CN203666986U

CN203666986U - Aircraft

Info

Publication number: CN203666986U
Application number: CN201420003634.8U
Authority: CN
Inventors: 曹乃承; 曹可瀚
Original assignee: Individual
Current assignee: Individual
Priority date: 2014-01-05
Filing date: 2014-01-05
Publication date: 2014-06-25
Anticipated expiration: 2024-01-05

Abstract

An aircraft is provided with more than two rotor wings, wherein each rotor wing is provided with at least two blades. The aircraft has two flight modes: rotor wing flight attitude and fixed wing flight attitude. The aircraft can convert between the rotor wing flight attitude and the fixed wing flight attitude during flight. During the rotor wing flight attitude, the aircraft can vertically take off with rotor wing attitude and has the control performance of a helicopter; during the fixed wing flight attitude, the blades of the rotor wings of the aircraft are bent to two sides of the aircraft to serve as wings of the aircraft, the aircraft flies in a fixed wing manner and has the flight speed and voyage of a fixed wing airplane. In the rotor wing state, the aircraft can adopt coaxial double rotors, cross double rotors and parallel double rotors.

Description

A kind of aircraft

Technical field

The conversion method of structural form while the present invention relates to a kind of aircraft and its flight, especially has rotor flying form and determine aircraft and its rotor flying form of two kinds of flight forms of wing flight form and determines the fly conversion method of form of the wing.

Background technology

Conventional aerodynamic vehicle has helicopter and fixed wing aircraft.Helicopter utilizes one or more rotor wing rotation to produce lift vertically upward, and relies on verting of rotor plane to make the lift of rotor produce in the horizontal direction the propelling thrust that component and then generation are advanced.The advantage of helicopter is can vertical takeoff and landing, does not need runway, can hover, and uses flexibly.The weak point of helicopter is that rotor produces larger resistance while flying before helicopter, and therefore its maximum flying speed is limited, needs to consume larger power simultaneously, and voyage is short.The wing of fixed wing aircraft can not rotate, and relies on the horizontal propulsive force promotion of the propelling unit generation aircraft of horizontal direction to advance, and air flow stream is crossed fixed wing and produced lift.The resistance ratios helicopter being subject to while flying before fixed wing aircraft is little, has helicopter and the fixed wing aircraft comparison of identical take-off weight and cruising speed, and the tractive power needing when fixed wing aircraft cruises is little, and consumption of fuel is few.Therefore, fixed wing aircraft is all better than comparable helicopter at the aspect such as course continuation mileage, flying speed.Fixed wing aircraft needs runway in the time taking off and land, and it is flexible that this point is not so good as helicopter.

There are now a lot of course of new aircraft schemes, wished that aircraft can have advantages of the characteristic of helicopter vertical takeoff and landing and fixed wing aircraft cruising speed is fast, power demand is little simultaneously.For example, the V-22 tiltrotor of the U.S. is a kind of aircraft that has rotor flying form and determine two kinds of forms of wing flight form, and its end at fixing wing has been arranged two rotors, and rotor can be changed in the horizontal direction and between vertical direction.In the time taking off, rotor is in vertical direction, and rotation produces lift, drives aircraft to take off vertically as helicopter.In the time that aircraft flies in the horizontal direction, the wing of aircraft produces lift, and rotor wing rotation, to horizontal direction, produces the propelling thrust that aircraft advances.The rotor of tiltrotor takes off vertically and two kinds of mode of operations of level cruise in order to take into account, and the diameter of rotor can not resemble helicopter large, can not resemble screw propeller little.Therefore rotor efficiency is not as lifting airscrew in the time of helicopter flight state for tiltrotor, and in the time of level flight condition, rotor efficiency is not as screw propeller.And because the rotor diameter of tiltrotor is little, in the time of aircraft fast-descending, the rotor of tiltrotor is easy to be absorbed in the downwash flow of self rotor and loses lift, causes aeroplane accident.The fixed wing of tiltrotor does not provide any lift in the time of its vertical uplift, becomes on the contrary the load of aircraft.

Xi Kesiji company has developed X shape wing research aircraft in the 80's of last century, and its basic ideas are bridges of frame between helicopter and fixed wing aircraft, and the X shape wing on machine top can rotate under helicopter state, produces lift; Before fly to reach after certain speed, the X shape wing pins fixing, uses as wing, aircraft proceeds to fixed-wing state.Although the X shape wing is rare, not inconceivable pneumatic, a pair of exactly swept wing adds a pair of buzzard-type wing.Under helicopter state, anti-twisted power problem has tail-rotor to solve, and more difficult is the single rotor that adopts rigidity, how to solve the problem of asymmetric lift.Boeing pushes the concept of the X shape wing to new height, has developed " dragonfly " (Dragonfly) research aircraft." dragonfly " has canard front wing and roomy tailplane, has the rotor-wing of " one " font on machine top.Under helicopter state, rotor-wing rotates under the effect of jet wing tip, produces lift.Rotor-the wing of in-line is equivalent to two-bladed rotor, can complete and wave and leading-hysteresis motion with seesaw hinge, so " dragonfly " is to the compensation of asymmetric lift or conventional.The engine installation of " dragonfly " is a fanjet, draws high pressure draft from compressor, arrives the wing tip of rotor-wing by Pipeline transport, drives jet wing tip.Because jet wing tip does not produce anti-twisted power, " dragonfly " do not have tail-rotor.Reach after certain level speed, canard and horizontal tail produce enough lift, and rotor-wing pins, and as fixing wing, aircraft proceeds to fixed-wing state.Above-mentioned two kinds of aircrafts, enter and determine after wing flight form towards rotor wing rotation direction in the leading edge of rotor flying form blade, and must have blade is on one side that " trailing edge " is towards heading.In order to overcome this problem, will adopt symmetrical airfoil, the aeroperformance of blade/wing is just not as adopting the aircraft of asymmetric airfoil like this.

Summary of the invention

In order to overcome the deficiency of existing aircraft, the object of this invention is to provide a kind of there is rotor flying form and determine the course of new aircraft of two kinds of offline mode of wing flight form and aircraft in rotor flying form with determine the wing method of changing between form of flying.Structural form when flight form is aircraft flight is the structure of aircraft.Corresponding each flight form, has specific structural relation between each component part of aircraft, and especially the rotor of aircraft and rotor blade have specific structural relation every kind of flight form.The form of flying in the present invention also can be described as state of flight, flight attitude, offline mode.In the time taking off and land, aircraft of the present invention adopts the flight of rotor flying form, and in the time of cruising flight, aircraft of the present invention adopts fixed wing state flight.

The invention provides a kind of aircraft, comprise at least one the first rotor and at least one the second rotor, the first rotor and the second rotor are arranged on the longitudinal plane of symmetry of aircraft or along the symmetrical distribution of body.Rotor comprises at least two blades, and wherein at least one blade can rotate around turning mechanism.The first rotor comprises at least one the first blade and at least one the second blade, and the second rotor comprises at least one the first blade and at least one the second blade.Blade adopts asymmetric airfoil, and the aerofoil profile of the cross-sectional plane of blade is non-symmetrical, and blade has leading edge and trailing edge; Blade leading edge is round and smooth, and blade trailing edge is sharp-pointed; The aspect of blade, the plane projection shape of blade can be symmetrical, can be also non-symmetrical.Aircraft has rotor flying form, and in rotor flying form, the blade of rotor is uniformly distributed along S. A. Rotational Symmetry, and blade leading edge is towards rotor wing rotation direction, rotor wing rotation and produce lift; Aircraft also has the wing of determining flight form, is determining wing flight form, and the first rotor and the second rotor stop the rotation, the direction that at least one blade of rotor is advanced towards aircraft by the blade leading edge of turning back.If rotor stops at the leading edge of a blade towards the position of aircraft working direction, other blade of turning back to leading edge towards the position of aircraft working direction to produce position that lift or blade wing tip point to aircraft forward/rear to reduce resistance.Point to the position of aircraft fore-and-aft direction if rotor stops at blade Huo Jiang Grains, at least one blade of turning back to blade leading edge towards the position of aircraft working direction with generation lift.Determining wing flight form, one or two of the first rotor or all blade be distributed in the left side of aircraft and the leading edge of blade towards aircraft working direction to produce lift, one or two of the second rotor or all blade be distributed in the right side of aircraft and the leading edge of blade towards aircraft working direction to produce lift.The first blade of the first rotor be distributed in the left side of aircraft and blade leading edge towards aircraft working direction to produce lift, the second blade be distributed in the left side of aircraft and blade leading edge towards aircraft working direction with the position that produces lift or the second blade and point to aircraft fore-and-aft direction to reduce resistance; The first blade of the second rotor be distributed in the right side of aircraft and blade leading edge towards aircraft working direction to produce lift, the second blade be distributed in the right side of aircraft and blade leading edge towards aircraft working direction with the position that produces lift or the second blade and point to aircraft fore-and-aft direction to reduce resistance.While determining wing flight form, overlook visual angle, the blade of the blade of the first rotor and the second rotor distributes along aircraft front and back longitudinal centerline rotational symmetry.Aircraft can be in flight course in rotor flying form with the conversion of the form of determining to fly between wing flight form.Aircraft also comprises at least one rotor start stop apparatus, stop the rotation of rotor and lock rotor position when determining wing flight form from rotor flying modality for aircraft in the time that the flying speed of aircraft is among conversion rate territory, and aircraft starts rotor wing rotation and keeps rotor wing rotation state when determining wing flight modality to rotor flying form.Aircraft also comprises at least one blade device of turning back, for in the time that the flying speed of aircraft is among conversion rate territory, aircraft is from rotor flying modality to determining to drive blade to turn to blade leading edge towards the position of aircraft working direction or the position of blade sensing aircraft fore-and-aft direction when the wing flies form, drive blade to turn to blade along the symmetrical position of rotor wing rotation central rotation with aircraft when determining wing flight modality to rotor flying form, and in the time determining wing flight form, adjust sweepforward angle and/or the sweepback angle of blade.Aircraft also comprises S. A. angle regulator, and it is arranged on one or more S. A., for regulating aircraft in the direction of determining wing flight form Shi Jiang Grains.Total square of rotor and/or cycle square control apparatus can be used in the dihedral angle and/or the inverted diherdral of adjusting aircraft blade in the time determining wing flight form.Can there is in the vertical non-vanishing angle in the blade of aircraft of the present invention the same side in the time determining wing flight form.Aircraft of the present invention can also be furnished with propelling unit on blade, propelling unit can produce along chord of blade to propulsive force.Aircraft of the present invention also comprises at least one fixed wing, and extra lift and/or control of sideward roll moment is provided when flying before aircraft.Aircraft of the present invention can also adopt canard configuration's structure, arranges canard in the front portion of aircraft.Aircraft of the present invention is coaxial double-oar form.Aircraft of the present invention is for intersecting two paddle structures.Aircraft of the present invention is row two-bladed structure.Aircraft of the present invention is the structure that 4 rotors are symmetrically distributed in front and back, aircraft fuselage both sides.Aircraft of the present invention also comprises at least one horizontal propulsion device, and horizontal propulsion device can be pusher, can be also extending type.Aircraft of the present invention can be unmanned vehicle, can be also piloted vehicle.

