CN108216614A

CN108216614A - The power wingtip device of adjustable angle applied to unmanned plane

Info

Publication number: CN108216614A
Application number: CN201711240165.6A
Authority: CN
Inventors: 赵国成; 漆鹏程; 罗伟
Original assignee: Ewatt Technology Co Ltd
Current assignee: Ewatt Technology Co Ltd
Priority date: 2017-11-30
Filing date: 2017-11-30
Publication date: 2018-06-29

Abstract

The present invention discloses the power wingtip device of the adjustable angle applied to unmanned plane, belongs to unmanned air vehicle technique field, is connected including generator with engine；Electric pressure converter is connected with generator；First voltage stabilizing input port is connected with electric pressure converter；Accumulator and the connection of the second voltage stabilizing input port；First steering engine input port is connected with the first shunting delivery outlet, and the first rotor shaft is connected with the first rotor；Second rotor shaft is connected with the second rotor；First driving motor is connected with third shunting delivery outlet, the rotor mechanism of adjustable angle and the connection of the first driving motor；First rotor includes the first rotating vane and clump weight；Second rotor includes the second rotating vane and clump weight；First winglet and the first postposition wing intersect；Second winglet and the second postposition wing intersect.The present invention be reached for unmanned plane provide needed for thrust or pulling force, make it have longer cruise duration and higher stability, promote practicability；Simplify rotor structure, the technique effect of rational in infrastructure.

Description

The power wingtip device of adjustable angle applied to unmanned plane

Technical field

The invention belongs to unmanned air vehicle technique fields, are more particularly to filled applied to the rotor power of the adjustable angle of unmanned plane It puts.

Background technology

Unmanned unmanned plane referred to as " unmanned plane ", is grasped using radio robot and the presetting apparatus provided for oneself Vertical not manned unmanned plane.Without cockpit on machine, but automatic pilot, presetting apparatus, information collecting device etc. are installed Equipment.On ground, naval vessels or machine tool remote control station personnel are by equipment such as radars, to its into line trace, positioning, remote control, telemetering and Digital Transmission.It can take off as common unmanned plane or be launched with booster rocket under wireless remotecontrol, it also can be by machine tool Aerial launch is taken to fly.

The rotor of unmanned plane is mainly made of multi-disc blade (2 or more).Before unmanned plane manufacture, often rotor is mounted on The top of unmanned plane during blade rotation in rotor, generates the pulling force along rotor shaft, which makes aircraft have what is moved up Lift.Alternatively, rotor to be mounted on to the tail portion of unmanned plane, when the blade in rotor rotates, the power along rotor shaft is generated, which makes Aircraft has the thrust of preceding movement.For providing the power source of power for rotor mainly by accumulator and the various electric appliances of unmanned plane Element is connected, and electric energy, such as electric power storage are provided for the various electrical appliances on unmanned plane by the accumulator being arranged on unmanned plane Pond is connected with steering engine, and electric energy is provided for steering engine, and steering engine is made to drive rotor work, then provides power for unmanned plane.But nothing It is man-machine in landing and in-flight larger to the demand of electric energy, since the capacity of accumulator is relatively low, unmanned plane can not be met to electric energy Demand so that the cruise duration of unmanned plane is short, poor practicability.Rotor is just mounted on to the top of unmanned plane before manufacture, then Required thrust can not be provided for the forward or backward of unmanned plane；And rotor is mounted on to the tail portion of unmanned plane, then can not be nothing Man-machine rising or landing provides required pulling force.And due to the presence of wing upper and lower surface pressure difference, the wing near wing tip Lower surface air can be formed wingtip vortex, cause the upper and lower surface pressure difference of wing tip near zone wing to reduce around upper surface is flowed to, after And the lift that this region is caused to generate also reduces.

In conclusion existing applied in the technology of unmanned plane, there is unmanned plane cruise duration is short, practicability Difference；Same rotor can not provide whole required thrust or pulling force for unmanned plane；And complicated, the daily maintenance of rotor It is inconvenient；And wing tip can reduce the technological deficiency of unmanned plane stability.

Invention content

The technical problems to be solved by the invention are that the cruise duration of unmanned plane is short, poor practicability；Same rotor can not be Unmanned plane provides whole required thrust or pulling force；The complicated of rotor, daily maintenance are also inconvenient；And wing tip can reduce Unmanned plane stability.

In order to solve the above technical problems, the present invention provides the power wingtip device of the adjustable angle applied to unmanned plane, The rotor power device of the adjustable angle applied to unmanned plane includes：Engine；Generator, the generator and the hair Motivation connects；Electric pressure converter, the electric pressure converter are connect with the generator；Voltage-stablizer, the voltage-stablizer include first Voltage stabilizing input port, the second voltage stabilizing input port and the first voltage stabilizing delivery outlet；The first voltage stabilizing input port and the electric pressure converter Connection, and the electric pressure converter is between the first voltage stabilizing input port and the generator；Accumulator, the accumulator It is connect with the second voltage stabilizing input port；Current divider, the current divider include at least：First shunting input port, the first shunting are defeated Outlet, the second shunting delivery outlet and third shunting delivery outlet；The first shunting input port connects with the first voltage stabilizing delivery outlet It connects；Steering engine, the steering engine include at least：First steering engine, the second steering engine and third steering engine；Wherein, first steering engine at least wraps It includes：First steering engine input port and the first rotor shaft, the first steering engine input port are connect with the described first shunting delivery outlet；It is described First rotor shaft is connect with the first rotor；Second steering engine includes at least：Second steering engine input port and the second rotor shaft, it is described Second steering engine input port is connect with the described second shunting delivery outlet；Second rotor shaft is connect with the second rotor；The third Steering engine includes third rotor shaft and third fixed seat；Driving motor, the driving motor include at least：First driving motor；Institute The first driving motor is stated to connect with third shunting delivery outlet；Wherein, first driving motor include the first drive shaft and Drive fixed seat；The rotor mechanism of adjustable angle is connect with first driving motor, and first driving motor is located at institute It states between third shunting delivery outlet and the rotor mechanism of the adjustable angle；Tailspin seat, the tailspin seat are fixed at described On second caudal face of unmanned plane and/or the both sides in the 4th caudal face, and it is described driving fixed seat be arranged on the tailspin seat and/ Or on the third ontology；Linkage portion, the linkage portion include the first cohesive end, the second cohesive end and tail rotor；Described first Cohesive end and the first driving axis connection, second cohesive end are connected with the third fixed seat, the third rotor shaft It is fixedly connected with the center of the tail rotor, and the rotational plane of the third rotor shaft and the tail rotor is perpendicular；Wherein, The driving force of first drive shaft is transferred to by second cohesive end, and the third rotor by first cohesive end Axis drives the tail rotor along the first caudal face, the second caudal face, the third side caudal face or the described 4th Tail side surface direction moves；First rotor, first rotor include：First rotating vane, first rotating vane with it is described First rotor shaft is fixedly connected；First clump weight, first clump weight are fixedly connected with first rotor shaft, and described One rotating vane and first clump weight are symmetrical relative to first rotor shaft；Second rotor, second rotor Including：Second rotating vane, second rotating vane are fixedly connected with second rotor shaft；Second clump weight, described Two clump weights are fixedly connected with second rotor shaft, and second rotating vane and second clump weight are relative to described Second rotor shaft is symmetrical；First winglet, first winglet and the first postposition wing intersect；And described first Winglet includes the first wing tip fastening end and the first wing tip openend；And the first wing tip fastening end and the first rear open end It is fixedly connected, the first wing tip openend deviates from first rear open end, described in the composition of the first wing tip fastening end The both ends of first winglet；And the first wing tip openend and vertical stabilizer are located at the both sides of the first postposition wing； Second winglet, second winglet and the second postposition wing intersect；And second winglet includes second wing Sharp fastening end and the second wing tip openend；And the second wing tip fastening end is fixedly connected with second rear open end, it is described Second wing tip openend deviates from second rear open end, and second winglet is formed with the second wing tip fastening end Both ends；And the second wing tip openend and vertical stabilizer are located at the both sides of the second postposition wing.

Further, the driving motor further includes：Second driving motor, second driving motor and the first aileron connect Connect, and second driving motor be fixed at first after between fastening end and the first rear open end.

Further, the driving motor further includes：Third driving motor, the third driving motor and the second aileron connect Connect, and the third driving motor be fixed at second after between fastening end and the second rear open end.

Further, the driving motor further includes：4th driving motor, the 4th driving motor connect with third aileron It connects, and the 4th driving motor is fixed on vertical stabilizer.

Further, the current divider further includes：4th shunting delivery outlet, the 4th shunting delivery outlet and described second Driving motor connects；

Further, the current divider further includes：5th shunting delivery outlet, the 5th shunting delivery outlet and the third Driving motor connects.

Further, the current divider further includes：6th shunting delivery outlet, the 6th shunting delivery outlet and the described 4th Driving motor connects；7th shunting delivery outlet；Third steering engine input port, the third steering engine input port and the described 7th shunting are defeated Outlet connection.

Further, first rotating vane is single blade blade, and second rotating vane is single blade blade.

Further, the engine is two stroke engine；The electric pressure converter is AC/DC converters.

Further, the generator connect with the engine including：The rotor of the generator and the engine Output shaft be fixedly connected；Wherein, the electric pressure converter is connected with the supply port of the generator, and the rotor is located at Between the supply port and the output shaft.

