CN206569248U - Multiaxis unmanned plane - Google Patents

Abstract

This disclosure relates to a kind of multiaxis unmanned plane, including fuselage (100) and rotor (200), the fuselage (100) is provided with first support arm (310) and second support arm (320) with extending transversely through, the rotor (200) is separately fixed at the two ends of the first support arm (310) and the second support arm (320), the fuselage (100) includes bottom plate (110), top plate (130), and the side plate (120) being parallel to each other stood between the bottom plate (110) and top plate (130), the through hole for passing through the first support arm (310) and the second support arm (320) is offered on the side plate (120), the bottom plate (110), top plate (130) and side plate (120) are respectively carbon plate.The hollow structure surrounded by bottom plate, side plate and top plate has a compact conformation, the high advantage of stability, and bottom plate, top plate and side plate are respectively carbon plate, can mitigate main screw lift, and the intensity of complete machine can be improved again.

Description

Multiaxis unmanned plane

Technical field

This disclosure relates to unmanned air vehicle technique field, in particular it relates to a kind of multiaxis unmanned plane.

Background technology

Multiaxis unmanned plane is multi-rotor unmanned aerial vehicle, and its main distinction is in fixed-wing unmanned plane, by taking four rotors as an example, four rotors Operation principle be：Quadrotor changes variable rotor speed by adjusting the rotating speed of four motors, realizes lift Change, so as to control posture and the position of aircraft.Existing multiaxis unmanned plane has problems, for example, complete machine structure compared with For heaviness, stability is poor；In addition, unmanned plane is when changing posture and position, it is brushless by flight control system regulation four The rotating speed of motor is realized, when unmanned plane is moved towards four direction in the horizontal plane, it is necessary to adjusted by flight control system Motor speed, which tilts fuselage, could carry out the motion of four direction (front and rear to left and right to), such case after certain angle Under, if other task devices of carry, such as head camera, infrared equipment, these equipment are in order to ensure the stabilization of task object Monitoring, then need also exist for also making banking motion therewith with the inclination of fuselage.

Utility model content

The purpose of the disclosure is to provide a kind of multiaxis unmanned plane, to solve unmanned plane structure bulky, the problem of stability is poor.

To achieve these goals, the disclosure provides a kind of multiaxis unmanned plane, including fuselage and rotor, and the fuselage is horizontal Penetratingly it is provided with first support arm and second support arm, the rotor is separately fixed at the first support arm and the second support arm Two ends, the fuselage includes bottom plate, top plate and the side plate being parallel to each other stood between the bottom plate and top plate, the side plate On offer through hole for passing through the first support arm and the second support arm, the bottom plate, top plate and side plate difference For carbon plate.

Alternatively, the fuselage is included in internal Longitudinal extending fuselage carbon pipe, and the fuselage carbon pipe is fixedly connected on described On bottom plate, top plate and side plate.

Alternatively, the side plate includes the front side board and back side panel that time interval is set, and the first support arm is described in Back side panel, the second support arm passes through the front side board.

Alternatively, compartment of terrain is supported by multiple connecting poles between the top plate and the bottom plate.

Alternatively, the first support arm and the second support arm are respectively round carbon pipe.

Alternatively, the rotor is connected with motor, and the motor is fixed on the first support arm or second The end of arm, the electric wire of the motor extends to the fuselage from the inside of the first support arm or the second support arm.

Alternatively, the motor is connected with electron speed regulator, and the electron speed regulator is arranged on the first support arm Or the inside of the second support arm, the electric wire of the electron speed regulator prolongs from the inside of the first support arm or the second support arm Extend the fuselage.

Alternatively, two pieces of batteries for being powered for the unmanned plane, two pieces of batteries pair are provided with the bottom plate Claim the longitudinal axis setting in the fuselage.

Alternatively, it is provided with the fuselage for the fixed interface for hanging over equipment.

Alternatively, it is provided with the first support arm and the second support arm on the shaft-like undercarriage of branch, the undercarriage It is provided with shock-damping structure.

By above-mentioned technical proposal, the hollow structure surrounded by bottom plate, side plate and top plate has compact conformation, stability High advantage, bottom plate, top plate and side plate are respectively carbon plate, can mitigate main screw lift, and the intensity of complete machine can be improved again.

Other feature and advantage of the disclosure will be described in detail in subsequent embodiment part.

