WO2017132982A1 - Véhicule aérien sans pilote à rotor - Google Patents

Véhicule aérien sans pilote à rotor Download PDF

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Publication number
WO2017132982A1
WO2017132982A1 PCT/CN2016/073621 CN2016073621W WO2017132982A1 WO 2017132982 A1 WO2017132982 A1 WO 2017132982A1 CN 2016073621 W CN2016073621 W CN 2016073621W WO 2017132982 A1 WO2017132982 A1 WO 2017132982A1
Authority
WO
WIPO (PCT)
Prior art keywords
propeller
assembly
mounting bracket
power
drone according
Prior art date
Application number
PCT/CN2016/073621
Other languages
English (en)
Chinese (zh)
Inventor
胡家祺
Original Assignee
胡家祺
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 胡家祺 filed Critical 胡家祺
Priority to PCT/CN2016/073621 priority Critical patent/WO2017132982A1/fr
Publication of WO2017132982A1 publication Critical patent/WO2017132982A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/21—Rotary wings

Definitions

  • the utility model belongs to the technical field of aircrafts, and in particular relates to a drone.
  • the most widely used rotator aircraft with photographic functions is the multi-rotor aircraft.
  • aircraft generally has four or more propellers, and a photographic device is installed underneath the aircraft to realize the function of aerial photography.
  • CN201220148590.9 publicly advertises an aircraft, but it cannot Hand-held photography on the ground; the aircraft is a multi-rotor form that can be folded and retracted for easy carrying.
  • each arm can be folded and equipped with an imaging device that can be shot during flight, but It can't be photographed by hand on the ground;
  • the whole fuselage is cylindrical, the propeller can be folded and fitted on both sides of the fuselage for easy carrying, and the pan/tilt device can be mounted under it. Get a more stable shot, however, you can't shoot with your hand.
  • quadrotor Another type of quadrotor is characterized by its small size, which is non-foldable but only the size of the palm, and is very convenient to carry. However, because of its small size, it has poor wind resistance and cannot be photographed by hand.
  • the purpose of the present invention is to provide a rotary wing drone, which aims to solve the technical problem that the rotorcraft cannot realize the propeller folding and the hand-held photography in the prior art.
  • a propeller assembly driven by the power unit, and including a center fixed shaft, a mounting bracket mounted on the center fixed shaft, and a propeller mounted on the mounting bracket and foldable relative to the mounting bracket; [0009] a cloud platform assembly, including a camera for photographing and a connection assembly for mounting the camera; [0010] a fuselage frame between the propeller and the connection assembly, the fuselage frame being provided with a capacity
  • the accommodating cavity of the power unit is disposed, and includes a grip portion that is convenient for hand-held photographing when the propeller is in a folded state for holding.
  • the rotor drone further includes a clamping assembly movably coupled to the grip portion for clamping the mobile terminal, and the mobile terminal is coupled to the camera signal.
  • the clamping assembly includes a connecting member connected to the grip portion, a clamping member connected to the connecting member and rotating relative to the connecting member to adjust an angle, the mobile terminal Clamped on the clamping member.
  • the clamping assembly further includes a pair of clamping members slidably mounted on the clamping member to adjust a spacing therebetween.
  • the body frame has a cylindrical shape and is provided with a housing groove for accommodating the propeller on an outer wall thereof.
  • the rotor drone further includes a battery housed in the accommodating cavity to supply power to the power device and the camera, and a fixing frame for fixedly mounting the battery.
  • the mounting bracket includes a first mounting bracket and a second mounting bracket disposed coaxially along the central fixing shaft
  • the propeller includes at least two first ends mounted on two ends of the first mounting bracket a propeller and at least two second propellers mounted at opposite ends of the second mounting bracket.
  • the propeller assembly further includes a first hinge member rotatably coupled to the first mounting bracket and configured to mount the first propeller, and is rotatably coupled to the second mounting bracket and used for mounting The second hinge of the second propeller.