Advantageous effect：The present invention provides the power wingtip device of the adjustable angle applied to unmanned plane, by by tailspin seat It is fixed on the second caudal face of unmanned plane and/or the both sides in the 4th caudal face, driving fixed seat is arranged on tailspin seat And/or on third ontology；By the first driving axis connection of the first cohesive end of linkage portion and the first driving motor, the of linkage portion Two cohesive ends are connected with the third fixed seat of third steering engine, and the third rotor shaft of third steering engine and the center of tail rotor is made to fix and connect It connects, and is mutually perpendicular to the third rotor shaft of third steering engine and the rotational plane of tail rotor.Then by the first cohesive end by The driving force of one drive shaft is transmitted to the second cohesive end, then drives first caudal of the tail rotor along unmanned plane by third rotor shaft Face, the second caudal face, third side caudal face or the 4th tail side surface direction are moved, and to change the direction of motion of tail rotor, are made Tail rotor generates variation to the thrust size and Orientation of unmanned plane, and the landing for unmanned plane provides the drawing in different size and direction Power, and the flight for unmanned plane provides required thrust.Due to by by current divider be respectively the first steering engine, the second steering engine, The rotor mechanism of first driving motor and adjustable angle provides electric energy, and unmanned plane is allow normally to be lifted and flown, More electric energy are provided for unmanned plane.Simultaneously because the first steering engine input port of the first steering engine and the first shunting output of current divider Mouth connection, the first rotor shaft of the first steering engine are connected with the first rotor；Second steering engine input port of the second steering engine and current divider Second shunting delivery outlet connection, the second rotor shaft of the second steering engine are connected with the second rotor.Second rotating vane and the second counterweight Block will be fixedly connected with the second rotor shaft respectively, make the second rotating vane and the second clump weight relative to the second rotor axial symmetry point Cloth is in in-flight in unmanned plane, and the first rotating vane and the second pivoting leaf can remain the direction consistent with air-flow, from And reduce resistance of the air-flow to rotor, traditional rotor is overcome to larger interference caused by unmanned plane during flying.And pass through First wing tip fastening end of the first winglet is fixedly connected with the first rear open end, by the second wing tip of the second winglet Fastening end is fixedly connected with the second rear open end, then so that being in flight course and the first postposition wing phase in unmanned plane The first winglet handed over and the second winglet for intersecting with the second postposition wing, respectively in the first postposition wing and the The air of upper lower aerofoil is hindered to stream on two postposition wings, to reduce induced drag, reduces the weakening streamed to unmanned plane lift. Required thrust or pulling force can be provided with flight whole process for the landing of unmanned plane so as to reach, but also unmanned plane is with longer Cruise duration, improve unmanned plane practicability；Simplify rotor structure, rational in infrastructure；Promote the skill of unmanned plane stability Art effect.

Description of the drawings

It in order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to institute in embodiment Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the present invention Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings Obtain other attached drawings.

Fig. 1 is the overall structure diagram of unmanned plane provided in an embodiment of the present invention；

Fig. 2 is the top view illustration of Fig. 1；Fig. 3 is the bottom view schematic diagram of Fig. 1；

Fig. 4 is the front view schematic diagram of Fig. 1；Fig. 5 is the rearview schematic diagram of Fig. 1；

Fig. 6 is the side view schematic diagram of Fig. 1；

Fig. 7 is the schematic diagram of the rotor mechanism of adjustable angle provided in an embodiment of the present invention；

Fig. 8 is generator provided in an embodiment of the present invention and engine connection relationship diagram；

Fig. 9 is the mechanism block diagram of circuit control system provided in an embodiment of the present invention.

Specific embodiment

The present invention discloses the power wingtip device of the adjustable angle applied to unmanned plane, by the way that tailspin seat is fixed at On second caudal face of unmanned plane and/or the both sides in the 4th caudal face, driving fixed seat is arranged on tailspin seat and/or third sheet On body；By the first driving axis connection of the first cohesive end of linkage portion and the first driving motor, the second cohesive end of linkage portion and The third fixed seat connection of third steering engine, makes the third rotor shaft of third steering engine be fixedly connected with the center of tail rotor, and make the The third rotor shaft of three steering engines and the rotational plane of tail rotor are mutually perpendicular to.Then by the first cohesive end by the first drive shaft Driving force is transmitted to the second cohesive end, then by first caudal face of the third rotor shaft drive tail rotor along unmanned plane, the second tail Side, third side caudal face or the 4th tail side surface direction are moved, and to change the direction of motion of tail rotor, make tail rotor to nothing Man-machine thrust size and Orientation generates variation, and the landing for unmanned plane provides the pulling force in different size and direction, and is nothing Man-machine flight provides required thrust.Due to by being respectively the first steering engine, the second steering engine, the first driving motor by current divider Electric energy is provided with the rotor mechanism of adjustable angle, unmanned plane is allow normally to be lifted and flown, is also provided for unmanned plane More electric energy.Simultaneously because the first steering engine input port of the first steering engine is connected with the first of current divider the shunting delivery outlet, first First rotor shaft of steering engine is connected with the first rotor；Second steering engine input port of the second steering engine and the second shunting output of current divider Mouth connection, the second rotor shaft of the second steering engine are connected with the second rotor.Second rotating vane and the second clump weight will be respectively with Two rotor shafts are fixedly connected, and make the second rotating vane and the second clump weight symmetrical relative to the second rotor shaft, in unmanned plane In in-flight, the first rotating vane and the second pivoting leaf can remain the direction consistent with air-flow, so as to reduce gas The resistance to rotor is flowed, overcomes traditional rotor to larger interference caused by unmanned plane during flying.And by by the first wing tip First wing tip fastening end of winglet is fixedly connected with the first rear open end, by the second wing tip fastening end of the second winglet and Two rear open ends are fixedly connected, then so that being in first wing that in flight course and the first postposition wing intersects in unmanned plane Sharp winglet and the second winglet intersected with the second postposition wing, respectively in the first postposition wing and the second postposition wing The air of lower aerofoil streams in upper obstruction, to reduce induced drag, reduces the weakening streamed to unmanned plane lift.It can so as to reach Required thrust or pulling force are provided with the landing for unmanned plane and flight whole process, but also when unmanned plane has longer continuation of the journey Between, improve unmanned plane practicability；Simplify rotor structure, rational in infrastructure；Promote the technique effect of unmanned plane stability.

In order to which the power wingtip device of the adjustable angle applied to unmanned plane provided invention elaborates, to support The technical problems to be solved by the invention in the following, in embodiment provided by the invention, first elaborate to unmanned plane, then During unmanned plane is described, the adjustable angle provided by the invention applied to unmanned plane is further targetedly drawn Power wingtip device, it is complete, clear, clear to achieve the purpose that.

Explanation is summarized below to the overall condition of unmanned plane first：The present invention is by the way that the fuselage of unmanned plane is divided at least Including three sections, i.e. the first fuselage 10, the second fuselage 20 and third fuselage 30, and pass through the connection of detachable connection between three sections Mode is attached, and is formed a dismountable unmanned plane of internal structure with this, so that when the fuselage of unmanned plane goes out current situation When portion damages, it corresponding can remove the position for occurring damaging and repair, there is simple, convenient technique effect.And And when the part of fuselage can not be repaired when damaging, can also the position that can not repair of corresponding dismounting, i.e., to can not The position of reparation is substituted, so as to overcome in the prior art because fuselage is using integrated global design so that occur When fuselage local damage can not be repaired, it has to replace the technological deficiency of the entire fuselage of unmanned plane, reach and significantly reduce The technique effect of maintenance cost.

Meanwhile unmanned plane perform landing operation during, the present invention in unmanned plane included by the first rotor 1211st, the rotor mechanism 331 of the second rotor 1221 and adjustable angle matches operation (being operated) and generates lifting force, pulls Fuselage rises or declines.Such as：When unmanned plane takes off, by the way that the first rotor 1211 and the second rotor 1221 is controlled to rotate, And the rotation direction (rotor mechanism 331 is made to provide upward pulling force) of the adjustable rotor mechanism 331 of angle is adjusted, by the first rotation Resultant force caused by the rotation of the wing 1211, the rotation of the second rotor 1221 and the operating of rotor mechanism 331, for unmanned plane provide to On lifting force, so as to fulfill taking off vertically for unmanned plane.When unmanned plane is drawn high certain altitude, then can by adjusting angle The rotation direction (rotor mechanism 331 is made to provide horizontal thrust) of the rotor mechanism 331 of tune, so as to which generation level pushes away on unmanned plane Power pushes unmanned plane to slide in the air and takes off, and then enters stabilized flight；When declining, by controlling the first rotor 1211, the The lifting force of two rotors 1221, and control the adjustable rotor mechanism 331 of angle that unmanned plane is made to pull fuselage under eminence stabilization Drop, until stablizing landing, the damage of fuselage and carrying equipment, greatly reduces landing accident caused by avoiding fuselage hard landing Risk, having reached makes unmanned plane be suitble to carry out the technique effect of landing operation in different flying field.

Below in conjunction with Figure of description, the technical solution in the embodiment of the present invention is clearly and completely described, is shown So, described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.

In order to which unmanned plane provided in an embodiment of the present invention is described in detail, first to involved in the embodiment of the present invention And technical term do description below explanation：

Detachable connection can be bolted or be bonded；Being fixedly connected can be welding or integrated molding；Ground Face can be the ground that unmanned plane is parked or the face with this plane parallel；First level face can be put down with level ground Capable face, and the center vertical pivot 123 of the first noumenon is located in the plane；Minimum flying speed can be that unmanned plane is made to keep flying Minimum flying speed when going, and not falling.Such as in the present embodiment, the minimum flying speed of unmanned plane can be 20m/s；It rises The winged stage can be the process that unmanned plane reaches aerial vertical ascent from ground；Take off winged stage that flattens can be that unmanned plane arrives Up to after aerial, the process of horizontal flight is carried out；The turning stage can be unmanned plane from level flight condition, the mistake turned Journey, such as left and right turning；Landing phases can be process of the unmanned plane from airborne to ground.

