(19)
(11)EP 3 202 662 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
24.06.2020 Bulletin 2020/26

(21)Application number: 16832251.9

(22)Date of filing:  27.07.2016
(51)Int. Cl.: 
B64C 1/06  (2006.01)
B64C 27/08  (2006.01)
(86)International application number:
PCT/CN2016/091932
(87)International publication number:
WO 2017/020763 (09.02.2017 Gazette  2017/06)

(54)

UNMANNED AERIAL VEHICLE

UNBEMANNTES LUFTFAHRZEUG

VÉHICULE AÉRIEN SANS PILOTE


(84)Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

(30)Priority: 31.07.2015 CN 201510468299
31.07.2015 CN 201520574460 U
31.07.2015 CN 201510467838

(43)Date of publication of application:
09.08.2017 Bulletin 2017/32

(73)Proprietor: Guangzhou Xaircraft Technology Co., Ltd.
Guangzhou, Guangdong 510000 (CN)

(72)Inventors:
  • HE, Jianbing
    Guangzhou Guangdong 510000 (CN)
  • LIN, Zhiwen
    Guangzhou Guangdong 510000 (CN)
  • JIANG, Pan
    Guangzhou Guangdong 510000 (CN)
  • XIAO, Dingfeng
    Guangzhou Guangdong 510000 (CN)
  • PENG, Bin
    Guangzhou Guangdong 510000 (CN)

(74)Representative: Romano, Giuseppe et al
Società Italiana Brevetti S.p.A Piazza di Pietra, 39
00186 Roma
00186 Roma (IT)


(56)References cited: : 
WO-A1-2009/115300
WO-A2-2008/147484
CN-A- 104 670 499
CN-A- 104 691 749
CN-U- 203 681 871
CN-U- 204 399 473
CN-U- 204 998 762
JP-A- 2009 269 493
US-A1- 2013 287 577
WO-A1-2012/162421
CN-A- 104 354 864
CN-A- 104 670 499
CN-A- 105 173 068
CN-U- 204 056 294
CN-U- 204 895 873
DE-A1-102008 018 901
TW-A- 201 526 967
US-A1- 2014 263 822
  
      
    Note: Within nine months from the publication of the mention of the grant of the European patent, any person may give notice to the European Patent Office of opposition to the European patent granted. Notice of opposition shall be filed in a written reasoned statement. It shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention).


    Description

    FIELD



    [0001] The present disclosure relates to the field of unmanned aerial vehicles.

    BACKGROUND



    [0002] An unmanned aerial vehicle is an unmanned aircraft manipulated by means of radio remote control equipment and a self-contained program control device. The application of the unmanned aerial vehicle has expanded to a plurality of civil fields. The unmanned aerial vehicle represented by agricultural applications usually adopts a form of multiple rotor wings, and is an aircraft having a plurality of propellers, and a plurality of aircraft arms for arrangement of the propellers which are in a crossed form. As the plurality of propellers are arranged around the aircraft and provide approximately equal lift forces, the total lift force is equivalent to acting on an intersection point of the aircraft arms, i.e. a geometric center of a plane where an airframe is. Thus, other weight-bearing components of the unmanned aerial vehicle are arranged upon and/or below the geometric center so as to make an acting point of the total gravity of the aircraft close to the geometric center of the plane of the airframe as much as possible, thus keeping a balance with the total lift force.

    [0003] However, the above configuration results in much mass distributed in a vertical direction of the unmanned aerial vehicle, and once the force acting on the aircraft in vertical direction changes, it is easy to produce an uncontrollable overturning force moment, which causes the aircraft bumping and losing balance.

    [0004] According to TW 201526967A, a foldable special-shaped six-rotary-wing flight vehicle includes a vehicle body, a control unit, two front-wing rods, two rear-wing rods, two side-wing rods, six rotary wings, and a battery. Each front-wing rod has one end fixed to the vehicle body and the other end extended from the front end of the vehicle body and expanded with a predetermined angle. Each rear-wing rod has one end fixed to the vehicle body and the other end extended from the rear end of the vehicle body and expanded with a predetermined angle. The front-wing rod has a length shorter than that of the rear-wing rod. The angle between the two front-wing rods is greater than that between the two rear-wing rods. Each side-wing rod has one end moveably connected to the vehicle body and the other end extended from two sides of the vehicle body. The two side-wing rods can be used to adjust a sweep angle. The six rotary wings are arranged on the two front-wing rods, the two rear-wing rods and the two side-wing rods, and are electrically connected to the control unit. The battery is arranged on the vehicle body and is electrically connected to the control unit for providing the power source required to rotate the rotary wings. As a result, the present invention is able to achieve the functions of easily identifying the headed direction, avoiding photographing the flight vehicle, and conveniently carrying the flight vehicle.

    [0005] According to DE102008018901A1, the aircraft (1) has a drive device comprising an even number of impeller drives (2, 2a, 2b), which produce an air jet for driving the aircraft, where the air jet counteracts a gravitation force. The impeller drives are formed such that rotors of two of the impeller drives rotate in a same direction. The impeller drives have an outlet area in which an outlet opening is arranged. The outlet area has a middle axis, which is inclined on a main plane of a support construction (3) against a plumb line for stabilizing flight characteristics of the aircraft.

    [0006] According to WO 2012162421A1, flying electric generator aircraft that include groupings of four rotors mounted to booms extending fore and aft of a fuselage structure wherein the rotors are placed so that when the aircraft is facing the wind, each rotor has a direct path to an undisturbed flow of air, regardless of pitch angle and during all flight maneuvers of the aircraft. The rotors are placed in counter-rotating pairs with the booms preferably angled so that the rotors in the front of the aircraft are spaced at a distance from one another that is different than a spacing of the rotors at the rear of the aircraft.

    SUMMARY



    [0007] The present disclosure seeks to solve one of the technical problems existing in the related art to at least some extent.

    [0008] Aiming at the defects in the prior art, embodiments of the present disclosure need to provide an unmanned aerial vehicle having a reasonable aircraft structure and reasonable weight disclosure, so as to make the unmanned aerial vehicle fly stably and be controlled simply.

    [0009] In order to solve the technical problems above, the invention is defined in claim 1.

    [0010] For the unmanned aerial vehicle provided in the above technical solution, the arms are connected to a front portion of the airframe, and the arms as well as an intersection point of the extension lines are moved forward relative to the center of the airframe, which spares space for disposing the articles storing device behind the airframe, prevents much mass distributed in a vertical direction of the unmanned aerial vehicle, and making the control over the unmanned aerial vehicle easy and stable.

    [0011] The arm may be formed to be a linear shape or an arc shape, which allows a plenty of available space to be spared between the arms in two sides so as to store or install other objects.

    [0012] The arm may be provided with at least two arm fixing pieces, and each of the arm fixing pieces includes: a first fixing portion connected with the airframe; and a second fixing portion connected with the airframe, the first fixing portion and the second fixing portion are connected and fitted with each other to define a mounting groove, the arm is disposed through the mounting groove, and the first fixing portion and the second fixing portion are separately provided with at least one outer flat surface connected with the airframe.

    [0013] Two or more arm fixing pieces spaced apart are adopted, making the airframe, the arm fixing pieces and the arms connected as a whole, the plurality of the arm fixing pieces are locked in a plurality of places, which ensures that the arm is not easy to swing in an axial direction. In addition, the arm is fixed to the plurality of the arm fixing pieces at a demanded deflection angle, the arm fixing pieces at the same side are flushed with an airframe plane, and then the arm is mounted to the airframe, which ensures that a deflection angle of the arm relative to the airframe plane is a demanded constant value.

    [0014] The arm may be provided with an arm deflection locking hole, the first fixing portion and the second fixing portion being provided with an arm deflection fixing hole in a position corresponding to the arm deflection locking hole. The arm may be locked in a radial direction of the arm, and be prevented from swinging in the axial direction when the arm is locked in a plurality of spaced positions along the axial direction of the arm.

    [0015] The first fixing portion and the second fixing portion may be separately provided with an arc inner surface matching with an outer wall of the arm. Thus, it is possible to enlarge an area of a contact surface of the first fixing portion and the second fixing portion with the arm, so as to increase friction and avoid sliding.

    [0016] The first fixing portion and the second fixing portion may separately be provided with an arm fastening hole for bolted connection with each other and an airframe connecting hole for bolted connection with the airframe.

    [0017] A folding cavity body, an adaptor and a sprinkle-nozzle foldable rod may be disposed below the arm, a driving assembly is disposed within the folding cavity body, a central portion of the adaptor is articulated within the folding cavity body, a front end of the adaptor is connected with the driving assembly, and a rear end of the adaptor passes through an opening of the folding cavity body and is fixedly connected with a first end of the sprinkle-nozzle foldable rod. By means of the foldable sprinkle-nozzle foldable rod, the sprinkle-nozzle foldable rod may be folded and stored in an un-working state, which is convenient for packaging and transportation and can prevent a sprinkling piece or other components disposed to the rod from touching the ground. When the unmanned aerial vehicle is used for spraying, the sprinkle-nozzle foldable rod may be unfolded to make the sprinkling piece to stretches below a bracket of the unmanned aerial vehicle, thus avoiding formation of a droplet phenomenon due to aggregation of fogdrops.

    [0018] The driving assembly may include a driving body, a driving shaft and a connection portion mounted within a casing. The driving shaft may be rotatably connected with the driving body and the connection portion, and the driving body is used to drive the driving shaft to rotate so that the connection portion pushes the adaptor to rotate relative to the casing between a first position and a second position. The driving body may be configured as a gear motor, the driving shaft is configured as a screw rod, and the connection portion is configured as a sliding block. The driving method is easy to realize and is also stable and reliable.

    [0019] An outer wall of the driving shaft may be provided with an outer thread, the connection portion being provided with a fitting hole, an inner wall bounding the fitting hole being provided with an inner thread, the driving shaft going through the connection portion, and the outer thread being fitted with the inner thread. The transmission control accuracy can be improved by means of connecting the driving shaft and the connection portion in a threaded manner.

    [0020] A first end of the driving shaft away from the driving body may be provided with a thrust bearing, the thrust bearing being fixed within the casing, and the driving shaft is rotatably disposed through the thrust bearing.

    [0021] A front end of the adaptor is formed to be a U-shaped groove and the connection portion is arranged in the U-shaped groove.

    [0022] The unmanned aerial vehicle may include: a control module used to control the driving assembly to drive the adaptor to rotate; and a current detection module, in which the current detection module is used to detect whether a current of the driving assembly is larger than a preset threshold, if the current of the driving assembly is not larger than the preset threshold, the current detection module is used to continue detecting whether the current of the driving assembly is larger than the preset threshold, and if the current of the driving assembly is larger than the preset threshold, the current detection module is used to send a control signal for turning off the driving assembly to the control module; the control module is used to turn off the driving assembly according to the control signal.