Brief description of the drawings

Accompanying drawing is, for providing further understanding of the disclosure, and to constitute a part for specification, with following tool Body embodiment is used to explain the disclosure together, but does not constitute limitation of this disclosure.In the accompanying drawings：

Fig. 1 is the structural representation of the multiaxis unmanned plane of an embodiment according to the disclosure；

Fig. 2 is the internal structure schematic diagram of the multiaxis unmanned plane of an embodiment according to the disclosure；

Fig. 3 is the principle schematic rotated according to the support arm of an embodiment of the disclosure；

Fig. 4 is the structural representation of the first pipe clamp in embodiment shown in Fig. 2；

Fig. 5 is the structural representation of the second pipe clamp in embodiment shown in Fig. 2；

Fig. 6 is the structural representation of the first joint in embodiment shown in Fig. 2；

Fig. 7 is the structural representation of the second joint in embodiment shown in Fig. 2；

During Fig. 8 is the multiaxis unmanned plane according to an embodiment of the disclosure, the front view of support arm and rotor；

Fig. 9 is the corresponding top views of Fig. 8；

Figure 10 is the top view of the multiaxis unmanned plane according to Fig. 1, top plate not shown in it；

Figure 11 is the structural representation of the connector shown in Figure 10.

Description of reference numerals

The side plate of 100 fuselage, 110 bottom plate 120

The top plate of 121 front side board, 122 back side panel 130

The rotor of 140 connecting pole, 150 bearing block 200

The second support arm of 300 support arm, 310 first support arm 320

400 interfaces 500 first vert the pipe clamp of steering wheel 610 first

The pipe clamp of 611 first journal stirrup, 612 second journal stirrup 620 second

The joint of 630 connecting rod, 640 rocking arm 650 first

The shock-damping structure of 660 second joint, 700 undercarriage 710

The motor cabinet 830 second of 810 motor 820 verts steering wheel

The connector of 840 steering engine seat, 160 fuselage carbon pipe 170

The connecting portion of 171 sleeve part 172

Embodiment

It is described in detail below in conjunction with accompanying drawing embodiment of this disclosure.It should be appreciated that this place is retouched The embodiment stated is merely to illustrate and explained the disclosure, is not limited to the disclosure.

In the disclosure, in the case where not making opposite explanation, the noun of locality used such as " upper and lower " refers to that unmanned plane is flat and flown Upper and lower during state, " left and right " refers to left and right during unmanned plane flight forward, and " inside and outside " is typically to be directed to corresponding zero For profile of part itself.In addition, term " first " " second " used in the disclosure etc. be in order to distinguish a key element and Another key element, without succession and importance.

The Multi-axis aircraft that the disclosure is provided refers to the unmanned plane with multiple rotors, and the unmanned plane does not have wing, its Flight attitude is realized by lift variation of each rotor etc..Specifically, as shown in figure 1, can be laterally through on fuselage 100 There is support arm 300, rotor 200 is arranged on the two ends of support arm 300.The disclosure is by taking four axle unmanned planes as an example, that is, four rotor wing unmanned aerial vehicles, Including fuselage 100 and the first rotor, the second rotor, the 3rd rotor and the 4th rotor that are distributed on the surrounding of fuselage 100.Such as Fig. 1 With shown in Fig. 8, rotor 200 is connected with the motor 810 that rotor 200 can be driven to rotate, and motor 810 passes through motor cabinet 820 are arranged on the end of support arm 300.

As shown in figure 1, the fuselage 100 for the unmanned plane that the disclosure is provided can include bottom plate 110, top plate 130 and stand in bottom Offered on the side plate 120 being parallel to each other between plate 110 and top plate 130, side plate 120 for making first support arm 310 and second The through hole that support arm 320 is passed through, this hollow structure surrounded by bottom plate 110, side plate 120 and top plate 130 has compact conformation, The high advantage of stability, unmanned plane load can be placed in above-mentioned hollow structure.Wherein, bottom plate 110, top plate 130 and Side plate 120 is respectively carbon plate, can mitigate main screw lift, the intensity of complete machine can be improved again.

