CN208086009U - A kind of titling coaxial bispin wing aircraft - Google Patents

Abstract

The utility model discloses a kind of titling coaxial bispin wing aircrafts, including fuselage, fixed wing, the front fuselage is equipped with cockpit, duct is equipped among fuselage, titling coaxial twin rotor system and transmission are installed to vert system in the duct, the transmission is verted the system control titling coaxial twin rotor system action.The utility model changes traditional fixed-wing and coaxial double-oar helicopter structure, high-performance cruise ability when having good low-speed operations performance, and having fixed-wing mode by the way that titling coaxial twin rotor system and transmission are verted system in duct.Due to rotor rotation and to vert be same set of dynamical system, therefore can still cooperate with the mobility that wing rudder face carries out three axes control, greatly enhances aircraft without deadweight and rotor in horizontal flight；The utility model has a safety feature when the complicated landforms such as jungle massif are hovered and are flown at low speed.

Description

A kind of titling coaxial bispin wing aircraft

Technical field

The utility model is related to a kind of space flight and aviation technical fields, especially tilting coaxial rotor aircraft.

Background technology

Titling coaxial DCB Specimen VTOL aircraft had both had the function of that the VTOL of helicopter and good low speed flew Row performance, and have the high-performance cruise ability of fixed wing aircraft.American Bell Incorporated just produced and fills for U.S. army in late nineteen nineties Standby the first tiltrotor osprey V22 in the world, advantage does not have to describe in detail, but has many disadvantages yet, be mainly manifested in Lower three aspects：(1) technical difficulty is high：Tiltrotor will realize rotor from upright position because existing rotor has wing again It verts to horizontal position or horizontal position to upright position, therefore rotor/wing, rotor/rotor, rotation during rotor verts Occurs aerodynamic interference problem between the wing/body.(2) structure composition design is complicated:Rotor will carry out dynamic analysis when verting Dynamic loading and stability problem are coupled with rotor/wing is solved, encounters manipulation and control technology and steerable system dynamics Design etc. Technical barrier.It is directly to be rotated by 90 ° the two groups of rotor mechanisms in left and right together with engine nacelle since V-22 verts, inertia is huge Greatly, therefore V-22 aircrafts use special construction and unconventional control system, but these special constructions in aircraft horizontal flight Added burden is reformed into unconventional control system and deadweight occurs.(3) security performance is poor：The two secondary propellers that V-22 is used Rotor is more unique cross-arranging type arrangement, once occurring side rotor in flight course enters vortex ring state and another Side work normally when, may result in the left and right sides lift it is unbalance, aircraft will to the rotor side rolling influenced by collar vortex, It is easily out of control.

As it can be seen that have been subjected to more than 50 years technology development, osprey V-22 tiltrotors technology be also far from being it is highly developed, also There are many technologies to need further to study and verify；So far, the air crash accident of multi rack V-22 aircrafts all has with above-mentioned factor It closes, is also derived from the leakage of hydraulic system in enging cabin, unconventional special flight control system associated components in engine nacelle The low problem of reliability；These constitute great threat to the safe flight of V-22 aircrafts；Why not reliability and maintainability It is very ideal, other than the factors such as single machine cost height and the technical merit of maintenance personnel, qualification are related, more importantly Derived from the design defect of aircraft.

Utility model content

The technical problems to be solved in the utility model is：A kind of better tilting type aircraft of comprehensive performance is provided.

The solution that the utility model solves its technical problem is：A kind of titling coaxial bispin wing aircraft, including machine The left and right ends of body, the fuselage are equipped with fixed wing, and cockpit is equipped in the fuselage, is equipped with and contains among the fuselage Road is equipped with titling coaxial twin rotor system and transmission in the duct and verts system, and the transmission is verted system control institute The titling coaxial twin rotor system action stated.