    [0023] A heat dissipation waterproof cover is disposed on an upper end face of the rotor-wing electric motor, the heat dissipation waterproof cover includes an upper sealing surface and a sidewall circumferential surface, a certain number of ventilation holes are disposed in the sidewall circumferential surface adjacent to the upper sealing surface, and a blade distant from a center of the heat dissipation waterproof cover is disposed in the heat dissipation waterproof cover and extends from the ventilation hole towards a center of an inner wall of the upper sealing surface. The heat dissipation waterproof cover is rotated along with a rotor of the rotor-wing electric motor as the rotor is rotated, and the blade inside the heat dissipation waterproof cover is rotated around a circle center, which makes the hot air produced by the rotation of the rotor-wing electric motor be thrown out by a centrifugal force produced by the rotation of the blade. Meanwhile, a negative pressure is produced in the heat dissipation waterproof cover, an airstream enters into a lower portion of the rotor-wing electric motor, and flows out from the ventilation hole of the sidewall circumferential surface after being thrown out by the centrifugal force, thereby keeping the airstream flowing to dissipate heat for the rotor-wing electric motor. In addition, as an upper end face of the heat dissipation waterproof cover of the rotor-wing electric motor covers an upper portion of the electric motor, rain cannot enter the rotor-wing electric motor from the upper portion, and is blown away by the high-speed airstream thrown out of the ventilation hole when flowing towards a joint area of the upper end face of the heat dissipation waterproof cover and the sidewall circumferential surface, which ensures that the rain cannot enter the heat dissipation waterproof cover, thus playing a waterproof role.

    [0024] An annular cavity fitted with an air hole inside the rotor-wing electric motor may be formed between the center of the inner wall center of the upper sealing surface and the blade.

    [0025] A height of a portion of the blades near the center of the inner wall center of the upper sealing surface may be smaller than a height of another portion of the blades near the ventilation hole.

    [0026] The advantages of the present disclosure are that: the structure is simple and reasonable, which distributes the weight of the unmanned aerial vehicle in front and in rear of the airframe equally, reduces a proportion of heavy objects distributed in a vertical direction of the unmanned aerial vehicle, and thus makes the control over the unmanned aerial vehicle simpler and more stable; in addition, the arm is connected to the front portion of the airframe, which spares valuable storing spaces in the central portion and rear portion; and with this tiled and unobstructed design, objects in the storing spaces are easy to be taken out and put in.

    [0027] Aiming at the defects in the prior art, the unmanned aerial vehicle provided in the present disclosure may also have the following additional technical features.

    [0028] In some embodiments of the present disclosure, the lift force center is adjacent to a geometric center of the articles storing device.

    [0029] In some embodiments of the present disclosure, the gravity center of the unmanned aerial vehicle, the lift force center and the geometric center of the articles storing device coincide.

    [0030] In some embodiments of the present disclosure, two front arms and two rear arms are provided.

    [0031] In some embodiments of the present disclosure, an included angle between the two front arms is larger than an included angle between the two rear arms.

    [0032] In some embodiments of the present disclosure, a length of the rear arm is larger than a length of the front arm.

    [0033] In some embodiments of the present disclosure, the second ends of the two front arms and the second ends of the two rear arms are located in four vertexes of a rectangle.

    [0034] In some embodiments of the present disclosure, the second ends of the two front arms and the second ends of the two rear arms are located in four vertexes of a square.

    [0035] In some embodiments of the present disclosure, the rear arm is configured to be a linear shape or an arc shape.

    [0036] In some embodiments of the present disclosure, the front end of the airframe includes a front arrangement plate, and the front arrangement plate is provided with the control module, the current detection module and an auxiliary device of the unmanned aerial vehicle. A battery of the unmanned aerial vehicle is disposed within the articles storing device.

    [0037] Additional aspects and advantages of the present disclosure will be given in part in the following descriptions, become apparent in part from the following descriptions, or be learned from the practice of the present disclosure.

    BRIEF DESCRIPTION OF THE DRAWINGS



    [0038] 

    Fig. 1 is a top view of an unmanned aerial vehicle of embodiments of the present disclosure;

    Fig. 2 is a partially enlarged view of portion D in Fig. 1;

    Fig. 3 is a front view of an arm, a first fixing portion, a second fixing portion and a rotor-wing electric motor in Fig. 1 assembled together;

    Fig. 4 is a partially exploded view of the arm and the rotor-wing electric motor in Fig. 3;

    Fig. 5 is a right view of assembled arm and rotor-wing electric motor in Fig. 3, in which the rotor-wing electric motor is in a deflected state relative to the arm;

    Fig. 6 is a front view of the sprinkle-nozzle foldable rod for fixing the sprinkle nozzle of the unmanned aerial vehicle in Fig. 1, in which it is in an unfolded state;

    Fig. 7 is a schematic view of the sprinkle-nozzle foldable rod for fixing the sprinkle nozzle in Fig. 6 where the sprinkle-nozzle foldable rod is in a folded state in another angle of view;

    Fig. 8 is an exploded view of a folding cavity body in Fig. 6;

    Fig. 9 is a schematic view of Fig. 8 in another angle of view;

    Fig. 10 is an exploded view of a heat dissipation waterproof cover and a rotor-wing electric motor in embodiments of the present disclosure;

    Fig. 11 is an assembling view of the heat dissipation waterproof cover and the rotor-wing electric motor in Fig. 10;

    Fig. 12 is a perspective view of the heat dissipation waterproof cover in Fig. 10;

    Fig. 13 is a schematic view of a blade distant from a center of the heat dissipation waterproof cover in other embodiments of the present disclosure;

    Fig. 14 is a side view of the heat dissipation waterproof cover in Fig. 10.


    Reference numerals:



    [0039] 

    100: unmanned aerial vehicle;

    1: unmanned aerial vehicle body; 101: front arm; 102: rear arm; 93a: front electric motor; 93b: rear electric motor;

    2: airframe; 3: front arrangement plate; 4: articles storing device;

    10: first fixing portion; 11: second fixing portion; 12: arm deflection locking hole; 13: arm fastening hole; 14: airframe connecting hole; 15: arm deflection fixing hole; 16: arc inner surface;

    41: sprinkling piece; 422: electric motor for sprinkle-nozzle rotation;

    81: folding cavity body; 811: left side casing; 812: right side casing; 813: linear sliding groove; 814: circular hole; 815: first end face;

    82: adaptor; 821: U-shaped groove; 822: convex shaft; 823: mounting hole of sprinkle-nozzle foldable rod; 824: hollow hole; 825: first contact surface;

    83: sprinkle-nozzle foldable rod; 831: sliding block; 832: screw rod;

    86: water outlet pipe adaptor; 87: signal interface circuit plate; 88: gear motor; 89: thrust bearing;

    90: heat-dissipation waterproof cover; 9: screw; 92: sidewall circumferential surface; 93: rotor-wing electric motor; 911: blade; 912: inner wall of sidewall circumferential surface; 913: positioning hole; 914: upper sealing surface; 915: ventilation hole; 916: annular cavity;

    A: first intersection point; B; second intersection point; C: lift force center; E: intersection region;

    α: included angle between two rear arms; γ: included angle between two front arms


    DETAILED DESCRIPTION



    [0040] Embodiments of the present disclosure will be described in detail in the following. Examples of the embodiments are shown in the drawings, and the same or similar elements and the elements having same or similar functions are denoted by like reference numerals throughout the descriptions. The embodiments described with reference to the drawings are illustrative, which is only used to explain the present disclosure and shouldn't be construed to limit the present disclosure.

    [0041] In the specification, it should be understood that terms such as "axial direction", "circumferential direction", "up", "down" ,"front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" should be construed to refer to the orientation as then described or as shown in the drawings under discussion. These relative terms are for convenience of description and do not require that the present disclosure be constructed or operated in a particular orientation, so shall not be construed to limit the present disclosure. In addition, terms such as "first" and "second" are used herein for purposes of description and are not intended to indicate or imply relative importance or significance or to imply the number of indicated technical features. Thus, the feature defined with "first" and "second" may comprise one or more of this feature. In the description of the present invention, "a plurality of' means two or more than two, unless specified otherwise.

    [0042] In the present invention, it should be noted that, unless specified or limited otherwise, the terms "mounted," "connected," "coupled," should be understood broadly, and may be, for example, fixed connections, detachable connections, or integral connections; may also be mechanical or electrical connections; may also be direct connections or indirect connections via intervening structures; may also be inner communications or interaction relationships of two elements, which can be understood by those skilled in the art according to specific situations.

    [0043] In the present invention, unless specified or limited otherwise, a structure in which a first feature is "on" or "below" a second feature may include an embodiment in which the first feature is in direct contact with the second feature, and may also include an embodiment in which the first feature and the second feature are not in direct contact with each other, but are contacted via an additional feature formed therebetween. Furthermore, a first feature "on," "above," or "on top of' a second feature may include an embodiment in which the first feature is right or obliquely "on," "above," or "on top of' the second feature, or just means that the first feature is at a height higher than that of the second feature; while a first feature "below," "under," or "on bottom of' a second feature may include an embodiment in which the first feature is right or obliquely "below," "under," or "on bottom of' the second feature, or just means that the first feature is at a height lower than that of the second feature.

    [0044] The present disclosure will be illustrated in detail with reference to drawings and in combination with the embodiments.

    [0045] As shown in Fig. 1, in embodiments of the present disclosure, a head portion of an unmanned aerial vehicle 100 is located at the front and a tail portion of the unmanned aerial vehicle 100 is located at the rear.

    [0046] The unmanned aerial vehicle 100 according to embodiments of the present disclosure is described with reference to Fig. 1 to Fig. 17 in the following. As shown in Fig. 1 to Fig. 17, the unmanned aerial vehicle 100 includes an unmanned aerial vehicle body 1, an arm and a rotor-wing electric motor 93.

    [0047] Referring to Fig. 1, the unmanned aerial vehicle body 1 includes an airframe 2 and an articles storing device 4 disposed behind the airframe 2 and used to store a variable weight part.

    [0048] The arm includes a front arm 101 and a rear arm 102, and the rotor-wing electric motor 93 includes a front electric motor 93a and a rear electric motor 93b.

    [0049] At least two front arms 101 are provided and symmetrically arranged with respect to a central axis of the airframe 2 along a front-rear direction, a first end of each of the front arms 101 is connected with a front end of the airframe 2, and a second end of each of the front arms 101 is provided with the front electric motor 93a so as to drive the unmanned aerial vehicle 100.

