WO2022266807A1 - Véhicule aérien sans pilote - Google Patents

Véhicule aérien sans pilote Download PDF

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Publication number
WO2022266807A1
WO2022266807A1 PCT/CN2021/101294 CN2021101294W WO2022266807A1 WO 2022266807 A1 WO2022266807 A1 WO 2022266807A1 CN 2021101294 W CN2021101294 W CN 2021101294W WO 2022266807 A1 WO2022266807 A1 WO 2022266807A1
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WO
WIPO (PCT)
Prior art keywords
unmanned aerial
aerial vehicle
fuselage
arm
vehicle according
Prior art date
Application number
PCT/CN2021/101294
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English (en)
Chinese (zh)
Inventor
肖翔
Original Assignee
深圳市大疆创新科技有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to CN202180099737.1A priority Critical patent/CN117561202A/zh
Priority to PCT/CN2021/101294 priority patent/WO2022266807A1/fr
Publication of WO2022266807A1 publication Critical patent/WO2022266807A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft

Definitions

  • the present application relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle.
  • UAVs have been widely used in aerial photography, industry inspections, disaster relief operations and other fields in recent years, and continue to develop towards miniaturization and portability. This requires that the drone can be easily carried and stored when not in use.
  • the arms of the UAV can be folded, and the maximum size of the UAV can be reduced by folding to facilitate carrying and storage. Therefore, it is necessary to provide a folding scheme for the arm, which can make the shape of the UAV in the folded state as regular as possible without obvious protrusions, so as to fill the enveloping cube surrounded by the maximum size of the UAV to the greatest extent. volume inside.
  • Embodiments of the present application provide a drone.
  • An embodiment of the present application provides an unmanned aerial vehicle, and the unmanned aerial vehicle includes a fuselage and a plurality of arms.
  • a plurality of arms are rotatably connected to the fuselage, so that the UAV can be in a folded state and an unfolded state, and the free ends of the arms are connected with power components, wherein, when the UAV is in the folded state In the process of switching between the unfolded state and the unfolded state, the arm rotates around an inclined shaft, and in the folded state, the arm is folded on the circumferential side of the fuselage, and a plurality of the power components are basically attached.
  • the arms when the unmanned aerial vehicle is in the folded state, the arms can be folded on the circumferential side of the fuselage, and a plurality of power components are basically attached, so that the unmanned aerial vehicle is in the folded state, without The arm and power components of the man-machine fill the volume of the envelope cube surrounded by the maximum size of the drone to the maximum extent, which improves the convenience of the drone.
  • FIG. 1 is a schematic structural view of an unmanned aerial vehicle in an unfolded state according to an embodiment of the present application
  • Fig. 2 is a schematic structural view of the tripod of the drone in the embodiment of the present application in a folded state
  • FIG. 3 is a schematic structural view of the UAV in a folded state according to the embodiment of the present application.
  • Fig. 4 is the perspective view of the unmanned aerial vehicle of the embodiment of the present application.
  • Fig. 5 is a schematic diagram of the folding process scene of the drone according to the embodiment of the present application.
  • 6 to 8 are perspective views of the drone according to the embodiment of the present application.
  • FIG. 9 is a schematic structural view of the unmanned aerial vehicle in the deployed state according to the embodiment of the present application.
  • FIG. 10 is a schematic structural view of the UAV in a folded state according to the embodiment of the present application.
  • FIG. 11 and FIG. 12 are schematic structural views of the pan-tilt camera of the drone according to the embodiment of the present application.
  • Fig. 13 is a schematic structural diagram of the battery of the drone in the embodiment of the present application in a pulled-out state.
  • first and second are used for descriptive purposes only, and cannot be interpreted as indicating or implying relative importance or implicitly specifying the quantity of indicated technical features.
  • a feature defined as “first” or “second” may explicitly or implicitly include one or more of said features.
  • “plurality” means two or more, unless otherwise specifically defined.