  • the propeller assembly further includes a pitch for controlling the periodic pitch of the second propeller Control component.
  • the pitch control assembly includes a power member, a rotating member that is sleeved on the central fixed shaft and is driven by the driving device to rotate around the central fixed shaft, and is set on the rotation
  • An swashplate assembly that is externally coupled to the second mount to periodically pitch the second propeller and a linkage for transmitting power of the power member to the swashplate assembly.
  • the swash plate assembly includes a swash plate that is sleeved outside the rotating member and has an inner wall that is spherical, one end is connected to opposite sides of the outer wall of the swash plate, and the other end is hinged to the swing of the second mounting frame. And a bearing fixed on the outer wall of the swash plate and a ring member fixedly connected to the bearing, wherein the ring member is provided with a fixing block connected to the link mechanism.
  • the link mechanism includes a first link hinged to the fixed block at one end and an output pivotally connected to the other end of the first link and the other end of which is pivotally connected to the power component.
  • the power member includes a fixing frame fixed to an end of the center fixing shaft and a pair of servo steering gear fixedly mounted on the fixing frame.
  • the pitch control assembly further includes a stopper fixed to the fixed frame for restricting lateral movement of the inclined disk.
  • the power unit includes a driving device that provides power and has an output shaft, a power transmission assembly that is mounted on the center fixed shaft and transmits power provided by the driving device to the propeller
  • the pan/tilt assembly further includes a shock absorbing assembly mounted between the connecting component and the fuselage frame for shock absorption.
  • the rotor drone further includes a plurality of light source assemblies fixedly mounted on the fuselage frame and irradiated with illumination light onto the propeller.
  • the utility model has the technical effect of the prior art: the rotor drone is foldable by the propeller and the mounting bracket, so as to facilitate the storage of the propeller in a non-flying state, and the utility model is convenient.
  • FIG. 1 is a schematic structural view of a rotary wing drone provided by a hand-held photographing cymbal according to an embodiment of the present invention
  • FIG. 2 is an exploded view of the rotor drone of FIG. 1; [0030] FIG.
  • FIG. 3 is a schematic structural view of a rotor-wing UAV according to an embodiment of the present invention in a flying state;
  • FIG. 4 is a schematic structural view of a rotary-wing UAV provided by a hand-held shooting device according to an embodiment of the present invention; The clamping assembly is omitted;
  • Figure 5 is a partial exploded view of the rotor drone of Figure 4.
  • FIG. 6 is a structural view of a rotor drone provided by an embodiment of the present invention, and the propeller is omitted;
  • FIG. 7 is an exploded view of the rotor drone of FIG. 6.
  • the rotor drone provided by the embodiment of the present invention includes:
  • a power device 10 configured to provide a driving force
  • the propeller assembly 20 is driven by the power unit 10 and includes a central fixed shaft 21, a mounting bracket 22 mounted on the central fixed shaft 21, and mounted on the mounting bracket 22 and mounted relative to the mounting a frame 22 foldable propeller 23;
  • a pan/tilt assembly 30 including a camera 32 for photographing and a connection assembly 34 for mounting the camera 32;
  • the fuselage frame 40 is located between the propeller 23 and the connecting component 34.
  • the fuselage frame 40 is provided with a receiving cavity (not shown) for accommodating the power device 10, and includes
  • the grip portion 44 is convenient for hand-held photographing when the propeller 23 is in a folded state for gripping.
  • the rotor drone provided by the embodiment of the present invention is foldably disposed by the propeller 23 and the mounting bracket 22, so as to facilitate the storage of the propeller 23 in a non-flying state, and is convenient to carry;
  • the pan-tilt assembly 30 is adapted to be photographed by the camera 32 in a flight state;
  • the grip portion 44 is disposed on the body frame 40 by accommodating the power device 10 in the accommodating cavity In the non-flying state, by holding the grip portion 44 and taking a picture with the camera 32, the rotor drone can be photographed by the camera 32 in both the flight state and the non-flying state, and is not flying.