For 10 part of the first fuselage：Fig. 1-6 is referred to, the first fuselage 10 includes：Portion 11, the first noumenon windward 12 and first connecting portion 13, the first noumenon 12 is located at windward between portion 11 and first connecting portion 13, and portion 11, first windward Body 12 and first connecting portion 13, which are integrally formed, forms the first fuselage 10.In the first fuselage 10, by that will be arranged in portion 11 windward The diameter of section in portion 11 windward is sequentially increased, and make the first noumenon by cone structure on the direction towards the first noumenon 12 12 diameter of section is sequentially reduced on the direction towards first connecting portion 13, is allowed in this way in unmanned plane during flying, first The global shape design of fuselage 10 in embodiments of the present invention advantageously reduces the resistance of air-flow.

In addition, the first forewing 121 and the second forewing 122 are additionally provided on the first noumenon 12.Wherein, first Forewing 121 includes：First preceding 1212 and first forward open end 1213 of fastening end.Second forewing 122 includes：Before second 1222 and second forward open end 1223 of fastening end.And first preceding 1212 and second preceding fastening end 1222 of fastening end along the first noumenon 12 Center vertical pivot be symmetrically distributed in the both sides of the first noumenon 12, and three is relatively fixed.

It specifically, can be by can between the first preceding fastening end 1212 of the first forewing 121 and the first noumenon 12 The connection mode being detachably connected with is attached.Second preceding fastening end 1222 of the second forewing 122 and the first noumenon 12 it Between can also be attached by the connection mode of detachable connection.The mode by being detachably connected is allowed in this way It is detachable between first forewing 121, the second forewing 122 and the first noumenon 12, convenient for the assembling of the first fuselage 10, make Obtain convenience easy to maintenance.

Fig. 4-Fig. 6 is referred to, the first forewing 121 and the angle in first level face can be 2.5 °, at unmanned plane When minimum flying speed, 2.5 ° of angle can be that unmanned plane obtains enough lift, to overcome the weight of unmanned plane itself, from And lift preferably is generated for unmanned plane, keep state of flight.Second forewing 122 can also be with first level face angle 2.5 °, when unmanned plane is in minimum flying speed, 2.5 ° of angle also can be that unmanned plane obtains enough lift, to overcome nothing The man-machine weight of itself so as to preferably generate lift for unmanned plane, keeps state of flight.

The first rotor 1211 is provided on the first forewing 121 and for the first rotor 1211 to be driven to be revolved The first steering engine 471 turned is provided with the second rotor 1221 on the second forewing 122 and for driving the second rotor 1221 The second steering engine 472 rotated.And in the first forward open end 1213 of the first forewing 121, also set up one first Storage region 12131；One second storage region 12231 is also set up in the second forward open end 1223 of the second forewing 122.

Wherein, the first steering engine 471 includes：First rotor shaft 4712 and the first fixed seat for fixing the first steering engine 471 4713, and the first fixed seat 4713 is fixed in the first storage region 12131；Second steering engine 472 includes：Second rotor shaft 4722 With for fixing the second fixed seat 4723 of the second steering engine 472, and the second fixed seat 4723 is fixed on the second storage region 12231 It is interior.First rotor 1211 includes：First rotating vane 12111 and the first clump weight 12112, the first rotating vane 12111 and One rotor shaft 4712 is fixedly connected, and the first clump weight 12112 is fixedly connected with the first rotor shaft 4712；And the first rotating vane 12111 and first clump weight 12112 it is symmetrical relative to the first rotor shaft 4712, the first rotor shaft 4712 and the first pivoting leaf The rotational plane of piece 12111 is perpendicular.Second rotor 1221 includes：Second rotating vane 12211 and the second clump weight 12212, Second rotating vane 12211 is fixedly connected with the second rotor shaft 4722, and the second clump weight 12212 is fixed with the second rotor shaft 4722 Connection, and the second rotating vane 12211 and the second clump weight 12212 are symmetrical relative to the second rotor shaft 4722, second Rotor shaft 4722 and the rotational plane of the second rotating vane 12211 are perpendicular.

Specifically, the size and shape of the first storage region 12131 and the second storage region 12231 can be according to required The form parameter of the steering engine 47 of placement and determine, such as the volume size of steering engine 47, so as to which the first steering engine 471 is positioned over first It is positioned in the second storage region 12231 in storage region 12131 and by the second steering engine 472.First steering engine 471 passes through its own The first fixed seat 4713 be fixed in the first storage region 12131, the first rotor shaft 4712 of the first steering engine 471 and the first rotation First rotating vane 12111 of the wing 1211 is fixedly connected, and the first rotor shaft 4712 and the first clump weight 12112 are fixed and connected It connects.First rotor shaft 4712 and the rotational plane of the first rotating vane 12111 are perpendicular, i.e., in the first rotating vane 12111 During rotation, the plane of the rotation is mutually perpendicular to the first rotor shaft 4712；First rotating vane 12111 and the first clump weight 12112 is symmetrical relative to the first rotor shaft 4712, i.e. the first rotating vane 12111 and the first clump weight 12112 are with first Rotor shaft 4712 is symmetric for axis.The making material of first clump weight 12112 can use rigid material so that the first rotation When the first rotating vane 12111 of drive of wing axis 4712 and the first clump weight 12112 rotate together, the first clump weight 12112 will not It deforms upon, so as to influence the balance of the first rotor 1211.

On the other hand, the second steering engine 472 is fixed on by the second fixed seat 4723 in the second storage region 12231, the Second rotor shaft 4722 of two steering engines 472 is fixedly connected with the second rotating vane 12211 of the second rotor 1221, and the second rotation Wing axis 4722 is fixedly connected with the second clump weight 12212.The rotational plane of second rotor shaft 4722 and the second rotating vane 12211 Perpendicular, i.e., in the rotation of the second rotating vane 12211, the plane of the rotation is mutually perpendicular to the second rotor shaft 4722；The Two rotating vanes 12211 and the second clump weight 12212 are symmetrical relative to the second rotor shaft 4722, i.e. the second rotating vane 12211 and second clump weight 12212 be symmetric with the second rotor shaft 4722 for axis.The making material of second clump weight 12212 Material can use rigid material so that the second rotor shaft 4722 drives the second rotating vane 12211 and the second clump weight 12,212 1 When playing rotation, the second clump weight 12212 will not deform upon, so as to influence the balance of the first rotor 1211.

In embodiment provided by the invention, it is especially desirable to it is to be noted that：First rotor 1211 includes the first rotating vane 12111 and first clump weight 12112；Second rotor 1221 includes the second rotating vane 12211 and the second clump weight 12212. Exactly the first rotor 1211 uses single blade, and what the second rotor 1221 used is also single blade.What traditional rotor used All it is twayblade, traditional rotor is namely made of two blades of similar first rotating vane 12111, the two blades lead to Often it is symmetric relative to the axis that movable vane piece rotates.Traditional rotor due to the use of be twayblade, if unmanned plane fly In row, which, so as to increase the resistance of air-flow, can produce the flight of unmanned plane larger do along flow rotation Disturb, be unfavorable for the balance of unmanned plane, at the same can cause unmanned plane amount of power can be lost it is larger.Provided in an embodiment of the present invention One rotor 1211 and the second rotor 1221 are all to use single blade, while be respectively arranged with the first clump weight with each single blade 12112 and second clump weight 12212, and then weight balancing is played to the first rotating vane 12111 and the second rotating vane 12211 Effect.Since rotor has single blade, if unmanned plane is awing, which will remain consistent with air-flow Direction so as to reduce the resistance of air-flow, overcomes traditional twayblade rotor to larger dry caused by the flight of unmanned plane It disturbs, to the destruction caused by the balance of unmanned plane and the technological deficiency for making the power capacity loss of unmanned plane larger.Reach Be conducive to the flight balance of unmanned plane, reduce the technique effect of the energy loss of unmanned mechanomotive force.

Refer to Fig. 2, the first forewing 121 is in the first preceding fastening end 1212, along to 1213 direction of the first forward open end On width be sequentially reduced；And/or second forewing 122 in the second preceding fastening end 1222, along to the second forward open end 1223 Width on direction is sequentially reduced.

Specifically, the shape for the first forewing 121 and the second forewing 122 provides following two embodiment party Formula illustrates：

The first embodiment, by by the first forewing 121 since the first preceding fastening end 1212, towards to first Width on 1213 direction of forward open end is sequentially reduced so that the first forewing 121 can be it is trapezoidal, due to tapered airfoil not By angle of sweep drag reduction, so the angle of sweep of the leading edge of a wing can be smaller, so as to make unmanned plane that can awing obtain preferable liter Power.

Second of embodiment, by by the second forewing 122 since the second preceding fastening end 1222, towards to second Width on 1223 direction of forward open end is sequentially reduced so that the second forewing 122 can be it is trapezoidal, due to tapered airfoil not By angle of sweep drag reduction, so the angle of sweep of the leading edge of a wing can be smaller, so as to make unmanned plane that can awing obtain preferable liter Power.

More than first embodiment and second embodiment can implement simultaneously, can also be in first embodiment Implement with optional one in second embodiment.Such as：Make the first forewing 121 trapezoidal, and make second preposition Wing 122 is also trapezoidal, so as to which unmanned plane be made to obtain preferable lift.Make the first forewing 121 trapezoidal or make second Forewing 122 is trapezoidal, so as to which unmanned plane in the global design of unmanned plane, be made to obtain preferable lift.

For 20 part of the second fuselage：Fig. 1-6 is referred to, the second fuselage 20 includes second connecting portion 21, second Body 22 and third connecting portion 23；Wherein, the second ontology 22 is between second connecting portion 21 and third connecting portion 23, and second connects Socket part 21, the second ontology 22 and third connecting portion 23, which are integrally formed, forms the second fuselage 20；Second connecting portion 21 and first connects Portion 13 is detachably connected, and the second ontology 22 is fixedly connected with second connecting portion 21, and 23 and second ontology 22 of third connecting portion is fixed Connection.

Specifically, since second connecting portion 21 and first connecting portion 13 are detachably connected so that the second fuselage 20 and It is also to pass through detachable connection between one fuselage 10.Pass through mode the first fuselage 10 being detachably connected and the second fuselage It is detachable between 20, convenient for the assembling of the second fuselage 20 so that convenience easy to maintenance significantly reduces maintenance cost.