  • connection should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection. connected, or integrally connected. It can be a mechanical connection or an electrical connection. It can be directly connected or indirectly connected through an intermediary, and it can be the internal communication of two elements or the interaction relationship between two elements. Those of ordinary skill in the art can understand the specific meanings of the above terms in this application according to specific situations.
  • a first feature being “on” or “under” a second feature may include direct contact between the first and second features, and may also include the first and second features Not in direct contact but through another characteristic contact between them.
  • “above”, “above” and “above” the first feature on the second feature include that the first feature is directly above and obliquely above the second feature, or simply means that the first feature is horizontally higher than the second feature.
  • "Below”, “under” and “under” the first feature to the second feature include that the first feature is directly below and obliquely below the second feature, or simply means that the first feature is less horizontally than the second feature.
  • the UAV 100 includes a body 10 and a plurality of arms 20 .
  • a plurality of machine arms 20 are rotatably connected to the fuselage 10, so that the unmanned aerial vehicle 100 can be in a folded state and an unfolded state, and the free ends of the machine arms 20 are connected with a power assembly 21.
  • the arm 20 rotates around a tilting shaft 13 , and in the folded state, the arm 20 is closed to the circumferential side 11 of the fuselage 10 , and the plurality of power components 21 are basically attached.
  • the machine arm 20 when the UAV 100 is in a folded state, the machine arm 20 can be folded on the circumferential side 11 of the fuselage 10, and a plurality of power components 21 are basically attached, so that the UAV 100 is in a folded state.
  • the arm 20 and the power assembly 21 of the UAV 100 fill up the volume of the enveloping cube surrounded by the maximum size of the UAV 100 to the greatest extent, which improves the convenience of the UAV 100 .
  • the UAV 100 in the embodiment of the present application may be used to perform tasks including but not limited to patrolling, exploration, photography, photographing, and agriculture.
  • the drone 100 includes a fuselage 10 , a plurality of arms 20 , a pan-tilt camera 30 , an obstacle avoidance component 40 , and a battery 50 .
  • a plurality of arms 20 are rotatably connected to the fuselage 10 .
  • the pan-tilt camera 30 is connected to the bottom 103 of the fuselage 10 .
  • the obstacle avoidance components 40 are distributed on the drone 100 , and the obstacle avoidance components 40 can realize effective obstacle perception and obstacle avoidance, ensuring the safety of the drone 100 during work.
  • the battery 50 is at least partially accommodated in the fuselage 10 , and the battery 50 can provide electric energy for the drone 100 . In one embodiment, most of the battery is accommodated in the body, and the top of the battery can be exposed from the body, so as to facilitate maintenance and other operations on the battery.
  • the circumferential side 11 includes a first side 101 and a second side 102 opposite to each other.
  • the circumferential side 11 of the fuselage 10 is provided with a mounting portion 111 , and each of the first side 101 and the second side 102 is provided with a mounting portion.
  • the fuselage 10 also includes a bottom 103 and a top surface 104 .
  • the bottom 103 of the fuselage 10 defines an accommodating slot 1031 , and the bottom 103 of the fuselage 10 is also connected with a tripod 12 .
  • the top surface 104 of the fuselage 10 defines a receiving groove 1041 .
  • the tripod 12 is connected to the bottom 103 of the fuselage 10 , and the tripod 12 is foldable. When the UAV 100 is in a folded state, the tripod 12 is folded on the circumferential side 11 of the fuselage 10 . At least a portion of the arm 20 covers at least a portion of the stand 12.
  • the stand 12 includes an unfolded state and a folded state. Please refer to FIG. 1 , which is a schematic diagram of the stand 12 in an unfolded state. Please refer to FIG. 2 , which is a schematic diagram of the stand 12 being folded.
  • the tripod 12 can support the UAV 100 when it is unfolded, and can make the UAV 100 rise on the ground or the platform smoothly; it can also make the UAV 100 land on the ground or the platform smoothly.
  • the fuselage 10 is provided with a gripping portion, through which the user can use the drone 100 by hand. That is to say, the user can disassemble the tripod 12 and hold the handle to raise and lower.