  • the state ⁇ only needs to fold the propeller 23 and then complete the shooting by holding the fuselage frame 40, and the structure is simple and convenient to use.
  • the propeller 23 can be folded around the mounting bracket 22 along the two ends of the body frame 40, that is, one side is folded toward the side of the grip portion 44 for storage, and One is folded and stored toward the side away from the grip portion 44.
  • the propeller 23 is detachably coupled to the mounting bracket 22, when not flying, The propeller 23 is detached from the mount 22 and photographed by the camera 32 by holding the grip portion 44.
  • a quick release structure is connected between the propeller 23 and the mounting bracket 22, and the propeller 23 can be quickly disassembled without using any tools, preferably by means of a snap connection. .
  • the rotor drone further includes a clamping assembly 50 movably coupled to the grip portion 44 and configured to clamp the mobile terminal 80, the mobile terminal 80. Signaled to the camera 32.
  • the mobile terminal 80 is mounted on the body frame 40 by setting the clamping assembly 50 so as to be hand-held, and the camera 32 is displayed by the mobile terminal 80. Improve the convenience of operation.
  • the mobile terminal 80 is connected to the camera 32 to transmit a picture captured and captured by the camera 32 to the mobile terminal 80.
  • the mobile terminal 80 and the camera 32 are connected by WIFI.
  • a wireless communication connection method such as a Bluetooth connection.
  • other signal connection methods may also be used, and are not limited thereto.
  • the shooting angle of the pan/tilt assembly 30 can be controlled by the mobile terminal 80 when the rotor drone is in an airplane mode or a handheld camera mode.
  • the clamping assembly 50 further includes a connecting member 52 connected to the grip portion 44, connected to the connecting member 52 and opposite to the The connecting member 52 is rotated to adjust the angled holding member 54, and the mobile terminal 80 is clamped to the holding member 54.
  • the connecting member 52 is detachably connected to the grip portion 44, for example, by a snap connection.
  • the clamping member 54 and the connecting member 52 are connected by a ball joint, so as to adjust the angle of the clamping member 54 relative to the body frame 40, so as to be suitable for different consumers' needs, preferably
  • the holder 54 is formed integrally with the ball joint.
  • the mobile terminal 80 is detachably snapped onto the clamping member 54.
  • the clamping assembly 50 further includes a pair of clamping members 56 slidably mounted on the clamping member 54 to adjust the spacing therebetween.
  • the clamping members 56 and the clamping members 56 are mutually engaged on both sides of the mobile terminal 80, and the size of the mobile terminal 80 can be adjusted to adjust the distance between the two clamping members 56 to fit Different sizes of mobile terminals 80 have a wide range of applications.
  • the clamping member 54 is provided with a pair of sliding slots (not shown), and the clamping members 56 are fixedly engaged with the sliding slots to make the clamping members. 56 guides sliding along the chute (not shown)
  • the body frame 40 has a cylindrical shape and a housing groove (not shown) for accommodating the propeller 23 is provided on an outer wall thereof.
  • the propeller 23 is concealed on the fuselage frame 40 by providing the receiving groove, thereby ensuring that the fuselage frame 40 is clean after the propeller 23 is folded, and is held by the grip portion 44. After taking a picture, it is not necessary to arrange the propeller 23, which is convenient to use.
  • a plurality of buckles may be disposed on the body frame 40, and the buckles 23 cooperate with the propellers 23 to fix the propellers 23 to the machine. On the frame 40, it is easy to hold and take pictures.
  • the rotor drone further includes a battery 60 housed in the accommodating cavity to supply power to the power unit 10 and the camera 32, and is used for fixing
  • the holder 70 of the battery 60 is mounted.
  • the battery 60 is disposed in the accommodating cavity to supply power to the power unit 10 and the camera 32, and the battery 60 no longer supplies power to the power unit 10 when it is not flying. To extend the battery life of the battery 60.
  • the camera 32 is powered by the battery 60.
