aircraft

Abstract

The present invention discloses an aircraft, which includes: a fuselage assembly; an arm device, the arm device being connected to the fuselage assembly; a power device, the power device being rotatably mounted on the outer end of the arm device, the power unit including a power motor and a propeller mounted on the power motor; a spray device, the spray device being located below the power device, the spray device being rotatably connected to the arm device; a drive device, the drive device being respectively connected to the power unit and the spray device, the drive device being used to drive the power unit and the spray device to rotate in the same direction. According to the aircraft of the present invention, when the aircraft moves forward, backward, or turns, the drive device drives the power unit and the spray device to rotate in the same direction, which is beneficial for ensuring that the central axis of the spray device and the rotational central axis of the propeller of the power device are always parallel to or coincide with each other, maintaining a state of uniform spraying of droplets, and improving the spraying effect of the aircraft.

Description

Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to an aircraft. Background Art

[0002] In related technologies, a drone has a propeller at the top of its arms and a spraying device at the bottom. Under normal circumstances, such as when the drone ascends or descends, the spray droplets are evenly dispersed downward by the downward pressure of the wind. However, when the drone moves forward, backward, or turns, the relative position of the spraying device and the downward pressure changes, resulting in uneven spraying of droplets and poor spraying effectiveness. Summary of the Invention

[0003] The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, the present invention provides an aircraft in which a drive device drives a power unit and a spraying device to rotate in the same direction when the aircraft moves forward, backward, or turns. This facilitates maintaining the central axis of the spraying device parallel to or coincident with the central axis of rotation of the propeller of the power unit, thereby maintaining a uniform spray of droplets and improving the spraying effect of the aircraft.

[0004] An aircraft according to an embodiment of the present invention includes: a fuselage assembly; an arm device, the arm device being connected to the fuselage assembly; a power device, the power device being rotatably mounted on the outer end of the arm device, the power unit comprising a power motor and a propeller mounted on the power motor; a spray device, the spray device being located below the power device, the spray device being rotatably connected to the arm device; and a drive device, the drive device being respectively connected to the power unit and the spray device, the drive device being used to drive the power unit and the spray device to rotate in the same direction.

[0005] According to the aircraft of the embodiment of the present invention, the driving device is respectively connected to the power unit and the spraying device. When the aircraft moves forward, backward or turns, the driving device drives the power unit and the spraying device to rotate in the same direction, which is beneficial for ensuring that the central axis of the spraying device and the rotational central axis of the propeller of the power device always remain parallel or coincident, maintaining a state of uniform spraying of droplets and improving the spraying effect of the aircraft.

[0006] In some embodiments of the present invention, the aircraft includes: a mounting seat, which is connected to the outer end of the arm device; the driving device includes: a driving motor and a transmission shaft, the output shaft of the driving motor is connected to the transmission shaft, the transmission shaft is rotatably connected to the mounting seat, and the transmission shaft is respectively connected to the power unit and the spraying device.

[0007] In some embodiments of the present invention, the power device further includes a fixing seat, the power motor is connected to the fixing seat, and the transmission shaft passes through the fixing seat and is detachably connected to the fixing seat.

[0008] In some embodiments of the present invention, the spraying device is connected to the mounting seat via a connecting rod, the connecting rod has a pivot shaft, the mounting seat is provided with a pivot hole, the pivot shaft is rotatably connected to the pivot hole, and the transmission shaft is connected to the pivot shaft to drive the connecting rod to rotate.

[0009] In some embodiments of the present invention, the transmission shaft is connected to the pivot shaft via a transmission device, the pivot shaft is located below the transmission shaft, and the rotation centerline of the pivot shaft is arranged parallel to the rotation centerline of the transmission shaft.

[0010] In some embodiments of the present invention, the transmission device includes: a first pulley, which is sleeved on the outer end of the transmission shaft; a second pulley, which is sleeved on the outer end of the pivot shaft; a transmission belt, one end of the transmission belt is sleeved on the outer peripheral side of the first pulley, and the other end of the transmission belt is sleeved on the outer peripheral side of the second pulley.

[0011] In some embodiments of the present invention, the driving device further includes: a fixed shell, which is detachably connected to the mounting base, the fixed shell including a main body, a first support part and a second support part, the first support part and the second support part are spaced apart on the main body, the transmission shaft is rotatably provided on the first support part and the second support part, and the driving motor is located below the transmission shaft.

[0012] In some embodiments of the present invention, the drive motor is connected to the transmission shaft through a connecting rod assembly, and the connecting rod assembly includes: a first adapter, one end of which is connected to the output shaft of the drive motor; a second adapter, which is located below the first adapter and one end of which is connected to the inner end of the transmission shaft; and a connecting rod, the two ends of which are pivotally connected to the other end of the first adapter and the other end of the second adapter, respectively.

