CN207748008U - A kind of airframe structure applied to unmanned plane - Google Patents

Abstract

The utility model discloses a kind of airframe structures applied to unmanned plane, belong to air vehicle technique field, including portion windward, windward the tapered structure in portion；The first noumenon, the first noumenon are fixedly connected with portion windward, and the diameter of section in portion is sequentially increased on the direction towards the first noumenon windward；The first forewing and the second forewing are provided on the first noumenon, and first forewing and the second forewing the both sides of the first noumenon are symmetrically distributed in along the center vertical pivot of the first noumenon, first rotor is arranged on the first forewing, and the second rotor is arranged on the second forewing；First connecting portion, first connecting portion are fixedly connected with the first noumenon, and the diameter of section of the first noumenon is sequentially reduced on the direction towards first connecting portion；Wherein, the first noumenon is located at windward between portion and first connecting portion.The utility model reaches the power capacity loss for reducing unmanned plane, is conducive to the technique effect of the normal flight of unmanned plane.

Description

A kind of airframe structure applied to unmanned plane

Technical field

The utility model belongs to air vehicle technique field, more particularly to a kind of airframe structure applied 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 are installed etc. 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 under wireless remotecontrol or be launched with booster rocket, it also can be by machine tool Aerial launch is taken to fly.

Currently, mainly using cylindrical structure for the fuselage applied to unmanned plane, and rotor is fixed on fuselage top Portion.Cylindrical fuselage can both accommodate the various electric elements needed for unmanned plane, can also be loaded in fuselage interior more Article.But be in flight course in unmanned plane, the fuselage of unmanned plane and the frictional resistance of air-flow are larger, can severe attrition The power source of aircraft, and interference also will produce to the normal flight of unmanned plane.

In conclusion existing applied in the body techniques of unmanned plane, the fuselage of unmanned plane understands severe attrition itself Power capacity, and have an adverse effect to normal flight.

Utility model content

Technical problem to be solved in the utility model is the power capacity of the fuselage meeting severe attrition itself of unmanned plane, and Have an adverse effect to normal flight.

In order to solve the above technical problems, the utility model provides a kind of airframe structure applied to unmanned plane, described one It plants and includes applied to the airframe structure of unmanned plane：Portion windward, the tapered structure in portion windward；The first noumenon, the first Body is fixedly connected with the portion windward, and the diameter of section in the portion windward increases successively on the direction towards the first noumenon Greatly；The first forewing and the second forewing, and first forewing and described are provided on the first noumenon Two forewings are symmetrically distributed in the both sides of the first noumenon, the setting of the first rotor along the center vertical pivot of the first noumenon On first forewing, the second rotor is arranged on second forewing；First connecting portion, first connection Portion is fixedly connected with the first noumenon, and the diameter of section of the first noumenon is on the direction towards the first connecting portion It is sequentially reduced；Wherein, the first noumenon is located at described windward between portion and the first connecting portion, and the portion windward, institute It states the first noumenon and the first connecting portion is integrally formed and constitutes the fuselage.

Further, first forewing includes the first preceding fastening end and the first forward open end；Described second is preposition Wing includes the second preceding fastening end and the second forward open end；Wherein, the described first preceding fastening end and first forward open end are The both ends of first forewing, the second preceding fastening end and second forward open end are second forewings Both ends.Second forewing is arranged on the first forewing of the first noumenon,

Further, the center vertical pivot pair of the described first preceding fastening end and the second preceding fastening end along the first noumenon The both sides for being distributed in the first noumenon claimed.

Further, first forward open end is provided with one first storage region, first storage region and first First fixed seat of steering engine is fixedly connected.

Further, second forward open end is provided with one second storage region, second storage region and second Second fixed seat of steering engine is fixedly connected.

Further, first forewing is in the described first preceding fastening end, along to first forward open end direction On width be sequentially reduced.

Further, second forewing is in the described second preceding fastening end, along to second forward open end direction On width be sequentially reduced.

Advantageous effect：The utility model provides a kind of airframe structure applied to unmanned plane, by that will be arranged in portion windward The diameter of section in portion windward is sequentially increased by cone structure on the direction towards the first noumenon, keeps the section of the first noumenon straight Diameter is sequentially reduced on the direction towards first connecting portion.And the first noumenon is fixedly connected with portion windward, is made first preposition Wing and the second forewing are symmetrically distributed in the both sides of the first noumenon along the center vertical pivot of the first noumenon.Then make windward Portion, the first noumenon and first connecting portion, which are integrally formed, constitutes the fuselage.Be in flight course in unmanned plane, integral body and When gas current friction, the resistance that air-flow generates on fuselage can be reduced.To reach the power capacity loss for reducing unmanned plane, favorably In the technique effect of the normal flight of unmanned plane.