  • the mounting bracket 22 includes a first mounting bracket 220 and a second mounting bracket 222 disposed coaxially along the central fixed shaft 21, and the propeller 23 includes at least two A first propeller 230 mounted on both ends of the first mounting bracket 220 and at least two second propellers 232 mounted on opposite ends of the second mounting bracket 222 are supported.
  • the first mounting bracket 220 and the second mounting bracket 222 are disposed along the axial direction of the central fixed shaft 21, and preferably, the first mounting bracket 220 and the second mounting bracket 222 are both opposite to the center.
  • the fixed shaft 21 is coaxially disposed.
  • At least two of the first propellers 23 0 are disposed on the first mounting bracket 220 and at least two of the second propellers 232 are disposed on the second mounting bracket 222, that is, aerodynamic layout using coaxial twin propellers .
  • the power device 10 is located between the first mounting bracket 220 and the second mounting bracket 222, or the second mounting bracket 222 is located in the first mounting bracket 220.
  • the positional relationship between the three and the power unit 10 is not limited thereto.
  • the propeller assembly 20 further includes a first hinge member 24 rotatably coupled to the first mounting bracket 220 and configured to mount the first propeller 230, and a rotational connection.
  • a first hinge member 24 rotatably coupled to the first mounting bracket 220 and configured to mount the first propeller 230, and a rotational connection.
  • the first propeller 230 is hinged to the first mounting bracket 220 and the other end is fixed to the first propeller 230 , the first propeller 230 is folded relative to the first mounting bracket 220; likewise, the second hinge 25 is hinged to the second mounting bracket 222 and the other ends are fixed by the second hinge 25
  • the second propeller 232 is configured to fold the second propeller 232 relative to the second mounting bracket 222.
  • the propeller assembly 20 further includes a pitch control assembly 26 for controlling the periodic pitch of the second propeller 232.
  • the second propeller 232 is periodically pitched by setting the pitch control assembly 26 to control the pitch and roll freedom of the rotor drone.
  • the pitch control assembly 26 includes a power member 260, is sleeved on the central fixed shaft 21, and is driven by the driving device to rotate around the center. a rotating rotating member 2 62, a swash plate assembly 27 sleeved outside the rotating member 262 and connected to the second mounting bracket 222 to periodically change the second propeller 2 32 and The power of the power member 260 is transmitted to the link mechanism 28 on the swash plate assembly 27. Controlling the inclination angle of the swash plate assembly 27 by the link mechanism 28 by the power member 260, thereby inducing a periodic change of the pitch of the second propeller 232, thereby controlling the pitch of the rotor drone And roll two degrees of freedom.
  • the link mechanism 28 is coupled between the swash plate assembly 27 and the power member 260, but the position is not limited thereto.
  • the swash plate assembly 27 includes a swash plate 270 sleeved on the outer side of the rotating member 262 and having a spherical inner surface, and one end is connected to opposite sides of the outer wall of the swash plate 270. and the other end hinged to the second mounting bracket 222 pivot member 272, is sleeved and fixed on the outer wall of the inclined plate 270 of the bearing 274 and bearing 274 is fixedly connected to the annular member 275, the annular member A fixing block 276 connected to the link mechanism 28 is provided on the 275.
  • the power member 260 drives the link mechanism 28 to rotate, thereby rotating the fixing block 276 and the ring member 275, and driving the swash plate 270 together with the swinging member 272 to drive the second mounting bracket 222.
  • the pitching motion is periodically tilted such that the pitch of the second propeller 232 periodically changes to control the two degrees of freedom of pitch and roll of the rotor drone.
  • the link mechanism 28 includes a first link 280 hinged to the fixed block 276 at one end and one end rotatably connected to the other end of the first link 280. And a second link 282 pivotally connected to the output shaft of the power member 260 at the other end.