Be used for the structure of the blade of aircraft of the present invention, blade at least comprises that from wing root to wing tip the chord length of wide string wing panel is at least the more than 1.2 times of narrow string wing panel chord length near the narrow string wing panel of the wide string wing panel of wing root and close wing tip.Blade also comprises transition wing panel, and transition wing panel is arranged between wide string wing panel and narrow string wing panel, and transition wing panel is identical with the aerofoil profile of the position that wide string wing panel is connected, and transition wing panel is identical with the aerofoil profile of the position that narrow string wing panel is connected.Blade also wraps wing root wing panel, and wing root wing panel is arranged in wide string wing panel and is connected near a side of wing root and with wide string wing panel, and wing root wing panel is shorter than be connected with the wide string wing panel chord length of position of wing root wing panel in the chord length at wing root place.The chord length of the wing root wing panel position that is connected with wide string wing panel from wing root wing panel shortens to wing root direction, and the chord length of wing root wing panel shortens to wing root direction from wing tip.Shortening of chord length can be that gradual change also can transition.In wide string wing panel, be furnished with aileron.Blade is in the aerofoil profile difference of different spanes place.

Aircraft of the present invention has advantages of helicopter alerting ability in the time of rotor flying state, in the time of fixed-wing state of flight, has advantages of that fixed wing aircraft power demand is little, voyage is long.With tiltrotor comparison, aircraft weight of the present invention is lighter, and while taking off, rotor diameter is large simultaneously, is not easy to be absorbed in downwash flow and has an accident when decline.With rotor-wing and the comparison of x wing aircraft of in-line, the blade of aircraft of the present invention/wing adopts non-symmetrical high-effect aerofoil profile, and efficiency is higher, and 1ift-drag ratio is larger.In the time taking off and land, aircraft of the present invention adopts rotor flying form to carry out vertical and landing takeoff, has the alerting ability that helicopter is identical, does not need runway; In the time of cruising flight, aircraft of the present invention adopts determines the flight of wing flight form, has advantages of that fixed wing aircraft flying speed is fast, voyage is long.

Accompanying drawing explanation

Below in conjunction with drawings and Examples, the present invention is further described.In the accompanying drawings, same or analogous label represents same or analogous parts.

Fig. 1 is the left view of the rotor flying form of one embodiment of the invention;

Fig. 2 is the front elevation of the rotor flying form of one embodiment of the invention;

Fig. 3 is the birds-eye view of the rotor flying form of one embodiment of the invention;

When Fig. 4 is rotor flying form, blade is turned back device with Jiang Grains position view;

Fig. 5 is that while determining wing flight form, blade is turned back device with Jiang Grains position view;

Fig. 6 be in Fig. 1 embodiment determine the wing flight form time Flight Vehicle Structure left view;

Fig. 7 be in Fig. 1 embodiment determine the wing flight form time Flight Vehicle Structure front elevation;

Fig. 8 be in Fig. 1 embodiment determine the wing flight form time Flight Vehicle Structure birds-eye view;

Fig. 9 be in Fig. 1 embodiment determine the wing flight form time blade longitudinally there is the Flight Vehicle Structure left view of angle;

Figure 10 be in Fig. 1 embodiment determine the wing flight form time blade longitudinally there is the Flight Vehicle Structure front elevation of angle;

Figure 11 be in Fig. 1 embodiment determine the wing flight form time blade longitudinally there is the Flight Vehicle Structure birds-eye view of angle;

The lateral plan of the rotor flying form of Figure 12 two paddle structure embodiment of intersection of the present invention;

The front elevation of the rotor flying form of Figure 13 two paddle structure embodiment of intersection of the present invention;

The birds-eye view of the rotor flying form of Figure 14 two paddle structure embodiment of intersection of the present invention;

Figure 15 is the part sectional view of the S. A. angle regulator of the two paddle structure aircraft of intersection in Figure 13;

Figure 16 is the lateral plan of determining wing flight form of the aircraft in Figure 12;

Figure 17 is the front elevation of determining wing flight form of the aircraft in Figure 12;

Figure 18 is the birds-eye view of determining wing flight form of the aircraft in Figure 12;

Figure 19 is the front elevation of the rotor flying form of the aircraft of two rotor lines layouts;

Figure 20 is the birds-eye view of the rotor flying form of the aircraft in Figure 19;

Figure 21 is the front elevation of determining wing flight form of the aircraft in Figure 19;

Figure 22 is the birds-eye view of determining wing flight form of the aircraft in Figure 19;

Figure 23 is the birds-eye view with the aircraft of 4 rotors;

Figure 24 is the rotor flying form birds-eye view that is furnished with the aircraft of propelling unit on blade;

Figure 25 be aircraft in Figure 24 determine wing flight form lateral plan;

Figure 26 be aircraft in Figure 24 determine wing flight form front elevation;

Figure 27 be aircraft in Figure 24 determine wing flight form birds-eye view;

Figure 28 is the one-sided blade rotor of the device constructional drawing in the time of rotor flying form of turning back that has;

Figure 29 is the one-sided blade rotor of the device constructional drawing in the time determining wing flight form of turning back that has;

Figure 30 is the structural representation of rotor in the time of rotor flying form with three blades;

Figure 31 is the structural representation of rotor in the time determining wing flight form with three blades;

Figure 32 is the plane structure chart that is applied to the blade of aircraft of the present invention;

Figure 33 is the plane structure chart that is applied to the another kind of blade of aircraft of the present invention.