As a further improvement of the above technical scheme, the titling coaxial twin rotor system includes：Upper rotor driver, It includes upper rotor, upper propeller hub, upper rotor shaft and upper pitch, and the upper propeller hub is fixed on the upper end of rotor shaft, it is described on Rotor connects with upper propeller hub axis, and the upper pitch is located at the lower section of upper propeller hub, and the upper rotor shaft passes through the upper pitch, The upper pitch is connect with upper rotor by upper pitch-change-link, the both ends of the upper pitch-change-link respectively with upper pitch, on Rotor is hinged；Lower rotor driver comprising lower rotor, lower propeller hub, lower rotor shaft and lower pitch, the lower pitch and updip The direction of swash plate is opposite.The lower propeller hub is fixed on the lower end of lower rotor shaft, and the lower rotor connects with lower propeller hub axis, described to have a down dip Swash plate is located at the top of lower propeller hub, and the lower rotor shaft passes through the lower pitch, the lower pitch to pass through with lower rotor The both ends of lower pitch-change-link connection, the lower pitch-change-link are hinged with lower pitch, lower rotor respectively；The upper rotor shaft is under Rotor shaft axle center overlaps, and the lower end of upper rotor shaft and the upper end of lower rotor shaft leave each other, and the steering of upper rotor shaft is under The steering of rotorshaft is opposite；The upper pitch is connect with lower pitch by two or more control sticks, control stick it is upper Lower both ends are hinged with upper pitch, lower pitch respectively.

As a further improvement of the above technical scheme, the upper rotor includes upper rotary wing oar jig and upper rotor blade, institute State the outer end that rotor blade is fixed on upper rotary wing oar jig, the inner end of the upper rotary wing oar jig is equipped with bearing and shaft, it is described on Propeller hub and shaft are connected, and the upper rotary wing oar jig is joined by shaft and the upper propeller hub stiff shaft, the upper pitch-change-link with it is upper Rotor folder is hinged；The lower rotor includes lower rotor folder and lower rotor blade, and the lower rotor blade is fixed on lower rotor The inner end of the outer end of paddle folder, the lower rotor folder also is provided with bearing and shaft, and the lower propeller hub is connected with its shaft, under described Rotor folder is joined by shaft and the lower propeller hub stiff shaft, and the lower pitch-change-link and lower rotor folder are hinged.

As a further improvement of the above technical scheme, connected by upper transmission arm between the upper pitch and upper propeller hub It connects；It is connected by underdrive arm between the lower pitch and lower propeller hub.

As a further improvement of the above technical scheme, the transmission system of verting includes：Left Drive device, including it is left solid Reservation, "Left"-deviationist turn bridge, left drive shaft, left driving mechanism, the left hollow setting of fixed seat, and the "Left"-deviationist turns bridge and is sleeved on left fixation It in seat, and can be rotated relative to left fixed seat, it is also hollow setting that the "Left"-deviationist, which turns bridge, and the left end of the left drive shaft is through described Left fixed seat turn bridge with "Left"-deviationist and connect with left driving mechanism；Right transmission device, including right fixed seat, Right deviation turn bridge, right biography Moving axis, right driving mechanism, the right hollow setting of fixed seat, the Right deviation turn bridge and are sleeved in right fixed seat, and can be relatively right solid Reservation rotates, and it is also hollow setting that the Right deviation, which turns bridge, and the right end of the right transmission shaft runs through the right fixed seat and Right deviation Turn bridge and is connect with right driving mechanism；The left drive shaft is overlapped with the axle center of right transmission shaft, the right end of the left drive shaft with The left end of right transmission shaft leaves each other；Lockable mechanism, including locking steering engine, locking sliding sleeve, the locking sliding sleeve are sleeved on left-leaning turn The outer end face of bridge, the "Left"-deviationist turn bridge outer end face be equipped with sliding slot, the left fixed seat be equipped at least two location holes, two Phase angle between location hole is 90 °, and the left end of the locking sliding sleeve is equipped with positioning pin, and the positioning pin can be nested with location hole Connection, the locking servo driving locking sliding sleeve are moved left and right along sliding slot.

As a further improvement of the above technical scheme, the right end of the left drive shaft and the left end of right transmission shaft are respectively mounted There is first bevel gear, mirror symmetry, the lower end of the upper rotor shaft and the upper end of lower rotor shaft are respectively mounted two bevel gears each other There are second bevel gear, the second bevel gear and bevel gear mutually ratcheting.

As a further improvement of the above technical scheme, the lockable mechanism further includes locking slip ring, the locking slip ring It is sleeved on "Left"-deviationist to turn outside bridge, and the locking slip ring, between locking sliding sleeve and left fixed seat, the locking steering engine passes through locking Pull rod is connect with the locking slip ring, and the right end of the locking slip ring is equipped with driving convex block, and the left end of the locking sliding sleeve is equipped with The both ends of groove, the groove are bevel edge.

As a further improvement of the above technical scheme, the "Left"-deviationist turns the periphery of bridge and is additionally provided with spring base, the spring Seat is located at the right side of locking sliding sleeve, and resetting spring is equipped between the spring base and locking sliding sleeve.

