CN108216612A

CN108216612A - Unmanned plane

Info

Publication number: CN108216612A
Application number: CN201711241638.4A
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 invention discloses unmanned planes, belong to unmanned air vehicle technique field, including：First fuselage, the second fuselage, third fuselage and power source.First fuselage includes：Portion, the first noumenon and first connecting portion windward are provided with the first forewing and the second forewing on the first noumenon；Second fuselage includes：Second connecting portion, the second ontology and third connecting portion, the second ontology include：First side, second side and third side are provided with the first postposition wing in first side, the second postposition wing are provided in second side, third is provided with vertical stabilizer on side；Third fuselage includes：4th connecting portion, third ontology and tail portion are provided with the rotor mechanism of an adjustable angle on tail portion；Power source includes：Engine, generator, electric pressure converter, voltage-stablizer, accumulator, current divider, steering engine and driving motor.It is fast with flying speed invention achieves the landing for making unmanned plane and flight operation simplicity, long-endurance technique effect.

Description

Unmanned plane

Technical field

The invention belongs to unmanned air vehicle technique fields, more particularly to unmanned plane.

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.

For unmanned plane, unmanned aerial vehicle body of the prior art is formed using integrally formed structure fabrication.Usually Be the operating personnel from having received professional training and with take off in the case of parasite power, the lift of flight is to pass through wing It is provided with the propeller positioned at head.

But in the prior art, for unmanned plane in landing and flight, operation difficulty is high；Unmanned plane awing, flies Speed is slow, the time of flight is short.

Invention content

The technical problems to be solved by the invention be unmanned plane in landing and flight, operation difficulty is high；Unmanned plane is flying In row, the speed of flight is slow, the time of flight is short.

In order to solve the above technical problems, the present invention provides unmanned plane, including：First fuselage, first fuselage include： Portion windward, the tapered structure in portion windward；The first noumenon, the first noumenon are fixedly connected, and described with the portion windward The diameter of section in portion is sequentially increased on the direction towards the first noumenon windward；Before first being provided on the first noumenon Put wing and the second forewing, and the center of first forewing and second forewing along the first noumenon Vertical pivot is symmetrically distributed in the both sides of the first noumenon, is provided with the first rotor on first forewing, and described second The second rotor is provided on forewing；First connecting portion, the first connecting portion are fixedly connected with the first noumenon, and institute The diameter of section for stating the first noumenon is sequentially reduced on the direction towards the first connecting portion；Wherein, the first position Between the portion windward and the first connecting portion, and the portion windward, the first noumenon and the first connecting portion one It is body formed to form first fuselage；Second fuselage, second fuselage include：Second connecting portion, the second connecting portion and The first connecting portion is detachably connected；Second ontology, second ontology are fixedly connected with the second connecting portion；It is and described Second ontology includes first side, second side and third side, and the first side and the second side are along described the The center vertical pivot of two ontologies is symmetrical, and the third side is between the first side and the second side；And institute It states and the first postposition wing is provided in first side, the second postposition wing, the third side are provided in the second side On be provided with vertical stabilizer；Third connecting portion, the third connecting portion are fixedly connected with second ontology；Wherein, described Two ontologies between the second connecting portion and the third connecting portion, and the second connecting portion, second ontology and The third connecting portion, which is integrally formed, forms second fuselage；Third fuselage, the third fuselage include：4th connecting portion, 4th connecting portion and the third connecting portion are detachably connected；Third ontology, the third ontology and the 4th connection Portion is fixedly connected；Tail portion, the tail portion are fixedly connected with the third ontology, and the diameter of section of the tail portion is described in It is sequentially increased on the direction of third ontology；And the rotor mechanism of an adjustable angle is provided on the tail portion；Wherein, the third Ontology is between the 4th connecting portion and the tail portion, and the 4th connecting portion, the third ontology and the tail portion It is integrally formed and forms the third fuselage；Power source, the power source include at least：Engine；Generator, the generator with The engine connection；Electric pressure converter, the electric pressure converter are connect with the generator；Voltage-stablizer, the voltage-stablizer packet Include the 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 voltage Converter connects, and the electric pressure converter is between the first voltage stabilizing input port and the generator；Accumulator, it is described Accumulator is connect with the second voltage stabilizing input port；Current divider, the current divider include at least：First shunting input port, first Shunt delivery outlet, the second shunting delivery outlet and third shunting delivery outlet；The first shunting input port and first voltage stabilizing are defeated Outlet connection；Steering engine, the steering engine include at least：First steering engine, first steering engine include at least：First steering engine input port and First rotor shaft, the first steering engine input port are connect with the described first shunting delivery outlet；First rotor shaft and described the One rotor connects；Second steering engine, second steering engine include at least：Second steering engine input port and the second rotor shaft, described second Steering engine input port is connect with the described second shunting delivery outlet；Second rotor shaft is connect with first rotor；Driving motor, The driving motor includes at least：First driving motor；First driving motor is connect with third shunting delivery outlet, institute The rotor mechanism for stating adjustable angle is connect with first driving motor, and first driving motor is located at third shunting Between the rotor mechanism of delivery outlet and the adjustable angle.