[0013] In some embodiments of the present invention, the second supporting portion is detachably connected to the main body.

[0014] In some embodiments of the present invention, the first supporting portion has an installation space therein, and the circuit board of the driving motor is arranged in the installation space.

[0015] In some embodiments of the present invention, the spraying device is connected to the arm device via a connecting rod, wherein the connecting rod includes an elastic rod segment and a rigid rod segment connected to each other, and the elastic rod segment is configured to reduce the vibration transmission between the spraying device and the arm device.

[0016] Additional aspects and advantages of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description which follows, or may be learned by practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a perspective schematic diagram of an aircraft according to one embodiment of the present invention;

[0018] Figure 2 yes Figure 1 Schematic diagram of the rear view;

[0019] Figure 3 yes Figure 1 A side view schematic diagram of

[0020] Figure 4 is a perspective view of a partial structure of an aircraft according to one embodiment of the present invention;

[0021] Figure 5 is a schematic structural diagram of a connecting beam according to an embodiment of the present invention;

[0022] Figure 6 is a schematic structural diagram of an installation frame according to an embodiment of the present invention;

[0023] Figure 7 This is a schematic diagram of the assembly of a machine arm, a power unit, a drive unit, a mounting base, a connecting rod, and a spraying device according to one embodiment of the present invention;

[0024] Figure 8 is an exploded schematic diagram of a power device, a drive device, and a mounting base according to one embodiment of the present invention;

[0025] Figure 9 yes Figure 8 A schematic diagram of the structure in another direction;

[0026] Figure 10 2 is a schematic structural diagram of a mounting base according to an embodiment of the present invention.

[0027] Reference numerals:

[0028] Aircraft 100;

[0029] Fuselage assembly 1;

[0030] Connecting beam 11;

[0031] Mounting frame 12;

[0032] Arm device 2; Arm rod 21; Pivot member 22;

[0033] Mounting seat 23; pivot hole 231;

[0034] Sleeve portion 232; fixing portion 233;

[0035] Landing gear 3;

[0036] Power unit 4;

[0037] Power unit 41; power motor 411; propeller 412;

[0038] Fixed seat 42;

[0039] Driving device 5; driving motor 51; output shaft 511; transmission shaft 52; bearing member 521;

[0040] Transmission device 53; first pulley 531; second pulley 532; transmission belt 533;

[0041] Fixed housing 54; main body 541; matching groove 5411; mounting portion 5412; first support portion 542; second support portion 543; first housing 544; second housing 545; mounting cavity 5451;

[0042] Connecting rod assembly 55; first adapter 551; second adapter 552; connecting rod 553;

[0043] Circuit board 56;

[0044] Storage container 6; Battery 7;

[0045] Spraying device 8;

[0046] Connecting rod 9; pivot shaft 91; rod body 92; rigid rod segment 93; elastic rod segment 94. DETAILED DESCRIPTION

[0047] The following describes embodiments of the present invention in detail, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and are not to be construed as limiting the present invention.

[0048] The disclosure below provides many different embodiments or examples for realizing different structures of the present invention. In order to simplify the disclosure of the present invention, the components and settings of specific examples are described below. Of course, they are merely examples and are not intended to limit the present invention. In addition, the present invention may repeat reference numbers and / or letters in different examples. This repetition is for the purpose of simplicity and clarity and does not in itself indicate the relationship between the various embodiments and / or settings discussed. In addition, the present invention provides examples of various specific processes and materials, but those skilled in the art will appreciate the applicability of other processes and / or the use of other materials.

[0049] Please refer to the attached Figure 1-10 , describes an aircraft 100 according to an embodiment of the present invention, which can be used in the agricultural industry to spray pesticides or irrigate crops. For example, Figure 1 and Figure 2 As shown, the aircraft 100 can be a plant protection drone, which is an unmanned aircraft used for agricultural and forestry plant protection operations. This type of unmanned aircraft consists of a flight platform, a navigation flight control, a spraying system, etc., and the spraying operation is achieved through ground remote control or navigation flight control. It can spray pesticides, seeds, powders, etc.

[0050] Reference Figure 1 and Figure 2 As shown, the aircraft 100 according to an embodiment of the present invention may include: a fuselage assembly 1, an arm device 2, a power device 4, a spraying device 8 and a driving device 5. The spraying device 8 is used to spray medicine, seeds, powders and the like.

[0051] Reference Figure 2 As shown, the arm assembly 2 is connected to the fuselage assembly 1 . For example, there are two arm assemblies 2 , which are symmetrically arranged about the fuselage assembly 1 , and the inner end of each arm assembly 2 is connected to the fuselage assembly 1 .