  • the stand 12 includes four supports, all of which can be manually expanded and folded, or electrically expanded and folded, which is not specifically limited here. When the tripod 12 is in the folded state, the four tripod supports are all gathered in the circumferential side 11 of the fuselage 10, the tripod support can be close to the circumferential side 11, and at least a part of the arm 20 covers at least part of the tripod 12.
  • the shape of the UAV 100 in the folded state is as regular as possible without obvious protrusions. It can be understood that, in other embodiments, the stand may also be non-foldable, that is, the stand is fixed to maintain an unfolded state.
  • the arm 20 includes a first section 201 and a second section 202 connected.
  • the free end of the arm 20 is connected with a power assembly 21 , that is to say, in the embodiment shown in FIG. 1 , the end of the second section 202 is connected with a power assembly 21 , and the power assembly 21 includes a motor 211 and a propeller 212 .
  • the plurality of arms 20 includes a first arm set 22 and a second arm set 24 .
  • FIG. 1 is a schematic diagram of the structure of the drone 100 in an unfolded state
  • FIG. 3 is a schematic diagram of the structure of the drone 100 in a folded state.
  • each arm 20 rotates around a tilting axis 13 .
  • the UAV 100 includes a tilting shaft 13, which is connected to the fuselage 10 and the arm 20.
  • the tilting shaft 13 is obliquely arranged in the fuselage 10.
  • the tilting shaft 13 can be understood as that the axis of rotation is not perpendicular to the rotation axis.
  • the axis of rotation of the plane is a tilting shaft 13, which is connected to the fuselage 10 and the arm 20.
  • the tilting shaft 13 is obliquely arranged in the fuselage 10.
  • the tilting shaft 13 can be understood as that the axis of rotation is not perpendicular to the rotation axis.
  • the axis of rotation of the plane is a tilting shaft 13 which is connected to the fuselage 10 and the arm 20.
  • the tilting shaft 13 includes a rotation axis L. It can be seen from FIG.
  • the formed rotation plane is not perpendicular to the tilting axis of rotation 13 .
  • FIG. 5 is a schematic diagram of a scene where one arm 21 of the UAV 100 is switched from an unfolded state to a folded state.
  • the downward folding rotation and twisting rotation of the machine arm 20 can be realized by one rotation, so that the machine arm 21 can be well folded on the circumferential side 11 of the fuselage 10 .
  • the fuselage 10 includes a first plane C1 , a second plane C2 and a third plane C3 that are orthogonal to each other.
  • the first surface C1 can be understood as the front of the fuselage 10
  • the second surface C2 can be understood as the top surface of the fuselage 10
  • the third surface C3 can be understood as the right side of the fuselage 10 .
  • the size of the first included angle ⁇ , the size of the second included angle ⁇ and the size of the third included angle ⁇ can also be selected within a certain range, so that the propeller 212 of the UAV 100 and the horizontal plane meet the design requirements. angle.
  • the first surface C1 is the front side of the fuselage
  • the second surface C2 is the top surface of the fuselage 10
  • the third surface C3 is the right side of the fuselage. It can be understood that the first surface C1 , the second surface C2 and the third surface C3 can be specifically set according to the configuration of the fuselage, and are not limited to the above-mentioned front side, top surface and right side.
  • the arms 20 of the same arm group are arranged side by side on the side, so that the shape of the drone 100 in the folded state is as regular as possible without obvious protrusions.
  • the arm 20 includes a first section 201 and a second section 202 connected, the first section 201 is rotatably connected to the fuselage 10 , and the second section 202 is inclined upward at a preset acute angle relative to the first section 201 . That is to say, the connection between the first section 201 and the second section 202 is not connected at 180 degrees, and the connection between the first section 201 and the second section 202 is at a certain angle, so that in the folded state, the arm
  • the turning structure formed by the first section 201 and the second section 202 of 20 can make the motor 211 not protrude from the outline of the fuselage 10, making the folded UAV 100 more regular and compact, and enhancing the portability of the UAV 100.
  • the second section 202 is inclined upward by a predetermined acute angle, which may vary according to different structures of the fuselage 10 or other structures, which is not limited here.