As a further improvement of the above technical scheme, there are four the location holes, two-by-two between adjacent location hole Phase angle is 90 °, and the left end of the locking sliding sleeve is equipped with locking claw, and the locking claw includes four positioning pins.

As a further improvement of the above technical scheme, three control devices, the control are additionally provided in the right fixed seat Device processed includes control operating rod, manipulates sliding sleeve and controls connecting rod, and the periphery of the right fixed seat is equipped with multiple tooth sockets, the manipulation The inner face of sliding sleeve is equipped with multiple latches, and the latch is connect with tooth socket, and the manipulation sliding sleeve is slidably connected with right fixed seat, institute The outer end face for manipulating sliding sleeve is stated equipped with rocking arm mounting base, the controls connecting rod is mounted in rocking arm mounting base, the control operating rod One end connect with control stick, other end with manipulate sliding sleeve rotation connection, in the end and cockpit of three controls connecting rods Control handle connects.

As a further improvement of the above technical scheme, the control operating rod is mounted on by holder and is manipulated on sliding sleeve, institute It states branch and puts up sector, shown holder is equipped with cambered way, and the control operating rod is connected by cambered way with sliding sleeve rotation is manipulated It connects.

The utility model has the beneficial effects that：The utility model changes traditional aircaft configuration, uses ripe indulge Coaxial positive and negative DCB Specimen technology is arranged, titling coaxial twin rotor system and transmission are verted into system in duct, it has good Good low-speed operations performance, has high-performance cruise ability again in fixed-wing mode.Due to rotor rotation and to vert be same set of Dynamical system, therefore there is no deadweight phenomenon in horizontal flight, and rotor system verts to control operating rod when level and remains to blade Feathering is carried out, Gu rotor at this time can cooperate with aircraft rudder surface to carry out three axes control.The utility model is in jungle massif etc. Complicated landform is hovered and is had a safety feature when flying at low speed.

Description of the drawings

It is required in being described below to embodiment in order to illustrate more clearly of the technical scheme in the embodiment of the utility model Attached drawing to be used is briefly described.Obviously, described attached drawing is a part of the embodiment of the utility model, rather than complete Portion's embodiment, those skilled in the art without creative efforts, can also be obtained according to these attached drawings it His design scheme and attached drawing.

Fig. 1 is the aircaft configuration schematic diagram of the utility model；

Fig. 2 is the titling coaxial twin rotor system of the utility model and the structural schematic diagram for being driven system of verting；

Fig. 3 is the three-dimensional structure diagram of the titling coaxial twin rotor system of the utility model；

Fig. 4 is the structural schematic diagram of the lockable mechanism of the utility model；

Fig. 5 is the explosive view of the locking structure of the utility model；

Fig. 6 is the stereoscopic schematic diagram of the control device of the utility model.

Specific implementation mode

The technique effect of the design of the utility model, concrete structure and generation is carried out below with reference to embodiment and attached drawing It clearly and completely describes, to be completely understood by the purpose of this utility model, feature and effect.Obviously, described embodiment It is a part of the embodiment of the utility model, rather than whole embodiments, it is based on the embodiments of the present invention, the skill of this field The other embodiment that art personnel are obtained without creative efforts belongs to the model of the utility model protection It encloses.In addition, all connection/connection relations being previously mentioned in text, not singly refer to component and directly connect, and referring to can be according to specific reality Situation is applied, by adding or reducing couple auxiliary, to form more preferably coupling structure.Each technology in the invention is special Sign, can be with combination of interactions under the premise of not conflicting conflict.

Referring to Fig.1~Fig. 6, a kind of titling coaxial bispin wing aircraft, including fuselage 1, the left and right ends of the fuselage 1 are equal Equipped with fixed wing 11 and aileron 14, it is equipped with cockpit 12 and the vertical wing 15 of rear end tail in the fuselage 1, is set among the fuselage 12 There is duct 13, titling coaxial twin rotor system 2 and transmission are installed in the duct 13 and verted system 3, the transmission is verted System 3 controls the titling coaxial twin rotor system 2 and acts.It of courses, other than above structure, the fuselage also wraps Include empennage, undercarriage, the mechanical, electrical tune of dynamical system < power electrics, lithium electricity or fuel cell unit etc.), transmission system etc..