[0052] Reference Figure 2 and Figure 3 As shown, the power unit 4 is rotatably mounted on the outer end of the arm assembly 2. The power unit 41 includes a power motor 411 and a propeller 412 mounted on the power motor 411. The spraying device 8 is located below the power unit 4 and is rotatably connected to the arm assembly 2. The drive device 5 is respectively connected to the power unit 41 and the spraying device 8. The drive device 5 is used to drive the power unit 41 and the spraying device 8 to rotate in the same direction. It can be understood that when the drive device 5 drives the power unit 41 to rotate counterclockwise around the arm assembly 2, the drive device 5 also drives the spraying device 8 to rotate counterclockwise; when the drive device 5 drives the unit 41 to rotate clockwise around the arm assembly 2, the drive device 5 also drives the spraying device 8 to rotate clockwise.

[0053] The inventors discovered in actual research that in related art, when a drone is in a hovering state, the propellers of the power unit rotate to form a downward pressure wind field below. The spraying device is located in the middle of the wind field, and the central axis of the spraying device is parallel to or coincides with the rotation axis of the propeller 4. The droplets sprayed from the spraying device are evenly dispersed downward along the downward pressure wind field. When the aircraft changes its flight state to fly forward, backward, left, or right, the drive motor at the bottom of the propeller controls the propeller to tilt around the arm device. However, the spraying device at the bottom of the arm cannot tilt synchronously with the propeller, resulting in a large angle between the propeller rotation axis and the central axis of the spraying device. The spray droplets are not evenly sprayed, thereby affecting the spraying effect of the aircraft 100.

[0054] In the aircraft 100 according to an embodiment of the present invention, the driving device 5 can drive the power unit 41 and the spraying device 8 to rotate in the same direction. When the aircraft 100 moves forward, backward or turns, it is beneficial to ensure that the central axis of the spraying device 8 and the rotation central axis of the propeller 412 of the power unit 4 always remain parallel or coincident. In other words, when the aircraft 100 changes its flight attitude, it is beneficial to ensure that the spraying device 8 is always located in the middle of the wind field. The droplets sprayed by the spraying device 8 can be evenly sprayed under the wind field formed by the power unit 41, thereby improving the spraying effect of the aircraft 100.

[0055] Alternatively, in some embodiments, a certain angle is preset between the central axis of the spraying device 8 and the central axis of rotation of the propeller 412 of the power device 4. At this angle, a better spraying effect can also be achieved. The spraying device 8 and the propeller 412 of the power device 4 rotate synchronously, so that the central axis of the spraying device 8 and the central axis of rotation of the propeller 412 of the power device 4 always maintain a suitable angle.

[0056] According to the aircraft 100 of the embodiment of the present invention, the driving device 5 is connected to the power unit 41 and the spraying device 8 respectively. When the aircraft 100 moves forward, backward or turns, the driving device 5 drives the power unit 41 and the spraying device 8 to rotate in the same direction, which is conducive to ensuring that the central axis of the spraying device 8 and the rotation central axis of the propeller 412 of the power unit 4 always remain parallel or coincident. The droplets sprayed by the spraying device 8 can be evenly sprayed under the wind field formed by the power unit 41, thereby improving the spraying effect of the aircraft 100.

[0057] Optionally, in some examples, reference Figure 7 and Figure 8As shown, the drive device 5 can drive the power unit 41 and the spraying device 8 synchronously and in the same direction. For example, when the drive device 5 drives the power unit 41 to rotate counterclockwise around the arm assembly 2 by a preset angle, the drive device 5 also drives the spraying device 8 to rotate counterclockwise by a preset angle. When the drive device 5 drives the power unit 41 to rotate clockwise around the arm assembly 2 by a preset angle, the drive device 5 also drives the spraying device 8 to rotate clockwise by a preset angle. As a result, the central axis of the spraying device 8 and the rotational central axis of the propeller 412 of the power unit 4 can be kept parallel or coincident at all times, which helps further improve the spraying accuracy of the spraying device 8, ensure the spray width, and further enhance the spraying effect of the spraying device 8.

[0058] In some embodiments of the present invention, reference Figure 7 and Figure 8 As shown, the aircraft 100 also includes a mounting seat 23, which is connected to the outer end of the arm assembly 2. For example, the arm assembly 2 includes two, and the two arm assemblies 2 are respectively located on both sides of the fuselage assembly 1. Each arm assembly 2 includes an arm rod 21 and a pivot member 22. The arm rod 21 is connected to the fuselage assembly 1 through the pivot member 22. The outer end of the arm rod 21 is the outer end of the arm assembly 2. The mounting seat 23 includes a sleeve portion 232 and two fixing portions 233. The sleeve portion 232 is sleeved on the outer end of the arm rod 21.