  • the plurality of arms 20 includes a first arm set 22 and a second arm set 24 .
  • the circumferential side 11 includes opposite first side 101 and second side 102 , the first side 101 defines a first recess 1010 , and the second side 102 defines a second recess 1020 .
  • the arms 20 of the first arm set 22 are at least partially located in the first recess 1010 .
  • the arms 20 of the second arm set 24 are at least partially located in the second recess 1020 .
  • the arm 20 can fill the volume of the enveloping cube enclosed by the maximum size of the UAV 100 to the greatest extent, which improves the convenience of the UAV 100 .
  • the power assembly 21 is connected to the free end of the machine arm 20 .
  • the free end refers to the end of the arm away from the fuselage 10 .
  • the arm 20 is closed to the circumferential side 11 of the fuselage 10 , and the plurality of power components 21 are basically attached. In this way, the arm 20 and the power assembly 21 of the UAV 100 fill up the volume of the enveloping cube surrounded by the maximum size of the UAV 100 to the maximum, which improves the convenience of the UAV 100 .
  • the so-called basic fit refers to gathering together, and is not limited to the fit of each part.
  • the propeller 212 of the power assembly 21 may not be attached, but the motor 211 may be attached.
  • Substantial fit may also refer to touching together, or may refer to being separated by a distance, the distance being within a desired range.
  • the power assembly 21 includes a first power assembly 21a and a second power assembly 21b.
  • a plurality of machine arms 20 includes a first machine arm group 22 and a second machine arm group 24, the circumferential side 11 includes a first side 101 and a second side 102 opposite to each other, and the first machine arm group 22 is rotatably connected to the first side 101, the second arm set 24 is rotatably connected to the second side 102, the first power assembly 21a of the first arm set 22 is basically attached, and the second power assembly 21b of the second arm set 24 is basically attached.
  • the first power assembly 21a is arranged on the first arm group 22
  • the second power assembly 21b is arranged on the second arm group 24 .
  • the arm 20 and the power assembly 21 of the UAV 100 fill the volume in the envelope cube surrounded by the maximum size of the UAV 100 to the greatest extent, which improves the unmanned Machine 100 Convenience.
  • the power assembly 21 includes a motor 211.
  • the two motors 211 of the same machine arm group are basically attached. That is to say, the power assembly 21 includes a first power assembly 21a and a second power assembly 21b.
  • the first power assembly 21a includes two motors 211, namely a first motor 211a and a second motor 211b
  • the second power assembly 21b includes two motors 211, namely a third motor 211c and a fourth motor 211d.
  • four arms 20 are rotatably connected to the fuselage 10 .
  • the four arms 20 include a first arm group 22 and a second arm group 24 .
  • the first arm set 22 may include a first arm 20a and a second arm 20b.
  • the second arm set 24 may include a third arm 20c and a fourth arm 20d.
  • the free end of the first machine arm 20a is connected to the first motor 211a
  • the free end of the second machine arm 20b is connected to the second motor 211b
  • the free end of the third machine arm 20c is connected to the third motor 211c
  • the free end of the fourth machine arm 20d The fourth motor 211d is connected.
  • the first motor 211a and the second motor 211b are basically attached on the first side 101, specifically, the bottom of the first motor 211a is basically attached to the bottom of the second motor 211b; the third motor 211c and the second The four motors 211d are basically attached on the second side 102, specifically, the bottom of the third motor 211c is basically attached to the bottom of the fourth motor 211d.
  • the motors 211 of the plurality of power assemblies 21 are located at the bottom 103 of the fuselage 10 .
  • the shape of the UAV 100 can be as regular as possible in the folded state, and the arm 20 and the power assembly 21 of the UAV 100 can fill the volume in the enveloping cube surrounded by the maximum size of the UAV 100 to the greatest extent.
  • the convenience of the UAV 100 is guaranteed.
  • the propeller 212 is connected to the motor 211 , and the propeller 212 includes folding paddles.
  • the drone includes four arms 20, namely: a first arm 20a, a second arm 20b, a third arm 20c and a fourth arm 20d.