    [0050] At least two rear arms 102 are provided and symmetrically arranged with respect to the central axis of the airframe, a first end of each of the rear arms 102 is connected with a rear end of the airframe 2, and a second end of each of the rear arms 102 is provided with the rear electric motor 93b so as to drive the unmanned aerial vehicle 100.

    [0051] In some embodiments of the present disclosure, as shown in Fig. 1 and Fig. 2, an intersection region E of an extension line of the rear arm 102 towards the airframe 2 and an extension line of the front arm 101 towards the airframe 2 is located in front of a lift force center C of the unmanned aerial vehicle 100, an acting point of a resultant force from the front electric motor 93a and the rear electric motor 93b exerted on the unmanned aerial vehicle 100 is the lift force center C, and a gravity center of the unmanned aerial vehicle 100 is adjacent to the lift force center C.

    [0052] The extension line of the rear arm 102 towards the airframe 2 intersects with the central axis of the airframe 2 at a first intersection point A, and the extension line of the front arm 101 towards the airframe 2 intersects with the central axis of the airframe 2 at a second intersection point B. As shown in Fig. 1, the extension line, towards the airframe 2, of the rear arm 102 in a right-back direction and the extension line, towards the airframe 2, of the front arm 101 in a left-front direction coincide approximately; the extension line, towards the airframe 2, of the rear arm 102 in a left-back direction and the extension line, towards the airframe 2, of the front arm 101 in a left-front direction coincide approximately; the extension line of the rear arm 102 towards the airframe 2 intersects with the extension line of the front arm 101 towards the airframe 2 substantially in a midpoint between the first intersection point A and the second intersection point B; and the midpoint of the first intersection point A and the second intersection point B is located in front of the lift force center C of the unmanned aerial vehicle 100. In some embodiments of the present disclosure, the first intersection point A and the second intersection point B are both located in front of the lift force center C of the unmanned aerial vehicle 100.

    [0053] It could be understood that, a junction of the rear arm 102 and the airframe 2 is located in the middle of the unmanned aerial vehicle body 1, a junction of the front arm 101 and the airframe 2 is located in the front of the unmanned aerial vehicle body 1, the lift force center C of the unmanned aerial vehicle 100 is located in a position rear of the center of the unmanned aerial vehicle body 1.Thus, a mounting space for the articles storing device 4 is defined in the position rear of the center of the unmanned aerial vehicle body 1 to makes the gravity center of the unmanned aerial vehicle 100 close to the lift force center C, which is beneficial for the front electric motor 93a and the rear electric motor 93b to drive the unmanned aerial vehicle 100.

    [0054] The gravity center of the unloaded unmanned aerial vehicle 100 is adjacent to the lift force center C of the unmanned aerial vehicle 100, and a gravity center of the articles (the variable weight part) loaded by the unmanned aerial vehicle 100 is also adjacent to the lift force center C of the unmanned aerial vehicle 100, such that a position of the gravity center of the unmanned aerial vehicle 100 changes slightly when the loaded unmanned aerial vehicle 100 is changed into an unloaded state.

    [0055] For the unmanned aerial vehicle 100 according to embodiments of the present disclosure, by moving the front arm 101 and the rear arm 102 of the unmanned aerial vehicle 100 forward, an influence of the articles (the variable weight part) loaded in the unmanned aerial vehicle 100 on the position of the gravity center of the unmanned aerial vehicle 100 can be reduced, so as to control the unmanned aerial vehicle 100 stably and reduce a difficulty in controlling the unmanned aerial vehicle 100.

    [0056] In some embodiments of the present disclosure, the front electric motor 93a and the rear electric motor 93b may be electric motors of the same type so as to decrease the kinds of the parts and components of the unmanned aerial vehicle 100, simplify a production process of the unmanned aerial vehicle 100 and reduce a production cost of the unmanned aerial vehicle 100.

    [0057] In some embodiments of the present disclosure, a plurality of hollow structures may be provided in the airframe 2 of the unmanned aerial vehicle 100 so as to reduce the weight of the unmanned aerial vehicle 100, which is beneficial to making the unmanned aerial vehicle 100 lightweight.

    [0058] In some embodiments of the present disclosure, as shown in Fig. 1, the lift force center C of the unmanned aerial vehicle 100 may be adjacent to a geometric center of the articles storing device 4. The gravity center of the articles (the variable weight part) loaded in the articles storing device 4 is adjacent to the geometric center of the articles storing device 4, and for liquids or powders, the gravity center thereof and the geometric center of the articles storing device 4 substantially coincide. The geometric center of the articles storing device 4 is disposed in a position adjacent to the lift force center C of the unmanned aerial vehicle 100, which is beneficial to reducing the influence of the articles (the variable weight part) on the gravity center of the unmanned aerial vehicle 100, and is convenient for controlling the unmanned aerial vehicle 100 when the weight of the unmanned aerial vehicle 100 is in a dynamic state (for example unloading the articles i.e. the variable weight part gradually).

    [0059] In some embodiments of the present disclosure, the gravity center of the unmanned aerial vehicle 100, the lift force center C of the unmanned aerial vehicle 100 and the geometric center of the articles storing device 4 may coincide so as to reduce an influence of the variable weight part on the gravity center of the unmanned aerial vehicle 100.

    [0060] In some embodiments of the present disclosure, the front end of the airframe 2 may include a front arrangement plate 3, and the front arrangement plate 3 is provided with a control module, a current detection module and an auxiliary device of the unmanned aerial vehicle 100. A battery of the unmanned aerial vehicle 100 is disposed within the articles storing device 4.

    [0061] It could be understood that, a constant weight part of the unmanned aerial vehicle 100 may include the unmanned aerial vehicle body 1, the front arm 101, the rear arm 102, the control module, the current detection module, the auxiliary device and the battery. The control module, the current detection module and the auxiliary device which are light are disposed in a front end of the unmanned aerial vehicle body 1, whereas the battery which is heavy is disposed in the rear end of the airframe 2, such that a gravity center of the constant weight part of the unmanned aerial vehicle 100 is located in the position rear of the center of the unmanned aerial vehicle body 1, which is beneficial to the balance of the unmanned aerial vehicle 100 and the arrangement of the variable weight part. In addition, the constant weight part and the variable weight part may be arranged as tiled in the front-rear direction, which is beneficial to remaining the gravity center of the unmanned aerial vehicle 100 around the airframe 2 in a gravity direction, and preventing the gravity center of the unmanned aerial vehicle 100 from rising or falling in the gravity direction. In addition, the variable weight part is arranged in an unobstructed position, which is beneficial for the loading and unloading of the variable weight part.

    [0062] In some embodiments of the present disclosure, at least a part of batteries may be disposed in a rear end of the articles storing device 4. In other words, at least part of the batteries may be disposed behind the variable weight part so as to reduce the influence on the gravity center of the unmanned aerial vehicle 100 when the articles (the variable weight part) are released, thus making it easy to control the unmanned aerial vehicle 100.

    [0063] In some embodiments of the present disclosure, two front arms 101 may be provided, four rear arms 102 may be provided, and the four rear arms 102 may be symmetrically disposed in two sides of the central axis. In some embodiments of the present disclosure, four front arms 101 may be provided, four rear arms 102 may be provided, the four front arms 101 may be symmetrically disposed in two sides of the central axis, and the four rear arms 102 may be symmetrically disposed in two sides of the central axis. The numbers of the front arm 101 and the rear arm 102 are not limited thereto.

    [0064] In some embodiments of the present disclosure, as shown in Fig. 1, two front arms 101 may be provided and disposed symmetrically in two sides of the central axis, and two rear arms 102 may be provided and disposed symmetrically in two sides of the central axis. Thus the unmanned aerial vehicle 100 can be provided with a sufficient driving force and have a simple structure.

    [0065] As shown in Fig. 1 and Fig. 2, the second intersection point B is located between the first intersection point A and the lift force center C.

    [0066] On one hand, it is helpful to spare a plenty of space around the lift force center C of the unmanned aerial vehicle 100 to load articles (the variable weight part), which makes the gravity center of the articles (the variable weight part) close to the lift force center C of the unmanned aerial vehicle 100 so as to reduce the influence of the variable weight part on the gravity center of the unmanned aerial vehicle 100, and as a result the unmanned aerial vehicle 100 is easy to operate.

    [0067] On the other hand, by providing the above structure, it equals to adding two triangular structures to the unmanned aerial vehicle 100. As shown in Fig. 2, the first intersection point A and the second intersection point B are common vertexes of the two triangles, for example, one of the two triangles is configured as a triangle of which a connection line of A and B serves as a first base and an intersection point of the extension line, towards the airframe 2, of the front arm 101 in the left-front direction and the extension line, towards the airframe 2, of the rear arm 102 in the left-back direction serves as a first fixed point, and the other triangle is configured as a triangle of which the connection line of A and B serves as a second base and an intersection point of the extension line, towards the airframe 2, of the front arm 101 in the right-front direction and the extension line, towards the airframe 2, of the rear arm 102 in the right-back direction serves as a second fixed point. Thus the unmanned aerial vehicle 100 has a stable structure.

    [0068] As shown in Fig. 2, a first included between the two rear arms 102 is α, a second included between the two front arms 101 is γ, and α and γ meet: α<γ. Relative to the two front arms 101, the two rear arms 102 may be retracted towards a direction close to the central axis so that the lift force center C of the unmanned aerial vehicle 100 is moved backwards.

    [0069] In some embodiments of the present disclosure, the first intersection point A may be disposed adjacent to or substantially coincide with the second intersection point B, such that spaces in a central portion and a rear portion of the unmanned aerial vehicle 100 are enlarged.

    [0070] In some embodiments of the present disclosure, as shown in Fig. 1, a length of the rear arm 102 may be larger than a length of the front arm 101. That is, a distance from the second end (the end mounted with the rear electric motor 93b) of the rear arm 102 to the first intersection point A may be larger than a distance from the second end (the end mounted with the front electric motor 93a) of the front arm 101 to the second intersection point B. As the junction of the rear arm 102 with the airframe 2 and that of the front arm 101 with the airframe 2 are both moved forward, by providing the above structure, the unmanned aerial vehicle 100 has a good balance performance and is convenient to control.

    [0071] In some embodiments of the present disclosure, as shown in Fig. 1, the rear arm 102 may be configured as a linear shape.

    [0072] In some embodiments of the present disclosure, the rear arm 102 may be configured as an arc shape.

    [0073] In some embodiments of the present disclosure, for the front arm 101 and the rear arm 102 located at the same side of the central axis, a connection line connecting the front electric motor 93a mounted to the front arm 101 and the rear electric motor 93b mounted to the rear arm 102 is paralleled with the central axis.