Further, the second ontology 22 can include：First side 221, second side 222 and third side 223, and First side 221 and second side 222 are symmetrical along the center vertical pivot 224 of the second ontology, and third side 223 is located at first Between side 221 and second side 222；And the first postposition wing 2211, second side 222 are provided in first side 221 On be provided with the second postposition wing 2221, be provided with vertical stabilizer 2231 on third side 223.First postposition wing 2211 wraps It includes：22111 and first rear open end 22112 of fastening end after first；Second forewing 122 includes：Fastening end 22211 after second With the second rear open end 22212.Wherein, behind fastening end 22111 and second center of the fastening end 22211 along the second ontology after first Vertical pivot 224 is symmetrically fixed at the both sides of the second ontology 22；And 22111 and first rear open end of fastening end after first 22112 be the both ends of the first postposition wing 2211 respectively, and 22211 and second rear open end 22212 of fastening end is respectively after second The both ends of second postposition wing 2221.

Connect specifically, the first postposition wing 2211 can be fixed by fastening end 22111 after first with first side 221 It connects, the second postposition wing 2221 can be fixedly connected by fastening end 22211 after second with second side 222, vertical stabilizer 2231 can be fixedly connected with third side 223.By setting the first postposition wing 2211 and the second postposition wing 2221, make this Two wings when unmanned plane is in flight, can provide the lift of bigger for unmanned plane.

Further, the second fuselage 20 further includes：First winglet 24 and the second winglet 25.Individually below to One winglet 24 and the second winglet 25 are described in detail：

For 24 part of the first winglet.The angle of first winglet 24 and the first postposition wing 2211 is 60 °- 90°；First winglet 24 includes the first wing tip fastening end 241 and the first wing tip openend 242；And the first wing tip fastening end 241 are fixedly connected with the first rear open end 22112, and the first wing tip openend 242 deviates from the first rear open end 22112, with first Wing tip fastening end 241 forms the both ends of the first winglet 24；And the first wing tip openend 242 and vertical stabilizer 2231 are located at The both sides of first postposition wing 2211；

For 25 part of the second winglet.The angle of second winglet 25 and the second postposition wing 2221 is 60 °- 90°；Second winglet 25 includes：Second wing tip fastening end 251 and the second wing tip openend 252；And the second wing tip fastens End 251 is fixedly connected with the second rear open end 22212, and the second wing tip openend 252 is away from the second rear open end 22212, with the Two wing tip fastening ends 251 form the both ends of the second winglet 25；And the second wing tip openend 252 and vertical stabilizer 2231 In the both sides of the second postposition wing 2221.

More than the first wing tip openend 242 of the first winglet 24 and the second wing tip openend of the second winglet 25 252 can symmetrically be distributed along the center vertical pivot 224 of the second ontology.Certainly, the first wing tip openend of the first winglet 24 242 and second second wing tip openend 252 of winglet 25 can be along 224 asymmetric points of the center vertical pivot of the second ontology Cloth.

Specifically, the first winglet 24 includes：First wing tip fastening end 241 and the first wing tip openend 242；First First wing tip fastening end 241 of winglet 24 is fixedly connected with the first rear open end 22112 of the first postposition wing 2211, and And first wing tip openend 242 away from the first rear open end 22112, i.e. the first wing tip openend 242 is as shown in figure 4, positioned at nothing The lower section of man-machine fuselage.At this point, the first winglet 24 and the first postposition wing 2211 form angle, the range of the angle is： 60°-90°；Second wing tip fastening end 251 of the second winglet 25 and the second rear open end of the second postposition wing 2221 22212 are fixedly connected, and the second wing tip openend 252 is away from the second rear open end 22212, i.e. the second wing tip openend 252 As shown in figure 4, positioned at the lower section of unmanned aerial vehicle body.At this point, the second winglet 25 and the second postposition wing 2221 form angle, The range of the angle is：60°-90°

Fig. 4, Fig. 5 are referred to, in order to which specification is made preferably to support the first winglet 24 and first in claims The numerical value of the numberical range of the angle of postposition wing 2211 and the angle of the second winglet 25 and the second postposition wing 2221 Range is now chosen two endpoint values of angular range, is explained as follows with two embodiments respectively：

The first embodiment, if the angle of the first winglet 24 and the first postposition wing 2211 is 60 °, and the The angle of two winglets 25 and the second postposition wing 2221 is also 60 °.I.e. when unmanned plane is parked in level ground, by first wing The angle that first wing tip openend 242 of sharp winglet 24 and the first rear open end 22112 of the first postposition wing 2211 are formed It is 60 °；And by the second wing tip openend 252 of the second winglet 25 and the second rear open end of the second postposition wing 2221 22212 angles formed are also 60 °.At this point, the first winglet 24 and the first postposition wing 2211 can effectively hinder first The air of the upper lower aerofoil of postposition wing 2211 streams, and the second winglet 25 also can be effective with the second postposition wing 2221 The air of the upper lower aerofoil of the second postposition wing 2221 is hindered to stream.So as to reduce caused by first box the second wing tip trailing vortex " induced drag ", and then reduce and stream to lift produced by the first postposition of unmanned plane wing 2211 and the second postposition wing 2221 Destruction, improve unmanned plane lift resistance ratio, increase voyage, have the function that increase unmanned plane lift.

Second of embodiment, if the angle of the second winglet 25 and the second postposition wing 2221 is 90 °, and the The angle of two winglets 25 and the second postposition wing 2221 is also 90 °.I.e. when unmanned plane is parked in level ground, by first wing The angle that first wing tip openend 242 of sharp winglet 24 and the first rear open end 22112 of the first postposition wing 2211 are formed It is 90 °；And by the second wing tip openend 252 of the second winglet 25 and the second rear open end of the second postposition wing 2221 22212 angles formed are also 90 °.At this point, the first winglet 24 and the first postposition wing 2211 can effectively hinder first The air of the upper lower aerofoil of postposition wing 2211 streams, and the second winglet 25 also can be effective with the second postposition wing 2221 The air of the upper lower aerofoil of the second postposition wing 2221 is hindered to stream.So as to reduce caused by the first and second wing tip trailing vortexs " induced drag ", reduce the destruction streamed to lift, improve lift resistance ratio, increase voyage, have the function that increase lift.Together When, since the first winglet 24 and the second winglet 25 are all mutually perpendicular to first level face, so the first winglet 24 and second the distance between winglet 25 and ground recently so that the first winglet 24 of manufacture and the second winglet 25 Required material is also less, so as to alleviate the own wt of the first winglet 24 and the second winglet 25, reduces nothing Man-machine overall weight, has reached increase voyage, reduce unmanned plane kinetic equation loss (such as：Oil consumption, the electric energy of accumulator 45) Technique effect.

Further, the second fuselage 20 further includes：First aileron 26, the second aileron 27 and third aileron 28.First aileron 26th, the second aileron 27 and third aileron 28 can be rectangle.The rotation of first aileron 26 is arranged on the first rear open end On 22112, and the first aileron 26 is rotated in the first rear open end 22112 relative to the first rear open end 22112； And/or second aileron 27 rotate be arranged in the second rear open end 22212, and the second aileron 27 is in the second rear open end It is rotated on 22212 relative to the second rear open end 22212；And/or third aileron 28 rotate be arranged on vertical stabilizer On 2231, and third aileron 28 is rotated on vertical stabilizer 2231 relative to vertical stabilizer 2231；Wherein, the first postposition Fastening end 22111 after first of wing 2211 are sequentially reduced along the width on 22112 direction of the first rear open end；And/or Second fastening end 22211 after second of postposition wing 2221, subtract successively along the width on 22212 direction of the second rear open end It is small.

Fig. 5 is referred to, specifically, the first aileron 26 is arranged on the first rear open end in the first postposition wing 2211 On 22112, the first aileron 26 can be relative to the plane of the first postposition wing 2211, along the plane of the first postposition wing 2211 Vertically rotate；Second aileron 27 is arranged in the second rear open end 22212 in the second postposition wing 2221, and second is secondary The wing 27 can be relative to the plane of the second postposition wing 2221, and the plane along the second postposition wing 2221 vertically turns It is dynamic；Third aileron 28 is arranged on vertical stabilizer 2231, is rotated in the lateral direction along the plane of vertical stabilizer 2231.

Meanwhile first postposition wing 2211 can be trapezoidal, after first fastening end 22111 be the trapezoidal bottom, favorably In the lift for improving unmanned plane, keep the in-flight stability of unmanned plane and flying for unmanned plane is controlled by the first aileron 26 Row posture；Second postposition wing 2221 can also be trapezoidal, and fastening end 22211 is also the trapezoidal bottom after second, is conducive to The lift of unmanned plane is improved, keep the in-flight stability of unmanned plane and the flight of unmanned plane is controlled by the second aileron 27 Posture.

Referring to Fig. 4, the angle of the first forewing 121 and the first postposition wing 2211 can be 15 °, meanwhile, second The angle of 122 and second postposition wing 2221 of forewing can also be 15 °.If the first forewing and the first postposition wing Angle is 15 °, and the angle of the second forewing 122 and the second postposition wing 2221 is also 15 °, is pushed in tail rotor 33123 During unmanned plane during flying, the balance of unmanned plane surrounding flow is beneficial to, so as to reach the technology for the stability for promoting unmanned plane effect Fruit.Fig. 3 is referred to, the abdomen of unmanned plane can include first (when i.e. unmanned plane is parked in level ground, close to the face of unmanned plane) The abdomen of the abdomen of fuselage 10, the abdomen of the second fuselage 20 and third fuselage 30, the abdomen of unmanned plane can be rendered as arc, should The abdomen of arc advantageously reduces obstruction of the air-flow to unmanned plane, reduces the energy loss of unmanned plane, reaches promotion unmanned plane and flies The technique effect of row distance.