  • the power assembly 21 includes propellers 212, four propellers 212 are respectively arranged on the first machine arm 20a, the second machine arm 20b, the third machine arm 20c and the fourth machine arm 20d, and the four propellers 212 are respectively connected with the first motor 211a , the second motor 211b, the third motor 211c and the fourth motor 211d are connected.
  • the first motor 211a, the second motor 211b, the third motor 211c and the fourth motor 211d can drive the four propellers 212 to rotate, thereby controlling the rotation direction and the rotation speed of the propellers 212 .
  • the propeller 212 includes an upper surface 2121 and a lower surface 2122 , and when the UAV 100 is in a folded state, the upper surface 2121 of the propeller 212 faces away from the fuselage 10 .
  • the paddle plane of the propeller 212 is substantially horizontal, and when the UAV 100 is in the folded state, the paddle plane of the propeller 212 is parallel to the circumferential side 11 of the fuselage 10 .
  • the unmanned aerial vehicle 100 can ensure stable flight performance in the unfolded state, and the appearance is as regular as possible in the folded state, without obvious protrusions, so as to fill the package surrounded by the maximum size of the unmanned aerial vehicle 100 to the greatest extent.
  • the paddle plane of the propeller 212 is parallel to the front side or the rear side of the fuselage 10 .
  • the pan-tilt camera 30 is connected to the bottom of the fuselage 10 .
  • the orthographic projections of the pan-tilt camera 30 and the machine arm 20 on a plane are staggered, and the plane is perpendicular to the length direction of the fuselage 10, so that physical interference between the machine arm 20 and the pan-tilt camera 30 can be avoided.
  • the bottom 103 of the fuselage 10 is provided with an accommodating groove 1031, and the gimbal camera 30 is at least partially located in the accommodating groove 1031, which can further reduce the space occupation of the UAV 100.
  • a part of the pan-tilt camera 30 is accommodated in the accommodating groove 1031 , and a part protrudes out of the accommodating groove 1031 .
  • the pan-tilt camera 30 When the UAV 100 is in a folded state, the pan-tilt camera 30 is located in the space surrounded by a plurality of arms 20 . In this way, the pan-tilt camera 30 is set in the space surrounded by a plurality of machine arms 20, and the volume in the envelope cube surrounded by the maximum size of the UAV 100 is filled to the greatest extent, and the convenience of the UAV 100 is improved.
  • a plurality of arms 20 can protect the pan-tilt camera 30, and try to prevent the pan-tilt camera 30 from being scratched, scratched, or damaged due to bumps when the drone 100 is carried after being folded.
  • the bottom 103 of the fuselage may not have the accommodating groove 1031 , and the pan-tilt camera 30 may be integrally protruded from the bottom 103 of the fuselage.
  • the pan-tilt camera 30 includes a pan-tilt 31 and a camera 32 .
  • the cloud platform 31 includes a first shaft assembly 311, a second shaft assembly 312 and a third shaft assembly 313, the first shaft assembly 311 is connected to the fuselage 10, the second shaft assembly 312 is connected to the first shaft assembly 311 and the third shaft assembly 313,
  • the camera 32 is mounted on the third axis assembly 313, so that the gimbal 31 has three degrees of freedom of the axis, plus the three axes of freedom of the UAV 100 itself, the camera 32 can realize a maximum of six degrees of freedom of the axis.
  • the first axis assembly 311 is the pitch axis assembly 311 of the gimbal 31 (ie, the Pitch axis assembly), and the second axis assembly 312 is the yaw axis assembly 312 of the gimbal 31 (ie, the Yaw axis assembly).
  • the third axis assembly 313 is the roll axis assembly 313 of the gimbal 31 (that is, the Roll axis assembly). That is to say, the pitch axis assembly 311 is connected to the fuselage 10 , the yaw axis assembly 312 is connected to the pitch axis assembly 311 and the roll axis assembly 313 , and the camera 32 is installed on the roll axis assembly 313 .
  • the pitch axis assembly 311 includes a pitch axis motor, which can control the pitch motion of the camera 32 .