Referring to Fig. 2, Fig. 3, it is further used as preferred embodiment, the titling coaxial twin rotor system 2 includes：On Rotor driver 21 comprising upper rotor 211, upper propeller hub 212, upper rotor shaft 213 and upper pitch 214, the upper propeller hub 212 are solid It is scheduled on the upper end of rotor shaft 213, the upper rotor 211 connects with 212 axis of upper propeller hub, and the upper pitch 214 is located at upper propeller hub 212 lower section, the upper rotor shaft 213 pass through the upper pitch 214, the upper pitch 214 to pass through with upper rotor 211 Upper pitch-change-link 215 connects, and the both ends of the upper pitch-change-link 215 are hinged with upper pitch 214, upper rotor 211 respectively；Backspin Swing device 22 comprising lower rotor 221, lower propeller hub 222, lower rotor shaft 223 and lower pitch 224, the lower propeller hub 222 are solid It is scheduled on the lower end of lower rotor shaft 223, the lower rotor 221 connects with lower 222 axis of propeller hub, and the lower pitch 224 is located at lower propeller hub 222 top, and the lower pitch and upper pitch installation direction on the contrary, the lower rotor shaft 223 pass through it is described under Pitch 224, the lower pitch 224 are connect with lower rotor 221 by lower pitch-change-link 225, the lower pitch-change-link 225 Both ends are hinged with lower pitch 224, lower rotor 221 respectively；The upper rotor shaft 213 is overlapped with lower 223 axle center of rotor shaft, and on The lower end of rotor shaft 213 and the upper end of lower rotor shaft 223 leave each other, and the steering of upper rotor shaft 213 and lower rotorshaft 223 Steering it is opposite；The upper pitch 214 is connect with lower pitch 224 by two or more control sticks 24, control stick 24 Upper and lower ends are hinged with upper pitch 214, lower pitch 224 respectively.By using the DCB Specimen of upper and lower coaxial separate structure Structure, and power is transmitted between two rotors, and so even if rotor verts, the drive mechanism of rotor can still be protected It holds relatively motionless so that the rotor system has better comprehensive performance.Preferably, upper and lower rotor has three pieces blade, above has Three pieces dextrorotation blade, under have three pieces derotation blade；And upper rotor is identical with the lower size of rotor, due to upper and lower rotor Direction is opposite so that the operation reaction of three axis of aircraft is quick, and corner power is cancelled out each other up and down, and stability is more preferable.

It is further used as preferred embodiment, the upper rotor 211 includes rotor folder 2111 and rotor blade 2112, the rotor blade 2112 is fixed on the outer end of rotor folder 2111, and the inner end of the rotor folder 2111 is equipped with bearing And shaft, the upper propeller hub 212 are connected firmly with shaft, and rotor folder 2111 is rigidly connected with upper propeller hub 212, the upper change It is hinged away from pull rod 215 and rotor folder 2111；The corresponding component of the lower rotor driver 22 and the structure of upper rotor 21 are one Sample.Rotor blade is fixedly mounted in rotor folder, and rotor folder is only attached by shaft with propeller hub, to So that rotor connect no flapping hinge, lead lag hinge, only pitch hinge with propeller hub, and to which upper and lower rotor is in rotary course, Bu Huiyu The bridge that verts interferes so that aircraft is more stablized when flight.

It is further used as preferred embodiment, is passed through between the rotable ring and upper propeller hub 212 of the upper pitch 214 Upper transmission arm 216 connects；Connected by underdrive arm 226 between the rotable ring of the lower pitch 224 and lower propeller hub 222 Connect, so that tilted upward disk can rotable ring it is synchronous with upper and lower rotor shaft and upper and lower propeller hub but rotate backward.