Further, first forewing includes：First preceding fastening end and the first forward open end；Described second is preposition Wing includes：Second preceding fastening end and the second forward open end；Wherein, the described first preceding fastening end and the second preceding fastening end edge The center vertical pivot of the first noumenon is symmetrically distributed in the both sides of the first noumenon；And the first preceding fastening end and described First forward open end is the both ends of first forewing, and the second preceding fastening end and second forward open end are described The both ends of second forewing；First forward open end is provided with one first storage region, the second forward open end setting There is the second storage region；First steering engine further includes：For fixing the first fixed seat of the first steering engine, first fixed seat It is fixed in first storage region；Second steering engine further includes：It is described for fixing the second fixed seat of the second steering engine Second fixed seat is fixed in second storage region；First rotor includes：First rotating vane, first rotation Blade is fixedly connected with first rotor shaft；First clump weight, first clump weight is fixed with first rotor shaft to be connected It connects, and first rotating vane and first clump weight are symmetrical relative to first rotor shaft, first rotation Wing axis and the rotational plane of first rotating vane are perpendicular；Second rotor includes：Second rotating vane, described second Rotating vane is fixedly connected with second rotor shaft；Second clump weight, second clump weight are consolidated with second rotor shaft Fixed connection, and second rotating vane and second clump weight are symmetrical relative to second rotor shaft, described the Two rotor shafts and the rotational plane of second rotating vane are perpendicular.

Further, first forewing is in the described first preceding fastening end, along to the first forward open end direction On width be sequentially reduced；And/or second forewing is in the described second preceding fastening end, along to second open front Width on extreme direction is sequentially reduced.

Further, the first postposition wing includes：Fastening end and the first rear open end after first；Described second is preposition Wing includes：Fastening end and the second rear open end after second；Wherein, behind fastening end and described second fastening end edge after described first The center vertical pivot of second ontology is symmetrically fixed at the both sides of second ontology；And after described first fastening end and First rear open end is the both ends of the first postposition wing, and fastening end and second rear open end are after described second The both ends of the second postposition wing；Second fuselage further includes：First winglet, first winglet with it is described The angle of first postposition wing is 60 ° -90 °；And first winglet includes：First wing tip fastening end and the first wing tip are opened Mouth end；And the first wing tip fastening end is fixedly connected with first rear open end, the first wing tip openend deviates from institute The first rear open end is stated, the both ends of first winglet are formed with the first wing tip fastening end；And first wing tip Openend and the vertical stabilizer are located at the both sides of the first postposition wing；Second winglet, second winglet Angle with the second postposition wing is 60 ° -90 °；And second winglet includes：Second wing tip fastening end and second Wing tip openend；And the second wing tip fastening end is fixedly connected with second rear open end, the second wing tip openend Away from second rear open end, the both ends of second winglet are formed with the second wing tip fastening end；And described Two wing tip openends and the vertical stabilizer are located at the both sides of the second postposition wing；Wherein, the first wing tip openend It is symmetrically distributed along the center vertical pivot of second ontology with the second wing tip openend.

Further, second fuselage further includes：First aileron, the first aileron rotation are arranged on described first In rear open end, and first aileron is rotated in first rear open end relative to first rear open end； And/or second aileron, the second aileron rotation are arranged in second rear open end, and second aileron is in institute It states and is rotated in the second rear open end relative to second rear open end；And/or third aileron, the third aileron turn Dynamic is arranged on the vertical stabilizer, and the third aileron carries out on the vertical stabilizer relative to the vertical stabilizer Rotation；Wherein, the first postposition wing fastening end after described first, along the width on the first rear open end direction It is sequentially reduced；And/or the second postposition wing fastening end after described second, along on the second rear open end direction Width be sequentially reduced；First aileron, second aileron and the third aileron are rectangle.

Further, the unmanned plane includes：Second driving motor, second driving motor connect with first aileron Connect, and second driving motor be fixed at described first after between fastening end and the first rear open end；Third driving electricity After machine, the third driving motor are connect with second aileron, and the third driving motor is fixed at described second Between fastening end and the second rear open end；4th driving motor, the 4th driving motor is connect with the third aileron, and institute The 4th driving motor is stated to be fixed on the vertical stabilizer.

Further, the current divider further includes：4th shunting delivery outlet, the 4th shunting delivery outlet and described second Driving motor connects；5th shunting delivery outlet, the 5th shunting delivery outlet are connect with the third driving motor；6th shunting Delivery outlet, the 6th shunting delivery outlet are connect with the 4th driving motor.

Further, the third fuselage further includes：First caudal face, the second caudal face, third side caudal face and the 4th Caudal face, and the first caudal face and the third side are symmetrically dispersed in the both sides in the second caudal face, and described One caudal face and the third side are symmetrically dispersed in the both sides in the 4th caudal face, with by the first caudal face, second Caudal face, third side caudal face and the 4th caudal face are surrounded to form the third fuselage；First driving motor further includes：The One drive shaft and driving fixed seat；The steering engine further includes：Third steering engine；Wherein, the third steering engine includes at least：Third is revolved Wing axis and third fixed seat；The rotor mechanism of the adjustable angle includes：Tailspin seat；Wherein, the tailspin seat is fixed at On the both sides in the second caudal face and/or 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：First cohesive end, the second cohesive end and tail rotor；Wherein, institute The first cohesive end and the described first driving axis connection are stated, second cohesive end is connect with the third fixed seat, the third Rotor shaft is fixedly connected with the center of the tail rotor, and the third rotor shaft and the rotational plane of the tail rotor mutually hang down Directly；Wherein, the driving force of first drive shaft is transferred to, and described by second cohesive end by first cohesive end Third rotor shaft drive the tail rotor along the first caudal face, the second caudal face, the third side caudal face or The 4th tail side surface direction movement.

