have carried out the warm place of wing body Reason, under the premise of improving its pneumatic efficiency, increase the structural strength of fuselage 1 wing 3 and 2 junction of canard；It is described Vertical fin 10 and fuselage 1 carry out fusion connection, increase intensity.The main wing 3, canard 2, upper limb 4, extension wing 5 and the end wing 6 are using normal Advise aerofoil profile, laminar flow airfoil, high-lift airfoil or supercritical airfoil.Canard 2 and extension wing 5 are using buzzard-type wing, swept-back wing or straight The wing.

Embodiment 2：

The utility model embodiment provides a kind of short takeoff aircraft, which includes：Fuselage 1 is arranged in fuselage 1 Main wing 3, upper limb 4 in 1 both sides of fuselage is arranged in the canard 2 of front end both sides), the end wing 6, vertical fin in 1 upper rear of fuselage is set 10；It is respectively provided with the end wing 6 in the end of the main wing 3 of 1 both sides of fuselage, the top of described two end wings 6 is respectively by being arranged in fuselage 1 The upper limb 4 of top is connect with the vertical fin 10 for being arranged in afterbody；The outsides of described two end wings 6 is provided with to be connected with upper limb Extension wing 5；It is both provided with elevator 7 on described two upper limbs 4, is both provided with aileron 8 on described two extension wings 5, described two The tail portion side of the being both provided with rudder 9 of a end wing 6；To support construction 17 is stretched out before described two 6 lower part of end wing settings, the forward direction is stretched Go out 17 front end of support construction and is provided with propeller inclination angle driving device 11；Main hair is installed in the driving device of the propeller inclination angle Motivation propeller 12；Described two 6 lower parts of the end wing are equipped with deployable and collapsible main landing gear 15；The rear upper of the vertical fin 10 is set To support construction 13 is stretched out after being equipped with, the backward top for stretching out support construction 13 is equipped with posture adjustment engine prop 14.

In takeoff phase, as long as the weight of aircraft is close to sustainer propeller powered lift, so that it may to realize aircraft Take off vertically it is liftoff.

Even if the powered lift of sustainer propeller 12 can substantially improve aircraft if being not enough to directly lift aircraft Takeoff data realizes short takeoff：In takeoff phase, it is still desirable to which aircraft is in ground roll-out speedup, when aircraft has had one When fixed flying speed, sustainer propeller 12 is tilted a certain angle upwards, will make sustainer propeller generate to Certain powered lift is generated while preceding pulling force；12 powered lift of sustainer propeller also will produce larger new line power Square is superimposed with the rudder effectiveness of canard 2 and elevator 7；6 following settings deployable and collapsible main landing gear 15 of the wing is held, aircraft is allowed to have Sufficiently large grazing angle；The result of its comprehensive function：Even if making aircraft at low speeds, it could be used that prodigious take off is met Angle increases the useful lift of full machine canard 2,5 lifting surface of main wing 3, upper limb 4 and extension wing, with the shorter liftoff liter of ground run distance It is empty.Then, the lift for gradually increasing posture adjustment engine prop 14 is gradually reduced flying angle, reduces flight resistance, and gradually Lean forward sustainer, increases 12 pulling force component of sustainer propeller, aircraft is made persistently to accelerate sporting flying, each lift of aircraft The lift in face will increase with the increase of flying speed, and the lift caused by each lifting surface of aircraft is enough that full machine is supported to fly Row weight, you can be transferred to the efficient cruising flight phase of fixed-wing.

Embodiment 3

The utility model embodiment provides a kind of vertical (short distance) landing aircrafts, which includes：Fuselage 1, setting Front fuselage both sides canard 2, be arranged the main wing 3 in 1 both sides of fuselage, upper limb 4, end the wing 6 and be arranged on afterbody The vertical fin 10 of side；Described be arranged is respectively provided with the end wing 6, the top difference of described two end wings 6 in the end of the main wing 3 of fuselage both sides It is connect with the vertical fin 10 for being arranged in afterbody by the way that the upper limb 4 in body upper is arranged；The outside of described two end wings 6 is arranged There is the extension wing 5 being connected with upper limb；It is both provided with elevator 7 on described two upper limbs 4, is respectively provided on described two extension wings 5 There are aileron 8, the tail portion side of the being both provided with rudder 9 of described two end wings 6；To stretching support knot before described two 6 lower part of end wing settings Structure 17, the forward direction stretch out 17 front end of support construction and are provided with propeller inclination angle driving device 11；The propeller inclination angle driving Airscrew engine is installed on device；Described two 6 lower parts of the end wing are equipped with deployable and collapsible main landing gear 15；The vertical fin 10 Rear upper be provided with after to support construction 13 is stretched out, the backward top for stretching out support construction 13 is equipped with posture adjustment and starts Machine propeller 14.