The specific embodiment

Fig. 1, Fig. 2, Fig. 3 are the three-view diagrams of the rotor flying form of a coaxial double-oar embodiment of aircraft of the present invention, and wherein rotor flying form is helicopter flight pattern.Fig. 1 is left view, and Fig. 2 is front elevation, and Fig. 3 is birds-eye view.The both sides of the fuselage 1 of aircraft are furnished with short limb 2, and short limb 2 provides auxiliary lifting can fly before aircraft time.On short limb 2, be furnished with aileron, rolling control torque is provided can fly before aircraft time.Fuselage 1 arranged beneath has alighting gear 3.There are two tail booms 4 at fuselage 1 rear portion, and tail boom can support level empennage 5 and vertical tail 6.On tailplane 5, be furnished with elevating rudder.On vertical tail 6, be furnished with yaw rudder.The rear portion of fuselage 1 is furnished with propelling unit 7, and propelling unit 7 is screw propeller, and it is longitudinal along standard of fuselage that propelling unit 7 can provide, i.e. the axial thrust of x.Aircraft of the present invention also can be arranged in other position propelling unit, as forebody, or on short limb.Aircraft of the present invention also can adopt the propelling unit of other form, as jet engine.Aircraft in the present embodiment is coaxial double-oar structure.Back is furnished with S. A. 20.S. A. 20 is connected with engine installation, can under the driving of engine installation, rotate.Screw propeller and S. A. 20 can share a set of engine installation, between engine installation and S. A., prop shaft, are furnished with respectively power-transfer clutch, for disconnecting as required or the power output of connecting power device.Screw propeller and S. A. 20 also can configure respectively engine installation.S. A. 20 is quill shaft, and the outer shaft of quill shaft is connected with lower rotor, and the interior axle of quill shaft is connected with upper rotor.Coaxial double-oar drives upper and lower two secondary rotor contrarotations with quill shaft.Lower rotor comprises two blades, blade 11 and blade 12.Blade 11 is connected Yu Jiang Grains 41 by the hinge 31 of turning back.Blade 12 is connected Yu Jiang Grains 41 by the hinge 32 of turning back.In the time of rotor flying form, radially, blade 11 and blade 12 distribute around S. A. Rotational Symmetry the plane of revolution that blade 11 and blade 12 point to rotor.Blade 11, blade 12 He Jiang Grains 41 are point-blank.Upper rotor comprises two blades, blade 13 and blade 14.Blade 13 is connected Yu Jiang Grains 43 by the hinge 33 of turning back, and blade 14 is connected Yu Jiang Grains 43 by the hinge 34 of turning back.Blade 13, blade 14 are point-blank.Upper rotor and lower rotor have formed a secondary lift wing pair.The lift wing is to being that hand of rotation is contrary, two rotors of the mutual balance of rotor inertia, and the slewing rate of right two rotors of the lift wing is identical conventionally.In Fig. 3, in rotor flying form, upper rotor clickwise, lower rotor left-hand revolution.Upper rotor and lower rotor are provided with cycle square and total square control mechanism, and cycle square and total square control of rotor can be provided.Aircraft of the present invention in the time of rotor flying form, according to the offline mode flight of autogyro, can vertical takeoff and landing, flight control method is identical with coaxial dual-rotor helicopter.By increasing or reduce total square, the lift of rotor changes, and aircraft can vertical uplift or decline.By the plane of revolution of the rotor that turns forward, the lift of rotor produces component in the horizontal direction, can promote to fly before aircraft.Meanwhile, aircraft of the present invention can also flight forward under the promotion of screw propeller.Upper rotor and lower rotor are all two-bladed rotors, replace flapping hinge and lead lag hinge with single " seesaw " hinge simultaneously.There is collision mutually in upper and lower rotor blade when preventing rotor flying form, arranges inhibiting device, to limit the amplitude of waving up and down of blade on " seesaw " hinge.Preferably, can adopt replacement " seesaw " hinge that is rigidly connected, Ji Jiang Grains and S. A. are rigidly connected, and do not wave with shimmy.Because the hand of rotation of upper and lower rotor is contrary, although so the lift of an independent rotor is inhomogeneous in rotor wing rotation plane while flying before helicopter, but the degree of irregularity of upper and lower rotor lift is symmetrical, even if not waving with shimmy, blade also there will not be roll.In this enforcement, be also furnished with short limb 2, in the time that forward flight speed is non-vanishing, the aileron on short limb 2 also can produce rolling moment, the overbalance situation of the rolling moment that can balance upper and lower rotor produces.The preferred wide string of blade, rigidity or the semirigid structure of the rotor of aircraft of the present invention.For the rotor that is furnished with flapping hinge and lead lag hinge on blade, the hinge of turning back can unite two into one with lead lag hinge.For adopting the rotor of Rou Jiang Grains and/or having the rotor of two blades, the independent hinge of turning back need to be set.Preferred ， Jiang Grains adopts rigidity Jiang Grains structure ， Jiang Grains and blade to be hinged by turning back.The rotor up and down of two oar layouts adopts point other total distance and cycle apart from control, and all blades have " three hinges " separately, i.e. pitch hinge, flapping hinge, lead lag hinge, or the corresponding elastic element of an equivalent effect.In the present embodiment, upper rotor and lower rotor have two blades, and upper rotor and lower rotor can also have 2 above blades.

Fig. 4 is that in Fig. 1, Fig. 2, Fig. 3, aircraft embodiment blade in the time of rotor flying form is turned back device with Jiang Grains positional structure schematic diagram.Upper rotor is identical with the connection structure of lower rotor and oar Grains with the connection structure of oar Grains.Jiang Grains 41 rigidly fixes connection ， Jiang Grains 41 with S. A. 20 can be along with rotation together with S. A. 20.Blade 11 is connected to by blade beam 51 hinge 31 of turning back.The hinge of turning back belongs to the one of turning mechanism, can also adopt other known turning mechanism.Jiang Grains axle 61 is connected with the hinge 31 of turning back along one end of rotor radial arrangement Jiang Grains 41 interior ， Jiang Grains axles 61, and the other end is connected with rocking arm 71.Jiang Grains axle 61 can the interior Yan Jiang Grains of Jiang Grains 41 axle 61 self axis rotate.Jiang Grains axle is a kind of form of bending moment hinge, can also adopt the bending moment hinge of other known forms.One end of rocking arm 71 is fulcrum, and fulcrum is connected with connecting rod, and connecting rod is connected with upper swash plate, and upper swash plate rotates with rotor.Upper swash plate is close to lower swash plate and is slided, and ball capable of reducing friction resistance also can be installed on contact surface, and the angle of inclination of upper swash plate is determined by lower swash plate.Lower swash plate does not rotate with rotor, but mechanical linkage or hydraulic actuator control can be passed through in angle of inclination, and lower swash plate drives upper swash plate to tilt, and upper swash plate drives rocking arm 71 by connecting rod, and rocking arm 71 drives oar Grains axle 61 to rotate.The rotation of Jiang Grains axle 61 drives blade to rotate around rotor beam 51.Jiang Grains axle 61 can transmit total square and cycle square control.In the time that rocking arm 71 is pulled down, the angle of attack of blade 11 increases, and in the time that rocking arm 71 is upwards pushed away, the angle of attack of blade 11 reduces.Blade 12 is connected ， Jiang Grains axle 62 with the hinge 32 of turning back one end by blade beam 52 is connected with the hinge 32 of turning back, and the other end is connected with rocking arm 72.The blade device of turning back comprises actuating mechanism and turning mechanism.Actuating mechanism comprises the mechanism that can produce linear displacement or angular transposition of ACTUATOR or other form.Turning mechanism comprises the mechanism that can produce angle displacement of turn back hinge or other form.Blade 11 and blade 12 are connected with a set of blade device of turning back respectively.A side of Jiang Grains 41 is furnished with ACTUATOR 81 and ACTUATOR 82.One end of ACTUATOR 81 is connected with blade beam 51, and the other end is connected Yu Jiang Grains 41.ACTUATOR be spherical linkage with blade beam with the two ends that Jiang Grains is connected, can on three-dimensional, rotate.ACTUATOR can be hydraulic actuator, or the ACTUATOR of other form such as air pressure, electromagnetism, machinery, and ACTUATOR can extend and shorten.One end of ACTUATOR 82 is connected Yu Jiang Grains 41, and the other end is connected with blade beam 52.In the time that ACTUATOR 81 shortens, can drive blade 11 to rotate in the counterclockwise direction around the hinge 31 of turning back, rotate along the direction identical with rotor wing rotation direction.When ACTUATOR 82 shortens, can drive blade 12 to rotate along clockwise direction around the hinge 32 of turning back, along rotating with the direction of rotor wing rotation opposite direction.ACTUATOR can play the work of damper in order to the vibration of the blade of decaying, and also can arrange the vibration of independent damping mechanism decay blade.The opposite side relative with ACTUATOR of Jiang Grains 41 is furnished with balance block 22, and the rotor inertia overbalance that balance block 22 can balance play cylinder causes, makes rotor wing rotation steady.Two blade turning mechanisms also can be arranged in the not homonymy of oar Grains.When the turning mechanism of blade is arranged in the not homonymy of oar Grains, from rotor form when determining wing modality, the ACTUATOR of a side pulls blade to rotate around the hinge of turning back, the ACTUATOR of opposite side promotes blade and rotates around the hinge of turning back.Blade 11 and blade 12, around S. A. 20 left-hand revolutions, produce lift upwards.Upper rotor has the structure identical with lower rotor.Upper rotor and lower rotor have the identical blade device of turning back.The front that in figure, x positive dirction is aircraft.