Description of the drawings

In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment Needed in attached drawing be briefly described, it should be apparent that, the accompanying drawings in the following description is only the utility model Some embodiments for those of ordinary skill in the art without creative efforts, can also be according to this A little attached drawings obtain other attached drawings.

Fig. 1 is the overall structure diagram for the unmanned plane that the utility model embodiment provides；

Fig. 2 is the top view illustration of Fig. 1；Fig. 3 is the upward 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 for the adjustable angle that the utility model embodiment provides；

Fig. 8 is the generator and engine connection relationship diagram that the utility model embodiment provides；

Fig. 9 is the mechanism block diagram for the circuit control system that the utility model embodiment provides.

Specific implementation mode

The utility model discloses a kind of airframe structures applied to unmanned plane, by that will be arranged to taper knot in portion windward The diameter of section in portion windward is sequentially increased by structure on the direction towards the first noumenon, makes the diameter of section of the first noumenon in court It is sequentially reduced on the direction of first connecting portion.And the first noumenon is fixedly connected with portion windward, make the first forewing and Second forewing is symmetrically distributed in the both sides of the first noumenon along the center vertical pivot of the first noumenon.Then make portion, first windward Ontology and first connecting portion, which are integrally formed, constitutes the fuselage.It is in flight course in unmanned plane, integral body and air-flow rub When wiping, the resistance that air-flow generates on fuselage can be reduced.To reach the power capacity loss for reducing unmanned plane, be conducive to nobody The technique effect of the normal flight of machine.

It is practical new to support in order to elaborate to a kind of airframe structure applied to unmanned plane that utility model provides Type technical problem to be solved first elaborates to unmanned plane in the following, in embodiment provided by the utility model, after And during describing unmanned plane, it further targetedly draws provided by the utility model a kind of applied to unmanned plane Airframe structure, it is complete, clear, clear to achieve the purpose that.

Following general description is done to the overall condition of unmanned plane first：The utility model is by the way that the fuselage of unmanned plane to be divided into Including at least three sections, i.e. the first fuselage 10, the second fuselage 20 and third fuselage 30, and pass through detachable connection between three sections Connection type is attached, and is constituted a dismountable unmanned plane of internal structure with this, so that when the fuselage of unmanned plane goes out When existing local damage, it corresponding can remove the position for occurring damaging and repair, there is simple, convenient technology to imitate Fruit.And when the part of fuselage can not be repaired because damaging, can also the position that can not repair of corresponding dismounting, i.e., pair The position that can not be repaired is substituted, to overcome in the prior art because fuselage is using integrated global design so that When fuselage local damage occur can not repair, it has to which the technological deficiency for replacing the entire fuselage of unmanned plane reaches and greatly drops The low technique effect of maintenance cost.

Meanwhile unmanned plane, during executing landing operation, first included by unmanned plane in the utility model is revolved The rotor mechanism 331 of the wing 1211, the second rotor 1221 and adjustable angle matches operation (being operated) and generates lifting force, draws It rises or declines with motivation.Such as：When unmanned plane takes off, revolved by controlling the first rotor 1211 and the second rotor 1221 Turn, and adjust the rotation direction (rotor mechanism 331 is made to provide upward pulling force) of the adjustable rotor mechanism of angle 331, by the Resultant force, carries for unmanned plane caused by the rotation of one rotor 1211, the rotation of the second rotor 1221 and the operating of rotor mechanism 331 For upward lifting force, to realize taking off vertically for unmanned plane.When unmanned plane is drawn high certain altitude, then pass through adjustment angle The rotation direction (rotor mechanism 331 is made to provide horizontal thrust) for spending adjustable rotor mechanism 331, to generate water on unmanned plane Flat-pushing 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 lifting force of the second rotor 1221, and controlling the adjustable rotor mechanism of angle 331 makes unmanned plane pull fuselage from eminence Stablize and decline, until stablizing landing, the damage of fuselage and carrying equipment caused by avoiding fuselage hard landing greatly reduces drop The risk for falling accident, having reached makes unmanned plane be suitble to carry out the technique effect of landing operation in different flying fields.

Below in conjunction with Figure of description, the technical scheme in the embodiment of the utility model is clearly and completely retouched It states, it is clear that the described embodiments are only a part of the embodiments of the utility model, instead of all the embodiments.