  • the second link 282 is connected between the power member 260 and the first link 280 to transmit the power of the power member 260 to the second link 28 2, and utilize the A link 280 is coupled between the second link 282 and the fixed block 276 to transmit the power to the fixed block 276, since the fixed block 276 is fixed to the ring 275
  • the ring member 275 is fixed to the swash plate 270 by the bearing 274 to drive the swash plate 270 to move, and a swinging member 272 is disposed between the swash plate 270 and the second mounting bracket 222. So that the pitch of the second propeller 232 is periodically changed to control the two degrees of freedom of pitch and roll of the rotor drone.
  • the power member 260 includes a fixing frame 262 fixed to an end of the center fixing shaft 21 and a pair of servo steering gears 264 fixedly mounted on the fixing frame 262. .
  • the servo frame 264 is mounted by the fixing frame 262.
  • the fixing frame 262 is fixedly mounted on the fixing frame 70 and located between the swash plate 270 and the fixing frame 70.
  • the pitch control assembly 26 further includes a stopper 90 fixed to the fixing frame 26 2 for restricting lateral movement of the swash plate 270.
  • a stopper 90 fixed to the fixing frame 26 2 for restricting lateral movement of the swash plate 270.
  • the power unit 10 includes a driving device 12 that provides power and has an output shaft 120, is mounted on the center fixed shaft 21, and is provided by the driving device 12. Power is transmitted to the power transmission assembly 14 of the propeller 23. Controlling the first propeller 230 and the second propeller 232 with the drive device 12 such that the first propeller 230 and the second propeller 232 obtain flight lift and control the rotor with the drive device 12 The yaw of the drone.
  • the power unit 10 further includes a fixing bracket fixedly mounted on the center fixing shaft 21 for fixedly mounting the driving device 12.
  • the first mounting frame 220 And the second mounting is located on opposite sides of the fixing bracket.
  • the number of the driving devices 12 is two, and are respectively located at two sides of the central fixed shaft 21 for respectively driving the first propeller 230 and the second propeller 232 through the power transmission
  • the assembly 14 controls the rotation of the first propeller 230 and the second propeller 232 to obtain flight lift, and controls the yaw degree of freedom by using the difference in rotational speeds of the two driving devices 12.
  • the power unit 10 is a motor.
  • the power transmission assembly 14 includes a driving wheel (not shown) mounted on the output shaft 120 and mounted on the center fixed shaft 21 and mated with the driving wheel
  • the driven wheel 140 that drives the propeller 23 to rotate has a certain deceleration effect by providing the driving wheel and the driven wheel 140.
  • the driving wheel and the driven wheel 140 are gears that mesh with each other, and may also be other A mechanism to achieve deceleration.
  • the number of the power transmission components 14 is two, which are respectively connected between a driving device 12 and the first propeller 230 and between the other driving device 12 and the second propeller 232, respectively The power of the two driving devices 12 is transmitted to the first propeller 230 and the second propeller 232.
  • the pan/tilt assembly 30 further includes a mounting portion between the connecting assembly 34 and the fuselage frame 40 for shock absorption. Shock absorbing assembly 36.
  • the rotor drone further includes a plurality of light source assemblies (not shown) fixedly mounted on the body frame 40 and irradiated with light to the propellers 23.