Fig. 5 is that in Fig. 1, Fig. 2, Fig. 3, aircraft embodiment blade in the time determining wing flight form is turned back device with Jiang Grains positional structure schematic diagram.Aircraft is in the time determining wing flight form, and S. A. 20 stops operating, and also locking holding position is motionless.Jiang Grains 41 is in the position parallel with aircraft x axle, and Ji Jiang Grains 41 points to the direction before and after aircraft.ACTUATOR 81 shortens, and drives blade 11 to rotate counterclockwise the direction of advancing towards aircraft to blade 11 leading edges around the hinge 31 of turning back, i.e. x axle positive dirction, and keep motionless.Shorten the difference of degree according to ACTUATOR 81, blade 11 can be vertical with fuselage, also can have certain sweepback angle.ACTUATOR 82 shortens, and drives blade 12 to be clockwise to blade 12 leading edges towards aircraft working direction around the hinge 32 of turning back.Now blade 11 and blade 12 are positioned at the right side towards aircraft working direction.Shorten the difference of degree according to ACTUATOR 82, blade 12 can be vertical with fuselage, also can have certain sweepforward angle.The angle at the sweepback angle of blade 11 can be identical with the angle of the sweepforward angle of blade 12, also can be different.By change the sweepforward angle of blade or sweepback angle can change of flight device lift and resistance situation when the different flying speed, improve flight quality, make aircraft all the time in flight optimization state.Two blades of upper rotor are turned back by the blade turning mechanism of upper rotor, and two blades are towards the left side of aircraft working direction, the direction that the leading edge of two blades is advanced towards aircraft.In the time of drop-down rocking arm simultaneously 71 and 72, while increasing total square of lower rotor, oar Grains axle 61 drives blade 11 to rotate counterclockwise around x axle, and the wing tip of blade 11 is moved upward, and blade 11 has the dihedral angle; Jiang Grains axle 62 drives blade 12 to clockwise rotate around x axle, and the wing tip of blade 12 moves downwards, and blade 12 has inverted diherdral.Blade 11 and blade 12 in the vertical directions produce angle, can avoid the air-flow that flows through blade 12 that blade 11 is produced and disturbed.When on while pushing away rocking

arm

71 and 72, the angle between blade reduces.When drop-down rocking arm 71 and on while pushing away rocking arm 72, can increase the dihedral angle of two blades simultaneously.When drop-down rocking arm 72 simultaneously and on while pushing away rocking arm 71, the dihedral angle that can simultaneously reduce by two blades.Drop-down rocking arm 71 and the situation that above pushes away rocking arm 72 above push away with drop-down rocking arm 72 situation of rocking arm 71 corresponding be the operation to cycle square.In order to guarantee that blade can be in correct position, can be at blade Yu between Jiang Grains position Locking Device limit and keep blade at rotor state and determine the position of wing state.Position Locking Device is known technology.ACTUATOR can be movement device, plays the effect of Locking Device simultaneously.

For the stationarity that guarantees that aircraft flies in flight modality process, when aircraft of the present invention from rotor flying form when determining wing flight modality, for having, the switching process of rotor of two blades is as follows: 1/4 circle before S. A. is by locking, when Ji Jiang Grains points to aircraft left and right directions, blade leading edge towards the blade of the blade in aircraft front turn back device start, blade reversing sense this blade of turning back that device rotates to S. A. with the angular rate identical with S. A. of turning back, to keep this blade to point to all the time aircraft left and right directions and leading edge towards aircraft forward, can provide lift for aircraft, meanwhile, blade leading edge starts towards the blade of the blade at the aircraft rear device of turning back, and blade is turned back device to the direction identical with the S. A. rotation direction lock position of this blade to blade of turning back.Adopt above-mentioned switching process, can guarantee each rotor have a slice blade in the end 1/4 circle all the time towards aircraft front to produce lift, guaranteed switching process steadily.

When aircraft of the present invention is when determining wing flight form to rotor flying modality, for having, the switching process of rotor of two blades is as follows: initial 1/4 circle that starts rotation at S. A., the blade of posterior blade turn back device start, blade reversing sense this blade of turning back that device rotates to S. A. with the angular rate identical with S. A. of turning back, to keep this blade sensing aircraft left and right directions and leading edge towards aircraft forward, think that aircraft provides lift; Meanwhile, the blade of preceding blade turn back device start, blade turn back device to the direction identical with S. A. rotation direction turn back this blade to blade Yu Jiang Grains point-blank.

Fig. 6, Fig. 7, Fig. 8 are the three-view diagrams of determining wing flight form of aircraft embodiment in Fig. 1.While determining wing flight form, aircraft is according to the offline mode flight of fixed wing aircraft.Fig. 6 is lateral plan, and Fig. 7 is front elevation, and Fig. 8 is birds-eye view.Determining wing flight form, the oar Grains 43 of upper rotor and the oar Grains 41 of lower rotor are locked in along aircraft direction end to end, along x direction of principal axis.On S. A. 20, be furnished with rotor start stop apparatus.Interior axle and outer shaft can be arranged respectively a set of rotor start stop apparatus, also can share a set of rotor start stop apparatus.Rotor start stop apparatus comprises the power-transfer clutch being arranged between rotor and engine installation.Power-transfer clutch can be any type of power-transfer clutch.Rotor start stop apparatus comprises S. A. speed reduction gearing, and S. A. speed reduction gearing can make to decelerate to quiescence in the S. A. of slew mode.S. A. speed reduction gearing comprises the brake gear being arranged on S. A..Brake gear can be disk type brake, can be also drum brakes, can also be the brake of electromagnetic form.Rotor start stop apparatus comprises S. A. Locking Device, and Locking Device can lock the position of S. A..S. A. Locking Device can be same device with brake gear, and brake gear maintenance braking state just can locking S. A..S. A. Locking Device can also be the axle Locking Device of other known forms.For quill shaft, the Locking Device of S. A. can be the lockable mechanism of interior axle and outer shaft synchronous device, and for example in locking, the synchronizer gear of axle and outer shaft just can the interior axle of while locking and outer shaft.S. A. Locking Device can also be independently two Locking Devices that are arranged on interior axle and outer shaft.S. A. 20 in the present embodiment is quill shafts, and the interior axle of quill shaft and outer shaft, all by locking, keep motionless.In the time of rotor flying form, blade 13 and blade 14 Yu Jiang Grains 43 are point-blank.When aircraft from rotor flying form when determining wing flight modality, rotor start stop apparatus stop the rotation axle rotation and to make S. A. be locked at Jiang Grains be the axial position of x towards fuselage fore-and-aft direction.In Fig. 8, the blade 13 of upper rotor is driven with respect to Jiang Grains 43 cws and turns back to the leading edge of blade 13 and fix towards aircraft working direction holding position by the blade of self device of turning back.Blade 14 is driven with respect to Jiang Grains 43 conter clockwises and turns back to blade leading edge towards the position of aircraft working direction and keep fixing by the blade device of turning back.In Fig. 7, blade 13 and blade 14 are positioned at the right side of aircraft fuselage.Blade 13 has certain sweepback angle, and blade 14 has certain sweepforward angle.Blade 13 and blade 14 are in same horizontal surface.Blade 11 and blade 12 are turned back to blade leading edge towards aircraft working direction by the blade device of turning back respectively.In Fig. 7, blade 11 and blade 12 be towards aircraft left side, and in same horizontal plane.Blade 11 has sweepback angle, and blade 12 has sweepforward angle.At the state of overlooking of Fig. 8,

blade

11,12,13,14 distributes along aircraft axis rotational symmetry, and blade becomes fixed wing.In Fig. 7, two blades of lower rotor stretch out to the left side of fuselage, and two blades of upper rotor stretch out to the right side of fuselage.While flying before aircraft, air flow stream is crossed

blade

11,12,13,14, produces lift upwards.Propelling unit 7 provides the power flying before aircraft.Tailplane 5 provides level stable control, and the elevating rudder on tailplane provide aircraft pitch control subsystem.Vertical tail 6 providers control to stable, and the yaw rudder on vertical tail provides vehicle yaw control.Aircraft is with the flying method flight of fixed wing aircraft.Conventionally the blade of lifting airscrew adopts narrow string, high aspect ratio structure, produces enough lift by the High Rotation Speed of

rotor.Blade

11,12,13,14 can provide enough lift when ensureing that aircraft of the present invention is determined wing flight form, and preferred