In order to which the unmanned plane that the utility model embodiment provides is described in detail, the utility model is implemented first Involved technical term does description below explanation in example：

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

The utility model provides a kind of embodiment of the airframe structure applied to unmanned plane.This is applied to the fuselage of unmanned plane It can refer to the first fuselage 10.For 10 part of the first fuselage：

Fig. 1-Fig. 6 is referred to, the first fuselage 10 includes：Portion 11, the first noumenon 12 and first connecting portion 13 windward, first Ontology 12 is located at windward between portion 11 and first connecting portion 13, and portion 11, the first noumenon 12 and first connecting portion 13 1 windward The first fuselage 10 of body formed composition.In the first fuselage 10, by the way that cone structure will be arranged in portion 11 windward, by portion 11 windward Diameter of section is sequentially increased on the direction towards the first noumenon 12, and makes the diameter of section of the first noumenon 12 in direction first It is sequentially reduced, allows in this way in unmanned plane during flying on the direction of interconnecting piece 13, the first fuselage 10 is implemented in the utility model Global shape design in example advantageously reduces the resistance of air-flow.

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

Specifically, can be by can between the first preceding fastening end 1212 of the first forewing 121 and the first noumenon 12 The connection type being detachably connected with is attached.The the second preceding fastening end 1222 and the first noumenon 12 of second forewing 122 it Between can also be attached by the connection type of detachable connection.It allows for making by way of being detachably connected in this way It is detachable between first forewing 121, the second forewing 122 and the first noumenon 12, it is convenient for the assembling of the first fuselage 10, makes 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 be preferably that unmanned plane generates lift, 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 keeps state of flight to be preferably that unmanned plane generates lift.

The first rotor 1211 is provided on the first forewing 121, and for driving the first rotor 1211 to be revolved The first steering engine 471 turned is provided with the second rotor 1221 on the second forewing 122, and for driving the second rotor 1221 The second steering engine 472 rotated.And in the first forward open end 1213 of the first forewing 121, also set up one first Storage region 12131；One second storage region 12231 is also set up in the second forward open end 1223 of the second forewing 122. Wherein, the first steering engine 471 includes：First rotor shaft 4712 and the first fixed seat 4713 for fixing the first steering engine 471, and One fixed seat 4713 is fixed in the first storage region 12131；Second steering engine 472 includes：Second rotor shaft 4722 and for solid Second fixed seat 4723 of fixed second steering engine 472, and the second fixed seat 4723 is fixed in the second storage region 12231.First Rotor 1211 includes：First rotating vane 12111 and the first clump weight 12112, the first rotating vane 12111 and the first rotor shaft 4712 are fixedly connected, and the first clump weight 12112 is fixedly connected with the first rotor shaft 4712；And 12111 He of the first rotating vane First clump weight 12112 is symmetrical relative to the first rotor shaft 4712, the first rotor shaft 4712 and the first rotating vane 12111 Rotational plane it is perpendicular.Second rotor 1221 includes：Second rotating vane 12211 and the second clump weight 12212, the second rotation Blade 12211 is fixedly connected with the second rotor shaft 4722, and the second clump weight 12212 is fixedly connected with the second rotor shaft 4722, and And second rotating vane 12211 and the second clump weight 12212 it is symmetrical relative to the second rotor shaft 4722, the second rotor shaft 4722 is perpendicular with the rotational plane of the second rotating vane 12211.

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 steering engine 47 volume size, 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 rotation of the first rotor shaft 4712 and first of the first steering engine 471 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 When 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 wing axis 4712 drives the first rotating vane 12111 and the first clump weight 12112 to rotate together, the first clump weight 12112 will not It deforms upon, to influence the balance of the first rotor 1211.On the other hand, the second steering engine 472 is passed through into the second fixed seat 4723 It is fixed in the second storage region 12231, the second rotor shaft 4722 of the second steering engine 472 and the second rotation of the second rotor 1221 Blade 12211 is fixedly connected, and the second rotor shaft 4722 is fixedly connected with the second clump weight 12212.Second rotor shaft 4722 Perpendicular with the rotational plane of the second rotating vane 12211, i.e., in the rotation of the second rotating vane 12211, which puts down Face is mutually perpendicular to the second rotor shaft 4722；Second rotating vane 12211 and the second clump weight 12212 are relative to the second rotor shaft 4722 is symmetrical, i.e. the second rotating vane 12211 and the second clump weight 12212 are divided for axis in symmetrical with the second rotor shaft 4722 Cloth.The making material of second clump weight 12212 can use rigid material so that the second rotor shaft 4722 drives the second pivoting leaf When piece 12211 and the second clump weight 12212 rotate together, the second clump weight 12212 will not deform upon, to influence the first rotation The balance of the wing 1211.