Further, fuselage 100 is additionally included in internal Longitudinal extending fuselage carbon pipe 160, and fuselage carbon pipe 160 is fixedly connected on On bottom plate 110, top plate 130 and side plate 120.There is the fuselage that bottom plate 110, top plate 130 and side plate 120 are surrounded with reference to above-mentioned 100 structure, fuselage carbon pipe 160 is arranged on inside fuselage 100, and the structure at four rotors 200 is during unmanned plane during flying Largely transmitted for the moment of flexure that fuselage 100 is produced by fuselage carbon pipe 160, seldom a part is transmitted by the grade of bottom plate 110 carbon plate, this Sample allows for fuselage 100 with a good Torsion Section, it is ensured that unmanned plane integrally-built stabilization in flight course Property.Specifically, as shown in Figure 10, the two ends of fuselage carbon pipe 160 can be respectively fixed with connector 170, connector 170 and set There is mounting hole to be fixed on bottom plate 110, top plate 130 and side plate 120.In one embodiment, as shown in figure 11, Connector 170 can include the sleeve part 171 for being used to regularly be set in the periphery of fuselage carbon pipe 160, and positioned at sleeve part 171 The connecting portion 172 for being used to fix with bottom plate 110, top plate 130 and side plate 120 in outside, connecting portion 172 is formed as flat board knot Structure, with the setting that can be fitted with bottom plate 110, top plate 130 and side plate 120, can closely be connected.The disclosure is to connector 170 Concrete structure be not limited, in other embodiments, connector 170 can be according to fuselage carbon pipe 160, bottom plate 110, top plate 130 and the concrete structure of the grade part of side plate 120 do the adjustment of adaptability.Connector 170 can be aluminium alloy plate, and cost is low simultaneously And it is lightweight.

Further, side plate 120 includes the front side board 121 and back side panel 122 that time interval is set, and first support arm 310 is worn The back side panel 122 is crossed, second support arm 320 passes through front side board 121.So, side plate 120 is designed as Split type structure, Ke Yijin One step mitigates the main screw lift of unmanned plane, and is conducive to carrying out the shape design of fuselage.For example shown in Fig. 1, top plate 130 and bottom The wide structure in narrow centre before and after plate 110 is formed as, front side board 121 and back side panel 122 may be mounted at top plate 130 and bottom plate 110 Narrower position and be slide plate, it is easy to process.Further, it is the stability of raising fuselage 100, top plate 130 and bottom plate 110 Between compartment of terrain be supported by multiple connecting poles 140, to avoid top plate 130 or the compressive deformation of bottom plate 110, connecting pole 140 can be Aluminum alloy material, its cost is relatively low, and lightweight, and stability is high.

In an embodiment of the disclosure, first support arm 310 and second support arm 320 are rotationally extended transversely through respectively In fuselage 100, rotor 200 is separately fixed at the two ends of first support arm 310 and the two ends of second support arm 320 can longitudinally incline Turn.Explanation is needed exist for, longitudinal direction here, which is verted, refers to rotor verting towards fore-and-aft direction, in addition, following horizontal strokes Referred to verting rotor towards fuselage verting laterally.In the case where support arm 300 can be rotated, rotor 200 can be with branch Arm 300 is together rotated, so, when unmanned plane is done it is longitudinally back and forth when, rotor 200 is verted certain angle, and it can either be provided Unmanned plane is maintained to the lift of certain altitude, the power that unmanned plane is moved forward and backward can be also provided, while fuselage 100 need not incline Tiltedly, have the advantages that the speed of response is fast, flying speed is high, and unmanned plane resistance in flight is greatly reduced.

In addition, as shown in figure 1, being provided with the interface 400 for fixing carry equipment on fuselage 100.Because unmanned plane exists When longitudinally back and forth, fuselage 100 keeps horizontality so that carry equipment also being capable of even running, it is ensured that task object Stability monitoring.Wherein, carry equipment is such as can be head camera, infrared equipment and laser radar.

Further, first support arm 310 is parallel with second support arm 320, and four rotors 200 are located at the four of a rectangular area Angle, stabilized structure.In addition, as shown in Fig. 2 being coaxially disposed bearing block 150, first in the through hole of above-mentioned side plate 120 Arm 310 and second support arm 320 are arranged on bearing block 150 by bearing, so that first support arm 310 and second support arm 320 are rotated Steadily, the response speed of rotor 200 is improved.