[0059] Reference Figure 7 and Figure 8 As shown, the drive device 5 includes a drive motor 51 and a transmission shaft 52. The output shaft 511 of the drive motor 51 is connected to the transmission shaft 52, which is rotatably connected to the mounting base 23. The transmission shaft 52 is respectively connected to the power unit 41 and the spraying device 8. The transmission shaft 52 is used to drive the power unit 41 and the spraying device 8 to rotate in the same direction. It will be understood that when the drive motor 51 is operating, the transmission shaft 52 can simultaneously drive the power unit 41 and the spraying device 8 to rotate, so that the power unit 41 and the spraying device 8 rotate in the same direction. In other words, only one drive motor 51 is required to achieve the same-direction rotation of the power unit 41 and the spraying device 8, which helps to simplify the structure of the aircraft 100 and reduce the cost of the aircraft 100.

[0060] Of course, the present invention is not limited to this. The driving device 5 may also include two sub-driving parts, which are respectively connected to the power unit 41 and the spraying device 8 to drive the power unit 41 and the spraying device 8 to rotate in the same direction. In other words, when one of the sub-driving parts controls the power unit 41 to rotate clockwise around the arm device 2, the other sub-driving part controls the spraying device 8 to rotate clockwise around the arm device 2; when one of the sub-driving parts controls the power unit 41 to rotate counterclockwise around the arm device 2, the other sub-driving part controls the spraying device 8 to rotate counterclockwise around the arm device 2. It should be noted that as long as the driving device 5 drives the power unit 41 and the spraying device 8 to rotate synchronously, it is within the protection scope of the present invention.

[0061] In some optional embodiments of the present invention, referring to Figure 8 As shown, the power unit 4 also includes a fixed base 42, a power motor 411 is connected to the fixed base 42, and a transmission shaft 52 is passed through the fixed base 42 and is detachably connected to the fixed base 42. For example, the power motor 411 and the fixed base 42 are detachably connected by means of threaded fasteners, clamping, or riveting. The outer peripheral wall of the transmission shaft 52 is provided with a plurality of mating teeth. The fixed base 42 has a fixing hole, and the inner peripheral wall of the fixing hole is provided with a plurality of tooth grooves. The plurality of mating teeth and the plurality of tooth grooves are matched in a one-to-one manner. Thus, by having the transmission shaft 52 pass through the fixed base 42 and be detachably connected to the fixed base 42, installation and removal between the power unit 4 and the transmission shaft 52 are facilitated, and maintenance is facilitated.

[0062] In some optional embodiments of the present invention, referring to Figure 7 and Figure 8 As shown, the spraying device 8 is connected to the mounting base 23 via a connecting rod 9. The connecting rod 9 has a pivot shaft 91. The mounting base 23 is provided with a pivot hole 231. The pivot shaft 91 is rotatably connected to the pivot hole 231. The transmission shaft 52 is connected to the pivot shaft 91 to drive the connecting rod 9 to rotate. For example, the connecting rod 9 includes a pivot shaft 91 and a rod body 92. The pivot shaft 91 is connected to one end of the rod body 92. The central axis of the pivot shaft 91 is perpendicular to the central axis of the rod body 92. The mounting base 23 is provided with two pivot holes 231. The axial ends of the pivot shaft 91 respectively correspond to the two pivot holes 231. Thus, through the rotatable connection between the connecting rod 9 and the mounting base 23, the spraying device 8 can rotate about the central axis of the pivot shaft 91. This reliable connection helps ensure the reliable spraying operation of the spraying device 8.

[0063] In some embodiments of the present invention, reference Figure 7 and Figure 8As shown, the transmission shaft 52 is connected to the pivot shaft 91 via a transmission device 53. The pivot shaft 91 is located below the transmission shaft 52, and the rotation centerline of the pivot shaft 91 is arranged parallel to the rotation centerline of the transmission shaft 52. For example, the transmission shaft 52 and the pivot shaft 91 are arranged parallel and spaced apart in the vertical direction, and the outer end of the pivot shaft 91 is connected to the outer end of the transmission shaft 52 via a belt transmission device. Of course, the present invention is not limited to this, and the pivot shaft 91 and the transmission shaft 52 can also be connected via a gear transmission device. It can be understood that by arranging the transmission shaft 52 and the pivot shaft 91 in parallel and spaced apart in the vertical direction, the transmission shaft 52, the connecting rod 9, and the spraying device 8 can be arranged compactly in the vertical direction, which helps to reduce the space occupied by the aircraft 100.

