WO2018095214A1 - Aéronef sans pilote et train d'atterrissage associé - Google Patents

Aéronef sans pilote et train d'atterrissage associé Download PDF

Info

Publication number
WO2018095214A1
WO2018095214A1 PCT/CN2017/109736 CN2017109736W WO2018095214A1 WO 2018095214 A1 WO2018095214 A1 WO 2018095214A1 CN 2017109736 W CN2017109736 W CN 2017109736W WO 2018095214 A1 WO2018095214 A1 WO 2018095214A1
Authority
WO
WIPO (PCT)
Prior art keywords
landing gear
connecting member
transmission rod
gear device
unmanned aerial
Prior art date
Application number
PCT/CN2017/109736
Other languages
English (en)
Chinese (zh)
Inventor
罗东东
胡亮军
吴兴文
Original Assignee
深圳市道通智能航空技术有限公司
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 深圳市道通智能航空技术有限公司 filed Critical 深圳市道通智能航空技术有限公司
Publication of WO2018095214A1 publication Critical patent/WO2018095214A1/fr

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/18—Operating mechanisms
    • B64C25/20—Operating mechanisms mechanical
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/02—Undercarriages
    • B64C25/08—Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/18—Operating mechanisms
    • B64C25/24—Operating mechanisms electric

Definitions

  • the present application relates to the field of aircraft technology, and in particular, to a landing gear device and an unmanned aerial vehicle having the same.
  • Unmanned Aerial Vehicle Today, Unmanned Aerial Vehicle (UAV) is widely used in aerial photography, transportation, monitoring, exploration, search and rescue.
  • the drone is equipped with a shooting device, such as a pan/tilt head with a shooting function, to realize real-time image transmission and high-risk area detection functions.
  • a shooting device such as a pan/tilt head with a shooting function
  • fixed landing gears are mostly used. Since the camera is usually installed at the bottom of the UAV, the fixed landing gear will block the aerial view during the aerial photography process and will not meet the customer's needs. In addition, when the UAV is flying, the landing gear increases the unnecessary resistance of the UAV in the air.
  • the embodiment of the present application provides a landing gear device that can be stowed/falled and an unmanned aerial vehicle having the landing gear device.
  • the UAV and its landing gear device of the embodiments of the present application are beneficial to improving the flight performance and shooting performance of the UAV, and are convenient to carry and store.
  • a landing gear device for an unmanned aerial vehicle comprising a fuselage
  • the landing gear device comprising: a landing gear body; and a power assembly for mounting to the fuselage, the power assembly comprising a driving device, a transmission unit and a connecting unit;
  • the transmission unit includes a transmission rod member driven by the driving device; one end of the connecting unit is fixedly connected to the landing gear body, and the other end of the connecting unit is The transmission rod members are connected, and the transmission rod member is driven by the driving device When the vehicle is moving, the landing gear body is driven up or down.
  • the transmission unit further includes a gear train, an output shaft of the drive device is coupled to one end of the gear train, and an input shaft of the drive member is coupled to the gear train One end.
  • the gear train includes a first gear set mounted on an output shaft of the drive device and a second gear set mounted on the drive The input shaft of the rod.
  • the first gear set meshes with the second gear set.
  • the gear train further includes a gear shaft, the first gear set and the second gear set being coupled by the gear shaft.
  • the gear train further includes a plurality of drive gears mounted between the first gear set and the second gear set.
  • the transmission rod member is a screw, a screw or a worm.
  • the connecting unit includes a first connecting member and a second connecting member, the first connecting member is sleeved on the transmission rod member and screwed to the transmission rod member, and the second connection One end of the piece is connected to the first connecting piece, and the other end of the second connecting piece is fixedly connected with the landing gear body.
  • the first connector moves linearly along the transmission member as the drive unit drives the transmission member to rotate.
  • one end of the second connecting member is provided with a sliding slot
  • the first connecting member is hinged in the sliding slot
  • the first connecting member moves linearly along the transmission rod member.
  • the first connecting member slides in the sliding groove.
  • the landing gear device further includes a housing, the drive unit and the transmission unit are mounted in the housing, and the second connector is hinged to the housing.
  • the second connecting member is provided with a pin shaft
  • the casing is provided with a shaft hole, and the pin shaft is inserted into the shaft hole, so that the second connecting member and the machine The shell is hinged.