Further, the current divider further includes：7th shunting delivery outlet；The third steering engine further includes：Third steering engine Input port；Wherein, the third steering engine input port is connect with the described 7th shunting delivery outlet；The engine is that two-stroke is started Machine；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 unmanned plane, and the first front end processor is set respectively in the first noumenon both sides of the first fuselage The first rotor and the second rotor are set respectively on the wing and the second forewing, the first forewing and the second forewing, passed through First steering engine of power source provides power to the first rotor, and the second steering engine of power source provides power to the second rotor；Second It is set gradually on second ontology of fuselage along first side, second side and third side：First postposition wing, the second postposition Wing and vertical stabilizer；The rotor mechanism of one adjustable angle on the tail portion of third fuselage is set, is driven by the first of power source Dynamic motor provides dynamic power to the rotor mechanism of adjustable angle；And the second connecting portion of the second fuselage and the first of the first fuselage Connecting portion is detachably connected, and the third connecting portion of the 4th connecting portion and the second fuselage of third fuselage is detachably connected, by first Fuselage, the second fuselage and third fuselage form the integral body of unmanned plane so that, can when fuselage local damage occur can not repair With local replacing component.The rotor mechanism of first rotor, the second rotor and adjustable angle make unmanned plane can with VTOL, so as to The landing of unmanned plane is made not limited by place size；The rotor mechanism of adjustable angle can also provide thrust for the flight of unmanned plane, So as to make the flying speed of unmanned plane fast.Landing and the flight operation for having reached unmanned plane are easy, have flying speed fast, continue a journey The technique effect of time length.

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

Before the embodiment of the present invention is introduced, the overall condition of unmanned plane provided by the invention is summarized below first It is bright：The present invention is by being divided into the fuselage of unmanned plane including at least three sections, i.e. the first fuselage 10, the second fuselage 20 and third fuselage 30, and be attached between three sections by the connection mode of detachable connection, it is dismountable to be formed an internal structure with this Unmanned plane, so that when local damage occurs in the fuselage of unmanned plane, corresponding can remove and the position damaged progress occur Repair has simple, convenient technique effect.And when the part of fuselage can not be repaired when damaging, also may be used With the position that corresponding dismounting can not repair, i.e., the position that can not be repaired is substituted, so as to overcome the prior art It is middle because fuselage is using integrated global design so that when fuselage local damage occur can not repair, it has to replace unmanned plane The technological deficiency of entire fuselage, reaches the technique effect for significantly reducing 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 implement to the present invention The unmanned plane that example provides is described in detail, and does description below to technical term involved in the embodiment of the present invention first and says It is bright：

Detachable connection can be：It is bolted or is bonded；Being fixedly connected to be：Welding is integrally formed； Ground can be：The ground or the face with this plane parallel that unmanned plane is parked；First level face can be：With level The parallel face in ground, and the center vertical pivot 123 of the first noumenon is located in the plane；Minimum flying speed can be：Make nothing Man-machine holding flight, and minimum flying speed when not falling.Such as：In the present embodiment, the minimum flight speed of unmanned plane Degree can be 20m/s；Takeoff phase can be：Unmanned plane reaches the process of aerial vertical ascent from ground；Taking off, it is winged to flatten Stage can be：After unmanned plane reaches in the air, the process of horizontal flight is carried out；The turning stage can be：Unmanned plane flies from level Row state, the process turned such as are turned left, turn right etc.；Landing phases can be：Unmanned plane is from airborne to ground Process.

For 10 part of the first fuselage：Fig. 1-Fig. 6 is referred to, the first fuselage 10 includes：Portion 11, first windward Body 12 and first connecting portion 13, the first noumenon 12 are located at windward between portion 11 and first connecting portion 13, and portion 11, first windward Ontology 12 and first connecting portion 13, which are integrally formed, forms the first fuselage 10.In the first fuselage 10, by that will set in portion 11 windward Into cone structure, the diameter of section in portion 11 windward is sequentially increased, and make first on the direction towards the first noumenon 12 The diameter of section of body 12 is sequentially reduced on the direction towards first connecting portion 13, is allowed in this way in unmanned plane during flying, the The global shape design of one fuselage 10 in embodiments of the present invention advantageously reduces the resistance of air-flow.In addition, in the first noumenon 12 On be additionally provided with the first forewing 121 and the second forewing 122.Wherein, the first forewing 121 includes：It is tight before first 1212 and first forward open end 1213 of fixed end.Second forewing 122 includes：Second preceding 1222 and second forward open end of fastening end 1223.And first the center vertical pivot of preceding fastening end 1212 and second preceding fastening end 1222 along the first noumenon 12 be symmetrically distributed in The both sides of one ontology 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.