Fig. 9 is referred to, further, the second driving motor 482 is connect with the first aileron 26, and the second driving motor 482 be fixed at first after between 22111 and first rear open end 22112 of fastening end；Third driving motor 483 and second is secondary The wing 27 connects, and third driving motor 483 be fixed at second after 22211 and second rear open end 22212 of fastening end it Between；4th driving motor 484 is connect with third aileron 28, and the 4th driving motor 484 is fixed on vertical stabilizer 2231.

Specifically, after the second driving motor 482 is connect with the first aileron 26, pass through the work of the second driving motor 482 The pulling force rotated upwardly and downwardly is provided for the first aileron 26；After third driving motor 483 is connect with the second aileron 27, driven by third The work of motor 483 provides the pulling force rotated upwardly and downwardly for the second aileron 27.4th driving motor 484 is connect with third aileron 28 Afterwards, the pulling force of left-right rotation is provided by the work of the 4th driving motor 484 for third aileron 28.

Continuing with referring to Fig. 9, further, current divider 46 further includes：The 4th shunting shunting output of delivery outlet the 465, the 5th 466 and the 6th shunting delivery outlet 467 of mouth.4th shunting delivery outlet 465 is connect with the second driving motor 482；5th shunting output Mouth 466 is connect with third driving motor 483；6th shunting delivery outlet 467 is connect with the 4th driving motor 484.

Specifically, it can be by current divider by conducting wire that the 4th shunting delivery outlet 465 is connect with the second driving motor 482 46 connect with the second driving motor 482, power on the second driving motor 482；5th shunting delivery outlet 466 drives with third The connection of motor 483 can be connect current divider 46 with third driving motor 483 by conducting wire, connect third driving motor 483 Energization source；It can be by current divider 46 and 4 wheel driven by conducting wire that 6th shunting delivery outlet 467 is connect with the 4th driving motor 484 Dynamic motor 484 connects, and powers on the 4th driving motor 484.So as to be the second driving motor 482 by current divider 46, the Three driving motors 483 and the 4th driving motor 484 provide electric energy.Refer to Fig. 2 and Fig. 3, it should be noted that unmanned plane is set The weight calculation heart is located at the first lift equalization point and first of the first forewing 121 and the second forewing 122 on unmanned plane Between the second lift equalization point of the 2211 and second postposition wing 2221 of postposition wing on unmanned plane；And the design weight of unmanned plane The heart is at the 3/4 of the first lift equalization point and the second lift equalization point spacing, and the design gravity of unmanned plane is close to the second lift Equalization point.

Specifically, the lift equalization point of the first forewing 121 and the second forewing 122 on unmanned plane is first Lift equalization point (abbreviation A points), the lift equalization point of the first postposition wing 2211 and the second postposition wing 2221 on unmanned plane It is the second lift equalization point (abbreviation B points)；Air line distance length between A points and B points is S, and the design gravity of unmanned plane is referred to as For C points.In order to explain in detail the design gravity of unmanned plane (C points) and the first lift equalization point (A points), the second lift equalization point (B Point) position relationship, now enumerate embodiment and be explained as follows：C points are located between A points and B points, and straight between C points and A points Linear distance is assumed to be L, and L needs to meet：L=(3/4) * S.Meanwhile A points, B points and C points may be alternatively located on same straight line.Due to nothing Man-machine design center of gravity is at the 3/4 of the first lift equalization point and the second lift equalization point spacing, when unmanned plane weight changes When, the control performance to unmanned plane will not be influenced.So the design gravity of unmanned plane is in the first lift equalization point and second liter At the 3/4 of power equalization point spacing, be conducive to adapt to the different weight of unmanned plane, and then reach the technology effect for not influencing control performance Fruit.

Obviously, in embodiment provided by the invention, to the design gravity of unmanned plane in the first lift equalization point and second At the 3/4 of lift equalization point spacing and explanation that position relationship that A points, B points and C points are located along the same line is carried out, and To provide constraints to the position, those of ordinary skill in the art, can by modifying to the link position or Equivalent replacement, but this modification or equivalent replacement are within protection scope of the present invention.Such as：The design gravity of unmanned plane exists At the 4/5 of first lift equalization point and the second lift equalization point spacing；C points are located at except the line of B points and C points.

For 30 part of third fuselage：Fig. 1-Fig. 6 is referred to, third fuselage 30 includes the 4th connecting portion 31, third Ontology 32 and tail portion 33；Third ontology 32 is between the 4th connecting portion 31 and tail portion 33, and the 4th connecting portion 31, third ontology 32 and tail portion 33 be integrally formed and form third fuselage 30, the diameter of section of tail portion 33 towards increasing on the direction of third ontology 32 successively Greatly.It is fixedly connected by tail portion 33 with third ontology 32, third ontology 32 is fixedly connected with the 4th connecting portion 31, the 4th connecting portion 31 and third connecting portion 23 be detachably connected, 30 and second fuselage 20 of third fuselage is made to be connected as a single entity.

Specifically, since the third connecting portion 23 of the 4th connecting portion 31 and the second fuselage 20 is detachably connected so that the It is also to pass through detachable connection between three fuselages 30 and the second fuselage 20.Pass through the mode third fuselage being detachably connected 30 and second detachable between fuselage 20, convenient for the assembling of third fuselage 30 so that convenience easy to maintenance significantly reduces dimension Accomplish this.

Further, the rotor mechanism 331 of an adjustable angle is provided on tail portion 33；Third fuselage 30 can be divided For：First caudal face 34, the second caudal face 35, third side caudal face 36 and the 4th caudal face 37 so that by the first caudal face 34, Second caudal face 35, third side caudal face 36 and the 4th caudal face 37 are surrounded to form third fuselage 30, and the first caudal face 34 The both sides in the second caudal face 35 and/or the 4th caudal face 37 are symmetrically dispersed in third side.

Meanwhile the 4th shunting delivery outlet 465 of setting on current divider 46.First driving motor 481 can also include：First Drive shaft 4811 and driving fixed seat 4812；Steering engine 47 can also include：Third steering engine 473, the third steering engine 473 include third Steering engine input port 4733, third rotor shaft 4731 and third fixed seat 4732；By by third steering engine input port 4733 with shunting 4th shunting delivery outlet 465 of device 46 connects, so as to provide electric energy for third steering engine 473.

It should be noted that for 331 part of rotor mechanism of adjustable angle, the rotor mechanism 331 of the adjustable angle can To include：Tailspin seat 3311, linkage portion 3312 and tail rotor 33123.Tailspin seat 3311 be fixed at the second caudal face 35 and/ Or the 4th caudal face 37 both sides on, and fixed seat 4812 is driven to be arranged on tailspin seat 3311 and/or the third ontology 32 On；Linkage portion 3312 includes：First cohesive end 33121 and the second cohesive end 33122, the first cohesive end 33121 and the first driving Axis 4811 connects；Second cohesive end 33122 is connect with third fixed seat 4732；Third rotor shaft 4731 and tail rotor 33123 Center is fixedly connected, and third rotor shaft 4731 and the rotational plane of tail rotor 33123 are perpendicular.Pass through the first cohesive end The driving force of first drive shaft 4811 is transferred to the second cohesive end 33122 by 33121, and third rotor shaft 4731 is made to drive tailspin The wing 33123 is moved along the first caudal face 34, the second caudal face 35, third side caudal face 36 or 37 direction of the 4th caudal face.

On the other hand, tailspin seat 3311 can also be opened including the first hinged seat, the first hollow portion, the first opening face, second Mouth face and the first mounting base；First hinged seat can be fixed at the first mounting base in the first hollow portion that (hollow portion can Be aircraft fuselage in), and the first opening face can be fixedly connected with the tail portion 33 of unmanned plane, and the first opening face and Second opening face can be two corresponding surfaces of the tailspin seat 3311 respectively；First driving of first driving motor 481 Fixed seat can be fixedly connected with first mounting base.Base assembly can include the second hinged seat, the second hollow portion, third Opening face and the 4th opening face；Third opening face can be with the second opening face flexible connection, i.e., third opening face can be with second Opening face is hinged, and the second hinged seat can be fixedly connected with the 4th opening face, and third opening face and the 4th opening face can To be two corresponding surfaces of the second base assembly respectively；Second driving fixed seat can be fixed on the tail portion 33.

Turning part may include housing, and housing may include third hollow portion, first side and second side；The first side It may include first end, second end and positioning area, first end can be hinged with the second hinged seat, and second hinged seat It can be between first end and the 4th opening face；It is hollow that the third fixed seat of third steering engine 473 can be arranged on third In portion, and third rotor shaft 4731 can also be located at outside the second side, and the third rotor shaft of third steering engine 473 4731 can also be fixedly connected with the center of tail rotor, and third rotor shaft 4731 can also be with the rotational plane phase of tail rotor It is mutually vertical.

Linkage portion 3312 may include the first cohesive end 33121, the second cohesive end 33122 and third cohesive end.First linking End 33121 can also be hinged with the second end；Second cohesive end 33122 can also be fixed with second drive shaft to be connected It connects；Third cohesive end can also be hinged with first hinged seat；And the second cohesive end 33122 can be located at described first Between cohesive end 33121 and the third cohesive end.

Driving section may include the first driving wheel and the second driving wheel, and the first driving wheel may also include first gear 50 and endoporus, endoporus The center of first gear 50 can be located at, and endoporus can be fixedly connected with the first drive shaft 4811.Second driving wheel can wrap Second gear 51 and supporter are included, supporter can include lateral surface and medial surface, and second gear 51 can be with the medial surface It is fixedly connected, and lateral surface can also be fixedly connected with the second hollow portion, and lateral surface can also be located at the second hollow portion It is interior, meanwhile, second gear 51 can be meshed with first gear 50；Lateral surface and medial surface can be two of the supporter Corresponding surface.