  • the driving unit drives the transmission rod to rotate such that the first connecting member moves linearly along the axial direction of the transmission rod member, the second connecting member and the One end of the first connector connection moves along with the first connector, thereby causing the second connector to rotate about the pin, and the second connector is fixedly coupled to the landing gear body One end moves in a direction opposite to the first connector.
  • the driving unit drives the transmission rod member to rotate, and the first connecting rod linearly moves downward along the axial direction of the transmission rod member.
  • One end of the second connecting member connected to the first connecting member moves along with the first connecting member, so that the second connecting member rotates around the pin shaft, and the second connecting member and the second connecting member The other end of the fixed connection of the landing gear body moves upward;
  • the driving unit drives the transmission rod member to rotate, and the first connecting rod linearly moves upward along the axial direction of the transmission rod member, the second connecting member and the second connecting member
  • One end of the first connector connection moves along with the first connector, thereby causing the second connector to rotate about the pin, and the second connector is fixedly coupled to the landing gear body The other end moves down.
  • the housing is further provided with a seat for fixing the transmission rod member, and an end of the transmission rod member is received in the holder.
  • a bearing is disposed between the inside of the seat and the end of the transmission member.
  • the gear train further includes a mounting plate for mounting the first gear set and/or the second gear set.
  • the gear train further includes a support for supporting the first gear set and/or the second gear set.
  • the second connector is fixedly coupled to the landing gear body by screws.
  • the landing gear body has a range of rotation angles less than 150 degrees.
  • the landing gear device further includes a reset mechanism that returns to a preset state when the UAV is powered off.
  • the drive device is a motor.
  • the connecting unit is further provided with a shock absorbing mechanism.
  • the embodiment of the present application further provides the following technical solutions:
  • An unmanned aerial vehicle includes: a fuselage and a landing gear device as described above, the landing gear device being coupled to the fuselage.
  • the UAV is a multi-rotor aircraft.
  • the UAV has two of the landing gear devices respectively mounted on opposite sides of the fuselage; the power assembly of the landing gear device causes the landing gear body to be opposite The fuselage transitions between a first state that allows the landing gear body to support the fuselage to rest on a surface, and a second state that increases the unmanned The functional space of the aircraft.
  • the body further includes an image capture device; in the second state, the The landing gear body is rotated out of the range of the viewing angle of the image capturing device to avoid obscuring the viewing angle of the image capturing device.
  • the embodiment of the present application further provides the following technical solutions:
  • An unmanned aerial vehicle comprising: a fuselage;
  • the landing gear device being coupled to the fuselage, the landing gear device being capable of being lowered or stowed relative to the fuselage;
  • the functional module being mounted below the fuselage;
  • the landing gear device is a landing gear device as described above.
  • the functional module is an image acquisition device.
  • the functional module is a pan/tilt.
  • the number of landing gear bodies (21) is two
  • the UAV and the landing gear device of the embodiment of the present application rotates the body of the UAV relative to the UAV to be stowed/dropped under the action of the power component, and the The landing gear body can be folded up and folded on both sides of the fuselage, thereby reducing the unnecessary resistance of the landing gear body to the unmanned aerial vehicle in the air, improving the flight performance of the UAV, and making the UAV In flight, the functional space is increased, especially for an unmanned aerial vehicle having an image capturing device, which avoids the landing gear device obscuring the shooting angle of the image capturing device, thereby improving the shooting performance of the unmanned aerial vehicle having the image capturing device;
  • the UAV with this landing gear device is also more convenient to carry and store.
  • FIG. 1 is a perspective view of an aircraft provided by an embodiment of the present application.
  • FIGS. 2a, 2b and 2c are schematic views of three different perspectives of the landing gear device provided by the embodiment of the present application.
  • FIGs 3a and 3b are schematic illustrations of two different perspectives in the power assembly of the landing gear assembly shown in Figures 2a-2c, wherein the attachment unit 24 is removed.
  • Figures 4a and 4b are schematic views of two different perspectives of the power assembly of the landing gear assembly shown in Figures 2a-2c, wherein the attachment unit 24 and the housing 30 are removed.