  • the yaw axis assembly 312 includes a yaw axis motor that can control the yaw motion of the camera 32 .
  • the roll axis assembly 313 includes a roll axis motor, which can control the roll motion of the camera 32 . In this way, flexible viewing of the UAV 100 can be realized.
  • the pan/tilt camera 30 can obtain a large control range of pitch motion through the configuration of the first axis assembly-Pitch axis assembly, the second axis assembly-Yaw axis assembly and the third axis assembly-Roll axis assembly, which is beneficial to the unmanned aerial vehicle 100 for overhead shooting, reverse shooting, and even overhead shooting. It can also obtain a large rolling motion control range, which is beneficial to shooting rotation and turnover images, and enhances the flexibility of film and television creation. At the same time, a larger rolling motion control range means that the image of the camera 32 can be directly rotated by 90 degrees Switching between horizontal and vertical shooting is beneficial for shooting vertical screen videos.
  • the yaw control range of the UAV 100 is controllable in any yaw direction of 360°, and the UAV 100 can complement the yaw control range of the gimbal camera 30 . That is to say, the unmanned aerial vehicle 100 can realize large-scale, preliminary yaw control, and the pan-tilt camera 30 can realize small-scale, fine yaw control, so that the unmanned aerial vehicle 100 can achieve the yaw control with the pan-tilt camera 30
  • the scope of navigation control is complementary.
  • the motor axis of the pitch axis assembly 311 is the first axis K1
  • the motor axis of the yaw axis assembly 312 is the second axis K2
  • the motor axis of the roll axis assembly 313 is the third axis K3 .
  • the first axis K1, the second axis K2 and the third axis K3 may not be orthogonal, that is, not perpendicular to each other.
  • the included angles among the three axes are all non-90-degree included angles, the configuration of the non-orthogonal pan/tilt camera 30 is formed.
  • the motor when a certain pan/tilt motor rotates, causing the camera 32 to take pictures in the rolling direction, the motor is called an orthogonal roll axis motor; when a certain pan/tilt motor rotates In the case of movement, the camera 32 causes movement in multiple directions such as the rolling direction and the pitching direction of the picture taken by the camera 32, and the motor is called a non-orthogonal rolling axis and pitching axis motor.
  • the movement of other axes can also be deduced by analogy.
  • the obstacle avoidance assembly 40 includes a plurality of visual sensors 41, and a plurality of visual sensors 41 are distributed in a polyhedron in space, and each plane of the polyhedron is distributed with at least one visual sensor 41, and two visual sensors 41 on different planes A binocular obstacle avoidance system is formed, and the obstacle avoidance observation area of the binocular obstacle avoidance system is the overlapping area of the observation ranges of the two visual sensors 41 .
  • the effective perception and avoidance of obstacles can be realized to ensure the safety of the drone during work.
  • the multiple visual sensors 41 are distributed in a polyhedron in space, and the polyhedron includes but not limited to tetrahedron, pentahedron, hexahedron, etc., which are not specifically limited here.
  • Each plane of the polyhedron is distributed with at least one visual sensor 41, and two visual sensors 41 on different planes form a binocular obstacle avoidance system, and the obstacle avoidance observation area of the binocular obstacle avoidance system is the range of observation of the two visual sensors 41. overlap area.
  • a plurality of visual sensors 41 can realize effective obstacle perception and obstacle avoidance if one of the following conditions is met: all visual sensors 41 are arranged on the fuselage 10, or some of the visual sensors 41 are arranged on the fuselage 10, and the rest of the visual sensors 41 are arranged on the machine arm 20, or all visual sensors 41 are arranged on the machine arm 20.
  • the obstacle avoidance assembly 40 includes four visual sensors 41, and the four visual sensors 41 can be arranged on the fuselage 10. The four visual sensors 41 are combined in pairs to form six binocular obstacle avoidance systems.
  • the collection of the obstacle avoidance observation areas of the binocular obstacle avoidance system covers the entire space sphere, so that obstacles in the obstacle avoidance observation area of the binocular obstacle avoidance system can be observed to realize effective obstacle perception and obstacle avoidance, and ensure the work of the UAV. safety in the process.