blade

11,12,13,14 adopts wide string rigid construction.The rotative speed of the rotor of aircraft of the present invention will be slower than common helicopter.Although the resistance while adopting wide string blade to increase rotor wing rotation, lower efficiency, but aircraft of the present invention is only taking off and landing stage employing rotor flying mode, determine wing mode and fly and adopt in the time cruising, because fly suffered resistance before aircraft while flying suffered resistance much smaller than rotor flying before aircraft while determining wing flight, so the efficiency of aircraft improves greatly while determining wing flight.In Fig. 7, while determining wing flight form, the upper blade of rotor and the blade of lower rotor be not in a horizontal surface.After aircraft takes off with rotor flying form, rotor leans forward and/or screw propeller promotion aircraft flies forward.Aircraft of the present invention has a conversion rate territory, and conversion rate territory is a speed range.The minimum stable flying speed that the lower limit speed value in conversion rate territory is aircraft when determining the flight of wing flight form, i.e. stalling speed, if the speed of aircraft lower than lower limit speed, aircraft just can not fly with surely wing state, and can only fly with rotor form; The upper limit speed value in conversion rate territory is the highest flying speed of aircraft while flying with rotor flying form.When the speed of aircraft is during higher than upper limit speed value, aircraft can only be with surely wing state stabilized flight.The lower limit speed value in conversion rate territory will be lower than upper limit speed value.When the speed of aircraft is during in flight modality speed territory, aircraft can be with the flight of rotor form, also can be with surely wing state flight, and aircraft can and determine the wing and fly and change between two kinds of structures of form in rotor flying form.Just can realize lower limit speed value lower than upper limit speed value by chord length, length and the shape of reasonable design blade.Common fixed wing aircraft needs rolling start, for shortening take off distance, can make aircraft just produce and go up to the air compared with large lift in the time of low speed as far as possible.In order to produce larger lift when the low speed, the measure of taking comprises increases the angle of attack of wing while taking off, increase wing area.And in the time of fixed wing aircraft high-speed flight, because speed is fast, can produce larger lift, and now the area of wing does not need to resemble needed while taking off large.In a preferred embodiment of the present invention, the lower limit speed in conversion rate territory is 140 kilometers/hour, and the takeoff speed of the fixed wing aircraft of same take-off weight is 90 kilometers/hour.Aircraft 0.42 times of required wing area in the time that 140 kilometers/hour of needed wing areas only have 90 kilometers/hour of speed to take off.Therefore the area of the blade of aircraft of the present invention greatly reduces with respect to comparable fixed wing aircraft.In the situation that length is identical, the minimizing of wing area will make wing chord length shorten, the less thick of wing, the resistance force diminishes that wing is suffered.Under same driving engine promotes, aircraft of the present invention will fly sooner, voyage is longer.Short limb 2 can provide extra lift in the time that aircraft has horizontal velocity.Short limb can adopt folding mode, and in the time that needs provide extra lift, short limb launches, and in the time not needing, short limb is folding packs up.When aircraft from rotor flying form when determining wing flight modality, the rotative speed of rotor declines gradually, the lift producing reduces, and now can compensate by increasing the angle of attack of whole aircraft the minimizing of lift, and the thrust that simultaneously increases propelling unit keeps flying speed.When aircraft is when determining wing flight form to rotor flying modality, also can improve lift by the angle of attack that increases aircraft, complete the conversion of flight form, ensure the stationarity of flight.In the time determining wing flight form, in two blades of same rotor, in being preceding blade near the blade of Vehicle nose position, be called for short at front blade; Be posterior blade in the blade near aircraft tail position, be called for short at rear blade.The blade of rotor can also be turned back to blade exhibition to the position of pointing to aircraft fore-and-aft direction, to reduce resistance, is now equivalent to the situation that blade sweepback angle is 90 degree.

Fig. 9, Figure 10, Figure 11 be in Fig. 1 aircraft embodiment determine wing flight form, and there is the three-view diagram of angle situation between longitudinally in blade.Fig. 9 is lateral plan, and Figure 10 is front elevation, and Figure 11 is birds-eye view.The blade 13 of upper rotor has the dihedral angle, and the wing tip of blade is upwards offset.The blade 14 of upper rotor has inverted diherdral, and the wing tip of blade offsets downward.There is in the vertical non-vanishing angle in blade 13 and blade 14.The blade 11 of lower rotor has the dihedral angle, and blade 12 has inverted diherdral.There is in the vertical angle in blade 11 and blade 12.The blade 13 of upper rotor and blade 14 are positioned at the same side of fuselage, if two blades do not have angle in the vertical, the wake flow of so preceding blade 14 will disturb posterior blade 13.And two blades exist angle in the vertical, just avoid the unfavorable interference at rear blade at the air-flow of front blade.Especially when having the dihedral angle at front blade, in the time that rear blade has inverted diherdral, the eddy current flow that the wake flow of preceding blade produces is crossed the upper surface of posterior blade, can increase the lift of posterior blade.Between preceding blade and posterior blade, keep in the vertical the above angle of at least 10 degree, preferred, at least keep angles more than 15 degree.Blade has the dihedral angle or inverted diherdral can regulate by total square control, and preceding blade has the dihedral angle or inverted diherdral also can regulate by total square control.When rotor state, regulate the cycle square control of rotor disc direction of tilt can in the time determining wing flight form, adjust longitudinal deflection angle of two blades to same direction.In Figure 10, in the time that

blade

11,12,13,14 has respectively the dihedral angle and inverted diherdral, the centre of lift line of blade is to the vertical distance difference of aircraft center of gravity, the rolling moment difference that each blade produces aircraft center of gravity, and aircraft can be subject to a rolling moment.Because aircraft has the speed moving ahead while determining wing flight form, the differential of the aileron rudder face on aircraft short limb 2 can produce the rolling moment that reverse rolling moment produces with balance blade, to keep the steady of aircraft form.Can also eliminate the rolling moment overbalance that blade causes by move down rotor in the time determining wing state of flight.A kind of scheme that moves down rotor is the interior glides downward quill shaft.

Figure 12, Figure 13, Figure 14 are the three-view diagrams of the rotor flying form of the two paddle structure aircraft of intersection of the present invention.Figure 12 is lateral plan, and Figure 13 is front elevation, and Figure 14 is birds-eye view.Flying instrument in the present embodiment has fuselage 1, has two tail booms 4 at the rear portion of fuselage, and the tail end of tail boom is furnished with two vertical tails 6, and there is yaw rudder the rear end of vertical tail.Between two tail booms, be furnished with tailplane 5, there is elevating rudder the rear end of tailplane.The present embodiment can also be furnished with canard in the front portion of aircraft.Aircraft has propelling unit 7, and the propelling unit in the present embodiment is screw propeller.Aircraft in the present embodiment, for intersecting two paddle structures, has two rotors, and the V-shaped layout of S. A. of two rotors, has the angle that is greater than 0 degree between S. A., and two rotors are symmetrical along aircraft longitudinal center face.Two rotors of the present embodiment have formed a secondary lift wing pair.In Figure 13, the rotor in left side rotates around S. A. 21, and rotor has blade 11 and blade 12.The rotor on right side rotates around S. A. 20, and rotor has blade 13 and blade 14.Blade adopts seesaw chain connection Yu be rigidly connected between Jiang Grains between ， Jiang Grains and S. A..Between Jiang Grains and S. A., also can adopt and be rigidly connected.The common each rotor of helicopter of the two oars of intersection has two blades, also can have 2 above blades., there is differential seat angle in the direction of rotation of two rotors, therefore the blade of two rotors can't collide between blade.Differential seat angle between two rotors can be 90 degree, in the time that the blade of a rotor points to fuselage fore-and-aft direction, the left and right that the blade of another rotor points to fuselage to.Between S. A. 20 and S. A. 21, there is synchronous device.The aircraft of this enforcement is in the time that rotor state flies, and the lift straight up of making a concerted effort to produce of two rotors, drives aircraft vertical uplift.Rotor has cycle square, total square control.In the time regulating rotor to turn forward by cycle square, aircraft can fly forward.Aircraft also can rely on the horizontal thrust of the generation of propelling unit 7 to move ahead.In the time that horizontal flight speed reaches the lower limit speed value in conversion rate territory, just can change flight form, from rotor flying modality to determining wing flight form.

Figure 15 is the part sectional view of the rotor angle regulator of the two paddle structure aircraft of intersection in Figure 12.Angle regulator can be arranged on S. A., also can be arranged between rotor Jiang Grains and S. A..On S. A. 21, be furnished with angle regulator.Angle regulator for from rotor flying form when determining wing flight modality and regulate the angle of S. A. while determine wing flight form, to regulate the direction of determining wing flight form Shi Jiang Grains, i.e. sensing.Angle regulator comprises quill shaft and action lockable mechanism.Quill shaft comprises outer shaft 212 and interior axle 211, bearing fit between interior axle 211 and outer shaft 212, and interior axle 211 can rotate in outer shaft 212.On interior axle 211, be fixedly connected with one heart turbine 213.On outer shaft 212, be fixedly connected with worm seat 215, worm screw 214 is arranged on worm seat 215, and worm drive device is also arranged on worm seat 215.Turbine 213 and worm screw 214 mesh together, and together with interior axle 211 is locked at outer shaft 212, interior axle 211 and outer shaft 212 are with identical speed rotation.Turbine 213, worm screw 214, worm seat 215 and worm drive device rotate together with S. A. 21.In rotor flying form, S. A. 20 and S. A. 21 synchronous rotaries.When from rotor flying form to determining wing state of flight when conversion, S. A. 20 and interior axle 211, by rotor start stop apparatus locking, keep maintaining static.Worm screw 214 is rotated under the drive of worm drive device, drives turbine 213, because the interior axle 211 that turbine 213 connects can not be rotated by locking, so worm screw 214 drives worm seat 215, outer shaft 212 to rotate together, and then drives rotor to rotate.For example, when the corner of the rotor on two rotor shaft tops differs 90 while spending, determining wing flight form, S. A. 20 is locked on the position that Jiang Grains points to fuselage fore-and-aft direction, now S. A. 21 top Jiang Grains point to the position of fuselage left and right directions; Worm screw promotes the outer shaft 212 of S. A. 21 upper ends rotates 90 degree and points to the oar Grains on top the position of fuselage fore-and-aft direction, makes the blade of two rotors and oar Grains along fuselage longitudinal center face symmetry.Also worm screw can be arranged on interior axle, turbine is arranged on outer shaft.Worm screw can adopt driven by servomotor, also can adopt hydraulic drive.While differing arbitrarily angled between two rotors, can both be adjusted to the rotor position of symmetry mutually by angle regulator.Can also adopt the angle regulator of other form, for example expanding-contracting action cylinder.One end of expanding-contracting action cylinder is hinged and connected on interior axle by spherical, and the other end is hinged and connected on outer shaft by spherical, and the elongation of expanding-contracting action cylinder and shortening are slided axle in drive in outer shaft, reach the object of adjusting angle.On S. A. 20, be furnished with rotor inertia balancing device 210, for keeping S. A. 20 identical with S. A. 21 rotor inertias.