  • the reference numerals are as follows: 10 unmanned aerial vehicle; 1 fuselage; 3 arm; 2 landing gear device; 21 landing gear body; 22 power assembly; 23 driving device; 231 output shaft; 241 first connector; 242 second connector; 2421 sliding slot; 243 pin; 26 holder; 28 gear train; 282 gear shaft; 283 mounting plate; 284 support; 287 first gear set; Two gear sets; 29 transmission units; 291 input shafts; 292 transmission rods; 30 housings; 301 shaft holes.
  • Figure 1 is a perspective view of an unmanned aerial vehicle 10 provided by one of the embodiments of the present application.
  • the UAV 10 includes a fuselage 1, an arm 3 and a landing gear device 2.
  • the arm 3 is connected to the body 1.
  • the arm 3 can also be integrally formed with the body 1.
  • the number of the landing gear devices 2 is two. In other embodiments, the number of landing gear devices 2 may be greater than two, and the plurality of landing gear devices 2 are evenly distributed around the fuselage 11.
  • the UAV 10 is a quadrotor. It can be understood that the UAV 10 can also be other multi-rotor aircraft, such as a six-rotor aircraft, an eight-rotor aircraft, a twelve-rotor aircraft, and the like.
  • the body 11 is a hollow housing structure.
  • the body 10 includes a control circuit component composed of electronic components such as an MCU, and the control circuit component includes a plurality of control modules, such as a control module for controlling the loading and unloading of the landing gear device 2, for Flight control to control the flight attitude of unmanned aerial vehicles Modules, GPS modules for navigating drones, and data processing modules for processing environmental information acquired by related onboard devices.
  • a control module for controlling the loading and unloading of the landing gear device 2
  • Flight control to control the flight attitude of unmanned aerial vehicles Modules
  • GPS modules for navigating drones
  • data processing modules for processing environmental information acquired by related onboard devices.
  • Two landing gear devices 2 are connected to the fuselage 1 and are respectively mounted on opposite sides of the fuselage 1.
  • the landing gear device 2 is used to support the UAV 10 when it takes off, land, or ground (surface), or as an accessory for the UAV 10 to move on the ground (surface).
  • the landing gear unit 2 as a component supporting the entire unmanned aerial vehicle 10, plays an important role in the safe take-off and landing of the unmanned aerial vehicle 10.
  • the landing gear device 2 includes a landing gear body 21 and a power assembly 22 that can be lowered or stowed relative to the body 1 under the drive of the power assembly 22. In the figure, a state in which the landing gear body 21 is in the stowed position P1 and the lowered position P2, respectively, is schematically shown.
  • the UAV 10 further includes a power system, a control module, a pan/tilt as an image capturing device, a power supply battery, and the like, which are not shown.
  • the power system is used to drive the entire unmanned aerial vehicle, which includes a power motor and a propeller.
  • the power motor is mounted at the end of the arm 3, and the propeller is mounted on the output shaft of the power motor to generate the unmanned aerial vehicle 10 under the driving of the power motor.
  • the lift or thrust of the flight is used to drive the entire unmanned aerial vehicle, which includes a power motor and a propeller.
  • the power motor is mounted at the end of the arm 3
  • the propeller is mounted on the output shaft of the power motor to generate the unmanned aerial vehicle 10 under the driving of the power motor.
  • the lift or thrust of the flight is not shown.
  • the pan/tilt includes a camera having a photographing function, and is usually installed on the bottom side of the body 1 of the unmanned aerial vehicle 10 in order to facilitate image acquisition.
  • the landing gear device 2 of the embodiment of the present application drives the landing gear body 21 through the power assembly 22, and rotates from the lowered position P2 to the stowed position P1, so that the camera of the landing gear body 21 can be prevented from being blocked by the landing gear body 21 in the flight state of the unmanned aerial vehicle.
  • the angle of shooting is a camera having a photographing function
  • the landing gear body 21 is rotatably entered into the stowed/down position by electronic control. Specifically, in the stowed position, the landing gear body 21 is deployed upward to the position P1, which is substantially parallel to the horizontal plane. At this time, the functional space of the UAV 10 can be increased, for example, the shooting of the head mounted on the UAV 10 is increased. Perspective. In the lowered position, the landing gear body 21 is rotated downward to a position P2 substantially parallel to the vertical plane, at which time the landing gear body 21 can support the body 1 to rest on a surface, such as the ground.
  • the stowage of the landing gear body 21 is similar to the spread of the wings of the bird, and the lowering of the landing gear body 21 is similar to the folding of the wings of the bird.