Referring to Fig. 2, Fig. 4, Fig. 5, it is further used as preferred embodiment, the system 3 of verting that is driven includes：Left Drive Device 31, including left fixed seat 311, "Left"-deviationist turn bridge 312, left drive shaft 313, left driving mechanism 314, the left fixed seat 311 Hollow setting, the "Left"-deviationist turn bridge 312 and are sleeved in left fixed seat 311, and can be rotated relative to left fixed seat 311, described left-leaning turn Bridge 312 is also hollow setting, the left end of the left drive shaft 313 through the left fixed seat 311 and "Left"-deviationist turn bridge 312 and with Left driving mechanism 314 connects；Right transmission device 32, including right fixed seat 321, Right deviation turn bridge 322, right transmission shaft 323, right drive Motivation structure 324,321 hollow setting of the right fixed seat, the Right deviation turn bridge 322 and are sleeved in right fixed seat 321, and can be opposite Right fixed seat 321 rotates, and it is also hollow setting that the Right deviation, which turns bridge 322, and the right end of the right transmission shaft 323 runs through the right side Fixed seat 321 turns bridge 322 with Right deviation and is connect with right driving mechanism 324；The axis of the left drive shaft 313 and right transmission shaft 323 The heart overlaps, and the right end of the left drive shaft 313 and the left end of right transmission shaft 323 leave each other；Lockable mechanism 33, including locking rudder Machine 331, locking sliding sleeve 332, the locking sliding sleeve 332 are sleeved on the left-leaning outer end face for turning bridge 312, and the "Left"-deviationist turns the outer of bridge 312 End face is equipped with sliding slot, and the left fixed seat 311 is equipped at least two location holes, and the phase angle between two location holes is 90 °, The left end of the locking sliding sleeve 332 is equipped with positioning pin 3321, and the positioning pin 3321 can be with location hole nested encryptions, the lock Only steering engine 331 drives locking sliding sleeve 332 to be moved left and right along sliding slot.It is right simultaneously by using two symmetrical driving devices Rotor drive and forces the bridge that verts to vert using the torsion difference of two driving devices, during entirely verting, two A driving device can keep the driving to rotor, so that the structure of verting of tilting type aircraft is relatively reliable, simple, conjunction Reason, and pass through locking structure, it is ensured that rotor will not surprisingly vert, and keep the stabilization of aircraft.

It is further used as preferred embodiment, the right end of the left drive shaft 313 and the left end of right transmission shaft 323 are pacified Equipped with first bevel gear, two bevel gears mirror symmetry each other, the lower end of the upper rotor shaft 213 and lower 223 upper end of rotor shaft It is mounted on second bevel gear, the second bevel gear and bevel gear are mutually ratcheting.Two groups of rotors up and down of rotor system are altogether What axis reversely rotated；When the output power size of left and right transmission mechanism is unequal, due to there is difference in torque, rotation will be forced Bevel gear in wing system rotates along the bevel gear on the transmission shaft of left and right, so that rotor system verts.And And when verting, the location hole of lockable mechanism is detached with positioning pin, and the bridge that verts left and right in this way can be along in drive shaft The heart rotates, to drive rotor system to vert with respect to fuselage, and when vert 90 ° after, on location hole and positioning pin are again nested, together When, is adjusted to the output power of left and right transmission mechanism identical, then rotor system is just without the power for continuing to vert.

It is further used as preferred embodiment, the lockable mechanism 33 further includes locking slip ring 333, and the locking is slided Ring 333 is sleeved on "Left"-deviationist and turns outside bridge 312, and the locking slip ring 333 is between locking sliding sleeve 332 and left fixed seat 311, institute It states locking steering engine 331 to connect with the locking slip ring 333 by locking pull rod 334, the right end of the locking slip ring 333, which is equipped with, to be driven The left end of dynamic convex block, the locking sliding sleeve 332 is equipped with groove, and the both ends of the groove are bevel edge.When rotor system needs to overturn When, the movement of locking servo driving locking pull rod, and locking pull rod drives locking slip ring to turn bridge rotation relative to "Left"-deviationist, and drive Convex block slides in the groove of locking sliding sleeve so that locking sliding sleeve generates the sliding of opposite left and right, and when locking sliding sleeve to When right sliding, positioning pin is detached with location hole, and "Left"-deviationist at this time, which turns bridge, can be relatively fixed seat rotation, so as to drive rotation Wing system occurs 90 degree and verts；And after verting in place, positioning pin and location hole are again on nested encryptions, so that rotor system It cannot vert again.Moreover, locking pull rod 334, which can be used as, assists the power that verts, because its direction of pull always will be with verting Direction is consistent, even if one group or two groups of driving forces disappear, rotor system can equally vert under the action of locking pull rod.

It is further used as preferred embodiment, the periphery that the "Left"-deviationist turns bridge 312 is additionally provided with spring base, the spring base Positioned at the right side of locking sliding sleeve 332, resetting spring is equipped between the spring base and locking sliding sleeve 332.Bullet is resetted by increase Spring can make the reset of sliding sleeve more intelligent.

It is further used as preferred embodiment, there are four the location holes, two-by-two the phase between adjacent location hole Angle is 90 °, and the left end of the locking sliding sleeve 332 is equipped with locking claw, and the locking claw includes four positioning pins 3321.Pass through Four location holes and four positioning pins are set, the bonding strength of positioning pin and location hole can be improved, and facilitate rotor again System is verted.