In embodiment provided by the utility model, it is especially desirable to it is to be noted that：First rotor 1211 includes the first rotation Blade 12111 and the first clump weight 12112；Second rotor 1221 includes the second rotating vane 12211 and the second clump weight 12212.Namely the first rotor 1211 uses single blade, and what the second rotor 1221 used is also single blade.Traditional rotation What the wing used is all twayblade, and traditional rotor is namely made of two blades of similar first rotating vane 12111, this two A blade is symmetric usually relative to the axis that movable vane piece rotates.Traditional rotor due to the use of be twayblade, if nothing It is man-machine awing, which, to increase the resistance of air-flow, can produce the flight of unmanned plane along flow rotation Larger interference is unfavorable for the balance of unmanned plane, while it is larger to cause the amount of power of unmanned plane that can be lost.The utility model is real It is all to use single blade, while being respectively arranged with each single blade to apply the first rotor 1211 of example offer and the second rotor 1221 First clump weight 12112 and the second clump weight 12212, and then the first rotating vane 12111 and the second rotating vane 12211 are risen The effect of weight balancing.Due to rotor have single blade, if unmanned plane is awing, the single blade will remain with The consistent direction of air-flow overcomes traditional twayblade rotor and is produced to the flight of unmanned plane to reduce the resistance of air-flow Destruction caused by raw larger interference, the balance to unmanned plane and make the power capacity of unmanned plane that larger technology be lost to lack It falls into.Reach the flight balance for being conducive to unmanned plane, reduces the technique effect of the energy loss of unmanned mechanomotive force.

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

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

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

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

Above first embodiment and second embodiment can be implemented simultaneously, can also be in first embodiment Implement with optional one in second embodiment.Such as：Keep the first forewing 121 trapezoidal, and makes second preposition Wing 122 is also trapezoidal, to make unmanned plane obtain preferable lift.Keep the first forewing 121 trapezoidal, or makes second Forewing 122 is trapezoidal, in the global design of unmanned plane, make unmanned plane obtain preferable lift.

For 20 part of the second fuselage：Fig. 1-6 is referred to, the second fuselage 20 includes second connecting portion 21, second Body 22 and third interconnecting piece 23；Wherein, the second ontology 22 is between second connecting portion 21 and third interconnecting piece 23, and second connects Socket part 21, the second ontology 22 and third interconnecting piece 23, which are integrally formed, constitutes the second fuselage 20；Second connecting portion 21 and first connects Portion 13 is detachably connected, and the second ontology 22 is fixedly connected with second connecting portion 21, and third interconnecting piece 23 and the second ontology 22 are 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.Make the first fuselage 10 and the second fuselage by way of being detachably connected It is detachable between 20, it is convenient for the assembling of the second fuselage 20 so that convenience easy to maintenance significantly reduces maintenance cost.

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

Second fuselage 20 further includes：First winglet 24 and the second winglet 25.It is small to the first wing tip individually below The wing 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 open end 242；And the first wing tip fastens End 241 is fixedly connected with the first rear open end 22112, and the first wing tip open end 242 is away from the first rear open end 22112, with the One wing tip fastening end 241 constitutes the both ends of the first winglet 24；And the first wing tip open end 242 and vertical stabilizer 2231 In the both sides of the first postposition wing 2211；

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

First wing tip open end 242 of above first winglet 24 and the second wing tip open end 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 open end of the first winglet 24 242 and second second wing tip open end 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 open end 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 open end 242 deviate from the first rear open end 22112, i.e. the first wing tip open end 242 as shown in figure 4, be located at nothing The lower section of man-machine fuselage.At this point, the first winglet 24 and the first postposition wing 2211 constitute angle, the range of the angle is： 60°-90°；Second rear open end of the second wing tip fastening end 251 and the second postposition wing 2221 of the second winglet 25 22212 are fixedly connected, and the second wing tip open end 252 deviates from the second rear open end 22212, i.e. the second wing tip open end 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 constitute angle, The range of the angle is：60°-90°.The spacing of first wing tip fastening end 241 and the first wing tip open end 242, with the second wing tip The spacing of fastening end 251 and the second wing tip open end 252 is equal to refer to：Assuming that the first wing tip fastening end 241 and first wing The spacing of sharp open end 242 is W1, and the spacing of the second wing tip fastening end 251 and the second wing tip open end 252 is W2, then W1= W2.Due to W1=W2, when unmanned plane is parked in level ground, the first wing tip open end 242 and the second wing tip open end 252 can be with It is all contacted with ground so that the stop of unmanned plane is more steady.