  • an image acquisition device (not shown) is provided on the bottom side of the UAV 10 , for example, in the case of a pan/tilt head having a photographing function, the stowed position of the landing gear body 21 is located in the image capturing device.
  • the shooting angle is outside the range. This configuration is advantageous for improving the photographing performance of the UAV 10.
  • the rotation angle ⁇ of the landing gear body 21 is limited to less than 150 degrees.
  • the landing gear device 2 is further provided with a reset mechanism that returns to the lowered position when the power system of the unmanned aerial vehicle 10 is suddenly powered off to ensure the flight safety of the unmanned aerial vehicle 10.
  • the landing gear device 2 includes a landing gear body 21, a power assembly 22, and a casing 30.
  • a power assembly 22 is mounted to the body 1 for driving the landing gear body 21 to be stowed and lowered relative to the body 1.
  • Power The assembly 22 further includes a cooperating drive 23 (shown in Figures 3a-4b), a transmission unit 29 and a connection unit 24.
  • the drive unit 23 and the transmission unit 29 are mounted in the casing 30.
  • the transmission unit 29 includes a transmission member 292 that is driven by a drive unit 23.
  • the housing 30 is also provided with a seat 26 for fixing the transmission rod member 292, and the end of the transmission rod member 292 is received in the holder 26.
  • a bearing is disposed between the inner side of the support 26 and the end of the transmission rod member 292.
  • one end of the coupling unit 24 is coupled to the transmission rod member 292, and the other end of the coupling unit 24 is fixedly coupled to the landing gear body 21.
  • the first connecting member 241 is sleeved on the transmission rod member 292 of the transmission unit 29 in a threaded manner at the middle thereof, and converts the rotational motion of the transmission rod member 292 into a linear motion.
  • the transmission lever member 292 is rotated by the driving device 23
  • the landing gear body 21 is rotated to be stowed or lowered.
  • the second connecting member 242 and the landing gear body 21 are fixedly connected by screws 244.
  • the second connecting member 242 can also be fixedly connected to the landing gear body 21 by other means, or the second connecting member 242 can be integrally formed with the landing gear body 21.
  • the driving device 23 is a motor for driving the transmission rod member 292 to rotate, so that one end of the connecting unit 24 (the end where the first connecting member 241 is located in FIG. 2a) is driven.
  • the rotation of the lever member 292 linearly moves in the axial direction of the transmission lever member 292.
  • the driving device 23 may be one of a cylinder or a hydraulic cylinder that drives one end of the connecting unit 24 to perform linear motion.
  • the transmission rod member 292 can be a lead screw, a screw, or a worm.
  • the connecting unit 24 includes a first connecting member 241 and a second connecting member 242.
  • the first connecting member 241 is sleeved on the transmission rod member 292 and is screwed to the transmission rod member 292.
  • One end of the second connecting member 242 is connected to the first connecting member 241, and the second The other end of the connecting member 242 is fixedly coupled to the landing gear body 21.
  • the second connecting member 242 is further provided with a pin shaft 243, and the casing 30 is provided with a shaft hole 301 (see FIG. 3a), and the pin shaft 243 is inserted into the shaft hole 301, so that the second connecting member 242 is The casing 30 is hinged.
  • the two connecting members 242 are hinged with the casing 30, so that the end of the second connecting member 242 and the first connecting member 241 is also linearly moved along the axial direction of the transmission rod member 292, so that the second connecting member 242 is wound around.
  • the pin 243 rotates, and the other end of the second connecting member 242, that is, the end connected to the landing gear body 21, along with the first connecting member 241 The opposite direction of motion.
  • the end of the second connecting member 242 connected to the first connecting member 241 is further provided with a sliding slot 2421, and the first connecting member 241 is hinged in the sliding slot 2421 when the first connecting member 241 is driven along While the rod member 292 is linearly moved, the first connecting member 241 slides in the sliding groove 2132.
  • the sliding groove 2421 is provided such that the process of linearly moving the first connecting member 241 of the connecting unit 24 along the axial direction of the transmission rod member 292 is smoother and smoother, and the second connecting member 242 is also connected to the first connecting member 241.
  • One end can also be driven more smoothly and smoothly by the first connecting member 241, and also linearly moves along the axial direction of the transmission rod member 292.