Referring to Fig. 6, it is further used as preferred embodiment, three control devices are additionally provided in the right fixed seat 321 4, the control device 4 includes control operating rod 41, manipulates sliding sleeve 42 and controls connecting rod 43, and the periphery of the right fixed seat 321 is set There are multiple tooth sockets, the inner face for manipulating sliding sleeve 42 to be equipped with multiple latches, the latch is connect with tooth socket, the manipulation sliding sleeve 42 are slidably connected with right fixed seat 321, and the outer end face for manipulating sliding sleeve 42 is equipped with rocking arm mounting base, and the controls connecting rod 43 is pacified In rocking arm mounting base, the left end of the control operating rod 41 is connect with control stick 24, and right end connects with the rotation of sliding sleeve 42 is manipulated It connects, control handle (not regarded in the figure) connection in the end and cockpit of three controls connecting rods 43, and the control crank is with existing There is the helicopter control handle in technology consistent.When bridge control tilting coaxial rotor system of verting is verted, together Step drives the control operating rod 41 in control device to vert along slideway 45 so that rotor system is in verting or verts to level It, similarly can be to being controlled by it when state.It, can be respectively to tilting coaxial rotor system by three above-mentioned control devices Upper and lower rotor always away from and up and down the period of rotor away from carry out simultaneously, synchronous and with amplitude control, to realize aircraft Steady landing, hover and vert after horizontal flight.

It is further used as preferred embodiment, the control operating rod 41 is mounted on by holder 44 and is manipulated on sliding sleeve 42, For the holder 44 at sector, shown holder 44 is equipped with cambered way 45, and the control operating rod 41 passes through cambered way 45 and behaviour Vertical sliding sleeve 42 is rotatablely connected.The center of circle of the cambered way 45 is overlapped with the center of circle for manipulating sliding sleeve 42, the cambered way 45 Central angle is 90-95 °.When the bridge that verts verts, control operating rod 41 can follow it to rotate, due to the bridge chair that verts Be relatively fixed on fuselage, be sleeved on the manipulation sliding sleeve 42 to vert on bridge chair also and opposite may only vert bridge chair horizontally slip and It will not rotate, control operating rod 41 is slided along with verting for the bridge that verts in cambered way 45, realizes the companion of manipulation It verts to synchronize and carry out.

It is further used as preferred embodiment, three control operating rods are shifted to install with three controls connecting rods.Due to three A control operating rod and three controls connecting rods, all can be with single movements, therefore by by its mutual sequence other than linkage Setting, it is ensured that they will not interfere when action.

It is further used as preferred embodiment, the control stick 24 described in three is parallel to each other.

Three mode of aircraft are as follows:

When helicopter mode:The pneumatic rudder face of wingflying aircraft does not work, and transmission system is responsible for leading to the power of two driving devices Cross transmission system and be transmitted to rotor system, which is one group of coaxial two secondary rotor up and down, and rotating speed is identical, turn on the contrary, The direction of pull of rotor is upward in VTOL, and rotor can carry out three axis behaviour by control device (referring to Fig. 6) up and down Make to realize steady landing and hovering.It is the positive paddle of three pieces on rotor blade, lower is the anti-paddle of three pieces, up and down totally six blades.It is outstanding Stopping time aircraft will such as have steering and driftage function, can design by the screw pitch that changes up or down rotor can also by change it is upper or The wing tip windward side (such as installation activity winglet) of lower rotor turns to and yaws to realize aircraft.

When mode of verting:It is connected to be mounted on machine when upper and lower rotor verts, in the limit locking organ pull rod on bridge that verts Servo motor on body or artificial pull rod, in the case where they link, the effect of automatic unlocking and the torsion difference in two driving devices Under vert.The mode because rotor thrust be decomposed always away from should be continuously increased until aircraft reach certain flying speed so that Fixed wing 11 itself can provide enough lift.The rotor period, and the aileron wing flap empennage of aircraft joined away from not operating up and down at this time It is dynamic that aircraft is allowed to be transitioned into fixed-wing mode.So up and down main shaft by it is longitudinal incline turn 90 degrees into the fixed-wing mode of horizontality after, Position-limit mechanism will be automatically locked the bridge that verts.It is similarly reversed reversible.The utility model has two driving devices in left and right to pass through driver Structure verts for rotor wing rotation and the bridge that verts simultaneously and provides power, even if while there is crash provided with one of which power, separately Outer one group of power can also undertake the function of landing and the horizontal flight of entire aircraft, and the power to vert, can also be by locking Pull rod is provided separately.