Specifically, tailspin seat 3311 is fixed to the second caudal face 35 and/or the 4th tail outside third fuselage 30 The the second caudal face 35 that tailspin seat 3311 can also be fixed in third fuselage 30 on the both sides of side 37 and/or On the both sides in four caudal faces 37.By driving the fixation of fixed seat 4812 and tailspin seat 3311, the first driving motor 481 is fixed On third fuselage 30；Directly the first driving motor 481 can also be fixed in third fuselage 30.

A kind of embodiment as the embodiment of the present invention.First driving motor 481 can also use straight line steering engine 47, connection Dynamic portion 3312 can also use upset connecting rod, and the first cohesive end 33121 and the second cohesive end 33122 of linkage portion 3312 can divide It is not the both ends of upset connecting rod.As shown in fig. 7, upset connecting rod is in " 7 " font, i.e., the first cohesive end 33121 is formed with second end Fixed angle, the numerical value of the angle can be 90 °.When the first driving motor 481 pushes the first cohesive end 33121 to move right When, it will drive the second cohesive end 33122 that will move down；When the first driving motor 481 pulls the first cohesive end 33121 to moving to left When dynamic, it will drive the second cohesive end 33122 that will move up.By the leftward or rightward mobile so as to lead of the first cohesive end 33121 Cause moving up or down for the second cohesive end 33122.

Also, tail rotor 33123 can use twayblade rotor, the third rotor of tail rotor 33123 and third steering engine 473 Axis 4731 is fixedly connected, and makes third rotor shaft 4731 that tail rotor 33123 be driven to rotate.When tail rotor 33123 rotates, third rotation Wing axis 4731 and the plane of the rotation are mutually perpendicular to.One tail rotor can be formed by tail rotor 33123 and third steering engine 473 33123 overturning components, the tail rotor 33123 overturning component can be included：Coniform shell.Third steering engine 473 can be with It is fixed in coniform shell, by the way that the third rotor shaft 4731 of third steering engine 473 is stretched out except coniform shell, from And tail rotor 33123 is made to be fixedly connected except coniform shell with third rotor shaft 4731.Since coniform shell can be set Sealing is set to, and then in the flight of rainwater day, damage of the rainwater to the electric elements inside unmanned plane can be prevented.It can also In coniform shell, connecting hole can be set on the one side of third fuselage 30, by by the second cohesive end 33122 with should Connecting hole is fixedly connected, so as to which the second cohesive end 33122 be made to be connect with third fixed seat 4732, if the second cohesive end 33122 It is mobile, also third steering engine 473 will be driven to move together.

Fig. 7 is referred to, second gear 51 can be set on the one side of third fuselage 30 in coniform shell, this Two gears 51 can be gear ring, and second gear 51 is made to be rotated centered on first gear 50.It can be in third fuselage 30 One servo motor of interior fixed setting, for first gear 50 is driven to rotate, since first gear 50 and second gear 51 rotate Connection, the rotation of first gear 50 will drive second gear 51 and then to rotate together.Or pass through 481 band of the first driving motor Dynamic first gear 50 rotates, and due to the connection that first gear 50 and second gear 51 rotate, the rotation of first gear 50 will drive Second gear 51 and then rotates together.Furthermore because second gear 51 by first gear 50 with rotating together, it will pass through The rotation of two gears 51 makes coniform shell or third steering engine 473 rotate together, so as to make tail rotor 33123 perpendicular far from first Axis 53 is moved close to the first vertical pivot 53.

In embodiment provided by the invention, since tail rotor 33123 moves up or down, tail rotor 33123 will be made It is moved relative to the first vertical pivot 53, i.e., tail rotor 33123 moves formed angular range relative to the first vertical pivot 53 to be 0°—90°.Since tail rotor 33123 is mobile to the left or to the right, tail rotor 33123 will be made to be moved relative to the first vertical pivot 53, i.e., It can be 0 ° -60 ° that tail rotor 33123 is moved to the left formed angular range relative to the first vertical pivot 53；Tail rotor 33123 It can be 0 ° -60 ° relative to the first vertical pivot 53 formed angular range that moves right.

Embodiment provided by the invention is described in detail in order to clearer, it is now upward to tail rotor 33123 respectively Or move down, tail rotor 33123 is mobile to the left or to the right to carry out following detailed description：

It is initially noted that：Tail rotor 33123, which moves up, to be：Tail rotor 33123 is along third caudal face Direction is moved, i.e., is moved along the direction of vertical stabilizer 2231, at this time far from the first horizontal axis 54；Tail rotor 33123 moves down Can be：Tail rotor 33123 is moved along 37 direction of the 4th caudal face, i.e., is moved away from the direction of vertical stabilizer 2231, at this time Close to the first horizontal axis 54；Tail rotor 33123, which is moved to the left, to be：Tail rotor 33123 is moved along 34 direction of the first caudal face, It such as Fig. 5, i.e., is moved along 2211 direction of the first postposition wing, at this time far from the first vertical pivot 53；Tail rotor 33123 moves right can To be：Tail rotor 33123 is moved along 35 direction of the second caudal face, such as Fig. 5, i.e., is moved along 2221 direction of the second postposition wing It is dynamic, at this time far from the first vertical pivot 53.

Tail rotor 33123 is moved up or down, below by way of two embodiments to tail rotor 33123 upwards or It moves down and is described in detail respectively：

The first embodiment.If the first cohesive end 33121 moves right, by cause the second cohesive end 33122 to Lower movement.Since the second cohesive end 33122 is connect with third fixed seat 4732, tail rotor 33123 and the with third steering engine 473 Three rotor shafts, 4731 fixed seat connects.Moving down for second cohesive end 33122 can drive tail rotor 33123 to move downwardly together It is dynamic, it is achieved thereby that unmanned plane, in flight, landing, tail rotor 33123 can move gradually downward, reach change tail rotor 33123 directions of motion, and then tail rotor 33123 is controlled thrust direction to be made gradually to move up the thrust direction of unmanned plane.

When tail rotor 33123 moves gradually downward, and is moved to the folder that tail rotor 33123 is moved relative to the first vertical pivot 53 When angle is 90 °.Tail rotor 33123 will upwards (such as Fig. 7) to the thrust direction of unmanned plane, and the rotation of tail rotor 33123 at this time will Lift is provided for unmanned plane, so as to increase the lift of unmanned plane.

Second of embodiment.If the first cohesive end 33121 is moved to the left, by cause the second cohesive end 33122 to Upper movement.Since the second cohesive end 33122 is connect with third fixed seat 4732, the third of tail rotor 33123 and third steering engine 473 4731 fixed seat of rotor shaft connects.Moving up for second cohesive end 33122 can drive tail rotor 33123 to move upwardly together, It is achieved thereby that unmanned plane, in flight, landing, tail rotor 33123 can be moved up gradually, reach change tail rotor 33123 directions of motion, and then tail rotor 33123 is controlled the direction of thrust to be made to move gradually downward the thrust direction of unmanned plane.

When tail rotor 33123 gradually moves up, and is moved to what tail rotor 33123 was moved relative to the first vertical pivot 53 When angle is 0 °.Tail rotor 33123 will be consistent with 11 direction of portion windward to the thrust direction of unmanned plane, and the thrust direction with First horizontal axis 54 parallel (such as Fig. 7), the thrust that the rotation of tail rotor 33123 at this time will provide advance for unmanned plane, so as to make nothing Man-machine thrust increase.

It is mobile to the left or to the right for tail rotor 33123, below by way of two embodiments to tail rotor 33123 to the left or It moves right and is described in detail respectively：

Fig. 5 and Fig. 7 are referred to, the first embodiment.If the rotation of first gear 50 drives second gear 51 clockwise Since second gear 51 is fixedly connected with third steering engine 473, drive tail rotor 33123 is moved right for rotation.It is achieved thereby that In flight, landing, tail rotor 33123 can gradually move right unmanned plane, reach 33123 side of moving of change tail rotor To, and then tail rotor 33123 is controlled the direction of thrust to be made gradually to move right the thrust direction of unmanned plane.

Fig. 7 is referred to, is gradually moved right in tail rotor 33123, and it is perpendicular relative to first to be moved to tail rotor 33123 When the angle that axis 53 moves is 60 °.Tail rotor 33123 to the thrust direction of unmanned plane will to the left, at this time tail rotor 33123 turn It is dynamic to provide thrust to the left for unmanned plane, change the thrust direction of unmanned plane, so as to change the stressing conditions of unmanned plane entirety.

Refer to Fig. 5, Fig. 7, second of embodiment.If the rotation of first gear 50 drives second gear 51 to turn counterclockwise It is dynamic, since second gear 51 is fixedly connected with third steering engine 473, drive tail rotor 33123 is moved to the left.It is achieved thereby that In unmanned plane during flying, landing, tail rotor 33123 can be gradually moved to the left, and reach 33123 direction of motion of change tail rotor, And then tail rotor 33123 is controlled the direction of thrust to be made gradually to move right the thrust direction of unmanned plane.

Fig. 7 is referred to, is gradually moved to the left in tail rotor 33123, and it is perpendicular relative to first to be moved to tail rotor 33123 When the angle that axis 53 moves is 0 °, tail rotor 33123 will be mutually perpendicular to the first horizontal axis 54.Tail rotor 33123 is to unmanned plane Thrust direction will be towards portion 11 windward, i.e., to the direction of advance of unmanned plane, the rotation of tail rotor 33123 at this time will be carried for unmanned plane For the thrust of advance, the thrust direction of unmanned plane is changed, so as to increase the thrust of unmanned plane.

Continuing with referring to Fig. 7, if tail rotor 33123 continues gradually to be moved to the left, and it is moved to 33123 phase of tail rotor When angle for the movement of the first vertical pivot 53 is 60 °.Tail rotor 33123 will to the right to the thrust direction of unmanned plane, tailspin at this time Thrust for unmanned plane to the right is changed the thrust direction of unmanned plane by the rotation of the wing 33123, so as to change unmanned plane it is whole by Power situation.