  • the driving device 23 drives the transmission rod member 292 to rotate, thereby causing the first connecting member 241 to move downward along the axial direction of the transmission rod member 292 (X In the direction shown, the end that drives the second connecting member 242 to connect with the first connecting member 241 also moves downward, so that the second connecting member 242 rotates clockwise around the pin 243, and the other end of the second connecting member 242 ( The one end connected to the landing gear body 21 is moved upward (in the direction indicated by Y), and the end portion of the landing gear body 21 is lifted up, and the landing gear body 21 is stowed upward. Finally, the landing gear body 21 is folded over the side of the fuselage 1 so that the landing gear body 21 does not obscure the aerial view during the aerial photography of the UAV 10 .
  • the driving device 23 drives the transmission rod member 292 to rotate, thereby causing the first connecting member 241 to move upward along the axial direction of the transmission rod member 292, the second connecting member 242 is connected to the first connecting member 241.
  • One end also moves upward, so that the second connecting member 242 rotates counterclockwise about the pin 243, and the other end of the second connecting member 242 (the end connected to the landing gear body 21) moves downward to drive the landing gear body 21.
  • the end is lowered and the landing gear body 21 is lowered downward.
  • the landing gear body 21 is lowered to be substantially parallel to the vertical plane and is in contact with the ground after the UAV 10 descends to support the UAV 10.
  • a shock absorbing mechanism is further provided in the connecting unit 24, which can well withstand the impact force when the UAV 10 is dropped.
  • FIGS 3a and 3b there are schematic views of two different perspectives of the power assembly 22 of the landing gear assembly 2 shown in Figures 2a-2c, wherein the attachment unit 24 is removed.
  • the housing 30 is provided with a shaft hole 301 that cooperates with the aforementioned third connecting member 243.
  • the power assembly 22 of the landing gear assembly 2 shown in Figures 2a-2c is further illustrated from two different perspectives, wherein the coupling unit 24 and the housing 30 are removed.
  • the power assembly 22 includes a drive unit 23 and a transmission unit 28.
  • the transmission unit 29 includes a gear train 28 in addition to the transmission member 292 as described above.
  • the transmission device 23 can drive the transmission rod member 292 to rotate by the transmission of the gear train 28.
  • the output shaft 231 of the driving device 23 is connected Connected to one end of the gear train 28, an input shaft 291 of the transmission member 292 is coupled to the other end of the gear train 28.
  • the power output from the driving device 23 passes through the output shaft 231 of the driving device 23, the gear train 28, and the input shaft 291 of the transmission member 292, and is transmitted to the transmission rod member 292 for driving the transmission rod member 292 to rotate.
  • the rotational linear velocity of the driving device 23 is too fast, the rotational power outputted from the driving device 23 is decelerated by the gear train 28, and then transmitted to the transmission lever member 292, so that the rotational power finally outputted to the transmission lever member 292 can be
  • the drive rod member 292 is brought to a suitable rotational linear velocity.
  • the gear train 28 further includes a first gear set 287 and a second gear set 288 that mesh with each other.
  • the gear train 28 further includes a gear shaft 282 that is coupled to the second gear set 288 via a gear shaft 282.
  • a plurality of drive gears can be disposed between the first gear set 287 and the second gear set 288.
  • the first gear set 287 and the second gear set 288 can be directly engaged to each other such that the gear shaft 282 can be omitted.
  • Gear train 28 also includes a mounting plate 283 and a support 284.
  • the drive unit 23 is fixed to the support plate 283.
  • the gear train 28 is mounted and secured by the mounting plate 283 and the support member 284.
  • the mounting plate 283 and the support member 284 cooperate to support and fix the first gear set 287 and the second gear set 288.
  • the UAV 10 and its landing gear device 2 of the present embodiment rotate the landing gear body 21 relative to the fuselage 1 of the UAV 10 by the power assembly 22 to be stowed. / falling, and the landing gear body 21 can be stowed and folded on both sides of the fuselage 1, thereby reducing unnecessary resistance of the landing gear body 21 to the unmanned aerial vehicle 10 in the air, and improving the unmanned
  • the flight performance of the aircraft 10 also increases the functional space of the UAV 10 when it is flying, especially for the UAV 10 with the image acquisition device, thereby preventing the landing gear device 2 from obscuring the viewing angle of the image acquisition device, thereby
  • the photographing performance of the unmanned aerial vehicle 10 having the image capturing device is improved; and, when the unmanned aerial vehicle 10 is not used, the unmanned aerial vehicle 10 having the landing gear device 2 is also more easily carried and stored.