When fixed-wing mode:Period of the rotary wing changing away from system when helicopter mode is away from still can be according to fixed-wing mode When needs assist being operated by three axis that fixed-wing rudder face undertakes because the rotor system in horizontal flight still can be at this time Feathering substantially increases the mobility of aircraft, and front and back rotor is utilized always to realize that forward pulling force becomes away from differential and throttle Change.

The better embodiment of the utility model is illustrated above, but the invention be not limited to it is described Embodiment, those skilled in the art can also make various equivalent changes without departing from the spirit of the present invention Type or replacement, these equivalent modifications or replacement are all contained in the application claim limited range.

Claims (11)

1. the left and right ends of a kind of titling coaxial bispin wing aircraft, including fuselage (1), the fuselage (1) are equipped with fixed machine The wing (11) and aileron (14), the front end of the fuselage (1) are equipped with cockpit (12) rear end and are equipped with the vertical wing (15) of tail, and feature exists In：Duct (13) is equipped among the fuselage (1), be equipped in the duct (13) titling coaxial twin rotor system (2) with It is driven system (3) of verting, the action for being driven system (3) the control titling coaxial twin rotor system (2) of verting.

2. titling coaxial bispin wing aircraft according to claim 1, it is characterised in that：The titling coaxial DCB Specimen System (2) includes：

Upper rotor driver (21) comprising upper rotor (211), upper propeller hub (212), upper rotor shaft (213) and upper pitch (214), the upper propeller hub (212) is fixed on the upper end of rotor shaft (213), the upper rotor (211) and upper propeller hub (212) axis It connects, the upper pitch (214) is located at the lower section of upper propeller hub (212), and the upper rotor shaft (213) passes through the upper pitch (214), the upper pitch (214) is connect with upper rotor (211) by upper pitch-change-link (215), the upper pitch-change-link (215) both ends are hinged with upper pitch (214), upper rotor (211) respectively；

Lower rotor driver (22) comprising lower rotor (221), lower propeller hub (222), lower rotor shaft (223) and lower pitch (224), the lower pitch (224) and upper pitch (214) are reversely installed, and the lower propeller hub (222) is fixed on lower rotor shaft (223) lower end, the lower rotor (221) connect with lower propeller hub (222) axis, and the lower pitch (224) is located at lower propeller hub (222) Top, the lower rotor shaft (223) passes through the lower pitch (224), the lower pitch (224) and lower rotor (221) connected by lower pitch-change-link (225), the both ends of the lower pitch-change-link (225) respectively with lower pitch (224), under Rotor (221) is hinged；

The upper rotor shaft (213) overlaps with lower rotor shaft (223) axle center, and the lower end of upper rotor shaft (213) and lower rotor shaft (223) upper end leaves each other, and the steering of upper rotor shaft (213) is opposite with the lower steering of rotor shaft (223)；The upper inclination Disk (214) is connect with lower pitch (224) by two or more control sticks (24), the upper and lower ends of control stick (24) respectively with Upper pitch (214), lower pitch (224) are hinged.

3. titling coaxial bispin wing aircraft according to claim 2, it is characterised in that：The upper rotor (211) includes Rotor presss from both sides (2111) and rotor blade (2112), and the rotor blade (2112) is fixed on the outer end of rotor folder (2111), The inner end of the rotor folder (2111) is equipped with bearing and shaft, and rotor is pressed from both sides (2111) and the upper propeller hub by the shaft (212) it is rigidly connected, the upper pitch-change-link (215) and the rocking arm of rotor folder (2111) are hinged.

4. titling coaxial bispin wing aircraft according to claim 3, it is characterised in that：The upper pitch (214) with It is connected by upper transmission arm (216) between upper propeller hub (212)；Under passing through between the lower pitch (224) and lower propeller hub (222) Transmission arm (226) connects.