As shown in Figure 1 to Figure 3, be fixed with fuselage 100 for make that first support arm 310 and second support arm 320 rotate the One verts steering wheel 500.First steering wheel 500 that verts can be two, first support arm 310 and second support arm 320 be controlled respectively, at this In the case of kind, by circuit Coupling Design between two first steering wheels 500 that vert, it is ensured that the lift of four rotors 200 is controllable；The One vert steering wheel 500 can also be one, drive one of first support arm 310 and second support arm 320, in this case, By link gear between first support arm 310 and second support arm 320, so that the two can be synchronized with the movement, i.e. so that the first rotation The wing, the second rotor, the 3rd rotor and the 4th rotor can in the same direction before and after vert.

First form for verting the driving support arm 300 of steering wheel 500 can be verted the driving of steering wheel 500 first to be a variety of with first Exemplified by support arm 310, as shown in Fig. 3, Fig. 4 and Fig. 6, the first output end for verting steering wheel 500 is connected with rocking arm 640, first The periphery of arm 310 is closely arranged with the first pipe clamp 610 and enables the first pipe clamp 610 and first support arm 310 while rotating, The first journal stirrup 611 is formed with one pipe clamp 610, the first joint 650 is connected between the first journal stirrup 611 and rocking arm 640, first connects First 650 two ends are rotatably coupled with the first journal stirrup 611 and rocking arm 640 respectively.So, first vert steering wheel 500 driving shake Arm 640 is rotated, and rocking arm 640 drives the first pipe clamp 610 to rotate so that first support arm 310 can be rotated.

As shown in Figures 2 to 7, in the case where only setting one first steering wheel 500 that verts, above-mentioned link gear can be with Including the connecting rod 630 being connected between first support arm 310 and second support arm 320.Specifically, the periphery of first support arm 310 is close Ground is arranged with the first pipe clamp 610 and enables the first pipe clamp 610 and first support arm 310 while rotating, the periphery of second support arm 320 Closely it is arranged with the second pipe clamp 620 and enables the second pipe clamp 620 and second support arm 320 while rotating, the He of the first pipe clamp 610 The second journal stirrup 612 is respectively formed with second pipe clamp 620, the two ends of connecting rod 630 are respectively fixed with the second joint 660, and second connects First 660 are rotatably coupled respectively with the second journal stirrup 612 on two support arms 300.So, two support arms 300 can turn simultaneously It is dynamic.Verted by above-mentioned first based on the driving first support arm 310 of steering wheel 500, the setting of coupler link 630, rocking arm 640, the All it is rigidly connected, is adjusted during assembling between one joint 650, the second joint 660, the first pipe clamp 610 and the second pipe clamp 620 After position relationship between each part, unmanned plane is front and rear when verting in flight course, the first pipe clamp 610 and the second pipe clamp 620 can sync response, first support arm 310 and second support arm 320 can synchronous axial system, improve manipulation precision.In this feelings Under condition, first verts steering wheel 500 installed in the rear end of fuselage 100, for example, be fixed on bottom plate 110, so as to save in fuselage 100 The space in portion, for laying other parts, and in order to ensure the stability of unmanned plane during flying, first verts steering wheel 500 On the longitudinal axis that fuselage 100 can be arranged on, it is to avoid machine gravity is offset.

In addition, in the above-described embodiment, because connecting rod 630 is extended in the longitudinal, fuselage carbon pipe 160 is also extended in the longitudinal, Connecting rod 630 can be arranged on inside fuselage carbon pipe 160, can improve space availability ratio.

Further, as shown in Figure 2 and Figure 6, the one of the second joint 660 on the first joint 650 and the first pipe clamp 610 into Type, so as to save cost.Reference picture 6, in the first joint 650 and the junction of the second joint 660, the two is connected to On one journal stirrup 611 and the second journal stirrup 612, in the first joint 650 and the remote part of the second joint 660, the two is connected to On rocking arm 640 and connecting rod 630.

In addition, above-mentioned connecting rod 630, first support arm 310 and second support arm 320 can be respectively circle carbon pipe, it has Lighter weight and higher intensity.

Because the flight attitude of the multiaxis unmanned plane in the disclosure is controlled by rotor 200 completely, in order to which unmanned plane has enough Lift stop in the air, be in state during level based on rotor 200, first support arm 310 and second support arm 320 are towards front and rear Both direction can tilt angle be 0 ° -45 °, so that it is guaranteed that the dynamic property and stability of unmanned plane.The wherein He of first support arm 310 Second support arm 320 can tilt angle controlled by first steering wheel 500 that verts, the first control rocking arm 640 of steering wheel 500 that verts is swung When, it is 0 ° -45 ° in the angle swung towards both direction that can make rocking arm 640.