Landscapes

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

Abstract

L'invention concerne un aéronef sans pilote (10) et un train d'atterrissage (2) associé. Le train d'atterrissage (2) comprend un corps (21) et un ensemble d'alimentation électrique (22) monté sur un fuselage (1). L'ensemble d'alimentation électrique (22) comprend un dispositif d'entraînement (23), une unité de transmission (29) et une unité de liaison (24). L'unité de transmission (29) comprend une pièce de tige de transmission (292) entraînée par le dispositif d'entraînement (23). Une extrémité de l'unité de liaison (24) est reliée de manière fixe au corps (21) de train d'atterrissage, et son autre extrémité est reliée à la pièce de tige de transmission (292). Lorsqu'elle est entraînée par le dispositif d'entraînement (23) pour tourner, la pièce de tige de transmission (292) commande l'élévation ou l'abaissement du corps (21) de train d'atterrissage. L'aéronef sans pilote (10) et le train d'atterrissage (2) de celui-ci non seulement facilitent l'amélioration des performances de vol, mais également un espace fonctionnel de l'aéronef sans pilote (10) s'en trouve agrandi. En ce qui concerne l'aéronef sans pilote (10) équipé d'un dispositif d'acquisition d'image, il est possible d'empêcher le train d'atterrissage (2) de bloquer la prise de vue du dispositif d'acquisition d'image, ce qui permet d'améliorer les performances de photographie de l'aéronef sans pilote (10), et l'aéronef sans pilote (10) est plus pratique à transporter et à stocker lorsqu'il n'est pas utilisé.
PCT/CN2017/109736 2016-11-22 2017-11-07 Aéronef sans pilote et train d'atterrissage associé WO2018095214A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201621269733.6 2016-11-22
CN201621269733.6U CN206187329U (zh) 2016-11-22 2016-11-22 飞行器及其起落架装置