    [0074] In a specific example of the present disclosure, as shown in Fig. 1, the respective second ends (the end mounted with the front electric motor 93a) of the two front arms 101 and the respective second ends (the end mounted with the rear electric motor 93b) of the two rear arms 102 may be located in four vertexes of a square.

    [0075] It could be understood that, the lift force center C of the unmanned aerial vehicle 100 in a stable state is a center of the above square, and the gravity center of the unloaded unmanned aerial vehicle 100 as well as the gravity center of the articles (the variable weight part) loaded by the unmanned aerial vehicle 100 may be both located near the center of the square, such that the unmanned aerial vehicle 100 is simple in structure, performs well in symmetry and balance, and is easy to control.

    [0076] The unmanned aerial vehicle 100 according to embodiments of the present disclosure may be an agricultural unmanned aerial vehicle, and correspondingly, the articles (the variable weight part) loaded by the unmanned aerial vehicle 100 may be agrichemicals. As the constant weight part and the variable weight part of the unmanned aerial vehicle 100 are arranged as tiled in the front-rear direction, the loading and unloading of the agrichemicals are convenient. During the flight of the unmanned aerial vehicle 100, the agrichemicals may be gradually sprinkled out from the articles storing device 4 through a hose, and in a process of reducing the agrichemicals (the weight of the variable weight part changes), the gravity center of the unmanned aerial vehicle 100 is always located around the lift force center C of the unmanned aerial vehicle 100. Thus, the control over the unmanned aerial vehicle 100 is simple and stable.

    [0077] In summary, the unmanned aerial vehicle 100 according to embodiments of the present disclosure includes at least two front arms 101 and at least two rear arms 102, by moving the junction of the rear arm 102 and the airframe 2 forward relative to the center of the airframe 2, the first intersection point A, the second intersection point B and the lift force center C of the unmanned aerial vehicle 100 are arranged in sequence from front to back along the front-rear direction of the unmanned aerial vehicle 100, and in addition, the articles storing device 4 is disposed in the position rear of center of the unmanned aerial vehicle 100, which makes the gravity center of the unmanned aerial vehicle 100 and that of the articles (the variable weight part) loaded by the unmanned aerial vehicle 100 adjacent to the lift force center C of the unmanned aerial vehicle 100. Thus, the influence of the articles (the variable weight part) loaded by the unmanned aerial vehicle 100 on the gravity center of the whole unmanned aerial vehicle 100 is reduced so as to simplify the control over the unmanned aerial vehicle 100 and make the unmanned aerial vehicle 100 fly more stably. Furthermore, the gravity center of the unmanned aerial vehicle 100 and that of the articles (the variable weight part) loaded by the unmanned aerial vehicle 100 are arranged as tiled, such that the gravity center of the unmanned aerial vehicle 100 is prevented from rising and falling in the gravity direction, and meanwhile, the articles storing device 4 is not obstructed, which is convenient for the loading and unloading of the articles (the variable weight part) of the unmanned aerial vehicle 100.

    [0078] The unmanned aerial vehicle 100 according to embodiments of the present disclosure will be described further with reference to Fig. 1 to Fig. 14.

    [0079] The technical solution provided in the present disclosure is not only applicable to a quadrotor, but also to a multi-rotor aircraft with multiple axes, such as six axes or eight axes.

    [0080] As shown in Fig. 1, the unmanned aerial vehicle 100 in the present embodiment includes four arms arranged around the airframe 2, respective axes of the arms extend toward the airframe 2, a first end of each arm is connected with the airframe 2, and a second end thereof is provided with the rotor-wing electric motor. In a heading direction of the unmanned aerial vehicle 100, the front arm 101 provided is shorter, and the provided rear arm 102 is longer. The extension lines of the arms connecting the position of the airframe 2 coincide approximately (i.e. the intersection region E in Fig. 1). The articles storing device 4 and other devices, for example the articles storing device 4 and the battery, may be arranged in the spare space in the central portion and the rear portion of the unmanned aerial vehicle 100. Meanwhile, in the front of the airframe 2 may the front arrangement plate 3 be provided for placing other accessories, such as a flight control module, the current detection module and the auxiliary device of the unmanned aerial vehicle 100.

    [0081] In the heading direction of the unmanned aerial vehicle 100, the intersection region E of the four arms is moved forward relative to the lift force center C, such that a part of space is spared in the central portion and the rear portion of the unmanned aerial vehicle 100, where the articles storing device 4 may be arranged and heavy objects of the unmanned aerial vehicle 100 may be placed . As a result, the gravity center and the lift force center C of the unmanned aerial vehicle 100 substantially coincide in condition that the gravity center does not rise or fall, when the agrichemicals or other kinds of preservation in the storing space are released out of the unmanned aerial vehicle 100, the position of the gravity center of the whole unmanned aerial vehicle 100 will not shift greatly so as to make the control over the unmanned aerial vehicle 100 stable and easy.

    [0082] With the above configuration and arrangement of the unmanned aerial vehicle 100, it can be guaranteed that the position of the gravity center of the unloaded unmanned aerial vehicle 100 is located around the lift force center C of the whole unmanned aerial vehicle 100, the position of the gravity center of the articles (the variable weight part) loaded by the unmanned aerial vehicle 100 is also located around the lift force center C of the unmanned aerial vehicle 100, and the articles

    [0083] (the variable weight part) are arranged as tiled basically on a plane of the airframe 2 of the unmanned aerial vehicle 100, which increases a proportion of the heavy objects in the horizontal arrangement and prevents the heavy objects staked up and down from causing an offset and rise or fall of the position of the gravity center. In addition, with the tiled and unobstructed design, objects in the articles storing device 4 are easier to be taken out and put in.

    [0084] The arm may be configured as a linear shape or an arc shape, and a plenty of available space may be spared easily at the two sides of the arc shaped arm, which is convenient to store and install other objects.

    [0085] As an improvement of the present disclosure, the arm is provided with a fixing piece, and the fixing piece includes a first fixing portion 10 and a second fixing portion 11.

    [0086] At least one of the first fixing portion 10 and the second fixing portion 11 is connected with the airframe 2, the first fixing portion 10 and the second fixing portion 11 are connected and fit with each other to define a mounting groove, and the arm is disposed through the mounting groove.

    [0087] In an embodiment of the present disclosure, specifically, the first fixing portion 10 is connected with the airframe 2, the second fixing portion 11 is connected with the airframe 2, the first fixing portion 10 and the second fixing portion 11 are connected and fit with each other to define the mounting groove, and the arm is disposed through the mounting groove. In addition, the first fixing portion 10 and the second fixing portion 11 are provided with at least one outer flat surface connected with the airframe 2 separately.

    [0088] In some embodiments of the present disclosure, the arm may be provided with an arm deflection locking hole 12, and at least one of the first fixing portion 10 and the second fixing portion 11 is provided with an arm deflection fixing hole 15 in a position corresponding to the arm deflection locking hole 12. In a specific embodiment of the present disclosure, the first fixing portion 10 and the second fixing portion 11 are both provided with the arm deflection fixing hole 15 in the position corresponding to the arm deflection locking hole 12. The first fixing portion 10 and the second fixing portion 11 may also be provided with an arc inner surface 16 matching with an outer wall of the arm separately, and the two arc inner surfaces 16 cooperate to form the mounting groove through which the arm is disposed. The first fixing portion 10 and the second fixing portion 11 are provided with an arm fastening hole 13 for bolted connection and an airframe connecting hole 14 for bolted connection with the airframe 2.

    [0089] A shape of the mounting groove may be designed to match with a shape of the arm. For example, a section shape of the mounting groove may be a circle when a section shape of the arm is a circle, and may be a square when the section shape of the arm is a square.

    [0090] A front view of an assembled arm is shown in Fig. 3, in which two arm fixing pieces, i.e. two first fixing portions 10 and two second fixing portions 11, and the arm are shown. The first fixing portion and the second fixing portion in a first arm fixing piece clamp the arm , and a second arm fixing piece is spaced apart from the first arm fixing piece by a certain distance and also clamps the arm .

    [0091] An exploded view of a partially assembled arm is shown in Fig. 4, in which the arm fastening hole 13, the airframe connecting hole 14, and the arm deflection fixing hole 15 are shown. The arm fastening hole 13 is used for fastening the first fixing portion 10 and the second fixing portion 11 with a screw, the airframe connecting hole 14 is used for fixing the first fixing portion 10 and the second fixing portion 11 to the airframe 2 with a screw, and the arm deflection fixing hole 15 is used for locking the arm in a fixed angle with a screw as required. The arc inner surface 16 is located at a position where the first fixing portion 10 and the second fixing portion 11 clamp the arm. In an axial direction of the arc inner surface 16, the first fixing portion 10 and the second fixing portion 11 each have an increased thickness, which makes the two arc inner surfaces 16 have a larger contact area with the arm, thus clamping the arm better.

    [0092] A schematic view of deflection of the arm is shown in Fig. 5, a screw for locking the deflection of the arm goes through the arm deflection locking hole 12 so as to fix a deflection angle Φ between the arm and the airframe 2 accurately.

    [0093] During the use, the first fixing portion 10 and the second fixing portion 11 of the first arm fixing piece clamp the arm, then screws go through the arm deflection fixing hole 15 and the arm deflection locking hole 12 in the arm and fasten the first fixing portion 10 and the second fixing portion 11 with the arm, and the arm is clamped with the screw going through the arm fastening hole 13; the second arm fixing piece is mounted to a corresponding position of the arm and spaced apart from the first arm fixing piece by a certain distance. Upper and lower planes of the above arm connection part are arranged in a same plane worktable and keep parallel with each other. Then the rotor-wing electric motor 93 is mounted to the second end of the arm, and by adjusting a lower surface of an electrical motor base to be horizontal or have a certain angle Φ, the rotor-wing electric motor 93 is perpendicular to or forms the angle Φ with a vertical plane, along an axial direction of the arm. When the rotor-wing electric motor 93 is fixed, the arm mounted with the arm fixing piece is assembled to the airframe 2 i.e. fastening the arm to the airframe 2 with screws through the airframe connecting hole 14.

    [0094] The method for fixing the arm and the airframe 2 guarantees that the arm is not easy to swing in the axial direction, such that the arm may be conveniently fixed to a plurality of fixing pieces at a required deflection angle, and then be mounted to the airframe 2, thus ensuring that the deflection angle of the arm relative to the plane of the airframe 2 is a demanded constant value or a target constant value.