The present invention provides the embodiment of the rotor power device for the adjustable angle that should be applied to unmanned plane.It is provided in the present invention Embodiment in, power source 40 can include：Engine 41, generator 42, electric pressure converter 43, voltage-stablizer 44, accumulator 45, Current divider 46, steering engine 47 and driving motor 48.Power source 40 can be fixed on the first fuselage 10, the second fuselage 20 or third machine The outside of body 30；In-flight damage of the rainwater to power source 40 in order to prevent, power source 40 can also sealed sets or direct It is fixed on the inside of the first fuselage 10, the second fuselage 20 or third fuselage 30.The effect of power source 40 is mainly unmanned plane Flight, landing provide power.

In embodiment provided by the invention, exist to increase thrust or increase unmanned plane of the unmanned plane in the landing stage The thrust of mission phase, shortens the departure time of unmanned plane VTOL, and improves flight of the unmanned plane in flight course Rate.The quantity of power source 40 can be positive integer in unmanned plane, i.e., the quantity of power source 40 can be：1,2,3, 4.

Fig. 2 is referred to, when the quantity of power source 40 is 2, two power sources 40 can symmetrically be distributed in the first machine The left and right sides of body 10.Since unmanned plane is in landing, flight course, the fuselage of unmanned plane needs to bear multidirectional pressure, Such as：Gravity, wind direction resistance, stream pressure of unmanned plane itself etc..And the pressure that the fuselage of unmanned plane is born is limited. If two power sources 40 are all fixed on the left side either right side of the first fuselage 10 of the first fuselage 10, easily increase by first The pressure that 10 left side of fuselage either the first fuselage, 10 right side is carried, so as to influence the stationarity of complete machine flight.If moreover, The pressure that one fuselage, 10 left side either the first fuselage, 10 right side is carried is more than itself to bear the limit of pressure, will be occurred There is situation about being broken in first fuselage, 10 left side either the first fuselage, 10 right side.So in embodiment provided by the invention, Two power sources 40 are symmetrically distributed in the left and right sides of the first fuselage 10, the steady of unmanned plane itself flight can be improved Property, and it is more than itself institute that can also prevent by the pressure that 10 left side of the first fuselage either the first fuselage, 10 right side is carried The limit of pressure is born, and there is a situation where 10 left side of the first fuselage either the first fuselage, 10 right side is broken.

Certainly, it is obvious to one skilled in the art that two power sources 40 can also symmetrically be distributed in the first machine The left and right sides of body 10, the second fuselage 20 and third fuselage 30, and first can be symmetrically distributed in for two power sources 40 The left and right sides of fuselage 10 is only a kind of embodiment provided in an embodiment of the present invention, is not the limitation to the present invention.It is practical In operating process, according to actual demand, the quantity for either reducing power source 40 can be increased or change power source 40 it is located at the The specific location of one fuselage 10, the second fuselage 20 or third fuselage 30, these may also apply to the present invention.

Fig. 9 is referred to, further, engine 41 can be two stroke engine 41, and generator 42 connects with engine 41 It connects；Electric pressure converter 43 can be AC/DC converters, and electric pressure converter 43 is connect with generator 42；Voltage-stablizer 44 includes：First Voltage stabilizing input port 441, the second voltage stabilizing input port 442 and the first voltage stabilizing delivery outlet 443, the first voltage stabilizing input port 441 turn with voltage Parallel operation 43 connects, and makes electric pressure converter 43 between the first voltage stabilizing input port 441 and generator 42；Accumulator 45 and Two voltage stabilizing input ports 442 connect；Current divider 46 can also include：First shunting input port 461, first shunts delivery outlet 462, the Two shunting delivery outlets 463, third shunting delivery outlet 464 and the 7th shunt delivery outlet 468, the first shunting input port 461 and first Voltage stabilizing delivery outlet 443 connects；Steering engine 47 includes at least：First steering engine 471, the second steering engine 472 and third steering engine 473, the first rudder Machine 471 includes at least：First steering engine input port 4711 and the first rotor shaft 4712, the first steering engine input port 4711 and the first shunting Delivery outlet 462 connects, so as to provide energy, and the first rotor shaft 4712 and first of the first steering engine 471 for the first steering engine 471 Rotor 1211 connects, and is driven by the rotation of the first rotor shaft 4712, carrys out the rotation of the first rotor 1211；Second steering engine 472 wraps It includes：Second steering engine input port 4721 and the second rotor shaft 4722；Second steering engine input port 4721 connects with the second shunting delivery outlet 463 It connects, so as to provide energy, and the second rotor shaft 4722 of the second steering engine 472 connects with the second rotor 1221 for the second steering engine 472 It connects, by the rotation of the second rotor shaft 4722, to drive the rotation of the second rotor 1221；Third steering engine 473 further includes：Third rudder Machine input port 4733, third steering engine input port 4733 is connect with the 7th shunting delivery outlet 468, so as to be provided for third steering engine 473 Energy.Driving motor 48 includes at least：First driving motor 481, the first driving motor 481 connect with third shunting delivery outlet 464 It connects, the rotor mechanism 331 of adjustable angle is connect with the first driving motor 481, and makes the first driving motor 481 positioned at third point It flows between delivery outlet 464 and the rotor mechanism 331 of adjustable angle.

Specifically, engine 41 is that other forms can be converted into mechanical energy；Generator 42 is to produce engine 41 Raw mechanical energy is converted into electric energy；Voltage-stablizer 44 is to maintain the electric energy as caused by generator 42 and is exported after voltage-stablizer 44 surely Fixed voltage, and accumulator 45 is also connect with voltage-stablizer 44.It is with the effect that voltage-stablizer 44 is connect for accumulator 45：Electric power storage Pond 45 can be that voltage-stablizer 44 provides electric energy, and voltage-stablizer 44 makes to be exported after voltage-stablizer 44 by the electric energy that accumulator 45 generates steady Fixed voltage；And if engine 41 or generator 42 break down, and electric energy can not be provided for unmanned plane, and it at this time can be automatic It is switched to accumulator 45 to power, electric energy is provided for unmanned plane by accumulator 45；If engine 41 or generator 42 can normal works Make, electric energy can be provided for unmanned plane, then accumulator 45 stops providing electric energy for unmanned plane；Certainly, if electricity occurs in accumulator 45 Power is insufficient, can not provide electric energy for unmanned plane, can be by engine 41 by the normal work of engine 41 or generator 42 Or generator 42 provides electric energy for accumulator 45, so as to supplement the electric energy of accumulator 45.

If only engine 41 and generator 42 is set to provide electric energy for voltage-stablizer 44, when engine 41 or generator 42 occur Failure, when can not provide electric energy for unmanned plane, unmanned plane in landing or in-flight will be faced with no power resources, and send out The danger of the raw damage unmanned plane that falls；Or only setting accumulator 45 provides electric energy for voltage-stablizer 44, when electricity occurs in accumulator 45 The failures such as energy deficiency, when can not provide electric energy for unmanned plane, unmanned plane in landing or in-flight will be faced with no power Source, and the danger for the damage unmanned plane that falls.So electric energy is provided for voltage-stablizer 44 by engine 41 and generator 42, with And accumulator 45 provides electric energy, and it is voltage-stablizer 44 that this accumulator 45 can mutually switch with generator 42 for voltage-stablizer 44 Electric energy is provided, can overcome unmanned plane awing since generator 42 breaks down or accumulator 45 breaks down, it can not Electric energy is provided for unmanned plane, makes unmanned plane that will be faced with no power resources, and the technological deficiency for the damage unmanned plane that falls, Reach the technique effect of the safety, the in-flight stability of power that improve unmanned plane.

Meanwhile the burning voltage that electric pressure converter 43 is exported will enter current divider 46, each shunting of current divider 46 is defeated Outlet is that electric energy is assigned to each steering engine 47 or driving motor 48, such as：First shunting 462 and first steering engine of delivery outlet 471 input ports connect, so as to provide energy for the first steering engine 471；Second 463 and second steering engine input port 4721 of shunting delivery outlet Connection, so as to provide energy for the second steering engine 472；Third shunting delivery outlet 464 connect with the first driving motor 481, so as to for First driving motor 481 provides energy.

In embodiment provided by the invention, engine 41 can be two-stroke aviation piston engine 41, i.e., piston from The engine 41 of top to bottm, from top to bottom two strokes, since two stroke engine 41 has simple in structure, lighter in weight, fortune The advantages of dynamic component is few easy to maintain, and power per liter density is big, so as to be suitble to the low latitude of unmanned plane, high speed (reality provided by the invention The unmanned plane F-Zero for applying example can be 60m/s) flight.Electric pressure converter 43 can be AC/DC converters, and AC/DC turns Parallel operation is the equipment that alternating current is become to direct current, and AC/DC converters have the AC-DC conversion of better stability, can be nothing Man-machine offer stable DC, from the stability for improving unmanned mechanomotive force.

Certainly, it is obvious to one skilled in the art that engine 41 can also be started using four stroke aviation pistons Machine 41.In actual mechanical process, the shunting delivery outlet of current divider 46 can also be set according to actual demand, such as：If nothing Video camera, automatic flight control system, current divider 46 or video camera, automatic flight control system point are provided on man-machine With electric energy, the mode (mode including being above steering engine 47, the distribution electric energy of driving motor 48) of the distribution electric energy can be passed through Conducting wire connects or using wireless power transmission, these may also apply to the present invention.