In another embodiment of the disclosure, rotor 200 can be arranged on the two ends of support arm 300 with laterally verting.This Sample, when unmanned plane does horizontal side-to-side movement, rotor 200 is verted certain angle towards both sides, and it can either be provided unmanned plane The lift of certain altitude is maintained at, the power of unmanned plane side-to-side movement can be also provided, while fuselage 100 need not be tilted so that Resistance of the unmanned plane in flight greatly reduces.When carry equipment is fixed with fuselage 100, carry equipment also can be transported steadily OK, it is ensured that the stability monitoring of task object.

Specifically, reference picture 1, Fig. 8 and Fig. 9, the end of support arm 300 are provided with steering engine seat 840, for driving rotor 200 second steering wheels 830 that vert laterally verted are fixed on steering engine seat 840, and motor cabinet 820 can be connected to described with laterally verting Second output end for verting steering wheel 830, such as motor cabinet 820 be arranged on second vert steering wheel 830 output revolving shaft on.So, When second vert steering wheel 830 act when, it 820 can be verted with motor seat towards both direction, and drive rotor 200 together Laterally vert.

In addition, in the present embodiment, state during level is in based on rotor 200, rotor 200 inclines towards inner side Gyration be 0 ° -10 °, towards outside can tilt angle be 0 ° -45 °.Due to the flight appearance of the multiaxis unmanned plane in the disclosure State is controlled by rotor 200 completely, by rotor 200 can tilt angle control within the specific limits, it can be ensured that unmanned plane it is dynamic Power and stability so that unmanned plane has enough lift to stop in the air.Meanwhile, to be touched when avoiding rotor 200 from verting inwardly Support arm 300 is hit, the angle that rotor 200 verts inwardly is smaller.Here the axis towards unmanned plane longitudinal direction, court are referred to towards inner side Refer to the direction opposite with the axis laterally.Specifically, for example when unmanned plane needs to full speed ahead laterally towards a left side, left side Two rotors 200 vert outwardly 45 °, two rotors on right side vert 10 ° inwardly, at the same adjust the left and right sides motor Power so that the lift that four rotors 200 are produced is identical.

It should be noted that two above-mentioned embodiments can be combined, i.e. rotor 200 can either longitudinally vert, and also can It is enough laterally to vert, it is achieved thereby that the omnidirectional of unmanned plane verts.Unmanned plane towards all directions when moving, and fuselage 100 is all the time Horizontality is kept, many is reduced to the free degree requirement for carrying task device, a greater variety of task devices can be carried To meet multiple-task requirement.In addition, rotor 200 either vert or laterally vert by longitudinal direction, it is receiving flight control system After the instruction of system, the speed of response made faster, improves the efficiency of task action.

In addition, in the above-mentioned embodiment of the disclosure, the longitudinal directions of four rotors 200 vert by support arm 300, connecting rod 630, The grade of rocking arm 640 linkage unit is realized, is laterally verted and is realized by being independently mounted at the structure of verting of the end of support arm 300.At it In his embodiment, it can also be transverse linkage that the linkage of four rotors 200, which is verted, for example, before being set in the both sides of fuselage 100 The rotatable pole extended afterwards, rotor 200 is arranged between the two ends of pole, two poles for example, by the company in the disclosure The structures such as bar 630 are attached, so as to realize the uniformity that four rotors 200 laterally vert.Other enable to the energy of rotor 200 Enough structures verted in the same direction are not done here to be repeated one by one, as long as so that each rotor 200 verts in the same direction in linkage, in the disclosure Protection domain in.By increasing linkage unit between individual each rotor 200, it can make it that the action of each rotor 200 is synchronous, protect Card being capable of quick response after actuating signal is received.

Further, when the first support arm 310 and second support arm 320 in the disclosure are the tubuloses such as circle carbon pipe as escribed above During structure, the electric wire of motor 810 can extend to fuselage 100 from the inside of support arm 300, with connection circuit, so that fully Space be make use of while also ensure that the terseness and aesthetic property of outward appearance.

Further, motor 810 is connected with electron speed regulator to change the rotating speed of rotor 200, and electron speed regulator is set Put in the inside of support arm 300, and, the electric wire of electron speed regulator extends from the inside of support arm 300 with motor 810 similarly To the fuselage, so as to take full advantage of space while also ensure that the terseness and aesthetic property of outward appearance.Electron speed regulator is installed In the position close to motor 810, it is ensured that compact conformation.