    [0095] As shown in Fig. 10 to Fig. 14, a heat dissipation waterproof cover 90 is disposed to an upper end face of the rotor-wing electric motor 93 of the unmanned aerial vehicle 100, and the heat dissipation waterproof cover 90 includes an upper sealing surface 914 and a sidewall circumferential surface 92. The sidewall circumferential surface 92 is provided with a certain number of ventilation holes 915 adjacent to the upper sealing surface 914, and a blade 911 distant from a center of the heat dissipation waterproof cover (abbreviated as blade 911 hereinafter) is disposed in the heat dissipation waterproof cover 90 and extends from the ventilation hole 915 towards a center of an inner wall of the upper sealing surface 914. In some embodiments of the present disclosure, an annular cavity 916 fitted with an air hole inside the rotor-wing electric motor 93 is formed between the center of the inner wall center of the upper sealing surface 914 and the blade 911. A height of a portion of the blades 911 adjacent to the center of the inner wall center of the upper sealing surface 914 is smaller than a height of another portion of the blades 911 adjacent to the ventilation hole 915.

    [0096] The above heat dissipation waterproof cover 90 may cover an upper portion and a circumference of the rotor-wing electric motor 93, and an upper portion of the heat dissipation waterproof cover 90 is sealed while the other end thereof is open. A positioning hole 913 may be provided in the upper sealing surface 914 sealed by the heat dissipation waterproof cover 90 so as to fix the heat dissipation waterproof cover 90 to an end face of a rotor of the rotor-wing electric motor 93 by means of a screw 91. A plurality of (twenty five in the present embodiment) blades 911 are disposed from an inner side of the upper sealing surface 914 to an inner wall 912 of the sidewall circumferential surface, an angle between a tangential direction and a radial direction of a tail end of the blade 911 is recorded as β, and a shape of the blade 911 may be designed as three types shown in the figures, namely a rearward type with 0°<β<90°, a radial type with β=90° and a forward type with 90°<β<180°. One annular cavity 916 is spared in a radial inner side of the blade 911, and a diameter of an outer circle of the annular cavity 916 is larger than a diameter of the air hole inside the electric motor. Meanwhile, the ventilation hole 915 is provided in an upper edge of the sidewall circumferential surface 92 around the heat dissipation waterproof cover 90, i.e. hollowing out a part of the sidewall circumferential surface 92 in a gap between two adjacent blades 911, and as a result the ventilation hole 915 located in a joint area of the upper sealing surface 914 and the sidewall circumferential surface 92 is formed.

    [0097] During rotation of the rotor of the rotor-wing electric motor 93, the heat dissipation waterproof cover 90 rotates along with the rotor, and the blades 911 inside the heat dissipation waterproof cover 90 rotate around an rotation center of the rotor-wing electric motor 93, which makes the hot air produced by the rotation of the rotor-wing electric motor 93 be thrown out by a centrifugal force produced by the rotation of the blades 911. A negative pressure is produced in the annular cavity 916 inside the heat dissipation waterproof cover 90, an airstream enters into a lower portion of the rotor-wing electric motor 93 and is thrown out from the ventilation hole 915 by the centrifugal force, thereby keeping the airstream flowing to dissipate heat for the rotor-wing electric motor 93. In addition, as an upper covering surface of the heat dissipation waterproof cover 90 covers the upper portion of the electric motor 93, rain cannot enter the rotor-wing electric motor from the upper portion thereof, and is blown away by the high-speed airstream thrown out of the ventilation hole when flowing towards the joint area of the upper sealing surface 914 and the sidewall circumferential surface 92 of the heat dissipation waterproof cover 90, which prevents the rain from entering the heat dissipation waterproof cover 93, thus playing a waterproof role.

    [0098] As shown in Fig. 6 to Fig. 9, a folding cavity body 81, an adaptor 82 and a sprinkle-nozzle foldable rod 83 are disposed below the arm, and a driving assembly is disposed within the folding cavity body 81. A central portion of the adaptor 82 is articulated within the folding cavity body 81, a front end of the adaptor 82 is connected with the driving assembly, and a rear end of the adaptor 82 passes through an opening of the folding cavity body 81 and is fixedly connected with a first end of the sprinkle-nozzle foldable rod 83.

    [0099] The driving assembly includes a driving body, a driving shaft and a connection portion mounted within a casing. The driving shaft is able to be rotatably connected with the driving body and the connection portion, and the driving body is used to drive the driving shaft to rotate so that the connection portion pushes the adaptor to rotate relative to the casing between a first position and a second position.

    [0100] The driving body is configured as a gear motor 88, the driving shaft is configured as a screw rod 832, and the connection portion is configured as a sliding block 831.

    [0101] An outer wall of the driving shaft is provided with an outer thread, the connection portion is provided with a fitting hole, an inner wall of the fitting hole is provided with an inner thread, the driving shaft goes through the connection portion, and the outer thread is fitted with the inner thread.

    [0102] A first end of the driving shaft away from the driving body is provided with a thrust bearing 89, the thrust bearing 89 is fixed within the casing, and the driving shaft is rotatably disposed through the thrust bearing 89.

    [0103] The front end of the adaptor 82 is formed to be a U-shaped groove 821 and the connection portion is arranged within the U-shaped groove 821.

    [0104] That is, a folding mechanism of the sprinkle nozzle is disposed below the arm, and includes the folding cavity body 81, the adaptor 82, the sprinkle-nozzle foldable rod 83, a sprinkle-nozzle rotating electric motor 422, and a sprinkling piece 41 driven to operate by the sprinkle-nozzle rotating electric motor 422. A first end of the folding cavity body 81 is provided with a signal interface circuit plate 87 and a second end thereof is provided with the opening. The gear motor 88 and the screw rod 832 are disposed within the folding cavity body 81. An output end of the signal interface circuit plate 87 is electrically connected with an input end of the gear motor 88. An output shaft of the gear motor 88 is in axial transmission connection with a first end of the screw rod 832, and a second end of the screw rod 832 is provided with the thrust bearing 89. A convex shaft 822 is disposed in an inner cavity wall of the folding cavity body 81 adjacent to the opening, and the convex shaft 822 is connected with the central portion of the adaptor 82. A first end of the adaptor 82 is formed to be the U-shaped groove 821, and the sliding block 831 is disposed in the U-shaped groove 821. A central portion of the sliding block 831 is provided with a threaded hole through which the screw rod 832 passes and by which the sliding block is in threaded connection with the screw rod 832. Two opposite inner cavity walls of the folding cavity body 81 are provided with linear sliding grooves 813 in which two ends of the sliding block 831 slide along an axial direction of the screw rod 832. A second end of the adaptor 82 extends from the opening of the folding cavity body 81 to the outside of the folding cavity body 81 and is fixedly connected with the first end of the sprinkle-nozzle foldable rod 83. The sprinkle-nozzle rotating electric motor 422 and the sprinkling piece 41 are disposed at a second end of the sprinkle-nozzle foldable rod 83.

    [0105] Fig. 6 is a schematic view of the sprinkle nozzle in a vertically laid down state, and Fig. 7 is a schematic view of the sprinkle nozzle in a horizontally folded state. The folding mechanism of the sprinkle nozzle mainly includes the folding cavity body 81, the adaptor 82, the sprinkle-nozzle foldable rod 83, the sprinkle-nozzle rotating electric motor 422 and the sprinkling piece 41. The sprinkle-nozzle foldable rod 83 is connected with the folding cavity body 81 by means of the adaptor 82, the sprinkle-nozzle rotating electric motor 422 and the sprinkling piece 41 are fixedly connected with the sprinkle-nozzle foldable rod 83, and the sprinkle-nozzle rotating electric motor 422 drives the sprinkling piece 41 to rotate.

    [0106] The first position may be designed as a retracted position of the sprinkle-nozzle foldable rod 83 and the sprinkling piece 41, and the second position may be designed as an unfolded position of the sprinkle-nozzle foldable rod 83 and the sprinkling piece 41. In a practical operation process, in an example for illustration, the retracted position of the sprinkle-nozzle foldable rod 83 and the sprinkling piece 41 is a horizontal position, and the unfolded position of the sprinkle-nozzle foldable rod 83 and the sprinkling piece 41 is a vertical position. It could be understood that, in other examples, the first position and the second position may be designed specifically according to application circumstances of the unmanned aerial vehicle 100 and not be limited to the specific positions defined by embodiments of the present disclosure.

    [0107] As shown in Fig. 8, a schematic view of an inner structure of the folding cavity body 81 is illustrated, including a left side casing 811, a right side casing 812, the gear motor 88, the adaptor 82, the screw rod 832, the sliding block 831 and the thrust bearing 89. The gear motor 88 is mounted in a square groove of the left side casing 811 and the right side casing 812. The screw rod 832 is connected with the output shaft of the gear motor 88, and the tail end of the screw rod 832 resists against the thrust bearing 89. The sliding block 831 centrally provided with the threaded hole is screwed onto the screw rod 832 and the threaded hole is spirally fitted with the screw rod 832.

    [0108] As shown in Fig. 8 and Fig. 9, two sides of the threaded hole in the center of the sliding block 831 are slidingly fitted with the U-shaped groove 821 of the adaptor 82, and two ends of the sliding block 831 are slidingly fitted with the corresponding linear sliding grooves 813 in the left side casing 811 and the right side casing 812 in the figures, i.e. the sliding block 831 may slide along the linear sliding grooves. The convex shafts 822 are provided at the left or the right side of a corner position of the adaptor 82, and the convex shaft 822 is rotatably fitted with corresponding circular holes 814 in the left side casing 811 and the right side casing 812 in the figures, and a rotational connection is formed. A hollow hole 824 is provided inside the adaptor 82, and cables used for circuit control and a water outlet pipe adaptor 86 for the sprinkle nozzle as well as the pipes thereof may go through the hollow hole 824.

    [0109] The unmanned aerial vehicle 100 further includes the following modules: the control module and the current detection module. The control module is used to control the driving assembly to drive the adaptor to rotate; the current detection module is used to detect whether a current of the driving assembly is larger than a preset threshold, if the current of the driving assembly is larger than the preset threshold, the current detection module is used to send a control signal for turning off the driving assembly to the control module, and if the current of the driving assembly is not larger than the preset threshold, the current detection module is used to continue detecting whether the current of the driving assembly is larger than the preset threshold; the control module is used to turn off the driving assembly according to the control signal. Thus, the control module and the current detection module are used for automatic control over the folding mechanism of the sprinkle nozzle.

    [0110] A method for using and controlling the folding mechanism of the sprinkle nozzle will be described below.