Figure 16, Figure 17, Figure 18 be aircraft in Figure 12 determine wing flight form three-view diagram.Figure 16 is lateral plan, and Figure 17 is front elevation, and Figure 18 is birds-eye view.S. A. 20 and S. A. 21 are kept transfixion by locking, and S. A. 20 is locked in the position of Jiang Grains sensing fuselage fore-and-aft direction, and S. A. 21 is also rotated to Jiang Grains to point to the position of fuselage fore-and-aft direction and keep motionless by angle regulator.On 4 blades, be furnished with respectively the blade device of turning back, the blade of can turning back to blade leading edge towards flight working direction and fix blade.In Figure 17, blade 13 and blade 14 are distributed in the right side of fuselage, and blade 11 and blade 12 are distributed in the left side of fuselage.The leading edge of

blade

11,12,13,14, towards the direction of aircraft flight, produces lift.On blade 13 and blade 14 are longitudinal, have angle, blade 14 can have sweepforward angle, and blade 13 can have sweepback angle.On blade 11 and blade 12 are longitudinal, have angle, blade 11 and blade 12 also can have sweepforward angle and/or sweepback angle.In Figure 18, blade 11 and blade 13, blade 12 and blade 14 distribute along fuselage longitudinal centerline rotational symmetry respectively.The centre of lift line of

blade

11 and 13 equates to the distance of aircraft center of gravity, the centre of lift line of

blade

12 and 14 also equates to the distance of aircraft center of gravity, so, even if blade has the dihedral angle and/or inverted diherdral, the rolling moment that blade produces is mutual balance also, does not need to introduce extra rolling moment measure of control aircraft again and also can keep stable.Two oars that intersect are blade/wing full symmetrics in the time determining wing flight form with respect to the advantage of coaxial double-oar, and the control of aircraft is fairly simple, and shortcoming is need to introduce angle regulator and regulate the angle of rotor, has increased the complexity of mechanism.In the time determining wing flight form, in order to reduce the resistance of S. A., Jiang Grains, turn back hinge, spar, can be at S. A. with Jiang Grains adds fairing outward, to reduce resistance.

Figure 19 is the rotor flying form front elevation of the aircraft of two rotor lines layouts; Figure 20 is the rotor flying form birds-eye view of the aircraft in Figure 19.Flying instrument in Figure 19 and Figure 20 has wing 8, is furnished with two nacelles at the two ends of wing 8, has arranged respectively a rotor on each nacelle.In nacelle, there is rotor drive device.Two rotors have formed a secondary lift wing pair.Be furnished with respectively screw propeller 71 and 72 at the rear portion of two nacelles, screw propeller 71 and 71 provides the power flying before aircraft.Aircraft can also adopt jet propulsion.The propelling unit of aircraft also can be arranged in the front portion of nacelle.S. A. 20 and 21 lays respectively at the top of two nacelles.There is rotor on the top of S. A. 20, and the two ends of Xuan Yi Jiang Grains are furnished with blade 13 and blade 14.The top of S. A. 21 is furnished with blade 11 and blade 12.On two rotors, there are total square, cycle square control.On rotor, there are flapping hinge and lead lag hinge.In the time that rotor only has two blades, can adopt seesaw hinge to replace flapping hinge and lead lag hinge, also can adopt the rotor of perfect rigidity.In the time of rotor flying form, blade rotates around S. A., for aircraft provides the lift of rising.Screw propeller 71 and screw propeller 72 promote aircraft and fly forward.Aircraft has vertical tail and tailplane, and the various flight controls of aircraft are provided.In the time that aircraft has had flying speed, wing 8 also can provide a part of lift.On wing 8, can arrange aileron.

Figure 21 is the front elevation of determining wing flight form of the aircraft in Figure 19; Figure 22 is the birds-eye view of determining wing flight form of the aircraft in Figure 19.In the time determining the flight of wing flight form, blade 13 and blade 14 are to the right lateral expansion of wing 8, and the leading edge of blade 13 and blade 14 is towards the front portion of aircraft.Blade 13 is horizontal and anti-and sweepback on blade 14.Blade 11 and blade 12 stretch to the left-external side of wing 8, and the leading edge of blade 11 and blade 12 is towards the front portion of aircraft.Blade 12 is horizontal and anti-and sweepback on blade 11.Blade maintenance level and on another blade anti-form can realize by the Collaborative Control of total square and cycle square.Before while flying,

blade

11,12,13,14 and wing 8 provide the lift of aircraft jointly.

Figure 23 is the birds-eye view with the aircraft of 4 rotors.Aircraft has two wings, has respectively arranged a rotor at the two ends of each wing.The rotor at anterior wing two ends has formed a secondary lift wing pair, and the rotor at wing two ends, rear portion has formed another secondary lift wing pair.On the wing of rear portion, be furnished with horizontal propulsion device.In the time that rotor flying form is flown, rotor provides the lift of aircraft vertical takeoff and landing.In the time determining wing flight form, the rotor of each wing both sides is turned back according to the identical mode of turning back of the rotor of embodiment in Figure 19, Figure 20, and the leading edge of each blade of turning back is towards the direction of aircraft flight.Eight blades of four rotors can provide lift.Aircraft can also adopt the version of more rotors such as 6 rotors, 8 rotors.

Figure 24 is the rotor flying form birds-eye view that is furnished with the aircraft of propelling unit on coaxial double-oar structure, blade.The present embodiment is the aircraft of the jet structure of a kind of wing tip, is furnished with propelling unit on blade, propelling unit can produce along chord of blade to propulsive force,, with the blade exhibition propulsive force to vertical direction, the direction of propulsive force is vertical with the length direction of blade.Connecting power device not on the S. A. of aircraft, rotor relies on the promotion of the propelling unit on blade and rotates, and then produces vertical lift.Propelling unit can be jet-propulsion plant, can be also propeller plant.The S. A. of aircraft is quill shaft, and lower rotor is connected with outer shaft, and upper rotor is connected with interior axle.Lower rotor has blade 11 and blade 12, and upper rotor has blade 13 and blade 14.On blade 11, be furnished with propelling unit 151, on blade 12, be furnished with propelling unit 152, on blade 13, be furnished with propelling unit 153, on blade 14, be furnished with propelling unit 154.Blade 13 and blade 14 clickwise under the promotion of propelling unit, blade 11 and 12 left-hand revolution under the promotion of propelling unit.Horizontal propulsion device provides the power flying before aircraft.Horizontal propulsion device can be cancelled.On upper rotor and lower rotor, be furnished with total square and cycle square control, wherein cycle square control can be omitted.

Figure 25,26, the 27th, in Figure 24, aircraft is determined the three-view diagram of wing flight form.Figure 25 is lateral plan; Figure 26 is front elevation; Figure 27 is birds-eye view.When the aircraft of the present embodiment enters while determining wing flight form, the

blade

13,14 of upper rotor stretches to fuselage right side, and blade leading edge is towards aircraft working direction, and jet-propulsion plant 153,154 is rearward jet, and thrust is forward provided; The

blade

11,12 of lower rotor stretches to the left side of fuselage.In the time determining wing flight form, the propelling unit on the blade of the aircraft of the present embodiment can promote aircraft and advance.The aircraft of the two paddle structures of intersection of the present invention also can adopt the mode of arranging propelling unit on blade.

The rotor of aircraft of the present invention is all arranged the turn back scheme of device of a blade except adopting on every a slice blade, can also adopt each rotor only on a slice blade, to be furnished with the turn back scheme of device of blade.Figure 28 is the one-sided blade rotor of the device constructional drawing in the time of rotor flying form of turning back that has.The spar of blade 11 is fixedly connected with Yu Jiang Grains axle 61, can be also integrative-structure.Blade 11 can not be turned back by Rao Jiang Grains 41.The spar 52 of blade 12 is connected with the hinge 32 of turning back, and the hinge 32 of turning back is connected Yu Jiang Grains axle 62.Spar 52 is fixedly connected with turbine 93.On Jiang Grains 41, be fixedly connected with worm seat 90, worm screw 91 engages with turbine 93 through worm seat.On worm seat, there is worm drive device.There is balance block 23 one end that there is no worm seat of Jiang Grains, for the rotor inertia of balance turbine and worm mechanism.In the time of rotor flying form, blade 11 and blade 12 distribute around S. A. 20 Rotational Symmetries, and rotor wing rotation produces lift.Turbine and worm screw have latching characteristics, itself are exactly Locking Device, position that can locking blade.

Figure 29 is the one-sided blade rotor of the device constructional drawing in the time determining wing flight form of turning back that has.S. A. 20 is by locking, and blade 11 is maintained at the position with certain sweepback angle, the direction that the leading edge of blade 11 is advanced towards aircraft.Now Jiang Grains 41 diagonally distributes along fuselage.Worm drive device drives worm screw 91 to rotate, and worm screw 91 drives turbine 93 to rotate, and turbine 93 drives blade 12 to be clockwise to the position of blade leading edge towards aircraft working direction.Blade 12 has certain sweepforward angle.One-sided have the turn back structure of device of blade and can save a set of blade device of turning back, and simplifies the structure.