Further, the first rotor 1211 is provided on the first forewing 121 and for driving the first rotor 1211 the first steering engines 471 rotated are provided with the second rotor 1221 on the second forewing 122 and for driving the The second steering engine 472 that two rotors 1221 are rotated.And in the first forward open end 1213 of the first forewing 121, also One first storage region 12131 is set；One second storage is also set up in the second forward open end 1223 of the second forewing 122 Region 12231.

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 Width on first forward open end, 1213 direction is sequentially reduced so that the first forewing 121 can be trapezoidal, due to trapezoidal The wing is 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 preferably Lift.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-Fig. 6 is referred to, the second fuselage 20 includes second connecting portion 21, second Ontology 22 and third connecting portion 23；Wherein, the second ontology 22 is between second connecting portion 21 and third connecting portion 23, and second Connecting portion 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 Socket part 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 solid 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 includes 22111 and first rear open end 22112 of fastening end after first；Second forewing 122 includes：22211 He of fastening end after second Second rear open end 22212.Wherein, fastening end 22211 is erected along the center of the second ontology behind fastening end 22111 and second after first Axis 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：First wing tip fastening end 241 and the first wing tip openend 242；And the first wing tip fastens End 241 is fixedly connected with the first rear open end 22112, and the first wing tip openend 242 is away from the first rear open end 22112, with the One 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 In the both sides of the first postposition wing 2211；For 25 part of the second winglet.Second winglet 25 and the second postposition wing 2221 angle 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 fastening end 251 is fixedly connected with the second rear open end 22212, after the second wing tip openend 252 deviates from second Openend 22212 forms the both ends of the second winglet 25 with the second wing tip fastening end 251；And the second wing tip openend 252 It is located at the both sides of the second postposition wing 2221 with vertical stabilizer 2231.

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.

Simultaneously as the first winglet 24 and the second winglet 25 are all mutually perpendicular to first level face, so the One winglet 24 and the second winglet 25 and ground interplanar distance are nearest, make manufacture the first winglet 24 and the second winglet Material needed for 25 is also less, so as to mitigate 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 in the first rear open end 22112, and the first aileron 26 is in the first after-opening It is rotated on end 22112 relative to the first rear open end 22112；And/or second aileron 27 rotate be arranged on second after open On mouthful end 22212, and the second aileron 27 in the second rear open end 22212 relative to 22212 turns of the second rear open end It is dynamic；And/or third aileron 28 rotate be arranged on vertical stabilizer 2231, and the phase on vertical stabilizer 2231 of third aileron 28 Vertical stabilizer 2231 is rotated；Wherein, the first fastening end 22111 after first of postposition wing 2211, along to first Width on 22112 direction of rear open end is sequentially reduced；And/or second fastening end 22211 after second of postposition wing 2221, edge The width on 22212 direction of the second rear open end is sequentially reduced.

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 the design gravity of unmanned plane is located at the first forewing 121 and second First lift equalization point and first postposition wing 2211 and second postposition wing 2221 of the forewing 122 on unmanned plane Between the second lift equalization point on unmanned plane；And the design gravity of unmanned plane is put down in the first lift equalization point and the second lift At the 3/4 of point spacing, and the design gravity of unmanned plane is close to the second lift equalization point.Specifically, the first forewing 121 It is the first lift equalization point (abbreviation A points) with lift equalization point of second forewing 122 on unmanned plane, the first postposition wing 2211 and second lift equalization point of the postposition wing 2221 on unmanned plane be the second lift equalization point (abbreviation B points)；A points and B Air line distance length between point is S, and the design gravity of unmanned plane is referred to as C points.In order to explain in detail the design weight of unmanned plane The heart (C points) and the first lift equalization point (A points), the position relationship of the second lift equalization point (B points), now enumerate embodiment and make such as Lower explanation：

C points are located between A points and B points, and the air line distance between C points and A points is assumed to be L, and L needs to meet：L= (3/4)*S.Meanwhile A points, B points and C points can also be located along the same line.Since the design gravity of unmanned plane is in the first lift At the 3/4 of equalization point and the second lift equalization point spacing, when the weight of unmanned plane changes, it will not influence to unmanned plane Control performance.So the design gravity of unmanned plane is at the 3/4 of the first lift equalization point and the second lift equalization point spacing, Be conducive to adapt to the different weight of unmanned plane, and then reach the technique effect for not influencing control performance.

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. 1-6 are referred to, third fuselage 30 includes the 4th connecting portion 31, third sheet Body 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 It is integrally formed with tail portion 33 and forms third fuselage 30,33 diameter of section of tail portion is towards being sequentially increased on 32 direction of third ontology.It is logical It crosses and is fixedly connected with tail portion 33 with third ontology 32, third ontology 32 is fixedly connected with the 4th connecting portion 31, the 4th connecting portion 31 It is detachably connected with 20 third connecting portion 23 of the second fuselage, 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 it is set on current divider 46 4th shunting delivery outlet 465.First driving motor 481 can also include：First drive shaft 4811 and driving fixed seat 4812；Rudder Machine 47 can also include：Third steering engine 473, the third steering engine 473 include third steering engine input port 4733, third rotor shaft 4731 With third fixed seat 4732；By the way that third steering engine input port 4733 is connect with the 4th shunting delivery outlet 465 of current divider 46, from And it is that third steering engine 473 provides electric energy.