Fig. 8 is referred to, Fig. 8 is 41 connection relationship diagram of generator 42 and engine provided in an embodiment of the present invention.Institute Rotor 61 and supply port can be included by stating generator 42, the rotor 61 of the generator 42 can directly with the engine 41 Output shaft 60 be fixedly connected, the end face that the electric machine casing 62 of generator 42 can be directly with 41 housing of engine is fixedly connected. And the electric pressure converter can with the supply port of the generator 42 (supply port be generator 42 electric energy output End) connection；Wherein, the rotor 61 can be between the supply port and the output shaft 60.When engine 41 rotates, Mechanical energy caused by engine 41 can be directly passed to the rotor 61 of generator 42 by the output shaft 60 of engine 41, Then the rotor 61 of generator 42 is driven to rotate together, the mechanical energy that engine 41 generates is converted by electricity by generator 42 Can, the electric energy of the conversion exports outward from the supply port of generator 42.The electric energy that the supply port of generator 42 exports outward Power unit can be delivered to, which has the function of distributing the power to different electrical appliances.The power distributes The electric energy that the supply port of generator 42 exports outward can be divided into two parts (abbreviation E1 and E2), the electric energy of E1 parts by unit Battery (can be accumulator) can be delivered to, which can provide electric energy required when carrying out VTOL for aircraft；E2 Partial electric energy can be conveyed to the uses such as flight control system, steering engine, motor, the load of aircraft respectively.

Since the mechanical energy that engine 41 generates can be directly passed to the rotor 61 of generator 42 by output shaft 60, and And can the mechanical energy that engine 41 generates be converted by electric energy by generator 42, then electric energy is conveyed to by conducting wire winged Electrical appliance in machine.So as to which the energy that engine 41 generates is converted into conveying by conducting wire by generator 42, to avoid Loss in energy process produced by engine 41 is conveyed.It should be noted that：Such as above-mentioned first fuselage 10, second Fuselage 20 and third fuselage 30, the integral body that embodiment provided by the invention provides unmanned plane be by：First fuselage 10, Two fuselages 20 and third fuselage 30 and form.The fuselage can also include the circuit control system of following unmanned plane, by nobody The circuit control system of machine carries out the unmanned plane whole control.

Fig. 9 is referred to, further, in embodiment provided by the invention, unmanned plane circuit control system can be down to Include less：Ground remote control device 56, engine 41, generator 42, electric pressure converter 43, voltage-stablizer 44, stores flight control system 55 Battery 45, current divider 46, the first steering engine 471, the second steering engine 472, third steering engine 473, the driving of the first driving motor 481, second Motor 482, third driving motor 483, the 4th driving motor 484.Wherein, for engine 41, generator 42, electric pressure converter 43rd, voltage-stablizer 44, accumulator 45, current divider 46, the first steering engine 471, the second steering engine 472, the driving electricity of third steering engine 473, first Machine 481, the second driving motor 482,483 and the 4th driving motor 484 of third driving motor, as described above in Example.Flight The ground remote control device 56 on control system 55 and ground carries out signal transmission, and then by being from ground remote control device 56 to flight control System 55 sends control instruction, and passes through the first steering engine 471, the second steering engine 472, third that flight control system 55 controls unmanned plane Steering engine 473, the first driving motor 481, the second driving motor 482,483 and the 4th driving motor 484 of third driving motor work Make state, and then realize and the state of unmanned plane landing, flight is controlled.

It is noted that flight control system 55 mainly passes through turn of the first rotor 1211 in the first steering engine 471 of control In dynamic speed, the second steering engine 472 in the velocity of rotation of second rotor 1221, third steering engine 473 velocity of rotation of third rotor and The first driving motor 481 is controlled to pull linkage portion 3312, and then tail rotor 33123 is controlled to be moved up and down relative to the first vertical pivot 53 The angle change and the first driving motor 481 of control of formed angle drive second gear 51 to rotate, and then control tail rotor 33123 move left and right the angle change of formed angle relative to the first vertical pivot 53.Reach and controlled by flight control system 55 The motion state to unmanned plane landing, flight is made, and controls the movement speed of unmanned plane landing, flight.

It should be noted last that more than specific embodiment is merely illustrative of the technical solution of the present invention and unrestricted, Although the present invention is described in detail with reference to example, it will be understood by those of ordinary skill in the art that, it can be to the present invention Technical solution be modified or replaced equivalently, without departing from the spirit and scope of technical solution of the present invention, should all cover In scope of the presently claimed invention.

Claims

1. the power wingtip device of the adjustable angle applied to unmanned plane, which is characterized in that the angle applied to unmanned plane Adjustable rotor structure includes：

Engine；

Generator, the generator are connect with the engine；

Electric pressure converter, the electric pressure converter are connect with the generator；

Voltage-stablizer, the voltage-stablizer include the first voltage stabilizing input port, the second voltage stabilizing input port and the first voltage stabilizing delivery outlet；Described One voltage stabilizing input port is connect with the electric pressure converter, and the electric pressure converter is located at the first voltage stabilizing input port and described Between generator；

Accumulator, the accumulator are connect with the second voltage stabilizing input port；

Current divider, the current divider include at least：First shunting input port, first shunting delivery outlet, second shunting delivery outlet and Third shunts delivery outlet；The first shunting input port is connect with the first voltage stabilizing delivery outlet；

Steering engine, the steering engine include at least：First steering engine, the second steering engine and third steering engine；Wherein, first steering engine at least wraps It includes：First steering engine input port and the first rotor shaft, the first steering engine input port are connect with the described first shunting delivery outlet；It is described First rotor shaft is connect with the first rotor；Second steering engine includes at least：Second steering engine input port and the second rotor shaft, it is described Second steering engine input port is connect with the described second shunting delivery outlet；Second rotor shaft is connect with the second rotor；The third Steering engine includes third rotor shaft and third fixed seat；

Driving motor, the driving motor include at least：First driving motor；First driving motor is shunted with the third Delivery outlet connects；Wherein, first driving motor includes the first drive shaft and driving fixed seat；The rotor mechanism of adjustable angle It is connect with first driving motor, and first driving motor is located at third shunting delivery outlet and the adjustable angle Rotor mechanism between；

Tailspin seat, the tailspin seat are fixed on the second caudal face of the unmanned plane and/or the both sides in the 4th caudal face, And the driving fixed seat is arranged on the tailspin seat and/or third ontology；

Linkage portion, the linkage portion include the first cohesive end, the second cohesive end and tail rotor；First cohesive end and described One driving axis connection, second cohesive end connects with the third fixed seat, the third rotor shaft and the tail rotor Center is fixedly connected, and the rotational plane of the third rotor shaft and the tail rotor is perpendicular；

Wherein, the driving force of first drive shaft is transferred to by second cohesive end, and institute by first cohesive end It states third rotor shaft and drives the tail rotor along the first caudal face, the second caudal face, third side caudal face or described the Four tail side surface directions move；

First rotor, first rotor include：

First rotating vane, first rotating vane are fixedly connected with first rotor shaft；

First clump weight, first clump weight are fixedly connected with first rotor shaft, and first rotating vane and institute It is symmetrical relative to first rotor shaft to state the first clump weight；

Second rotor, second rotor include：

Second rotating vane, second rotating vane are fixedly connected with second rotor shaft；

Second clump weight, second clump weight are fixedly connected with second rotor shaft, and second rotating vane and institute It is symmetrical relative to second rotor shaft to state the second clump weight；

First winglet, first winglet and the first postposition wing intersect；And first winglet includes the One wing tip fastening end and the first wing tip openend；And the first wing tip fastening end is fixedly connected with the first rear open end, it is described First wing tip openend deviates from first rear open end, and first winglet is formed with the first wing tip fastening end Both ends；And the first wing tip openend and vertical stabilizer are located at the both sides of the first postposition wing；

Second winglet, second winglet and the second postposition wing intersect；And second winglet includes the Two wing tip fastening ends and the second wing tip openend；And the second wing tip fastening end is fixedly connected with second rear open end, The second wing tip openend deviates from second rear open end, and it is small to form second wing tip with the second wing tip fastening end The both ends of the wing；And the second wing tip openend and vertical stabilizer are located at the both sides of the second postposition wing.

2. the power wingtip device applied to the adjustable angle of unmanned plane as described in claim 1, which is characterized in that the driving Motor further includes：

Second driving motor, second driving motor are connect with the first aileron, and second driving motor is fixed at After first between fastening end and the first rear open end.

3. the power wingtip device applied to the adjustable angle of unmanned plane as claimed in claim 2, which is characterized in that the driving Motor further includes：

Third driving motor, the third driving motor are connect with the second aileron, and the third driving motor is fixed at After second between fastening end and the second rear open end.

4. the power wingtip device applied to the adjustable angle of unmanned plane as claimed in claim 3, which is characterized in that the driving Motor further includes：

4th driving motor, the 4th driving motor are connect with third aileron, and the 4th driving motor is fixed on vertically On wing.

5. the power wingtip device applied to the adjustable angle of unmanned plane as claimed in claim 4, which is characterized in that the shunting Device further includes：

4th shunting delivery outlet, the 4th shunting delivery outlet are connect with second driving motor.

6. the power wingtip device applied to the adjustable angle of unmanned plane as claimed in claim 5, which is characterized in that the shunting Device further includes：

5th shunting delivery outlet, the 5th shunting delivery outlet are connect with the third driving motor.

7. the power wingtip device applied to the adjustable angle of unmanned plane as claimed in claim 6, which is characterized in that the shunting Device further includes：

6th shunting delivery outlet, the 6th shunting delivery outlet are connect with the 4th driving motor；

7th shunting delivery outlet；

Third steering engine input port, the third steering engine input port are connect with the described 7th shunting delivery outlet.

8. the power wingtip device applied to the adjustable angle of unmanned plane as claimed in claim 7, it is characterised in that：

First rotating vane is single blade blade, and second rotating vane is single blade blade.

9. the power wingtip device applied to the adjustable angle of unmanned plane as claimed in claim 8, it is characterised in that：

The engine is two stroke engine；

The electric pressure converter is AC/DC converters.

10. the power wingtip device applied to the adjustable angle of unmanned plane as claimed in claim 9, which is characterized in that the hair Motor connect with the engine including：

The rotor of the generator is fixedly connected with the output shaft of the engine；

Wherein, the electric pressure converter is connected with the supply port of the generator, and the rotor is located at the supply port Between the output shaft.