The rotor of aircraft of the present invention, except adopting the structure of two blades, can also adopt each rotor to have the structure of more than two blade.Figure 30 is the structural representation of rotor in the time of rotor flying form with three blades.Jiang Grains 40 is connected on S. A. 20, follows S. A. and rotates together.Oar Grains 40 has three interval 120Du branches.Spar 52 is connected on Jiang Grains 40 by the hinge 32 of turning back, and between Jiang Grains 40 and spar 52, has been arranged in juxtaposition ACTUATOR 82.Spar 53 is connected on Jiang Grains 40 by the hinge 33 of turning back, and between Jiang Grains 40 and spar 53, is furnished with ACTUATOR 83.Spar 51 is directly connected on Jiang Grains 40, in the branch that Jiang Grains 40 is connected with spar 51, is furnished with balance block 23.Three blades distribute apart from one another by 120 degree Rotational Symmetries.

Figure 31 is the structural representation of rotor in the time determining wing flight form with three blades.In the time determining wing flight form, the S. A. 20 Jiang Grains 40 that stops operating is locked in that not connect the blade blade leading edge that the branch of device connects of turning back be the foursquare position of x axle towards the square of aircraft flight, and the blade leading edge that spar 51 connects is towards the position of heading.Spar 53 is under the drive of ACTUATOR 83, and around turning back, hinge 33 rotates counterclockwise to position the locking of blade leading edge towards aircraft front.Spar 52 is clockwise to the position of blade leading edge towards aircraft forward around the hinge 32 of turning back under the drive of ACTUATOR 82.Three blades, all towards the front of aircraft, produce lift.Rotor can also comprise three above blades.

Figure 32 is the plane structure chart that is applied to the blade of aircraft of the present invention.When aircraft flies in rotor form, blade rotates around S. A., and the speed of wing tip is the highest can approach velocity of sound, and the speed at wing root place is very low, and lift mainly produce near the blade section of wing tip at outer section of blade.And in the time determining wing flight form, air flow stream cross the wing root of blade/wing and the speed of wing tip basic identical, the wing of unit length, if chord length is longer, this section of wing area is larger, the lift that this section of wing produces is more.On the contrary, chord length is shorter, and this section of wing area is less, and the lift of this section of wing generation is fewer.In order to make full use of the air-flow characteristic distributions of blade/wing under different flight forms, to take into account better rotor flying form and determine wing flight form two states, blade adopts the aspect shown in Figure 32.Blade has blade beam 50, and blade beam 50 is connected Yu Jiang Grains by the hinge 30 of turning back.Blade comprises wide string wing panel 113 and narrow string wing panel 117 from wing root to wing tip.Wide string wing panel and narrow string wing panel are mutually relative, and the chord length of wide string wing panel is greater than the chord length of narrow string wing panel.The chord length of common wide string wing panel is at least the more than 1.2 times of narrow string wing panel chord length, and further, the chord length of wide string wing panel is at least the more than 1.5,1.8,2,3,4,5,6 times of narrow string wing panel chord length.The chord length of wide string wing panel can change.The chord length of narrow string wing panel also can change.Wide string wing panel is near wing root, and in the time of rotor flying form, the peripheral linear speed of this wing panel is lower, so although chord length is long, the resistance that wide string wing panel produces is also smaller, and the lift producing is greater than the narrow beam string structure blade that is positioned at same radius place; In the time determining wing flight form, because the wing area of wide string wing panel is larger, can produce the lift that is greater than narrow string wing.Narrow string wing panel is near wing tip, and in the time of rotor flying form, peripheral linear speed is higher, can produce larger lift, and resistance is less.Between wide string wing panel 113 and narrow string wing panel 117, be furnished with transition wing panel 115.Be connected with wide string wing panel 113 aerofoil profile of position of transition wing panel 115 is identical, and transition wing panel 115 is identical with the aerofoil profile of the position that narrow string wing panel 117 is connected.Transition wing panel can realize seamlessly transitting between wide string wing panel and narrow string wing panel, improves the flow field of flowing through blade, reduces induced drag.The aerofoil profile of different spanes place of blade can be different, the aerofoil profile of the preferred fixed wing of aerofoil profile of wide string wing panel, and the aerofoil profile of the preferred rotor blade of aerofoil profile of narrow string wing panel is to bring into play to greatest extent the effect of each wing panel.The chord length of different spanes place of common narrow string wing panel is identical, and the aspect of narrow string wing panel is rectangle.The aspect of wide string wing panel can be leading edge and/or the trailing edge rectangle, trapezoidal that is straight line, can be also that leading edge and/or trailing edge are other shape of curve.In exhibition upwards, wide string wing panel is positioned between the length of wing root to 1/4 ~ 3/4, and preferred wide string wing panel is positioned between the length of wing root to 1/3 ~ 3/5, and further preferred wide string wing panel is positioned between the length of wing root to 1/3 ~ 1/2.Be furnished with movable rudder face 121 at the trailing edge of wide string wing panel 113.The Thickness Ratio of wide string wing panel is larger, and wing inside can arrange that hydraulic pressure or electronic servomechanism are to drive movable rudder face 121.Movable rudder face on different blades can be differential to produce rolling moment, can be for compensating the rolling moment due to anti-on blade and/or lower anti-generation while determining wing flight form.In the time flying modality, in the time that blade rotative speed is lower, can deflects down movable rudder face and produce extra lift, keep the steady of aircraft flight.

Figure 33 is the plane structure chart that is applied to the another kind of blade of aircraft of the present invention.Be furnished with wing root wing panel 119 in wide string wing panel 113 near a side of wing root, wing root wing panel 119 is shorter than be connected with the wide string wing panel chord length of position of wing root wing panel in the chord length at wing root place.The chord length of wing root wing panel 119 shortens to wing root direction gradually from wing tip, shorter the closer to the chord length of S. A. blade.Wing root wing panel narrows near a side of S. A., can avoid collision and interference between the wing root of multiple blades of same rotor in the time determining wing flight form, reduces the induced drag at wing root place simultaneously.Wing root wing panel can be trapezoidal, can be also other shape with curved edge, as ellipse.In exhibition upwards, wide string wing panel 113 is positioned between the length of wing root wing panel to 1/4 ~ 3/4, and preferred wide string wing panel is positioned between the length of wing root wing panel to 1/3 ~ 3/5, and further preferred wide string wing panel is positioned between the length of wing root wing panel to 1/3 ~ 1/2.

Aircraft of the present invention in use, takes off vertically with rotor flying form, and rotor leans forward or propelling unit promotes to fly before aircraft, and when speed reaches conversion rate territory, aircraft forwards to determines the cruising flight of wing flight form; When landing, aircraft is from determining wing flight modality to rotor flying form, vertical landing.

Aircraft of the present invention is in the time that flying speed is among conversion rate territory, comprise that from rotor flying form to the switching process of determining the wing flight form rotor stops step and the blade step of turning back: stop step at rotor, the rotor start stop apparatus being connected with S. A. stops the rotation of rotor and S. A. the position of locking Xuan Yi Jiang Grains; In the blade step of turning back, blade turn back device turn back the blade of rotor to blade leading edge towards aircraft working direction and keep blade position, aircraft enters determines wing flight form.Stop step at rotor, rotor shaft and engine installation disconnect, and brake gear brakes to S. A., and Locking Device is for being locked in S. A. on correct position and keeping S. A. motionless.Can between S. A. and engine installation, arrange that power-transfer clutch disconnects or in conjunction with being connected between S. A. and engine installation.Rotor start stop apparatus comprises power-transfer clutch.Power-transfer clutch can be that magnetic clutch can be also mechanical clutch.Brake gear can be that disc brake device can be also drum type braking device, can also be electromagnetic brake device.The brake disc of brake gear is arranged on S. A., is fixedly connected with S. A. is concentric.Rotor start stop apparatus comprises brake gear.Locking Device can be one with brake gear, can be also independent device.In the time that Locking Device and brake gear are one, can on brake disc, open knock hole, then by being inserted to knock hole, fastening screw realizes location.Rotor start stop apparatus comprises Locking Device.Turning back of blade can realize by the blade device of turning back.Power-transfer clutch, brake gear, Locking Device are all known technologies.Rotor start stop apparatus can adopt known axle start stop apparatus.

Aircraft of the present invention is in the time that flying speed is among conversion rate territory, comprise blade turn back step and rotor setting up procedure from determining wing flight form to the switching process of rotor flying form: in the blade step of turning back, blade turns to blade exhibition to pointing to rotor disc position radially under blade is turned back the driving of device, also be the state that blade distributes around S. A. Rotational Symmetry, now blade is circumferentially uniformly distributed along S. A.; At rotor setting up procedure, now S. A. and the release of rotor Locking Device, S. A. and rotor brake device unclamp, and power-transfer clutch engages S. A. and engine installation, and S. A. and rotor start rotation under the drive of engine installation.Aircraft enters rotor flying pattern.