  • the light source assembly includes at least one illuminating light source, and the different illuminating light sources are used for two or more illuminating light sources, by arranging the light source assembly to illuminate the propeller 23 with optical light emitted therefrom. With the visual persistence effect, the corresponding color of light can be reflected on the blades of the propeller 23, so that the operator can clarify the flight direction of the rotor drone or the orientation of the camera.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Accessories Of Cameras (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un véhicule aérien sans pilote à rotor comprenant un dispositif d'alimentation (10), un ensemble d'hélices (20), un ensemble tête de support (30) et un cadre de corps de machine (40). L'ensemble d'hélices (20) comprend un arbre fixe central (21), un cadre de montage (22) monté sur l'arbre fixe central (21) et des hélices (23) montées sur le cadre de montage (22) et pouvant être pliées par rapport au cadre de montage (22). L'ensemble tête de support (30) comprend une caméra (32). Le cadre de corps de machine (40) est situé entre les hélices (23) et un ensemble de connexion (34), et comprend une partie de maintien (44) utilisée pour assurer un maintien pour faciliter une photographie portative lorsque les hélices (23) sont dans un état plié. Dans le véhicule aérien sans pilote à rotor, les hélices (23) et le cadre de montage (22) sont disposés d'une manière pliable, le dispositif d'alimentation (10) est reçu dans une chambre de réception et la partie de maintien (44) est disposée sur le corps de cadre de machine (40), ce qui contribue à mettre en œuvre une photographie au moyen de la partie de maintien (44) et de la caméra (32) lorsque le véhicule aérien sans pilote à rotor se trouve dans un état de non-vol, de sorte que la photographie puisse être mise en œuvre au moyen de la caméra (32) que le véhicule aérien sans pilote à rotor soit dans un état de vol ou dans l'état de non-vol, et lorsque le véhicule aérien sans pilote à rotor est dans l'état de non-vol, la photographie puisse être réalisée par un simple maintien du cadre de corps de machine (40) une fois les hélices (23) pliées ; le véhicule aérien sans pilote à rotor présente une structure simple et est pratique à utiliser.
PCT/CN2016/073621 2016-02-05 2016-02-05 Véhicule aérien sans pilote à rotor WO2017132982A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/CN2016/073621 WO2017132982A1 (fr) 2016-02-05 2016-02-05 Véhicule aérien sans pilote à rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2016/073621 WO2017132982A1 (fr) 2016-02-05 2016-02-05 Véhicule aérien sans pilote à rotor

Publications (1)

Publication Number Publication Date
WO2017132982A1 true WO2017132982A1 (fr) 2017-08-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2016/073621 WO2017132982A1 (fr) 2016-02-05 2016-02-05 Véhicule aérien sans pilote à rotor

Country Status (1)

Country Link
WO (1) WO2017132982A1 (fr)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4163535A (en) * 1971-12-13 1979-08-07 Westland Aircraft Limited Unmanned multimode helicopter
JP2006051864A (ja) * 2004-08-10 2006-02-23 Seiko Epson Corp 自動飛行制御システムおよび自動飛行制御方法
JP4826785B2 (ja) * 2006-11-14 2011-11-30 国立大学法人神戸大学 飛行型情報処理装置
CN203996917U (zh) * 2014-08-07 2014-12-10 深圳市奇旺塑胶有限公司 一种无人飞行器
CN105000163A (zh) * 2015-08-23 2015-10-28 张子林 一种向下折叠式多旋翼无人飞行器
CN105059528A (zh) * 2015-07-23 2015-11-18 致导科技（北京）有限公司 一种可折叠式无人机
WO2015192421A1 (fr) * 2014-06-19 2015-12-23 庆安集团有限公司 Dispositif de réglage du pas des pales entre les hélices d'un hélicoptère à double hélice coaxiale
WO2016072587A1 (fr) * 2014-11-04 2016-05-12 Lg Electronics Inc. Drone

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4163535A (en) * 1971-12-13 1979-08-07 Westland Aircraft Limited Unmanned multimode helicopter
JP2006051864A (ja) * 2004-08-10 2006-02-23 Seiko Epson Corp 自動飛行制御システムおよび自動飛行制御方法
JP4826785B2 (ja) * 2006-11-14 2011-11-30 国立大学法人神戸大学 飛行型情報処理装置
WO2015192421A1 (fr) * 2014-06-19 2015-12-23 庆安集团有限公司 Dispositif de réglage du pas des pales entre les hélices d'un hélicoptère à double hélice coaxiale
CN203996917U (zh) * 2014-08-07 2014-12-10 深圳市奇旺塑胶有限公司 一种无人飞行器
WO2016072587A1 (fr) * 2014-11-04 2016-05-12 Lg Electronics Inc. Drone
CN105059528A (zh) * 2015-07-23 2015-11-18 致导科技（北京）有限公司 一种可折叠式无人机
CN105000163A (zh) * 2015-08-23 2015-10-28 张子林 一种向下折叠式多旋翼无人飞行器

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