    [0111] When the unmanned aerial vehicle 100 is in a takeoff awaiting state, the sprinkle-nozzle foldable rod 83 and the sprinkling piece 41 are folded in the horizontal position by means of the folding mechanism of the sprinkle nozzle, and the sliding block 831 is located at an extreme position of the screw rod 832 near the gear motor 88. After the unmanned aerial vehicle 100 takes off, the sprinkle nozzle needs to perform an agricultural sprinkling operation, and the gear motor 88 receives a driving signal from the signal interface circuit plate 87 and hence rotates clockwise to push the sliding block 831 to the end of the screw rod 832 close to the thrust bearing 89. In this process, the two ends of the sliding block 831 are limited to move in parallel along a straight line by the linear sliding grooves 813 on the left side casing 811 and the right side casing 812, thus preventing the sliding block 831 from rotating around the axial direction of the screw rod 832. Meanwhile, the sliding block 831 is limited within the U-shaped groove 821 of the adaptor 82, and as a result, the sliding block 831 pushes the U-shaped groove 821 during the movement so that the adaptor 82 rotates around the convex shaft 822. The second end of the adaptor 82 is connected with the first end of the sprinkle-nozzle foldable rod 83 fixed with the sprinkle nozzle through a mounting hole 823 of the sprinkle-nozzle foldable rod 83, so that the sprinkle-nozzle foldable rod 83 is driven to rotate around the convex shaft 822 till the sprinkle-nozzle foldable rod 83 rotates to the vertical position. When a first contact surface 825 of the adaptor 82 touches a first end face 815 of an open end of the left side casing 811 and the right side casing 812, the adaptor 82 is plugged up and cannot rotate (being limited to the first position), meanwhile the sliding block 831 cannot continue rotating, and neither can the screw rod 832. In such a case, the load of the gear motor 88 is increased, so the current through the gear motor 88 instantly increases greatly. When the current detection module in the unmanned aerial vehicle 100 detects that the current increases greatly, the current detection module sends a detection signal to the control module, then the control module sends the control signal to the gear motor 88, and finally the electric motor is made to stop. During the flight of the unmanned aerial vehicle 100, the sprinkle-nozzle foldable rod 83 fixed with the sprinkle nozzle is retained to be perpendicular to the arm and face downwards. When the operation is finished, the unmanned aerial vehicle 100 hovers above a landing position, and at this time the control module sends the driving signal to the gear motor 88 to make it rotate counterclockwise so as to retract the sprinkle-nozzle foldable rod 83 fixed with the sprinkle nozzle to the horizontal position, in which this process is similar to the process of unfolding the sprinkle-nozzle foldable rod 83 and the relevant mechanisms move in an opposite direction.

    [0112] With the above folding mechanism of the sprinkle nozzle, on one hand, the sprinkle-nozzle foldable rod 83 can be folded and stored during packaging and transportation, and on the other hand, the sprinkle-nozzle foldable rod 83 fixed with the sprinkle nozzle can be unfolded when the unmanned aerial vehicle 100 performs the sprinkling operation so as to prevent formation of a droplet phenomenon due to aggregation of fogdrops, and in addition, the sprinkle-nozzle foldable rod 83 can be folded when not in use, thereby avoiding touching the ground.

    [0113] As shown in Fig. 1, in embodiments of the present disclosure, an unmanned aerial vehicle body 1 including an airframe 2 and an articles storing device 4 disposed behind the airframe 2 and configured to store a variable weight part is shown.

    [0114] In some embodiments of the present disclosure, the unmanned aerial vehicle body 1 is configured for an unmanned aerial vehicle 100. As shown in Fig. 1 to Fig. 17, the unmanned aerial vehicle 100 further includes: an arm including at least two front arms 101 symmetrically arranged with respect to a central axis of the airframe 2 along a front-rear direction and at least two rear arms 102 symmetrically arranged with respect to the central axis of the airframe 2; and a rotor-wing electric motor including a front electric motor 93a and a rear electric motor 93b. A first end of the front arm 101 is connected with a front end of the airframe 2, and a second end of the front arm 101 is provided with the front electric motor 93a to drive the unmanned aerial vehicle 100. A first end of the rear arm 102 is connected with a rear end of the airframe 2, and a second end of the rear arm 102 is provided with the rear electric motor 93b to drive the unmanned aerial vehicle 100. An acting point of a resultant force from the front electric motor 93a and the rear electric motor 93b exerted on the unmanned aerial vehicle 100 is the lift force center, and a gravity center of the unmanned aerial vehicle 100 is adjacent to the lift force center, a projection of the lift force center on a horizontal plane is configured to be adjacent to a projection of a gravity center of the variable weight part on the horizontal plane.

    [0115] Reference throughout this specification to "an embodiment," "some embodiments," "illustrative embodiment", "an example," "a specific example," or "some examples," means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In the present specification, the illustrative statement of the terms above is not necessarily referring to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics may be combined in any suitable manner in one or more embodiments or examples.

    [0116] Although embodiments of the present disclosure have been shown and described, it would be appreciated by those skilled in the art that changes, alternatives, variation and modifications can be made in the embodiments without departing from spirit and principles of the present disclosure, and the scope of the present disclosure is limited by the claims.


    Claims

    1. An unmanned aerial vehicle (100), comprising:

    an unmanned aerial vehicle body (1) comprising an airframe (2) and an articles storing device (4) disposed behind the airframe (2) and configured to store a variable weight part;

    at least two front arms (101) symmetrically arranged with respect to a central axis of the airframe (2) along a front-rear direction and at least two rear arms (102) symmetrically arranged with respect to the central axis of the airframe (2);

    preferably, each of the front arms (101) and the rear arms (102) is formed to be a linear shape or an arc shape;

    preferably, two front arms (101) and two rear arms (102) are provided, and an included angle between the two front arms (101) is larger than an included angle between the two rear arms (102);

    preferably, a length of the rear arm (102) is larger than a length of the front arm (101);

    rotor-wing electric motors (93) comprising at least two front electric motors (93a) and at least two rear electric motors (93b);

    wherein a first end of each of the front arms (101) is connected with a front end of the airframe (2), and a second end of each of the front arms (101) is provided with a front electric motor (93a) to drive the unmanned aerial vehicle (100); a first end of each of the rear arms (102) is connected with a rear end of the airframe (2), and a second end of each of the rear arms (102) is provided with a rear electric motor (93b) to drive the unmanned aerial vehicle (100);

    wherein an acting point of a resultant force from the front electric motors (93a) and the rear electric motors (93b) exerted on the unmanned aerial vehicle (100) is the lift force center (C), and a gravity center of the unmanned aerial vehicle (100) is adjacent to the lift force center (C), a projection of the lift force center (C) on a horizontal plane is configured to be adjacent to a projection of a gravity center of the variable weight part on the horizontal plane,

    a projection of an intersection region (E) bounded by extension lines of the rear arms (102) towards the airframe (2) and extension lines of the front arms (101) towards the airframe (2) on the horizontal plane is located in front of a projection of a lift force center (C) of the unmanned aerial vehicle (100) on the horizontal plane,

    characterized in that a heat dissipation waterproof cover is disposed to an upper end face of the rotor-wing electric motors (93), the heat dissipation waterproof cover comprises an upper sealing surface (914) and a sidewall circumferential surface, the sidewall circumferential surface is provided with a certain number of ventilation holes (915) adjacent to the upper sealing surface (914), and a blade (911) distant from a center of the heat dissipation waterproof cover is disposed in the heat dissipation waterproof cover and extends from the ventilation hole (915) towards a center of an inner wall of the upper sealing surface (914).


     
    2. The unmanned aerial vehicle (100) according to claim 1, wherein each of the front arms and the rear arms is provided with an arm fixing piece and the arm fixing piece comprises:

    a first fixing portion (10) connected with the airframe (2); and

    a second fixing portion (11) connected with the airframe (2),

    wherein the first fixing portion (10) and the second fixing portion (11) are connected and fitted with each other to define a mounting groove, each of the front arms and the rear arms is disposed through the mounting groove, and the first fixing portion (10) and the second fixing portion (11) are separately provided with at least one outer flat surface connected with the airframe (2).


     
    3. The unmanned aerial vehicle (100) according to claim 2, wherein each of the front arms and the rear arms is provided with an arm deflection locking hole (12), the first fixing portion (10) and the second fixing portion (11) are both provided with an arm deflection fixing hole (15) in a position corresponding to the arm deflection locking hole (12).
     
    4. The unmanned aerial vehicle (100) according to claim 2, wherein the first fixing portion (10) and the second fixing portion (11) are separately provided with an arc inner surface (16) configured to be matched with an outer wall of each of the front arms and the rear arms.
     
    5. The unmanned aerial vehicle (100) according to claim 2, wherein the first fixing portion (10) and the second fixing portion (11) are provided with an arm fastening hole (13) configured for bolted connection and an airframe connecting hole configured for bolted connection with the airframe (2).
     
    6. The unmanned aerial vehicle (100) according to claim 1, wherein a folding cavity body (81), an adaptor (82) and a sprinkle-nozzle foldable rod (83) are disposed below the front arms and the rear arms, a driving assembly is disposed within the folding cavity body (81), a central portion of the adaptor (82) is articulated within the folding cavity body (81), a front end of the adaptor (82) is connected with the driving assembly, and a rear end of the adaptor (82) passes through an opening of the folding cavity body (81) and is fixedly connected with a first end of the sprinkle-nozzle foldable rod (83).
     
    7. The unmanned aerial vehicle (100) according to claim 6, wherein the driving assembly comprises a driving body, a driving shaft and a connection portion mounted within a casing, the driving shaft is configured to be rotatably connected with the driving body and the connection portion, and the driving body is used to drive the driving shaft to rotate so that the connection portion pushes the adaptor (82) to rotate relative to the casing between a first position and a second position.
     
    8. The unmanned aerial vehicle (100) according to claim 7, wherein an outer wall of the driving shaft is provided with an outer thread, the connection portion is provided with a fitting hole, an inner wall of the fitting hole is provided with an inner thread, the driving shaft is configured to go through the connection portion, and the outer thread is configured to be fitted with the inner thread.
     
    9. The unmanned aerial vehicle (100) according to claim 7, wherein a first end of the driving shaft away from the driving body is provided with a thrust bearing (89), the thrust bearing (89) is fixed within the casing, and the driving shaft is rotatably disposed through the thrust bearing (89).
     
    10. The unmanned aerial vehicle (100) according to claim 7, wherein the front end of the adaptor (82) is formed to be a U-shaped groove (821) and the connection portion is arranged within the U-shaped groove (821).
     