In order further to improve the stationarity of conversion, from rotor flying form when determining wing flight modality, also can adopt following step: first, S. A. and the engine installation of rotor disconnect.Then, brake gear carries out brake deceleration to S. A. and/or rotor.Next, at S. A. with when last 1/4 circle of Jiang Grains before stopping the rotation, blade leading edge towards the blade of the blade of aircraft working direction turn back device start, blade reversing sense that device rotates Xiang Jiang Grains/S. A. with the angular rate identical Yu Jiang Grains/S. A. this blade of turning back of turning back, to keep this blade to point to all the time aircraft left and right directions and leading edge towards aircraft forward, can provide lift for aircraft.Meanwhile, another sheet blade, blade leading edge towards the blade of the blade at aircraft rear turn back device start, blade is turned back to the lock position of this blade to the direction identical with S. A. rotation direction, this step also can not carried out with previous step simultaneously.The position of last locking S. A., Jiang Grains and blade.Aircraft enters into and determines wing flight form from rotor flying form.Adopt above-mentioned switching process, can guarantee each rotor have a slice blade in the end 1/4 circle all the time towards aircraft front to produce lift, guaranteed switching process steadily.

In order further to improve the stationarity of conversion, when determining wing flight form to rotor flying modality, can adopt following step: first, S. A. Locking Device and/or the release of blade Locking Device; Then, power-transfer clutch engages being connected between S. A. and engine installation, and S. A. starts, and S. A. starts rotation; Next, start initial 1/4 circle of rotation at S. A., the blade of rear blade turn back device start, blade reversing sense that device rotates Xiang Jiang Grains/S. A. with the angular rate identical Yu Jiang Grains/S. A. this blade of turning back of turning back, points to aircraft left and right directions with the leading edge that keeps this blade towards aircraft working direction and wing tip; , start at the blade of the front blade device of turning back meanwhile, blade turn back device to the direction identical with S. A. rotation direction turn back this blade to blade and oar Grains point-blank, i.e. the initial position of blade in the time of rotor state; This step also can not carried out with previous step simultaneously.Rotor starts rotation, and aircraft enters rotor flying form.

Comprise that to determining the wing flight morphological transformation rotor stops step and the blade step of turning back from rotor flying form for the aircraft that is furnished with propelling unit on blade: stop step at rotor, stop the rotation of rotor the position of locking Xuan Yi Jiang Grains; In the blade step of turning back, blade turn back device turn back the blade of rotor to blade leading edge towards aircraft working direction and keep blade position, aircraft enters determines wing flight form.The aircraft of arranging propelling unit on blade does not need S. A. to drive rotor, therefore on S. A., does not need to arrange power-transfer clutch.If Xuan Yi Jiang Grains is fixedly connected with S. A., rotor can rotate by driven rotary axle together, brake gear and Locking Device can be arranged on S. A..If only have Jiang Grains to rotate, S. A. does not rotate, and brake gear and Locking Device can be arranged on Jiang Grains.

Comprise blade turn back step and rotor setting up procedure from determining wing flight form to the switching process of rotor flying form for the aircraft that is furnished with propelling unit on blade: in the blade step of turning back, initial position when blade turns to rotor state under blade is turned back the driving of device and/or propelling unit, be that blade exhibition is to pointing to rotor position radially, also be the state that blade distributes around S. A. Rotational Symmetry, now blade is circumferentially uniformly distributed along S. A.; At rotor setting up procedure, Locking Device release, brake gear releasing of brake, rotor starts rotation under the drive of propelling unit.Rotor starts rotation, and aircraft enters rotor flying pattern.

In order further to improve the stationarity of conversion, for the aircraft that is furnished with propelling unit on blade from rotor flying form when determining wing flight modality, can adopt following step: first, brake gear carries out brake deceleration to S. A. and/or rotor.Then when last 1/4 circle of Jiang Grains before stopping the rotation, blade leading edge towards the blade of the blade of aircraft working direction turn back device start, blade reversing sense this blade of turning back that device rotates Xiang Jiang Grains with the angular rate identical Yu Jiang Grains of turning back, to keep this blade to point to all the time aircraft left and right directions and leading edge towards aircraft forward, can be for aircraft provides lift, the propelling unit on blade can provide the thrust of forward direction.Meanwhile, another sheet blade, blade leading edge towards the blade of the blade at aircraft rear turn back device start, blade is turned back to the lock position of this blade to the direction identical Yu Jiang Grains rotation direction; This step also can not carried out with previous step simultaneously.The position of last locking Xuan Yi Jiang Grains and blade.Aircraft enters into and determines wing flight form from rotor flying form.

In order further to improve the stationarity of conversion, for the aircraft that is furnished with propelling unit on blade when determining wing flight form to rotor flying modality, also can adopt following step: first, in the Locking Device release of front blade, then, the device of turning back of preceding blade starts, the blade device of turning back is turned back this blade to blade Yu Jiang Grains position point-blank to the direction identical with rotor rotation direction, be the initial position of blade in the time of rotor state, now Jiang Grains does not start rotation; Next ， Jiang Grains Locking Device and/or the release of posterior blade Locking Device; Next, Jiang Grains start rotation initial 1/4 circle, the blade of posterior blade turn back device start, blade turn back device with the angular rate identical Yu Jiang Grains Xiang Jiang Grains rotate reversing sense turn back this blade to Yu Jiang Grains on the same line.Rotor starts rotation, and aircraft enters rotor flying form.

The present invention is had been described in detail for specific embodiment although above, it will be appreciated by those skilled in the art that and the invention is not restricted to above disclosed specific embodiment.In the situation that not departing from essence of the present invention and scope, can carry out various modifications and replacement to the present invention.Scope of the present invention is only limited by appended claims.

Claims

1. an aircraft, comprises at least one the first rotor and at least one the second rotor, and described the first rotor comprises at least one the first blade and at least one the second blade, and described the second rotor comprises at least one the first blade and at least one the second blade;

Described aircraft has rotor flying form, and in rotor flying form, the blade Rotational Symmetry of described rotor distributes, and rotor can rotate and produce lift; It is characterized in that:

Described aircraft also has the wing of determining flight form, is determining wing flight form, and described the first rotor and described the second rotor stop the rotation;

Described first blade of described the first rotor be distributed in the left side of described aircraft and blade leading edge towards aircraft working direction to produce lift, described the second blade be distributed in the left side of described aircraft and blade leading edge towards aircraft working direction with the position that produces the wing tip of lift or described the second blade and point to aircraft fore-and-aft direction to reduce resistance;

Described first blade of described the second rotor be distributed in the right side of described aircraft and blade leading edge towards aircraft working direction to produce lift, described the second blade be distributed in the right side of described aircraft and blade leading edge towards aircraft working direction with the position that produces the wing tip of lift or described the second blade and point to aircraft fore-and-aft direction to reduce resistance;

Described aircraft can be in flight course in the conversion of described rotor flying form and the described form of determining to fly between wing flight form.

2. aircraft according to claim 1, is characterized in that described aircraft also comprises:

At least one rotor start stop apparatus, for in the time that the flying speed of described aircraft is among conversion rate territory, described aircraft stops the rotation of rotor and locks rotor position when determining wing flight form from rotor flying modality, and described aircraft starts rotor wing rotation and keeps rotor wing rotation state when determining wing flight modality to rotor flying form;

At least one blade device of turning back, for in the time that the flying speed of described aircraft is among conversion rate territory, described aircraft is from rotor flying modality to determining to drive blade to turn to blade leading edge towards the position of aircraft working direction or the position of blade sensing aircraft fore-and-aft direction when the wing flies form, drive blade to turn to blade along the symmetrical position of rotor wing rotation central rotation with described aircraft when determining wing flight modality to rotor flying form, and in the time determining wing flight form, adjust sweepforward angle and/or the sweepback angle of blade.

3. aircraft as claimed in claim 1 or 2, is characterized in that also comprising: rotor angle regulator, and for regulating described aircraft in the direction of determining wing flight form Shi Jiang Grains.

4. aircraft as claimed in claim 1 or 2, is characterized in that: on described blade, be furnished with propelling unit, described propelling unit can produce along described chord of blade to propulsive force.

5. aircraft as claimed in claim 1 or 2, is characterized in that also comprising: at least one fixed wing, provides extra lift and/or control of sideward roll moment when flying before described aircraft.

6. aircraft as claimed in claim 1 or 2, is characterized in that: described aircraft is coaxial double-oar structure.

7. aircraft as claimed in claim 1 or 2, is characterized in that: described aircraft is for intersecting two paddle structures.

8. aircraft as claimed in claim 1 or 2, is characterized in that: the blade of described aircraft comprises wide string wing panel and narrow string wing panel, and the chord length of described wide string wing panel is at least the more than 1.2 times of described narrow string wing panel chord length.

9. aircraft as claimed in claim 8, is characterized in that: in the described wide string wing panel of described blade, be furnished with aileron.

10. aircraft as claimed in claim 8, is characterized in that: described blade is in the aerofoil profile difference of different spanes place.