Fig. 4, Fig. 5 are referred to, in order to make specification preferably 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 open end 242 of sharp winglet 24 and the first rear open end 22112 of the first postposition wing 2211 are constituted It is 60 °；And the second rear open end of the second wing tip open end 252 and the second postposition wing 2221 by the second winglet 25 22212 angles constituted 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.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 open end 242 of sharp winglet 24 and the first rear open end 22112 of the first postposition wing 2211 are constituted It is 90 °；And the second rear open end of the second wing tip open end 252 and the second postposition wing 2221 by the second winglet 25 22212 angles constituted 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.To reduce caused by the first and second wing tip trailing vortexs " induced drag ", reduce the destruction streamed to lift, improve lift resistance ratio, increase voyage, have the function that increase lift.Together When, since the first winglet 24 and the second winglet 25 are all mutually perpendicular to first level face, so the first winglet 24 and second the distance between winglet 25 and ground recently so that the first winglet 24 of manufacture and the second winglet 25 Required material is also less, to alleviate the own wt of the first winglet 24 and the second winglet 25, reduces nothing Man-machine overall weight, has reached increase voyage, reduce unmanned plane kinetic equation loss (such as：Oil consumption, accumulator 45 electric energy) Technique effect.

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

Fig. 5 is referred to, specifically, the first rear open end in the first postposition wing 2211 is arranged in the first aileron 26 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 vertically turn relative to the plane of the second postposition wing 2221, the plane along the second postposition wing 2221 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, keeps 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, the in-flight stability of unmanned plane is kept 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 forewing 122 and the second postposition wing 2221 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 When unmanned plane during flying, it is beneficial to the balance of unmanned plane surrounding flow, to reach the technology effect for the stability for promoting unmanned plane Fruit.Fig. 3 is referred to, the abdomen of unmanned plane may include first (when i.e. unmanned plane is parked in level ground, the face of close unmanned plane) The abdomen of fuselage 10, the second fuselage 20 abdomen and third fuselage 30 abdomen, 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 fastening end 22111 and the first rear open end 22112；Third driving motor 483 and the second pair The wing 27 connects, and third driving motor 483 be fixed at second after fastening end 22211 and the second rear open end 22212 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 is that the second aileron 27 provides the pulling force rotated upwardly and downwardly.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 Mouth 466 and the 6th shunting delivery outlet 467.4th 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 conducting wire by current divider that the 4th shunting delivery outlet 465 is connect with the second driving motor 482 46 connect with the second driving motor 482, and the second driving motor 482 is made to power on；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, and third driving motor 483 is made to connect Energization source；It can be by conducting wire by current divider 46 and 4 wheel driven that 6th shunting delivery outlet 467 is connect with the 4th driving motor 484 Dynamic motor 484 connects, and the 4th driving motor 484 is made to power on.To be the second driving motor 482, the by current divider 46 Three driving motors 483 and the 4th driving motor 484 provide electric energy.Refer to Fig. 2 and Fig. 3, it should be noted that unmanned plane is set The weight calculation heart is located at the first lift equalization point and first of the first forewing 121 and the second forewing 122 on unmanned plane Between the second lift equalization point of postposition wing 2211 and the second postposition wing 2221 on unmanned plane；And the design weight of unmanned plane The heart is at the 3/4 of the first lift equalization point and the second lift equalization point spacing, and the design gravity of unmanned plane is close to the second lift Equalization point.

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

Obviously, in embodiment provided by the utility model, to the design gravity of unmanned plane in the first lift equalization point and At the 3/4 of second lift equalization point spacing and what position relationship that A points, B points and C points are located along the same line was carried out says It is bright, it is not to provide constraints to the position, those skilled in the art can be by modifying to the link position Either equivalent replacement but this modification or equivalent replacement both be within the protection scope of the present invention.Such as：Unmanned plane is set The heart is counted weight at the 4/5 of the first lift equalization point and the second lift equalization point spacing；C points are located at except the line of B points and C points.

For 30 part of third fuselage：Fig. 1-Fig. 6 is referred to, third fuselage 30 includes the 4th interconnecting piece 31, third Ontology 32 and tail portion 33；Third ontology 32 is between the 4th interconnecting piece 31 and tail portion 33, and the 4th interconnecting piece 31, third ontology 32 and tail portion 33 be integrally formed and constitute third fuselage 30, the diameter of section of tail portion 33 towards increasing on the direction of third ontology 32 successively Greatly.It is fixedly connected with third ontology 32 by tail portion 33, third ontology 32 is fixedly connected with the 4th interconnecting piece 31, the 4th interconnecting piece 31 and third interconnecting piece 23 be detachably connected, so that third fuselage 30 and the second fuselage 20 is linked together.

Specifically, since the third interconnecting piece 23 of the 4th interconnecting piece 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.Make third fuselage by way of being detachably connected 30 and second detachable between fuselage 20, it is 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 being arranged 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 drive fixed seat 4812 be arranged in 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 driving of the first cohesive end 33121 and first 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 may include the second hinged seat, the second hollow portion, third opening face and the 4th opening face；Third is open Face can be with the second opening face flexible connection, i.e., third opening face can be hinged with the second opening face, and the second hinged seat It can be fixedly connected with the 4th opening face, third opening face and the 4th opening face can be two of the second base assembly right respectively Answer face；Second driving fixed seat can be fixed on the tail portion 33.