  • the four visual sensors 41 include a front upper visual sensor 41 , a rear upper visual sensor 41 , a lower left visual sensor 41 and a lower right visual sensor 41 .
  • the front upper visual sensor 41 and the rear upper visual sensor 41 are located at the same height of the fuselage 10
  • the left lower visual sensor 41 and the right lower visual sensor 41 are located at the same height of the fuselage 10 .
  • the four visual sensors 41 can also be arranged in other ways, for example, the four visual sensors 41 include an upper left visual sensor 41, an upper right visual sensor 41, a front lower visual sensor 41 and a rear lower visual sensor 41, etc. .
  • the four visual sensors 41 may all be located at the same height, or may be located at four different heights. It is not limited here.
  • the vision sensors 41 When part of the visual sensors 41 are arranged on the fuselage 10, and the rest of the visual sensors 41 are arranged on the machine arm 20, still taking four visual sensors 41 as an example, three visual sensors 41 can be arranged on the circumferential side 11 or the bottom of the fuselage 103, another visual sensor can be set on the top of the fuselage (that is, the top surface 104).
  • the vision sensors 41 on the circumferential sides 11 can be arranged at different heights of the fuselage 10, or at the same height.
  • the UAV 100 includes four machine arms, and each visual sensor 41 can be arranged on the free end of a corresponding machine arm 20. . It is advisable that the motor 211 and the propeller 212 do not enter the field of view (FOV) of the visual sensor 41 .
  • FOV field of view
  • the FOV of the visual sensor 41 in the above-mentioned embodiment can be selected according to the configuration of the drone 100 and the arrangement of the visual sensor 41, so that the binocular obstacle avoidance system formed by the visual sensor 41 can completely cover or basically cover the drone 100.
  • the FOV may be greater than 180 degrees, such as 190 degrees, 220 degrees, etc.
  • the plurality of visual sensors 41 may be two, three, or more than four, and so on.
  • the visual sensor 41 can be arranged on the installation part 111 , and the installation part 111 is arranged on the circumferential side 11 of the fuselage 10 , and when the UAV 100 is in a folded state, the installation part 111 abuts against the arm 20 .
  • the installation part 111 facilitates the installation of the visual sensor 41
  • the installation part 111 can limit the arms 20 to prevent the arms 20 from colliding and being damaged when they rotate, and can also protect the tilting shaft 31 at the same time.
  • the battery 50 can provide electric energy for the drone 100 .
  • the top surface 104 of the fuselage 10 defines a receiving slot 1041 , and the battery 50 is at least partially received in the receiving slot 1041 .
  • the battery 50 is detachably accommodated in the receiving slot 1041 , and the detachment or installation direction of the battery 50 is along the length direction of the fuselage 10 .
  • the center of gravity of the battery 50 coincides with the center of lift of the drone 100 in the vertical direction.
  • the receiving slot 1041 includes a battery compartment, and the receiving slot 1041 is used for receiving the battery 50 .
  • the receiving slot 1041 and the battery 50 can be fixed by engaging, which is not limited herein.
  • the size of the receiving groove 1041 is related to the size of the battery 50 .
  • the center of gravity of the battery 50 coincides with the center of lift of the drone 100 in the vertical direction.
  • the center of lift may be the center of the resultant of the lift of the four propellers 212 .
  • the battery 50 includes an extended battery, which can enhance the endurance of the drone 100 .
  • the center of gravity of the extended battery coincides with the center of lift of the UAV 100 in the vertical direction, and the lengthening and weighting of the battery will not cause the center of gravity of the UAV to shift horizontally (the horizontal direction is perpendicular to the vertical direction).
  • the center of gravity of the UAV coincides with the center of lift of the UAV 100 in the vertical direction, which can make the output of the four propellers 212 of the UAV 100 average, which can improve the efficiency of the propellers 212 and is beneficial to battery life.
  • the UAV 100 includes a fuselage 10 and a plurality of arms 20 .