[0064] In some embodiments of the present invention, reference Figure 7 and Figure 8 As shown, the transmission device 53 includes a first pulley 531, a second pulley 532, and a transmission belt 533. The first pulley 531 is mounted on the outer end of the transmission shaft 52, and the second pulley 532 is mounted on the outer end of the pivot shaft 91. One end of the transmission belt 533 is mounted on the outer circumference of the first pulley 531, and the other end of the transmission belt 533 is mounted on the outer circumference of the second pulley 532. It can be understood that the belt transmission device 53 provides stable transmission, cushioning and vibration absorption, simple structure, low cost, and easy use and maintenance, thereby simplifying the overall structural complexity of the aircraft 100 and reducing costs.

[0065] In some embodiments of the present invention, reference Figure 7 As shown, the driving device 5 further includes a fixed housing 54 , which is detachably connected to the mounting seat 23 . For example, the fixed housing 54 and the mounting seat 23 are connected via threaded fasteners.

[0066] Reference Figure 8 and Figure 9As shown, the fixed housing 54 includes a main body 541, a first support portion 542, and a second support portion 543. The first support portion 542 and the second support portion 543 are spaced apart on the main body 541. The transmission shaft 52 is rotatably mounted on the first support portion 542 and the second support portion 543. For example, the transmission shaft 52 is pivotally connected to the first support portion 542 and the second support portion 543 via bearings 521, respectively. The drive motor 51 is located below the transmission shaft 52. It will be appreciated that rotatably mounting the transmission shaft 52 on the first support portion 542 and the second support portion 543 facilitates secure mounting of the transmission shaft 52 and ensures reliable operation of the transmission shaft 52. Furthermore, locating the drive motor 51 below the transmission shaft 52 and connected to the fixed housing 54 not only ensures secure mounting of the drive motor 51 but also makes the transmission shaft 52 and the drive motor 51 compact in the vertical direction, thereby optimizing the structural design of the aircraft 100.

[0067] In some embodiments of the present invention, reference Figure 7 and Figure 8 As shown, the driving motor 51 is connected to the transmission shaft 52 through a connecting rod assembly 55. The connecting rod assembly 55 includes a first adapter 551, a second adapter 552 and a connecting rod 553. One end of the first adapter 551 is connected to the output shaft 511 of the driving motor 51, the second adapter 552 is located above the first adapter 551, and one end of the second adapter 552 is connected to the transmission shaft 52. The two ends of the connecting rod 553 are pivotally connected to the other end of the first adapter 551 and the other end of the second adapter 552 respectively.

[0068] It can be understood that the drive motor 51 drives the first adapter 551 to rotate, thereby driving the connecting rod 553 to rotate the second adapter 552, the second adapter 552 drives the transmission shaft 52 to rotate, and the transmission shaft 52 drives the power unit 41 and the spraying device 8 to rotate in the same direction, so that when the aircraft 100 moves forward, backward or turns, the drive device 5 drives the power unit 41 and the spraying device 8 to rotate in the same direction, which is beneficial for keeping the central axis of the spraying device 8 and the central axis of the propeller 412 of the power device 4 always parallel or coincident, which is beneficial for maintaining a state of uniform spraying of droplets and improving the spraying effect of the aircraft 100, and the connecting rod assembly 55 has a simple structure and reliable operation.

[0069] In some optional embodiments of the present invention, referring to Figure 7 and Figure 8As shown, the second support portion 543 is detachably connected to the main body 541. For example, the second support portion 543 and the main body 541 are connected by threaded fasteners. It is understandable that by making the second support portion 543 detachably connected to the main body 541, it is convenient to realize the assembly and disassembly between the drive motor 51 and the transmission shaft 52 and the fixed housing 54, which is conducive to improving assembly and installation efficiency. For example, in some embodiments, the main body 541 and the first support portion 542 are integrated and constitute the first housing 544, the second support portion 543 is detachably connected to the first housing 544, and the fixed housing 54 further includes a second housing 545, the second housing 545 is arranged between the first support portion 542 and the second support portion 543, and the drive motor 51 is arranged in the installation cavity 5451 of the second housing 545.

[0070] In some optional embodiments of the present invention, the first support portion 542 includes an installation space, and the circuit board 56 of the drive motor 51 is disposed within the installation space. It will be appreciated that signals are transmitted between the circuit board 56 and the drive motor 51 to control the operation of the drive motor 51. By disposing the circuit board 56 of the drive motor 51 within the first support portion 542, the overall structure of the drive device 5 can be made compact, which helps reduce space usage. It also helps isolate the circuit board 56 of the drive motor 51 from the external environment, thereby ensuring the reliability of the operation of the drive device 5.

[0071] In some embodiments of the present invention, reference Figure 7 As shown, the spraying device 8 is connected to the arm device 2 via a connecting rod 9, and the connecting rod 9 includes an elastic rod segment 94 and a rigid rod segment 93 connected to each other. The elastic rod segment 94 is configured to reduce the vibration transmission between the spraying device 8 and the arm device 2. For example, in the top-down direction, the upper part of the connecting rod 9 may be the elastic rod segment 94, and the lower part of the connecting rod 9 may be the rigid rod segment 93, or, as shown in FIG. Figure 7 The upper portion of the connecting rod 9 is a rigid rod section 93 , and the lower portion of the connecting rod 9 is an elastic rod section 94 .