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

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

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

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

A kind of embodiment as the utility model embodiment.First driving motor 481 can also use straight line steering engine 47, linkage portion 3312 can also use upset connecting rod, the first cohesive end 33121 and the second cohesive end 33122 of linkage portion 3312 Can be the both ends of upset connecting rod respectively.

As shown in fig. 7, upset connecting rod is in " 7 " font, i.e., the first cohesive end 33121 constitutes 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 being moved to the left or right so as to cause the second cohesive end for the first cohesive end 33121 33122 move up or down.

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

Fig. 7 is referred to, second gear 51 can be set on the one side of third fuselage 30 in coniform shell, this Two gears 51 can be gear ring, and second gear 51 is made to be rotated centered on first gear 50.It can be in third fuselage 30 One servo motor of interior fixed setting, for driving first gear 50 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, to keep tail rotor 33123 perpendicular far from first Axis 53 is moved close to the first vertical pivot 53.

In embodiment provided by the utility model, since tail rotor 33123 moves up or down, tail rotor will be made 33123 move relative to the first vertical pivot 53, i.e. the angular range constituted relative to the movement of the first vertical pivot 53 of tail rotor 33123 can To be 0 ° -90 °.Since tail rotor 33123 is moved to the left or right, tail rotor 33123 will be made to be moved relative to the first vertical pivot 53 Dynamic, i.e., it can be 0 ° -60 ° that tail rotor 33123 is moved to the left constituted angular range relative to the first vertical pivot 53；Tail rotor 33123 relative to the first vertical pivot 53 constituted angular range that moves right can be 0 ° -60 °.

Embodiment provided by the utility model is described in detail in order to clearer, now respectively to tail rotor 33123 It moves up or down, it is described further below that tail rotor 33123 is moved to the left or right progress：

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

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

The first embodiment.If the first cohesive end 33121 moves right, by cause the second cohesive end 33122 to Lower movement.Since the second cohesive end 33122 is connect with third fixed seat 4732, tail rotor 33123 and the with third steering engine 473 Three rotor shafts, 4731 fixed seat connects.Moving down for second cohesive end 33122 can drive tail rotor 33123 to move downwardly together Dynamic, to realize 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 to the thrust direction of unmanned plane, so that thrust direction is gradually moved up.

When tail rotor 33123 moves gradually downward, and it 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, to make the lift of unmanned plane increase.

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, To realize 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 to the thrust direction of unmanned plane, so that the direction of thrust is moved gradually downward.

When tail rotor 33123 gradually moves up, and it 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 rotation of tail rotor 33123 at this time will provide the thrust of advance for unmanned plane, to make nothing Man-machine thrust increases.

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

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

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

Refer to Fig. 5, Fig. 7, second of embodiment.If the rotation of first gear 50 drives second gear 51 to turn counterclockwise It is dynamic, since second gear 51 is fixedly connected with third steering engine 473, tail rotor 33123 will be driven to be moved to the left.To realize In unmanned plane during flying, landing, tail rotor 33123 can be gradually moved to the left, and reach 33123 direction of motion of change tail rotor, And then tail rotor 33123 is controlled to the thrust direction of unmanned plane, so that the direction of thrust is gradually moved right.Fig. 7 is referred to, in tail Rotor 33123 is 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 °, Tail rotor 33123 will be mutually perpendicular to the first horizontal axis 54.Tail rotor 33123 will be towards portion windward to the thrust direction of unmanned plane 11, i.e., to the direction of advance of unmanned plane, the rotation of tail rotor 33123 at this time will provide the thrust of advance for unmanned plane, change The thrust direction of unmanned plane, to make the thrust of unmanned plane increase.

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, to change unmanned plane it is whole by Power situation.In embodiment provided by the utility model, power source 40 may include：Engine 41, generator 42, voltage conversion Device 43, voltage-stablizer 44, accumulator 45, current divider 46, steering engine 47 and driving motor 48.Power source 40 can be fixed on the first fuselage 10, the outside of the second fuselage 20 or third fuselage 30；In-flight damage of the rainwater to power source 40 in order to prevent, power source 40 Can also sealed set be either directly anchored to the inside of the first fuselage 10, the second fuselage 20 or third fuselage 30.Power source 40 effect mainly provides power for flight, the landing of unmanned plane.

In embodiment provided by the utility model, in order to increase unmanned plane the landing stage thrust or increase nobody Machine shortens the departure time of unmanned plane VTOL in the thrust of mission phase, and improves unmanned plane in flight course Flight speed.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 It is a.