In addition, two pieces of batteries for being powered for unmanned plane are provided with the bottom plate 110 of fuselage 100, to ensure unmanned plane Endurance.The longitudinal axis that two pieces of batteries are symmetrical with fuselage 100 is set, positioned at the both sides of connecting rod 630, top plate 130 and bottom Between plate 110, to control the change of machine gravity on the longitudinal axis of fuselage 100 without departing from excessive.

As shown in figure 1, being provided with vertical undercarriage 700, the undercarriage on the support arm 300 for the unmanned plane that the disclosure is provided 700 be rod-like structure, is evenly distributed in the end of support arm 300, it is ensured that it is steady that unmanned plane lands.Further, undercarriage Shock-damping structure 710 is provided with 700, so as to absorb the most of impulsive force being subject to during unmanned plane landing.The shock-damping structure 710 such as can be ball or spring.

The preferred embodiment of the disclosure is described in detail above in association with accompanying drawing, still, the disclosure is not limited to above-mentioned reality The detail in mode is applied, in the range of the technology design of the disclosure, a variety of letters can be carried out with technical scheme of this disclosure Monotropic type, these simple variants belong to the protection domain of the disclosure.

It is further to note that each particular technique feature described in above-mentioned embodiment, in not lance In the case of shield, can be combined by any suitable means, in order to avoid unnecessary repetition, the disclosure to it is various can The combination of energy no longer separately illustrates.

In addition, can also be combined between a variety of embodiments of the disclosure, as long as it is without prejudice to originally Disclosed thought, it should equally be considered as disclosure disclosure of that.

Claims (10)

1. a kind of multiaxis unmanned plane, including fuselage (100) and rotor (200), it is characterised in that the fuselage (100) is laterally passed through It is provided with first support arm (310) and second support arm (320) with wearing, the rotor (200) is separately fixed at the first support arm (310) and the second support arm (320) two ends, the fuselage (100) includes bottom plate (110), top plate (130) and standing in institute State and offered on the side plate (120) being parallel to each other between bottom plate (110) and top plate (130), the side plate (120) for making institute State the through hole that first support arm (310) and the second support arm (320) are passed through, the bottom plate (110), top plate (130) and side plate (120) it is respectively carbon plate.

2. multiaxis unmanned plane according to claim 1, it is characterised in that the fuselage (100) is included in internal longitudinal direction and prolonged Fuselage carbon pipe (160) is stretched, the fuselage carbon pipe (160) is fixedly connected on the bottom plate (110), top plate (130) and side plate (120) on.

3. multiaxis unmanned plane according to claim 1, it is characterised in that the side plate (120) is set including time interval Front side board (121) and back side panel (122), the first support arm (310) pass through the back side panel (122), the second support arm (320) front side board (121) is passed through.

4. multiaxis unmanned plane according to claim 3, it is characterised in that the top plate (130) and the bottom plate (110) it Between compartment of terrain be supported by multiple connecting poles (140).

5. multiaxis unmanned plane according to claim 1, it is characterised in that the first support arm (310) and described second Arm (320) is respectively round carbon pipe.

6. multiaxis unmanned plane according to claim 5, it is characterised in that the rotor (200) is connected with motor (810), the motor (810) is fixed on the end of the first support arm (310) or second support arm (320), the driving The electric wire of motor (810) extends to the fuselage from the inside of the first support arm (310) or the second support arm (320) (100)。

7. multiaxis unmanned plane according to claim 6, it is characterised in that the motor (810) is connected with electronics tune Fast device, the electron speed regulator is arranged on the inside of the first support arm (310) or the second support arm (320), the electronics The electric wire of speed regulator extends to the fuselage from the inside of the first support arm (310) or the second support arm (320).

8. multiaxis unmanned plane according to claim 1, it is characterised in that being provided with the bottom plate (110) is used for for institute Two pieces of batteries that unmanned plane is powered are stated, the longitudinal axis that two pieces of batteries are symmetrical with the fuselage (100) is set.

9. multiaxis unmanned plane according to claim 1, it is characterised in that be provided with the fuselage (100) for fixing Hang over the interface (400) of equipment.

10. multiaxis unmanned plane according to claim 1, it is characterised in that the first support arm (310) and described second It is provided with arm (320) on the shaft-like undercarriage (700) of branch, the undercarriage (700) and is provided with shock-damping structure (710).