[0072] It is understandable that since the aircraft 100 will have certain vibrations during flight, and when the entire connecting rod 9 is a rigid rod, the vibration will be transmitted to the spraying device 8 through the connecting rod 9, which will have a certain negative impact on the spraying effect. Therefore, by making the connecting rod 9 include an elastic rod segment 94, the elastic rod segment 94 can reduce the vibration transmission between the spraying device 8 and the arm device 2, thereby improving the reliability of the spraying device 8 and ensuring the spraying effect.

[0073] Reference below Figures 1-10An aircraft 100 according to a specific embodiment of the present invention will now be described. It should be understood that the following description is merely illustrative and intended to explain the present invention, and should not be construed as limiting the present invention. Specifically, aircraft 100 can be used in the agricultural industry for operations such as spraying pesticides or watering crops. Of course, aircraft 100 can also be used in other fields, such as spraying fire extinguishing fluid during forest fires, aerial photography, power inspections, environmental monitoring, forest fire prevention, and disaster inspections.

[0074] refer to Figure 1-Figure 3 As shown, an aircraft 100 according to an embodiment of the present invention includes: a fuselage assembly 1, an arm device 2, a landing gear 3, a power device 3, a drive device 4, a storage container 5, a battery 7, an electronic control module, a spray device 8 and a connecting rod 9.

[0075] Reference Figure 1 and Figure 2 As shown, there are two arm devices 2, which are distributed on both sides of the fuselage assembly 1 and connected to the fuselage assembly 1. The landing gear 3 is fixed under the fuselage assembly 1 to ensure the stability of the aircraft during takeoff and landing. The power device 3 and the drive device 4 are installed at the outer ends of the arm devices 2. The power unit 41 includes a power motor 411 and a propeller 412 installed on the power motor 411. The power unit 41 provides lift for the flight of the aircraft 100.

[0076] Reference Figure 1 and Figure 2 As shown, the storage container 5 is mounted on the fuselage assembly 1 for containing items to be sprayed or transported, the battery 7 is fixed on the fuselage assembly 1 for providing power to the power unit 3 and the drive unit 4, the electronic control module is fixed on the fuselage assembly 1 for controlling the flight posture of the aircraft, the spraying device 8 is located below the power unit 3, the spraying device 8 is rotatably connected to the arm device 2, the spraying device 8 is used to spray the material in the storage container 5, such as solution, onto crops, and the drive unit 4 rotates in the same direction as the power unit and the spraying device 8 respectively.

[0077] Reference Figure 4-Figure 6 As shown, the fuselage assembly 1 includes a connecting beam 11 and a mounting frame 12 fixedly connected to the connecting beam 11. The connecting beam 11 includes a connecting portion 111 and two pivoting portions 112 connected at both ends of the connecting portion 111. Figure 5 As shown, a matching portion 113 extends from the end of the pivoting portion 112 , and the matching portion 113 is suitable for connecting with the inner end of the corresponding arm device 2 .

[0078] Reference Figure 4 and Figure 6The mounting frame 12 is adapted to be connected to the connecting portion 111. Specifically, the mounting frame 12 includes a front plate 121, a rear plate 122, and two side plates 123 connected to the front plate 121 and the rear plate 122. First mounting protrusions 124 are formed on the front plate 121 and the two side plates 123, and are adapted to be fixedly connected to the connecting portion 111.

[0079] Reference Figure 6 As shown, the front end panel 121, the rear end panel 122, and the two side panels 123 collectively enclose a mounting cavity 120 that extends vertically therethrough. The storage container 5 and the battery 7 are adapted to be inserted into the mounting cavity 120 and detachably connected to the front end panel 121, the rear end panel 122, and one or more of the two side panels 123. The two side panels 123 are formed into a first side panel portion 1231 and a second side panel portion 1232 that are bent and connected. The first side panel portion 1231 and the second side panel portion 1232 are connected by a transition portion 1233. Continuous reinforcing ribs are also formed on the side surfaces of the first side panel portion 1231, the second side panel portion 1232, and the transition portion 1233.

[0080] Further, refer to Figure 4 As shown, the installation frame 12 also includes an isolation plate 125, the two ends of which are respectively connected to the ends of the two second side plate portions 1232 close to the transition portion 1233. The isolation plate 125 divides the installation cavity 120 into a first installation cavity 1201 and a second installation cavity 1202. The battery 7 is installed in the first installation space 1201, and the storage container 6 is installed in the second installation space 1202.