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.It turns over Transfer part can include housing, and housing can include third hollow portion, first side and second side；The first side can wrap First end, second end and positioning area are included, first end can be hinged with the second hinged seat, and second hinged seat can be with Between first end and the 4th opening face；The third fixed seat of third steering engine 473 can be arranged in third hollow portion, And third rotor shaft 4731 can also be located at outside the second side, and the third rotor shaft 4731 of third steering engine 473 It can be fixedly connected with the center of tail rotor, and third rotor shaft 4731 can also mutually hang down with the rotational plane of tail rotor Directly.

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 can include the first driving wheel and the second driving wheel, and the first driving wheel may be used also To include first gear 50 and endoporus, endoporus can be located at the center of first gear 50, and endoporus can be with the first drive shaft 4811 are fixedly connected.Second driving wheel can include second gear 51 and supporter, and supporter can include lateral surface and medial surface, Second gear 51 can be fixedly connected with the medial surface, and lateral surface can also be fixedly connected with the second hollow portion, and Lateral surface can also be located in the second hollow portion, meanwhile, second gear 51 can be meshed with first gear 50；Lateral surface and interior Side can be two corresponding surfaces of the supporter.

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 forms fixed angle with second end, The numerical value of the angle can be 90 °.When the first driving motor 481 pushes the first cohesive end 33121 to move right, the will be driven Two cohesive ends 33122 will move down；When the first driving motor 481 pulls the first cohesive end 33121 to be moved to the left, will drive Second cohesive end 33122 will move up.By the leftward or rightward mobile so as to cause the second cohesive end of the first cohesive end 33121 33122 move up or down.And twayblade rotor, tail rotor 33123 and third steering engine can be used in tail rotor 33123 473 third rotor shaft 4731 is fixedly connected, and makes third rotor shaft 4731 that tail rotor 33123 be driven to rotate.In tail rotor 33123 During rotation, third rotor shaft 4731 and the plane of the rotation are mutually perpendicular to.It can group by tail rotor 33123 and third steering engine 473 Component is overturn into a tail rotor 33123, the tail rotor 33123 overturning component can be included：Coniform shell.Third rudder Machine 473 can be fixed in coniform shell, by the way that the third rotor shaft 4731 of third steering engine 473 is stretched out outside cone Except shell, so as to which tail rotor 33123 be made to be fixedly connected except coniform shell with third rotor shaft 4731.Outside due to cone Shell can be arranged to sealing, and then in the flight of rainwater day, can prevent damage of the rainwater to the electric elements inside unmanned plane Evil.Can also connecting hole can be set on the one side of third fuselage 30 in coniform shell, by by the second cohesive end 33122 are fixedly connected with the connecting hole, so as to which the second cohesive end 33122 be made to be connect with third fixed seat 4732, if the second rank 33122 movement of end is connect, 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:It can be tail rotor 33123 along third caudal face side that tail rotor 33123, which moves up, It to movement, 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 To be that tail rotor 33123 is moved along 37 direction of the 4th caudal face, i.e., moved away from the direction of vertical stabilizer 2231, now close to First horizontal axis 54；It can be that tail rotor 33123 is moved along 34 direction of the first caudal face that tail rotor 33123, which is moved to the left, such as scheme 5, i.e., it is moved along 2211 direction of the first postposition wing, at this time far from the first vertical pivot 53；Tail rotor 33123, which moves right, 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, 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 move up or down and are 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 rotates clockwise, since second gear 51 is fixedly connected with third steering engine 473, will drive tail rotor 33123 to It moves right.It is achieved thereby that unmanned plane, in flight, landing, tail rotor 33123 can gradually move right, and reach change tail 33123 direction of motion of rotor, and then control tail rotor 33123 to the thrust direction of unmanned plane makes the direction of thrust gradually to the right It is mobile.Fig. 7 is referred to, is gradually moved right in tail rotor 33123, and is moved to tail rotor 33123 relative to the first vertical pivot When the angle of 53 movements is 60 °.Tail rotor 33123 will to the left to the thrust direction of unmanned plane, the rotation of tail rotor 33123 at this time Thrust to the left will be provided for unmanned plane, change the thrust direction of unmanned plane, so as to change the stressing conditions of unmanned plane entirety.Please With continued reference to Fig. 5, Fig. 7, second of embodiment.If the rotation of first gear 50 drives second gear 51 to rotate counterclockwise, by It is fixedly connected in second gear 51 with third steering engine 473, tail rotor 33123 will be driven to be moved to the left.It is achieved thereby that at nobody In machine flight, 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, in tail rotor 33123 are gradually moved to the left, and when to be moved to tail rotor 33123 relative to the angle that the first vertical pivot 53 moves be 0 °, tailspin The wing 33123 will be mutually perpendicular to the first horizontal axis 54.Tail rotor 33123 will be towards portion 11 windward, i.e., to the thrust direction of unmanned plane The thrust for advance being provided for unmanned plane to the direction of advance of unmanned plane, the at this time rotation of tail rotor 33123, changes unmanned plane Thrust direction, 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.

For 40 part of power source：In embodiment provided by the invention, power source 40 can include：Engine 41st, 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 outside of the first fuselage 10, the second fuselage 20 or third fuselage 30；In order to prevent in-flight rainwater to dynamic The damage in power source 40, power source 40 can also sealed set be either directly anchored to the first fuselage 10, the second fuselage 20 or The inside of three fuselages 30.The effect of power source 40 mainly provides power for flight, the landing of unmanned plane.