5. titling coaxial bispin wing aircraft according to claim 2, it is characterised in that：It is described to be driven system (3) of verting Including：

Left Drive device (31), including left fixed seat (311), "Left"-deviationist turn bridge (312), left drive shaft (313), left driving mechanism (314), the hollow setting of the left fixed seat (311), the "Left"-deviationist turn bridge (312) and are sleeved in left fixed seat (311), and can be opposite Left fixed seat (311) rotation, it is also hollow setting that the "Left"-deviationist, which turns bridge (312), and the left drive shaft (313) runs through the left side Fixed seat (311) turns bridge (312) with "Left"-deviationist and is connect with left driving mechanism (314)；

Right transmission device (32), including right fixed seat (321), Right deviation turn bridge (322), right transmission shaft (323), right driving mechanism (324), the hollow setting of the right fixed seat (321), the Right deviation turn bridge (322) and are sleeved in right fixed seat (321), and can be opposite Right fixed seat (321) rotation, it is also hollow setting that the Right deviation, which turns bridge (322), and the right transmission shaft (323) runs through the right side Fixed seat (321) turns bridge (322) with Right deviation and is connect with right driving mechanism (324)；

The left drive shaft (313) overlaps with the axle center of right transmission shaft (323), right end and the right biography of the left drive shaft (313) The left end of moving axis (323) leaves each other；

Lockable mechanism (33), including locking steering engine (331), locking sliding sleeve (332), the locking sliding sleeve (332) are sleeved on left-leaning turn The outer end face of bridge (312), the outer end face that the "Left"-deviationist turns bridge (312) are equipped with sliding slot, and the left fixed seat (311) is equipped at least Two location holes, the phase angle between two location holes is 90 °, and the left end of the locking sliding sleeve (332) is equipped with positioning pin (3321), the positioning pin (3321) can be with location hole nested encryptions, locking steering engine (331) the driving locking sliding sleeve (332) It is moved left and right along sliding slot.

6. titling coaxial bispin wing aircraft according to claim 5, it is characterised in that：The left drive shaft (313) The left end of right end and right transmission shaft (323) is mounted on first bevel gear, two bevel gears mirror symmetry each other, the upper rotor The lower end of axis (213) and the upper end of lower rotor shaft (223) are mounted on second bevel gear, the second bevel gear and the first cone tooth Wheel is mutually ratcheting.

7. titling coaxial bispin wing aircraft according to claim 5, it is characterised in that：The lockable mechanism (33) is also wrapped Locking slip ring (333) is included, the locking slip ring (333) is sleeved on "Left"-deviationist and turns bridge (312) outside, and the locking slip ring (333) is located at Between locking sliding sleeve (332) and left fixed seat (311), the locking steering engine (331) passes through locking pull rod (334) and the locking Slip ring (333) connects, and the right end of the locking slip ring (333) is equipped with driving convex block, and the left end of the locking sliding sleeve (332) is equipped with The both ends of groove, the groove are bevel edge.

8. titling coaxial bispin wing aircraft according to claim 7, it is characterised in that：The "Left"-deviationist turns bridge (312) Periphery is additionally provided with spring base, and the spring base is located at the right side of locking sliding sleeve (332), the spring base and locking sliding sleeve (332) Between be equipped with resetting spring.

9. titling coaxial bispin wing aircraft according to claim 8, it is characterised in that：There are four the location holes, and two Phase angle between two adjacent location holes is 90 °, and the left end of the locking sliding sleeve (332) is equipped with locking claw, the locking Claw includes four positioning pins (3321).

10. titling coaxial bispin wing aircraft according to claim 5, it is characterised in that：On the right fixed seat (321) Three control devices (4) are additionally provided with, the control device (4) includes control operating rod (41), manipulates sliding sleeve (42) and controls connecting rod (43), the periphery of the right fixed seat (321) is equipped with multiple tooth sockets, and the inner face for manipulating sliding sleeve (42) is equipped with multiple cards Tooth, the latch are connect with tooth socket, and the manipulation sliding sleeve (42) is slidably connected with right fixed seat (321), the manipulation sliding sleeve (42) outer end face is equipped with rocking arm mounting base, and the controls connecting rod (43) is mounted in rocking arm mounting base, the control operating rod (41) one end is connect with control stick (24), and other end is rotatablely connected with sliding sleeve (42) is manipulated, three controls connecting rods (43) End is connect with control handle.

11. titling coaxial bispin wing aircraft according to claim 10, it is characterised in that：The control operating rod (41) is logical It crosses holder (44) to be mounted on manipulation sliding sleeve (42), the holder (44) is equipped with cambered way at sector, shown holder (44) (45), the control operating rod (41) is rotatablely connected by cambered way (45) with sliding sleeve (42) is manipulated；The cambered way (45) The center of circle is overlapped with the center of circle for manipulating sliding sleeve (42), the central angle of the cambered way (45) is 90-95 °.