[0081] Optionally, refer to Figure 4 As shown, the installation frame 12 further includes a reinforcing plate 126 . The reinforcing plate 126 is arranged parallel to the front end plate 121 , and both ends of the reinforcing plate 126 are connected to the first side plate portion 1231 .

[0082] Reference Figures 1-4 As shown, the two arm devices 2 are rotatably connected to the two pivotal portions 112 of the connecting beam 11 , respectively. Each arm device 2 includes an arm rod 21 and a pivot member 22 . The arm rod 21 is connected to the mounting frame 12 via the pivot member 22 .

[0083] Reference Figures 1-4 As shown, the landing gear 3 includes two support leg assemblies 301 . The two support leg assemblies 201 are mirror-symmetrical structures. The two support leg assemblies 301 are installed below the fuselage assembly 1 in a left-right symmetrical manner.

[0084] Reference Figure 10As shown, the mounting base 23 includes a sleeve portion 232 and two fixing portions 233. The sleeve portion 232 is sleeved on the outer end of the arm rod 21. The two fixing portions 233 are spaced apart and connected to the top end of the sleeve portion 232. The fixed shell 54 is connected to the two fixing portions 233 by threaded fasteners.

[0085] Reference Figures 8-10 As shown, the drive device 5 includes a fixed housing 54, a drive motor 51, and a circuit board 56. Specifically, the fixed housing 54 includes a first housing 544, a second housing 545, and a second support portion 543. The first housing 544 includes a main body 541 and a first support portion 542. The main body 541 has mating grooves 5411 formed on both side walls, and mounting portions 5412 formed on the side walls of the mating grooves 5411. The mounting portions 5412 are adapted to be connected to the two fixing portions 233 via fasteners.

[0086] Further, refer to Figure 8 As shown, the first shell 544 includes a main body 541 and a first support portion 542. An installation space suitable for installing a circuit board 56 is formed in the first support portion 542. An installation cavity 5451 for installing the drive motor 51 is formed in the second shell 545. The output shaft 511 of the drive motor 51 passes through the second shell 545 along the open end of the first shell 544. The second support portion 543 can be detachably installed on the first shell 544 to fix the second shell 545.

[0087] Further, refer to Figure 8 and Figure 9 As shown, the drive device 5 also includes two bearings 521, a transmission shaft 52, and a connecting rod assembly 55, wherein the two bearings 521 are respectively fixed to the second support portion 543 and the first support portion 542 at the top of the first housing 544, the transmission shaft 52 is provided through the two bearings 521, and the connecting rod assembly 446 includes a first adapter 551 connected to the output shaft 511 of the drive motor 51, a second adapter 552 connected to the transmission shaft 52, and a connecting rod 553 connected between the first adapter 551 and the second adapter 552, and the first adapter 551 and the second adapter 552 are respectively pivotally connected to the connecting rod 553. When the aircraft 100 needs to adjust its flight attitude, the drive motor 51 can be controlled to drive the transmission shaft 52 to rotate, thereby driving the power device 4 to rotate.

[0088] Reference Figure 7-10As shown, the spraying device 8 is rotatably fixed below the mounting seat 41. Specifically, the spraying device 8 is rotatably connected to the mounting seat 41 through a connecting rod 9, wherein the connecting rod 9 has a pivot shaft 91, and the connecting rod 9 and the mounting seat 41 are pivotally connected through the pivot shaft 91. Specifically, two pivot holes 231 are provided at the bottom of the sleeve portion 232 of the mounting seat 23, and the axial ends of the pivot shaft 91 of the connecting rod 9 respectively correspond to the two pivot holes 231 one by one.

[0089] Furthermore, the pivot shaft 91 is in transmission connection with the transmission shaft 52 via the transmission device 53. Thus, when the aircraft 100 needs to adjust its flight attitude, the drive motor 51 drives the transmission shaft 52 to rotate and drives the power unit 4 to rotate about the central axis of the transmission shaft 52. Simultaneously, the transmission shaft 52 drives the connecting rod 9 to rotate via the transmission device 53, causing the spraying device 8 to rotate in the same direction as the power unit 4. It will be appreciated that in the aircraft according to this embodiment of the present invention, when the power unit 4 rotates about the central axis of the transmission shaft 52, the pivot shaft 91 is simultaneously driven to rotate in the same direction via the transmission device 53, thereby driving the connecting rod 9 and the spraying device 8 to rotate in the same direction. This allows the droplets sprayed by the spraying device 8 to be evenly sprayed under the wind field formed by the power unit 4, thereby improving the spraying accuracy of the aircraft 100 and ensuring the spray width.

[0090] Other structures and operations of the aircraft 100 according to the embodiment of the present invention are well known to those skilled in the art and will not be described in detail here.