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 is connect with engine 41； Electric pressure converter 43 can be AC/DC converters, and electric pressure converter 43 is connect with generator 42；It is defeated that voltage-stablizer 44 includes the first voltage stabilizing Entrance 441, the second voltage stabilizing input port 442 and the first voltage stabilizing delivery outlet 443, the first voltage stabilizing input port 441 and electric pressure converter 43 Connection, and make electric pressure converter 43 between the first voltage stabilizing input port 441 and generator 42；45 and second voltage stabilizing of accumulator Input port 442 connects；Current divider 46 further includes the first shunting input port 461, first shunting shunting output of delivery outlet 462, second Mouth 463, third shunting delivery outlet 464 and the 7th shunt delivery outlet 468, the first shunting 461 and first voltage stabilizing delivery outlet of input port 443 connections；Steering engine 47 includes at least the first steering engine 471, the second steering engine 472 and third steering engine 473, and the first steering engine 471 at least wraps The first steering engine input port 4711 and the first rotor shaft 4712 are included, the first steering engine input port 4711 connects with the first shunting delivery outlet 462 It connects, to provide energy for the first steering engine 471, and the first rotor shaft 4712 of the first steering engine 471 is connect with the first rotor 1211, leads to The rotation for crossing the first rotor shaft 4712 drives, and carrys out the rotation of the first rotor 1211；Second steering engine 472 includes the second steering engine input port 4721 and second rotor shaft 4722；Second steering engine input port 4721 is connect with the second shunting delivery outlet 463, so as to be the second steering engine 472 provide energy, and the second rotor shaft 4722 of the second steering engine 472 is connect with the second rotor 1221, passes through the second rotor shaft 4722 rotation, to drive the rotation of the second rotor 1221；Third steering engine 473 further includes third steering engine input port 4733, third Steering engine input port 4733 is connect with the 7th shunting delivery outlet 468, so as to provide energy for third steering engine 473.Driving motor 48 to Include the first driving motor 481 less, the first driving motor 481 is connect with third shunting delivery outlet 464, the gyroplane of adjustable angle Structure 331 is connect with the first driving motor 481, and the first driving motor 481 is made to be located at third shunting delivery outlet 464 and adjustable angle Rotor mechanism 331 between.

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 electric pressure converter 43 is exported Burning voltage will enter current divider 46, and each shunting delivery outlet of current divider 46 is that electric energy is assigned to each steering engine 47 or is driven Dynamic motor 48, such as：First shunting delivery outlet 462 is connect with 471 input port of the first steering engine, so as to be provided for the first steering engine 471 Energy；Second shunting delivery outlet 463 is connect with the second steering engine input port 4721, so as to provide energy for the second steering engine 472；Third Shunting delivery outlet 464 is connect with the first driving motor 481, so as to provide energy for the first driving motor 481.

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 (the present embodiment unmanned plane F-Zero can be 60m/s) flight.Electric pressure converter 43 can be AC/DC converters, and AC/DC converters are that will hand over The equipment that galvanic electricity becomes direct current, AC/DC converters have the AC-DC conversion of better stability, can provide stabilization for unmanned plane Direct current, from the stability for improving unmanned mechanomotive force.Certainly, those skilled in the art are obviously it is understood that engine 41 also may be used To use four stroke aviation piston engines 41.In actual mechanical process, the shunting delivery outlet of current divider 46 can also basis Actual demand is set, such as：If being provided with video camera, automatic flight control system on unmanned plane, current divider 46 may be Video camera, automatic flight control system distribution electric energy, the mode of the distribution electric energy is (including being steering engine 47, driving motor 48 above Distribute the mode of electric energy) can be connected by conducting wire 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, the circuit control system of unmanned plane can be with It includes at least：Ground remote control device 56, flight control system 55, engine 41, generator 42, electric pressure converter 43, voltage-stablizer 44, Accumulator 45, current divider 46, the first steering engine 471, the second steering engine 472, third steering engine 473, the first driving motor 481, second drive Dynamic motor 482, third driving motor 483, the 4th driving motor 484.Wherein, engine 41, generator 42, voltage are converted Device 43, voltage-stablizer 44, accumulator 45, current divider 46, the first steering engine 471, the second steering engine 472, third steering engine 473, first drive Motor 481, the second driving motor 482,483 and the 4th driving motor 484 of third driving motor, such as above example.Flight control The ground remote control device 56 on system 55 processed and ground carries out signal transmission, and then by from ground remote control device 56 to flight control system 55 send control instruction, and pass through the first steering engine 471, the second steering engine 472, third rudder that flight control system 55 controls unmanned plane The work of machine 473, the first driving motor 481, the second driving motor 482,483 and the 4th driving motor 484 of third driving motor State, and then realize and the state of unmanned plane landing, flight is controlled.

It is noted that flight control system 55 is mainly by controlling the first rotor 1211 in the first steering engine 471 In velocity of rotation, the second steering engine 472 in the velocity of rotation of second rotor 1221, third steering engine 473 third rotor velocity of rotation Linkage portion 3312 is pulled with the first driving motor 481 of control, and then controls tail rotor 33123 relative to being moved down on the first vertical pivot 53 The dynamic angle change for forming angle to control the first driving motor 481 that second gear 51 is driven to rotate, and then controls 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.