  • a plurality of machine arms 20 are rotatably connected to the fuselage 10, so that the unmanned aerial vehicle 100 can be in a folded state and an unfolded state, and the free ends of the machine arms 20 are connected with a power assembly 21.
  • the machine arm 20 performs compound rotation around a rotating shaft, and the compound rotating includes rotating around a tilted rotating shaft direction. 21 basic fit.
  • the arm 20 and the power assembly 21 of the UAV 100 fill the volume in the envelope cube surrounded by the maximum size of the UAV 100 to the maximum, which improves the UAV. 100's in convenience.

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Abstract

Véhicule aérien sans pilote (100) comprenant un fuselage (10) et une pluralité de bras (20). La pluralité de bras (20) est reliée en rotation au fuselage (10) pour permettre au véhicule aérien sans pilote (100) d'être dans un état plié ou dans un état déplié ; une extrémité libre de chaque bras (20) est reliée à un ensemble d'alimentation (21) ; pendant le processus de commutation du véhicule aérien sans pilote (100) entre l'état plié et l'état déplié, chaque bras (20) tourne autour d'un axe incliné (31) ; et dans l'état plié, les bras (20) sont rétractés sur les surfaces latérales circonférentielles (11) du fuselage (10), et la pluralité d'ensembles d'alimentation (21) est fondamentalement ajustée.
PCT/CN2021/101294 2021-06-21 2021-06-21 Véhicule aérien sans pilote WO2022266807A1 (fr)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115714230A (zh) * 2023-01-06 2023-02-24 河南锂动电源有限公司 一种便于快速组装的软包电池支架
CN117342023A (zh) * 2023-08-04 2024-01-05 珠海市双捷科技有限公司 一种无人机桨叶折叠控制方法和系统、阵列平台系统、无人机

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107235139A (zh) * 2017-03-29 2017-10-10 深圳市科卫泰实业发展有限公司 便携式多旋翼无人飞行器
US20200346739A1 (en) * 2015-08-03 2020-11-05 X-Control System Co., Ltd. Unmanned helicopter
CN112678147A (zh) * 2020-12-19 2021-04-20 湖北航天飞行器研究所 一种可自行展开并锁定旋翼臂的折叠展开装置
CN112744348A (zh) * 2016-02-22 2021-05-04 深圳市大疆创新科技有限公司 无人飞行器的机架、无人飞行器及其使用方法
CN112874759A (zh) * 2021-02-25 2021-06-01 中国南方电网有限责任公司超高压输电公司贵阳局 便携式电网巡检用无人机
CN112874770A (zh) * 2021-03-04 2021-06-01 陈秀梅 一种筒式发射旋翼飞行器

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20200346739A1 (en) * 2015-08-03 2020-11-05 X-Control System Co., Ltd. Unmanned helicopter
CN112744348A (zh) * 2016-02-22 2021-05-04 深圳市大疆创新科技有限公司 无人飞行器的机架、无人飞行器及其使用方法
CN107235139A (zh) * 2017-03-29 2017-10-10 深圳市科卫泰实业发展有限公司 便携式多旋翼无人飞行器
CN112678147A (zh) * 2020-12-19 2021-04-20 湖北航天飞行器研究所 一种可自行展开并锁定旋翼臂的折叠展开装置
CN112874759A (zh) * 2021-02-25 2021-06-01 中国南方电网有限责任公司超高压输电公司贵阳局 便携式电网巡检用无人机
CN112874770A (zh) * 2021-03-04 2021-06-01 陈秀梅 一种筒式发射旋翼飞行器

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115714230A (zh) * 2023-01-06 2023-02-24 河南锂动电源有限公司 一种便于快速组装的软包电池支架
CN117342023A (zh) * 2023-08-04 2024-01-05 珠海市双捷科技有限公司 一种无人机桨叶折叠控制方法和系统、阵列平台系统、无人机
CN117342023B (zh) * 2023-08-04 2024-03-29 珠海市双捷科技有限公司 一种无人机桨叶折叠控制方法和系统、阵列平台系统、无人机

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