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, 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 the limit of itself born pressure, will be occurred The case where first fuselage, 10 left side either the first fuselage, 10 right side is broken.So in implementation provided by the utility model In example, two power sources 40 are symmetrically distributed in the left and right sides of the first fuselage 10, unmanned plane itself flight can be improved Stationarity, and can also prevent by the pressure that 10 left side of the first fuselage either the first fuselage, 10 right side is carried to be more than certainly The limit of the born pressure of body, and there is a situation where 10 left side of the first fuselage either the first fuselage, 10 right sides to be 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 that the utility model embodiment provides, and is not the office to the utility model Limit.In actual mechanical process, according to actual demand, the quantity for either reducing power source 40 can be increased or change power source 40 are located at the specific location of the first fuselage 10, the second fuselage 20 or third fuselage 30, these may also apply to the utility model.

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

Specifically, engine 41 is to convert other forms to 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 caused by generator 42 and is exported after voltage-stablizer 44 surely Fixed voltage, and accumulator 45 is also connect with voltage-stablizer 44.The effect being connect with voltage-stablizer 44 for accumulator 45 is：Electric power storage Pond 45 can be that voltage-stablizer 44 provides electric energy, and voltage-stablizer 44 makes the electric energy generated by accumulator 45 be exported after voltage-stablizer 44 surely 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 the power supply of accumulator 45, 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 is that accumulator 45 provides electric energy, to supplement the electric energy of accumulator 45.

If it is that voltage-stablizer 44 provides electric energy that engine 41 and generator 42, which is only arranged, 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 is that voltage-stablizer 44 provides electric energy, 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 be that voltage-stablizer 44 provides electric energy by engine 41 and generator 42, with And accumulator 45 is that voltage-stablizer 44 provides electric energy, and it is voltage-stablizer 44 that this accumulator 45 can mutually switch with generator 42 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 safety for improving unmanned plane, in-flight the technique effect of the stability of power.

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

In embodiment provided by the utility model, engine 41 can be two-stroke aviation piston engine 41, i.e., living Plug from top to bottom, the engine 41 of two strokes from top to bottom, due to two stroke engine 41 have it is simple in structure, weight compared with Gently, moving component lacks easy to maintain, the big advantage of power per liter density, to be suitble to low latitude, high speed (the utility model of unmanned plane The unmanned plane F-Zero of the embodiment of offer can be 60m/s) flight.Electric pressure converter 43 can be AC/DC converters, AC/DC converters are the equipment that alternating current is become to direct current, and there is AC/DC converters the alternating current-direct current of better stability to turn It changes, stable DC can be provided for unmanned plane, from the stability for improving unmanned mechanomotive force.Certainly, those skilled in the art are aobvious So it is appreciated that engine 41 can also use four stroke aviation piston engines 41.In actual mechanical process, current divider 46 Shunting delivery outlet can also be arranged according to actual demand, such as：If being provided with video camera, automatic flight control on unmanned plane System, current divider 46 or video camera, automatic flight control system distribute electric energy, the mode of the distribution electric energy (including with The upper mode that electric energy is distributed for steering engine 47, driving motor 48) can connect or use wireless power transmission by conducting wire, this It may also apply to the utility model.

Fig. 8 is referred to, Fig. 8 is the generator 42 that the utility model embodiment provides and the signal of 41 connection relation of engine Figure.The generator 42 may include rotor 61 and supply port, and the rotor 61 of the generator 42 can the direct and hair The output shaft 60 of motivation 41 is fixedly connected, and the electric machine casing 62 of generator 42 can be fixed directly with the end face of 41 shell of engine Connection.And the electric pressure converter can with the supply port of the generator 42 (supply port be generator 42 electricity Energy output end) connection；Wherein, the rotor 61 can be between the supply port and the output shaft 60.Engine 41 When rotation, mechanical energy caused by engine 41 can be directly passed to generator 42 by the output shaft 60 of engine 41 Rotor 61 then drives the rotor 61 of generator 42 to rotate together, and is turned by the mechanical energy that generator 42 generates engine 41 Electric energy is turned to, 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 can be delivered to power unit, which has Distribute the power to the function of different electrical appliances.What the power distribution unit can export the supply port of generator 42 outward Electric energy is divided into two parts (abbreviation E1 and E2), and the electric energy of the parts E1 can be delivered to battery (can be accumulator), which can Required electric energy when carrying out VTOL to be provided for aircraft；The electric energy of the parts E2 can be conveyed to the winged control system of aircraft respectively The uses such as system, steering engine, motor, load.