Advantageous effect：The present invention provides unmanned plane, before setting first respectively in 12 both sides of the first noumenon of the first fuselage 10 121 and second forewing 122 of wing is put, first rotor is set respectively on the first forewing 121 and the second forewing 122 1211 and second rotor 1221, power is provided to the first rotor 1211 by the first steering engine 471 of power source 40, power source 40 Second steering engine 472 provides power to the second rotor 1221；On the second ontology 22 of the second fuselage 20 along first side 221, Second side 222 and third side 223 are set gradually：First postposition wing 2211, the second postposition wing 2221 and vertical stabilizer 2231；The rotor mechanism 331 of one adjustable angle on the tail portion of third fuselage 30 33 is set, passes through the first driving of power source 40 Motor 481 provides dynamic power to the rotor mechanism 331 of adjustable angle；And 21 and first machine of second connecting portion of the second fuselage 20 The first connecting portion 13 of body 10 is detachably connected, the 4th connecting portion 31 of third fuselage 30 and the third connecting portion of the second fuselage 20 23 are detachably connected, and the integral body of unmanned plane is made of the first fuselage 10, the second fuselage 20 and third fuselage 30 so that occur It, can be with local replacing component when fuselage local damage can not be repaired.First rotor 1211, the second rotor 1221 and adjustable angle Rotor mechanism 331 makes unmanned plane can be with VTOL, so as to which the landing of unmanned plane be made not limited by place size；Adjustable angle Rotor mechanism 331 can also provide thrust for the flight of unmanned plane, so as to make the flying speed of unmanned plane fast.Unmanned plane is reached Landing and flight operation are easy, fast with flying speed, long-endurance technique effect.

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. unmanned plane, which is characterized in that including：

First fuselage, first fuselage include：

Portion windward, the tapered structure in portion windward；

The first noumenon, the first noumenon are fixedly connected with the portion windward, and the diameter of section in the portion windward is towards institute It states and is sequentially increased on the direction of the first noumenon；The first forewing and the second forewing are provided on the first noumenon, and The center vertical pivot of first forewing and second forewing along the first noumenon is symmetrically distributed in described The both sides of one ontology are provided with the first rotor on first forewing, the second rotation are provided on second forewing The wing；

First connecting portion, the first connecting portion are fixedly connected with the first noumenon, and the diameter of section of the first noumenon It is sequentially reduced on the direction towards the first connecting portion；

Wherein, the first noumenon is located at described windward between portion and the first connecting portion, and the portion windward, described first Ontology and the first connecting portion, which are integrally formed, forms first fuselage；

Second fuselage, second fuselage include：

Second connecting portion, the second connecting portion and the first connecting portion are detachably connected；

Second ontology, second ontology are fixedly connected with the second connecting portion；And second ontology include first side, Second side and third side, and the first side and the second side are symmetrically divided along the center vertical pivot of second ontology Cloth, the third side is between the first side and the second side；And it is provided with first in the first side Postposition wing is provided with the second postposition wing in the second side, vertical stabilizer is provided on the third side；

Third connecting portion, the third connecting portion are fixedly connected with second ontology；

Wherein, second ontology is between the second connecting portion and the third connecting portion, and the second connecting portion, Second ontology and the third connecting portion, which are integrally formed, forms second fuselage；

Third fuselage, the third fuselage include：

4th connecting portion, the 4th connecting portion and the third connecting portion are detachably connected；

Third ontology, the third ontology are fixedly connected with the 4th connecting portion；

Tail portion, the tail portion are fixedly connected with the third ontology, and the diameter of section of the tail portion is towards the third sheet It is sequentially increased on the direction of body；And the rotor mechanism of an adjustable angle is provided on the tail portion；

Wherein, the third ontology is between the 4th connecting portion and the tail portion, and the 4th connecting portion, described Three ontologies and the tail portion, which are integrally formed, forms the third fuselage；

Power source, the power source include at least：

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 and the second steering engine；Wherein, first steering engine includes at least：First rudder Machine input port and the first rotor shaft, the first steering engine input port are connect with the described first shunting delivery outlet；First rotor Axis is connect with first rotor；Second steering engine includes at least：Second steering engine input port and the second rotor shaft, described second Steering engine input port is connect with the described second shunting delivery outlet；Second rotor shaft is connect with first rotor；

Driving motor, the driving motor include at least：First driving motor；First driving motor is shunted with the third Delivery outlet connects, and the rotor mechanism of the adjustable angle is connect with first driving motor, and the first driving motor position It is shunted between delivery outlet and the rotor mechanism of the adjustable angle in the third.