In landing period, as long as the weight of aircraft is close to 12 powered lift of sustainer propeller, so that it may be flown with realizing The vertical landing of machine.

Even if powered lift caused by sustainer propeller 12 is not enough to support the landing weight of full machine, can also make The landing speed for obtaining aircraft substantially reduces.When landing glide closes on ground, the work at full capacity of sustainer propeller 12 can be allowed Make, utilizes propeller inclination angle driving device 11 so that most thrusts is in lift direction, sustainer propeller 12 Generated lift is equivalent to the landing weight for alleviating aircraft.In the later stage of landing, sustainer propeller 12 can be enabled complete It is vertical in omnidirectional, and make maximum rating operating, at this time nose-up pitching moment and canard 2 caused by sustainer propeller 12, Under the collective effect of elevator 7, aircraft may make to generate compared with High Angle of Attack or pitch angle, at this point, sustainer propeller 12 and tune Appearance engine prop 14 can also generate prodigious while generating maximum powered lift on its flying speed direction Propulsive thrust enables aircraft slow down rapidly；Simultaneously as used deployable and collapsible main landing gear 15 has almost unrestricted wiping Ditch enables aircraft with High Angle of Attack/big aerodynamic drag posture ground connection, moves ahead, even if sustainer propeller lift is not enough to protect It demonstrate,proves aircraft vertical to land, can also greatly shorten distance of landing run.

In addition, super large main wheel track possessed by deployable and collapsible main landing gear 15, it can be ensured that aircraft take off High Angle of Attack from Problem does not occur for horizontal shipping-direction stability when ground, landing daying corner-of-delta grounding.

Conventional aerofoil profile, laminar flow airfoil, high lift hardware can be used in the canard 2, main wing 3, upper limb 4, the end wing 6 and extension wing 5 The blade of type or supercritical airfoil, sustainer propeller 12 and posture adjustment engine prop 14 is two leaf paddles, three leaf paddles, four leaves Paddle, five leaf paddles or six leaf paddles.

Claims (9)

1. a kind of short takeoff vertical landing aircraft, including fuselage (1), sustainer, vertical fin (10) and it is separately positioned on Main wing (3), upper limb (4), the end wing (6) and the canard (2) of fuselage both sides；The top of two end wings (6) is respectively by being arranged in machine Square upper limb (4) is connect with vertical fin (10) with it；It is held at two on the outside of the wing (6) and is both provided with the extension being connected with upper limb (4) The wing (5)；It is both provided with elevator (7) on two upper limbs (4), it is characterised in that：The lower part of the wing is held to be equipped at two preceding to stretching Support construction (17), in each of front to stretch out support construction on setting one sustainer, sustainer propeller (12) and Propeller inclination angle driving device (11), and in the lower part of each end wing setting deployable and collapsible main landing gear (15)；In the vertical fin (10) support construction (13) is stretched out in rear portion setting backward, stretches out in support construction be equipped with posture adjustment engine prop backward at this (14)。

2. a kind of short takeoff vertical landing aircraft as described in claim 1, it is characterised in that：On two extension wings It is provided with aileron (8)；The tail portion of described two end wings is both provided with rudder (9).

3. a kind of short takeoff vertical landing aircraft as described in claim 1, it is characterised in that：The main wing, canard, on The wing and extension wing use buzzard-type wing, swept-back wing or the straight wing.

4. a kind of short takeoff vertical landing aircraft as claimed in claim 3, it is characterised in that：The main wing uses sweepback The wing, upper limb use buzzard-type wing.

5. a kind of short takeoff vertical landing aircraft as described in claim 1, it is characterised in that：It drives at the propeller inclination angle Dynamic device (11) uses ball screw drive mechanism.

6. a kind of short takeoff vertical landing aircraft as described in claim 1, it is characterised in that：The end wing (6) and prolong It stretches the wing (5) and is all made of conventional aerofoil profile, laminar flow airfoil, high-lift airfoil or supercritical airfoil.

7. a kind of short takeoff vertical landing aircraft as claimed in claim 6, it is characterised in that：The leading edge band of the end wing There is angle of sweep, the rear of the wing is held to carry sweepforward angle.

8. a kind of short takeoff vertical landing aircraft as described in claim 1-7 any claims, it is characterised in that：Institute State main wing (3) the slightly upper counterangle；The upper limb (4) slightly inverted diherdral.

9. a kind of short takeoff vertical landing aircraft as claimed in claim 8, it is characterised in that：The sustainer spiral The blade of paddle (12) and posture adjustment engine prop (14) is two leaf paddles, three leaf paddles, four leaf paddles, five leaf paddles or six leaf paddles.