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 the mechanical energy that engine 41 generates can be converted to electric energy by generator 42, then electric energy is conveyed to by conducting wire winged Electrical appliance in machine.To which the energy that engine 41 generates is converted into conveying by conducting wire by generator 42, to avoid Loss in produced by conveying engine 41 energy process.It should be noted that：Such as above-mentioned first fuselage 10, second Fuselage 20 and third fuselage 30, the integral body of the provided unmanned plane of embodiment provided by the utility model be by：First fuselage 10, the second fuselage 20 and third fuselage 30 and form.The fuselage can also include the circuit control system of following unmanned plane, pass through The circuit control system of unmanned plane carries out the unmanned plane whole control.

Fig. 9 is referred to, further, in embodiment provided by the utility model, unmanned plane circuit control system can To include 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 Driving motor 482, third driving motor 483, the 4th driving motor 484.Wherein, engine 41, generator 42, voltage are turned Parallel operation 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 Dynamic motor 481, the second driving motor 482, third driving motor 483 and the 4th driving motor 484, as described above in Example. The ground remote control device 56 on flight control system 55 and ground carries out signal transmission, and then by being controlled from ground remote control device 56 to flight System 55 processed sends control instruction, and by flight control system 55 control the first steering engine 471 of unmanned plane, the second steering engine 472, Third steering engine 473, the first driving motor 481, the second driving motor 482, third driving motor 483 and the 4th driving motor 484 Working condition, and then realize the state of unmanned plane landing, flight is controlled.

It is noted that flight control system 55 mainly passes through turn of the first rotor 1211 in the first steering engine 471 of control In dynamic speed, the second steering engine 472 in the velocity of rotation of second rotor 1221, third steering engine 473 velocity of rotation of third rotor and It controls the first driving motor 481 and pulls linkage portion 3312, and then control tail rotor 33123 and moved up and down relative to the first vertical pivot 53 The angle change of constituted angle, and the first driving motor 481 of control drive second gear 51 to rotate, and then control tail rotor 33123 move left and right the angle change of constituted angle relative to the first vertical pivot 53.Reach and is 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 utility model provides a kind of airframe structure applied to unmanned plane, by that will be arranged in portion windward The diameter of section in portion windward is sequentially increased by cone structure on the direction towards the first noumenon, keeps the section of the first noumenon straight Diameter is sequentially reduced on the direction towards first connecting portion.And the first noumenon is fixedly connected with portion windward, is made first preposition Wing and the second forewing are symmetrically distributed in the both sides of the first noumenon along the center vertical pivot of the first noumenon.Then make windward Portion, the first noumenon and first connecting portion, which are integrally formed, constitutes the fuselage.Be in flight course in unmanned plane, integral body and When gas current friction, the resistance that air-flow generates on fuselage can be reduced.To reach the power capacity loss for reducing unmanned plane, favorably In the technique effect of the normal flight of unmanned plane.

It should be noted last that the above specific implementation mode is only to illustrate the technical solution of the utility model rather than limit System, although the utility model is described in detail with reference to example, it will be understood by those of ordinary skill in the art that, it can be right The technical solution of the utility model is modified or replaced equivalently, without departing from the spirit and model of technical solutions of the utility model It encloses, should all cover in the right of the utility model.

Claims (7)

1. a kind of airframe structure applied to unmanned plane, which is characterized in that a kind of airframe structure packet applied to unmanned plane It includes：

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 First forewing and second forewing are symmetrically distributed in described along the center vertical pivot of the first noumenon The both sides of one ontology, the first rotor are arranged on first forewing, and the second rotor is arranged in second forewing On；

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, constitutes the fuselage.

2. a kind of airframe structure applied to unmanned plane as described in claim 1, it is characterised in that：

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

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

Wherein, the described first preceding fastening end and first forward open end are the both ends of first forewing, described second Preceding fastening end and second forward open end are the both ends of second forewing.

3. a kind of airframe structure applied to unmanned plane as claimed in claim 2, it is characterised in that：

The first preceding fastening end and the second preceding fastening end are symmetrically distributed in institute along the center vertical pivot of the first noumenon State the both sides of the first noumenon.

4. a kind of airframe structure applied to unmanned plane as claimed in claim 3, it is characterised in that：

First forward open end is provided with one first storage region, the first fixation of first storage region and the first steering engine Seat is fixedly connected.

5. a kind of airframe structure applied to unmanned plane as claimed in claim 4, it is characterised in that：

Second forward open end is provided with one second storage region, the second fixation of second storage region and the second steering engine Seat is fixedly connected.

6. a kind of airframe structure applied to unmanned plane as claimed in claim 5, it is characterised in that：

First forewing subtracts in the described first preceding fastening end along the width on first forward open end direction successively It is small.

7. a kind of airframe structure applied to unmanned plane as claimed in claim 6, it is characterised in that：

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