2. unmanned plane as described in claim 1, it is characterised in that：

First forewing includes：First preceding fastening end and the first forward open end；

Second forewing includes：Second preceding fastening end and the second forward open end；

Wherein, the described first preceding fastening end and the second preceding fastening end are symmetrically distributed along the center vertical pivot of the first noumenon In the both sides of the first noumenon；And the first preceding fastening end and first forward open end are first forewings Both ends, the second preceding fastening end and second forward open end are the both ends of second forewing；It is opened before described first Mouth end is provided with one first storage region, and second forward open end is provided with the second storage region；

First steering engine further includes：For fixing the first fixed seat of the first steering engine, first fixed seat is fixed on described In first storage region；

Second steering engine further includes：For fixing the second fixed seat of the second steering engine, second fixed seat is fixed on described In second storage region；

First rotor includes：

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 State that the first clump weight is symmetrical relative to first rotor shaft, first rotor shaft turns with first rotating vane Dynamic plane is perpendicular；

Second rotor includes：

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 State that the second clump weight is symmetrical relative to second rotor shaft, second rotor shaft turns with second rotating vane Dynamic plane is perpendicular.

3. unmanned plane as claimed in claim 2, it is characterised in that：

First forewing subtracts successively in the described first preceding fastening end, width of the edge on the first forward open end direction It is small；

And/or

Second forewing subtracts successively in the described second preceding fastening end, width of the edge on the second forward open end direction It is small.

4. unmanned plane as described in claim 1, it is characterised in that：

The first postposition wing includes：Fastening end and the first rear open end after first；

Second forewing includes：Fastening end and the second rear open end after second；

Wherein, fastening end is symmetrically fixed along the center vertical pivot of second ontology behind fastening end and described second after described first It is arranged on the both sides of second ontology；And fastening end and first rear open end are the first postposition machines after described first The both ends of the wing, fastening end and second rear open end are the both ends of the second postposition wing after described second；

Second fuselage further includes：

First winglet, the angle of first winglet and the first postposition wing is 60 ° -90 °；And described first Winglet includes：First wing tip fastening end and the first wing tip openend；And behind the first wing tip fastening end and described first Openend is fixedly connected, and the first wing tip openend deviates from first rear open end, with the first wing tip fastening end structure Into the both ends of first winglet；And the first wing tip openend and the vertical stabilizer are located at the first postposition machine The both sides of the wing；

Second winglet, the angle of second winglet and the second postposition wing is 60 ° -90 °；And described second Winglet includes：Second wing tip fastening end and the second wing tip openend；And behind the second wing tip fastening end and described second Openend is fixedly connected, and the second wing tip openend deviates from second rear open end, with the second wing tip fastening end structure Into the both ends of second winglet；And the second wing tip openend and the vertical stabilizer are located at the second postposition machine The both sides of the wing；

Wherein, the first wing tip openend and the second wing tip openend are symmetrical along the center vertical pivot of second ontology Distribution.

5. unmanned plane as claimed in claim 4, which is characterized in that second fuselage further includes：

First aileron, the first aileron rotation are arranged in first rear open end, and first aileron is described It is rotated in first rear open end relative to first rear open end；

And/or

Second aileron, the second aileron rotation are arranged in second rear open end, and second aileron is described It is rotated in second rear open end relative to second rear open end；

And/or

Third aileron, the third aileron rotation are arranged on the vertical stabilizer, and the third aileron is described vertical It is rotated on wing relative to the vertical stabilizer；

Wherein, the first postposition wing fastening end after described first, along the width on the first rear open end direction It is sequentially reduced；

And/or

Second postposition wing fastening end after described second subtracts successively along the width on the second rear open end direction It is small；First aileron, second aileron and the third aileron are rectangle.

6. unmanned plane as claimed in claim 5, it is characterised in that：

Second driving motor, second driving motor are connect with first aileron, and second driving motor fixation is set It puts after described first between fastening end and the first rear open end；

Third driving motor, the third driving motor are connect with second aileron, and third driving motor fixation is set It puts after described second between fastening end and the second rear open end；

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

7. unmanned plane as claimed in claim 6, which is characterized in that the current divider further includes：

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

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

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

8. unmanned plane as described in claim 1, it is characterised in that：

The third fuselage further includes：First caudal face, the second caudal face, third side caudal face and the 4th caudal face, and it is described First caudal face and the third side are symmetrically dispersed in the both sides in the second caudal face, and the first caudal face and described Third side is symmetrically dispersed in the both sides in the 4th caudal face, with by the first caudal face, the second caudal face, third side tail Side and the 4th caudal face are surrounded to form the third fuselage；

First driving motor further includes：First drive shaft and driving fixed seat；

The steering engine further includes：Third steering engine；Wherein, the third steering engine includes at least：Third rotor shaft and third fixed seat；

The rotor mechanism of the adjustable angle includes：Tailspin seat；Wherein, the tailspin seat is fixed at the second caudal face And/or on the both sides in the 4th caudal face, and the driving fixed seat is arranged on the tailspin seat and/or the third ontology On；

Linkage portion, the linkage portion include：First cohesive end, the second cohesive end and tail rotor；Wherein, first cohesive end with The first driving axis connection, second cohesive end are connect with the third fixed seat, the third rotor shaft and the tail The center of rotor is fixedly connected, and the third rotor shaft and the rotational plane of the tail rotor are 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, the third side caudal face Or the 4th tail side surface direction movement.

9. unmanned plane as claimed in claim 8, it is characterised in that：

The current divider further includes：7th shunting delivery outlet；

The third steering engine further includes：Third steering engine input port；Wherein, the third steering engine input port and the described 7th shunting are defeated Outlet connection；

The engine is two stroke engine；

The electric pressure converter is AC/DC converters.

10. unmanned plane as described in claim 1, which is characterized in that the generator 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.