    11. The unmanned aerial vehicle (100) according to claim 6, wherein the unmanned aerial vehicle (100) further comprises:

    a control module used to control the driving assembly to drive the adaptor (82) to rotate; and

    a current detection module,

    wherein the current detection module is used to detect whether a current of the driving assembly is larger than a preset threshold, and if the current of the driving assembly is larger than the preset threshold, the current detection module is used to send a control signal for turning off the driving assembly to the control module; and the control module is used to turn off the driving assembly according to the control signal.


     
    12. The unmanned aerial vehicle (100) according to claim 1,
    wherein an annular cavity (916) fitted with an air hole inside the rotor-wing electric motor (93) is formed between the center of the inner wall of the upper sealing surface (914) and the blade (911).
     
    13. The unmanned aerial vehicle (100) according to claim 12, wherein a height of a portion of blades (911) adjacent to the center of the inner wall of the upper sealing surface (914) is smaller than a height of another portion of blades (911) adjacent to the ventilation hole (915).
     
    14. The unmanned aerial vehicle (100) according to any one of claims 1-13, wherein the lift force center (C) is adjacent to a geometric center of the articles storing device (4), and preferably, the gravity center of the unmanned aerial vehicle (100), the lift force center (C), and the geometric center of the articles storing device (4) coincide.
     


    Ansprüche

    1. Unbemanntes Luftfahrzeug (100), umfassend:

    einen Rahmen (1) des unbemannten Luftfahrzeugs mit einem Flugwerk (2) und einer Aufbewahrungsvorrichtung (4) für Gegenstände, die hinter dem Flugwerk (2) angeordnet ist und konfiguriert ist, um ein Teil mit variablem Gewicht aufzubewahren;

    wenigstens zwei Frontarme (101), die mit Bezug auf eine zentrale Achse des Luftwerks (2) entlang einer Front-Heck-Richtung symmetrisch angeordnet sind, und wenigstens zwei Heckarme (102), die mit Bezug auf die zentrale Achse des Flugwerks (2) symmetrisch angeordnet sind;

    wobei vorzugsweise jeder der Frontarme (101) und der Heckarme (102) ausgebildet ist, um eine lineare Form oder eine Bogenform aufzuweisen;

    wobei vorzugsweise zwei Frontarme (101) und zwei Heckarme (102) vorgesehen sind und ein von den beiden Frontarmen (101) eingeschlossener Winkel größer ist als ein von den beiden Heckarmen (102) eingeschlossener Winkel;

    wobei vorzugsweise eine Länge des Heckarms (102) größer als die Länge des Frontarms (101) ist;

    elektrische Rotorflügelmotoren (93), die wenigstens zwei elektrische Frontmotoren (93a) und wenigstens zwei elektrische Heckmotoren (93b) umfassen;

    wobei ein erstes Ende von jedem der Frontarme (101) mit einem Frontende des Flugwerks (2) verbunden ist und ein zweites Ende von jedem der Frontarme (101) mit einem elektrischen Frontmotor (93a) versehen ist, um das unbemannte Luftfahrzeug (100) anzutreiben; wobei ein erstes Ende von jedem der Heckarme (102) mit einem hinteren Ende des Flugwerks (2) verbunden ist und ein zweites Ende von jedem der Heckarme (102) mit einem elektrischen Heckmotor (93b) versehen ist, um das unbemannte Luftfahrzeug (100) anzutreiben;

    wobei ein Angriffspunkt einer resultierenden Kraft von dem elektrischen Frontmotor (93a) und dem elektrischen Heckmotor (93b), welche auf das unbemannte Luftfahrzeug (100) ausgeübt wird, das Hebekraftzentrum (C) ist, wobei ein Schwerkraftzentrum des unbemannten Luftfahrzeugs (100) benachbart zu dem Hebekraftzentrum (C) ist, wobei eine Projektion des Hebekraftzentrums (C) auf eine horizontale Ebene konfiguriert ist, um benachbart zu einer Projektion eines Gravitationszentrums des Teils mit variablem Gewicht auf die horizontale Ebene ist,

    wobei eine Projektion eines Schnittbereichs (E), begrenzt durch Erweiterungslinien der Heckarme (102) in Richtung auf das Flugwerk (2) und Begrenzungslinien der Frontarme (101) in Richtung auf das Flugwerk (2), auf die horizontale Ebene vor einer Projektion eines Hebekraftzentrums (C) des unbemannten Luftfahrzeugs (100) auf die horizontale Ebene angeordnet ist,

    dadurch gekennzeichnet, dass eine wärmeableitende wasserdichte Abdeckung auf einer oberen Endfläche der elektrischen Rotorflügelmotoren (93) angeordnet ist, wobei die wärmeableitende wasserdichte Abdeckung eine obere Dichtoberfläche (914) und eine umlaufende Seitenwandoberfläche umfasst, wobei die umlaufende Seitenwandoberfläche mit einer gewissen Anzahl von Belüftungslöchern (915) benachbart zu der oberen Dichtoberfläche (914) versehen ist, wobei ein Flügel (911) mit Abstand von einem Zentrum der wärmeableitenden wasserdichten Abdeckung in der wärmeableitenden wasserdichten Abdeckung angeordnet ist und sich von dem Belüftungsloch (915) in Richtung auf ein Zentrum einer inneren Wand der oberen Dichtoberfläche (914) erstreckt.


     
    2. Unbemanntes Luftfahrzeug (100) nach Anspruch 1, wobei jeder der Frontarme und der Heckarme mit einem Armfixierungsstück versehen ist, wobei das Armfixierungsstück umfasst:

    einen ersten Fixierungsteil (10), der mit dem Flugwerk (2) verbunden ist; und

    einen zweiten Fixierungsteil (11), der mit dem Flugwerk (2) verbunden ist,

    wobei der erste Fixierungsteil (10) und der zweite Fixierungsteil (11) verbunden sind und aneinander angepasst sind, um eine Montagenut zu definieren, wobei jeder der Frontarme und der Heckarme durch die Montagenut angeordnet sind, wobei der erste Fixierungsteil (10) und der zweite Fixierungsteil (11) separat mit wenigstens einer äußeren flachen Oberfläche versehen sind, die mit dem Flugwerk (2) verbunden ist.


     
    3. Unbemanntes Luftfahrzeug (100) nach Anspruch 2, wobei jeder der Frontarme und der Heckarme mit einem Armdeflexionsverriegelungsloch (12) versehen ist, wobei der erste Fixierungsteil (10) und der zweite Fixierungsteil (11) beide mit einem Armdeflexionsfixierungsloch (15) in einer Position versehen sind, die dem Armdeflexionsverriegelungsloch (12) entspricht.
     
    4. Unbemanntes Luftfahrzeug (100) nach Anspruch 4, wobei der erste Fixierungsteil (10) und der zweite Fixierungsteil (11) separat mit einer inneren Bogenoberfläche (16) versehen sind, die konfiguriert ist, dass sie mit einer äußeren Wand von jedem der Frontarme und der Heckarme zusammenpasst.
     
    5. Unbemanntes Luftfahrzeug (100) nach Anspruch 2, wobei der erste Fixierungsteil (10) und der zweite Fixierungsteil (11) mit einem Armbefestigungsloch (13) versehen sind, das für eine geschraubte Verbindung konfiguriert ist, und einem Flugwerkverbindungsloch, das für eine geschraubte Verbindung mit dem Flugwerk (2) konfiguriert ist.
     
    6. Unbemanntes Luftfahrzeug (100) nach Anspruch 1, wobei ein Falthohlraumkörper (81), ein Adapter (82) und eine faltbare Sprühdüsenstange (83) unter den Frontarmen und den Heckarmen angeordnet sind, wobei eine Antriebsanordnung innerhalb des Falthohlraumkörpers (81) angeordnet ist, wobei ein zentraler Teil des Adapters (82) gelenkig innerhalb des Falthohlraumkörpers (81) angeordnet ist, wobei ein vorderes Ende des Adapters (82) mit der Antriebsanordnung verbunden ist und wobei ein hinteres Ende des Adapters (82) durch eine Öffnung des Falthohlraumkörpers (81) hindurchgeht und fest mit einem ersten Ende der faltbaren Sprühdüsenstange (83) verbunden ist.
     
    7. Unbemanntes Luftfahrzeug (100) nach Anspruch 6, wobei die Antriebsanordnung einen Antriebskörper, eine Antriebswelle und einen Verbindungsteil, montiert in einem Gehäuse, umfasst, wobei die Antriebswelle konfiguriert ist, um drehbar mit dem Antriebskörper und dem Verbindungsteil verbunden zu sein und wobei der Antriebskörper verwendet wird, um die Antriebswelle zum Rotieren anzutreiben, so dass der Verbindungsteil den Adapter (82) drückt, so dass er sich relativ zu dem Gehäuse zwischen einer ersten Position und einer zweiten Position dreht.
     
    8. Unbemanntes Luftfahrzeug (100) nach Anspruch 7, wobei eine äußere Wand der Antriebswelle mit einem Außengewinde versehen ist, wobei der Verbindungsteil mit einem Passloch versehen ist, wobei eine innere Wand des Passlochs mit einem Innengewinde versehen ist, wobei die Antriebswelle konfiguriert ist, um durch den Verbindungsteil hindurchzugehen, und wobei das Außengewinde konfiguriert ist, um mit dem Innengewinde zusammenzupassen.
     
    9. Unbemanntes Luftfahrzeug (100) nach Anspruch 7, wobei ein erstes Ende der Antriebswelle entfernt von dem Antriebskörper mit einem Axiallager (89) versehen ist, wobei das Axiallager (89) in dem Gehäuse fixiert ist und wobei die Antriebswelle drehbar durch das Axiallager (89) angeordnet ist.
     
    10. Unbemanntes Luftfahrzeug (100) nach Anspruch 7, wobei das Frontende des Adapters (82) so ausgebildet ist, dass es eine U-förmige Nut (821) bildet, und der Verbindungsteil innerhalb der U-förmigen Nut (821) angeordnet ist.
     
    11. Unbemanntes Luftfahrzeug (100) nach Anspruch 6, wobei das unbemannte Luftfahrzeug (100) weiterhin umfasst:

    ein Steuermodul, das verwendet wird, um die Antriebsanordnung so zu steuern, dass sie den Adapter (82) zum Drehen antreibt; und

    ein Stromerfassungsmodul,

    wobei das Stromerfassungsmodul genutzt wird, um zu erfassen, ob ein Strom der Antriebsanordnung größer als eine voreingestellte Schwelle ist, wobei, wenn der Strom der Antriebsanordnung größer als die voreingestellte Schwelle ist, das Stromerfassungsmodul genutzt wird, um ein Steuersignal zum Ausschalten der Antriebsanordnung an das Steuermodul zu senden; wobei das Steuermodul genutzt wird, um die Antriebsanordnung gemäß dem Steuersignal abzuschalten.