[0091] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0092] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature identified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0093] In the present invention, unless otherwise expressly specified or limited, terms such as "mounted," "connected," "connect," and "fixed" should be understood broadly. For example, they may refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0094] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0095] In the description of this specification, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0096] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to the embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the claims and their equivalents.

Claims

1. An aircraft (100), characterized in that: include; Fuselage assembly (1); An arm device (2), the arm device (2) being connected to the fuselage assembly (1); a power device (4), the power device (4) being rotatably mounted on the outer end of the arm device (2), the power device comprising a power unit, the power unit (41) comprising a power motor (411) and a propeller (412) mounted on the power motor (411), the power unit providing lift for the flight of the aircraft; a spraying device (8), the spraying device (8) being located below the power device (4), and the spraying device (8) being rotatably connected to the arm device (2); a driving device (5), the driving device (5) being connected to the power unit (41) and the spraying device (8) respectively, and the driving device (5) being used to drive the power unit (41) and the spraying device (8) to rotate in the same direction; When the aircraft changes its flight attitude, the central axis of the spraying device and the rotation central axis of the propeller of the power device always remain parallel or coincide with each other.

2. The aircraft (100) according to claim 1, characterized in that include: A mounting seat (23), the mounting seat (23) being connected to the outer end of the arm device (2); The driving device (5) comprises a driving motor (51) and a transmission shaft (52), wherein an output shaft (511) of the driving motor (51) is connected to the transmission shaft (52), the transmission shaft (52) is rotatably connected to the mounting seat (23), and the transmission shaft (52) is respectively connected to the power unit (41) and the spraying device (8).

3. The aircraft (100) according to claim 2, characterized in that The power device (4) further comprises a fixing seat (42), the power motor (411) is connected to the fixing seat (42), and the transmission shaft (52) passes through the fixing seat (42) and is detachably connected to the fixing seat (42).

4. The aircraft (100) according to claim 2, characterized in that The spraying device (8) is connected to the mounting seat (23) via a connecting rod (9), the connecting rod (9) having a pivot shaft (91), the mounting seat (23) being provided with a pivot hole (231), the pivot shaft (91) being rotatably connected to the pivot hole (231), and the transmission shaft (52) being connected to the pivot shaft (91) to drive the connecting rod (9) to rotate.

5. The aircraft (100) according to claim 4, characterized in that The transmission shaft (52) is connected to the pivot shaft (91) via a transmission device (53); the pivot shaft (91) is located below the transmission shaft (52); and the rotation centerline of the pivot shaft (91) is arranged parallel to the rotation centerline of the transmission shaft (52).

6. The aircraft (100) according to claim 5, characterized in that The transmission device (53) comprises: a first pulley (531), wherein the first pulley (531) is sleeved on the outer end of the transmission shaft (52); a second pulley (532), the second pulley (532) being sleeved on the outer end of the pivot shaft (91); A transmission belt (533), one end of the transmission belt (533) is sleeved on the outer peripheral side of the first pulley (531), and the other end of the transmission belt (533) is sleeved on the outer peripheral side of the second pulley (532).

7. The aircraft (100) according to claim 2, characterized in that The driving device (5) further comprises: A fixed shell (54) is detachably connected to the mounting seat (23), and the fixed shell (54) includes a main body (541), a first support portion (542), and a second support portion (543). The first support portion (542) and the second support portion (543) are spaced apart on the main body (541). The transmission shaft (52) is rotatably provided on the first support portion (542) and the second support portion (543). The drive motor (51) is located below the transmission shaft (52).

8. The aircraft (100) according to claim 7, characterized in that The driving motor (51) is connected to the transmission shaft (52) via a connecting rod assembly (55), and the connecting rod assembly (55) includes: a first adapter (551), one end of the first adapter (551) being connected to the output shaft (511) of the drive motor (51); a second adapter (552), the second adapter (552) being located below the first adapter (551), and one end of the second adapter (552) being connected to the inner end of the transmission shaft (52); A connecting rod (553), both ends of which are pivotally connected to the other end of the first adapter (551) and the other end of the second adapter (552), respectively.

9. The aircraft (100) according to claim 7, characterized in that The second supporting portion (543) is detachably connected to the main body portion (541).

10. The aircraft (100) according to any one of claims 7 to 9, characterized in that The first supporting portion (542) has an installation space therein, and the circuit board (56) of the driving motor (51) is arranged in the installation space.

11. The aircraft (100) according to claim 1, characterized in that The spraying device (8) is connected to the arm device (2) via a connecting rod (9), wherein the connecting rod (9) comprises an elastic rod segment (93) and a rigid rod segment (94) connected to each other, and the elastic rod segment (93) is configured to reduce vibration transmission between the spraying device (8) and the arm device (2).

Images