     
    12. Unbemanntes Luftfahrzeug (100) nach Anspruch 1,
    wobei ein Ringhohlraum (916), der mit einem Luftloch innerhalb des elektrischen Rotorflügelmotors (93) eingepasst ist, zwischen dem Zentrum der inneren Wand der oberen Dichtfläche (914) und dem Flügel (911) ausgebildet ist.
     
    13. Unbemanntes Luftfahrzeug (100) nach Anspruch 12, wobei eine Höhe eines Teils von Flügeln (911) benachbart zu dem Zentrum der inneren Wand der oberen Dichtfläche (914) kleiner als eine Höhe eines anderen Teils von Flügeln (911) benachbart zu dem Belüftungsloch (915) ist.
     
    14. Unbemanntes Luftfahrzeug (100) nach einem der Ansprüche 1 bis 13, wobei das Hebekraftzentrum (C) benachbart zu einem geometrischen Zentrum der Aufbewahrungsvorrichtung (4) für Gegenstände angeordnet ist und wobei vorzugsweise das Schwerkraftzentrum des unbemannten Luftfahrzeugs (100), das Hebekraftzentrum (C) und das geometrische Zentrum der Aufbewahrungsvorrichtung (4) für Gegenstände zusammenfallen.
     


    Revendications

    1. Véhicule aérien sans pilote (100), comprenant :

    un corps de véhicule aérien sans pilote (1) comprenant une cellule (2) et un dispositif de stockage d'articles (4) disposé derrière la cellule (2) et configuré pour stocker une partie de poids variable ;

    au moins deux bras avant (101) agencés symétriquement par rapport à un axe central de la cellule (2) le long d'une direction avant-arrière, et au moins deux bras arrière (102) agencés symétriquement par rapport à l'axe central de la cellule (2) ;

    de préférence, chacun des bras avant (101) et des bras arrière (102) est formé pour avoir une forme linéaire ou une forme en arc ;

    de préférence, deux bras avant (101) et deux bras arrière (102) sont prévus, et un angle inclus entre les deux bras avant (101) est plus grand qu'un angle inclus entre les deux bras arrière (102) ;

    de préférence, une longueur du bras arrière (102) est supérieure à une longueur du bras avant (101) ;

    des moteurs électriques à aile-rotor (93) comprenant au moins deux moteurs électriques avant (93a) et au moins deux moteurs électriques arrière (93b) ;

    dans lequel une première extrémité de chacun des bras avant (101) est reliée à une extrémité avant de la cellule (2), et une deuxième extrémité de chacun des bras avant (101) est pourvue d'un moteur électrique avant (93a) pour entraîner le véhicule aérien sans pilote (100) ; une première extrémité de chacun des bras arrière (102) est reliée à une extrémité arrière de la cellule (2), et une deuxième extrémité de chacun des bras arrière (102) est pourvue d'un moteur électrique arrière (93b) pour entraîner le véhicule aérien sans pilote (100) ;

    dans lequel un point d'action d'une force résultante des moteurs électriques avant (93a) et des moteurs électriques arrière (93b) exercée sur le véhicule aérien sans pilote (100) est le centre de force de portance (C), et un centre de gravité du véhicule aérien sans pilote (100) est adjacent au centre de force de portance (C), une saillie du centre de force de portance (C) sur un plan horizontal est configurée pour être adjacente à une saillie d'un centre de gravité de la partie de poids variable sur le plan horizontal,

    une saillie d'une région d'intersection (E), délimitée par des lignes de prolongement des bras arrière (102) vers la cellule (2) et par des lignes de prolongement des bras avant (101) vers la cellule (2) sur le plan horizontal, est située devant une saillie d'un centre de force de portance (C) du véhicule aérien sans pilote (100) sur le plan horizontal,

    caractérisé en ce qu'un couvercle de dissipation de chaleur étanche à l'eau est disposé sur une face d'extrémité supérieure des moteurs électriques à aile-rotor (93), le couvercle de dissipation de chaleur étanche à l'eau comprend une surface d'étanchéité supérieure (914) et une surface circonférentielle de paroi latérale, la surface circonférentielle de paroi latérale est pourvue d'un certain nombre de trous de ventilation (915) adjacents à la surface d'étanchéité supérieure (914), et une pale (911), distante d'un centre du couvercle de dissipation de chaleur étanche à l'eau, est disposée dans le couvercle de dissipation de chaleur étanche à l'eau et s'étend du trou de ventilation (915) vers un centre d'une paroi intérieure de la surface d'étanchéité supérieure (914).


     
    2. Véhicule aérien sans pilote (100) selon la revendication 1, dans lequel chacun des bras avant et des bras arrière est pourvu d'une pièce de fixation de bras, et la pièce de fixation de bras comprend :

    une première portion de fixation (10) reliée à la cellule (2) ; et

    une deuxième portion de fixation (11) reliée à la cellule (2),

    dans lequel la première portion de fixation (10) et la deuxième portion de fixation (11) sont reliées et ajustées l'une à l'autre pour définir une rainure de montage, chacun des bras avant et des bras arrière est disposé à travers la rainure de montage, et la première portion de fixation (10) et la deuxième portion de fixation (11) sont pourvues séparément d'au moins une surface extérieure plate reliée à la cellule (2).


     
    3. Véhicule aérien sans pilote (100) selon la revendication 2, dans lequel chacun des bras avant et des bras arrière est pourvu d'un trou de verrouillage de déviation de bras (12), la première portion de fixation (10) et la deuxième portion de fixation (11) sont toutes deux pourvues d'un trou de fixation de déviation de bras (15) dans une position correspondant au trou de verrouillage de déviation de bras (12).
     
    4. Véhicule aérien sans pilote (100) selon la revendication 2, dans lequel la première portion de fixation (10) et la deuxième portion de fixation (11) sont pourvues séparément d'une surface intérieure en arc (16) configurée pour s'adapter à une paroi extérieure de chacun des bras avant et des bras arrière.
     
    5. Véhicule aérien sans pilote (100) selon la revendication 2, dans lequel la première portion de fixation (10) et la deuxième portion de fixation (11) sont pourvues d'un trou d'attache de bras (13) configuré pour un raccord boulonné, et d'un trou de raccordement de cellule configuré pour un raccord boulonné avec la cellule (2).
     
    6. Véhicule aérien sans pilote (100) selon la revendication 1, dans lequel un corps de cavité repliable (81), un adaptateur (82) et une tige repliable de buse d'arrosage (83) sont disposés en dessous des bras avant et des bras arrière, un ensemble d'entraînement est disposé à l'intérieur du corps de cavité repliable (81), une portion centrale de l'adaptateur (82) est articulée à l'intérieur du corps de cavité repliable (81), une extrémité avant de l'adaptateur (82) est reliée à l'ensemble d'entraînement, et une extrémité arrière de l'adaptateur (82) passe à travers une ouverture du corps de cavité repliable (81) et est reliée de manière fixe à une première extrémité de la tige repliable de buse d'arrosage (83).
     
    7. Véhicule aérien sans pilote (100) selon la revendication 6, dans lequel l'ensemble d'entraînement comprend un corps d'entraînement, un arbre d'entraînement et une portion de raccordement montée à l'intérieur d'un boîtier, l'arbre d'entraînement est configuré pour être relié rotatif au corps d'entraînement et à la portion de raccordement, et le corps d'entraînement est utilisé pour entraîner l'arbre d'entraînement en rotation, de sorte que la portion de raccordement pousse l'adaptateur (82) à tourner par rapport au boîtier entre une première position et une deuxième position.
     
    8. Véhicule aérien sans pilote (100) selon la revendication 7, dans lequel une paroi extérieure de l'arbre d'entraînement est pourvue d'un filetage extérieur, la portion de raccordement est pourvue d'un trou d'ajustement, une paroi intérieure du trou d'ajustement est pourvue d'un taraudage intérieur, l'arbre d'entraînement est configuré pour traverser la portion de raccordement, et le filetage extérieur est configuré pour être compatible avec le taraudage intérieur.
     
    9. Véhicule aérien sans pilote (100) selon la revendication 7, dans lequel une première extrémité de l'arbre d'entraînement, éloignée du corps d'entraînement, est pourvue d'un palier de butée (89), le palier de butée (89) est fixé à l'intérieur du boîtier, et l'arbre d'entraînement est disposé rotatif à travers le palier de butée (89).
     
    10. Véhicule aérien sans pilote (100) selon la revendication 7, dans lequel l'extrémité avant de l'adaptateur (82) est formée pour être une rainure en forme de U (821) et la portion de raccordement est agencée à l'intérieur de la rainure en forme de U (821).
     
    11. Véhicule aérien sans pilote (100) selon la revendication 6, dans lequel le véhicule aérien sans pilote (100) comprend en outre :

    un module de commande utilisé pour commander l'ensemble d'entraînement pour entraîner l'adaptateur (82) en rotation ; et

    un module de détection de courant,

    dans lequel le module de détection de courant est utilisé pour détecter si un courant de l'ensemble d'entraînement est supérieur à un seuil prédéfini, et si le courant de l'ensemble d'entraînement est supérieur au seuil prédéfini, le module de détection de courant est utilisé pour envoyer, au module de commande, un signal de commande pour éteindre l'ensemble d'entraînement ; et le module de commande est utilisé pour éteindre l'ensemble d'entraînement selon le signal de commande.


     
    12. Véhicule aérien sans pilote (100) selon la revendication 1, dans lequel une cavité annulaire (916) compatible avec un trou d'air à l'intérieur du moteur électriques à aile-rotor (93), est formée entre le centre de la paroi intérieure de la surface d'étanchéité supérieure (914) et la pale (911).
     
    13. Véhicule aérien sans pilote (100) selon la revendication 12, dans lequel une hauteur d'une portion des pales (911) adjacente au centre de la paroi intérieure de la surface d'étanchéité supérieure (914), est inférieure à une hauteur d'une autre portion des pales (911) adjacente au trou de ventilation (915).
     
    14. Véhicule aérien sans pilote (100) selon l'une quelconque des revendications 1 à 13, dans lequel le centre de force de portance (C) est adjacent à un centre géométrique du dispositif de stockage d'articles (4), et de préférence, le centre de gravité du véhicule aérien sans pilote (100), le centre de force de portance (C), et le centre géométrique du dispositif de stockage d'articles (4) coïncident.
     




    Drawing

































    REFERENCES CITED IN THE DESCRIPTION



    This list of references cited by the applicant is for the reader's convenience only. It does not form part of the European patent document. Even though great care has been taken in compiling the references, errors or omissions cannot be excluded and the EPO disclaims all liability in this regard.

    Patent documents cited in the description