Publications (1)

Publication Number Publication Date
WO2018095214A1 true WO2018095214A1 (fr) 2018-05-31

Family

ID=58723838

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2017/109736 WO2018095214A1 (fr) 2016-11-22 2017-11-07 Aéronef sans pilote et train d'atterrissage associé

Country Status (2)

Country Link
CN (1) CN206187329U (fr)
WO (1) WO2018095214A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112478139A (zh) * 2020-11-30 2021-03-12 重庆空翼航天科技有限公司 用于无人机的起落架控制系统及方法
CN112693599A (zh) * 2021-01-22 2021-04-23 宁夏翼航智控科技有限公司 一种具备可快速诊断识别预警功能的无人机
WO2023053213A1 (fr) * 2021-09-28 2023-04-06 株式会社エアロネクスト Véhicule volant

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107985564A (zh) * 2017-12-28 2018-05-04 深圳市道通智能航空技术有限公司 起落架及具有该起落架的无人飞行器
CN108216593A (zh) * 2017-12-31 2018-06-29 深圳市道通智能航空技术有限公司 起落架及具有此起落架的无人飞行器
JP2021154808A (ja) * 2020-03-26 2021-10-07 セイコーエプソン株式会社 無人航空機

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110233323A1 (en) * 2010-03-29 2011-09-29 Eurocopter Deutschland Gmbh Skid-type landing gear for a helicopter
CN204197278U (zh) * 2014-10-31 2015-03-11 湖北易瓦特科技有限公司 一种用于起落架连接的机构
CN204871591U (zh) * 2015-07-17 2015-12-16 零度智控（北京）智能科技有限公司 一种飞行器可收放起落架及飞行器
CN204998756U (zh) * 2015-09-24 2016-01-27 向曼 起落架摆动装置
CN205168874U (zh) * 2015-12-07 2016-04-20 深圳市帝翼飞科技有限公司 一种脚架能收放的多旋翼飞行器
CN105539818A (zh) * 2015-12-25 2016-05-04 小米科技有限责任公司 飞行器的脚架结构和飞行器
CN205602094U (zh) * 2015-12-25 2016-09-28 小米科技有限责任公司 飞行器的脚架结构和飞行器

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110233323A1 (en) * 2010-03-29 2011-09-29 Eurocopter Deutschland Gmbh Skid-type landing gear for a helicopter
CN204197278U (zh) * 2014-10-31 2015-03-11 湖北易瓦特科技有限公司 一种用于起落架连接的机构
CN204871591U (zh) * 2015-07-17 2015-12-16 零度智控（北京）智能科技有限公司 一种飞行器可收放起落架及飞行器
CN204998756U (zh) * 2015-09-24 2016-01-27 向曼 起落架摆动装置
CN205168874U (zh) * 2015-12-07 2016-04-20 深圳市帝翼飞科技有限公司 一种脚架能收放的多旋翼飞行器
CN105539818A (zh) * 2015-12-25 2016-05-04 小米科技有限责任公司 飞行器的脚架结构和飞行器
CN205602094U (zh) * 2015-12-25 2016-09-28 小米科技有限责任公司 飞行器的脚架结构和飞行器

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112478139A (zh) * 2020-11-30 2021-03-12 重庆空翼航天科技有限公司 用于无人机的起落架控制系统及方法
CN112478139B (zh) * 2020-11-30 2023-02-07 重庆空翼航天科技有限公司 用于无人机的起落架控制系统及方法
CN112693599A (zh) * 2021-01-22 2021-04-23 宁夏翼航智控科技有限公司 一种具备可快速诊断识别预警功能的无人机
WO2023053213A1 (fr) * 2021-09-28 2023-04-06 株式会社エアロネクスト Véhicule volant

Also Published As

Publication number Publication date
CN206187329U (zh) 2017-05-24

Similar Documents

Publication Publication Date Title
WO2018095214A1 (fr) Aéronef sans pilote et train d'atterrissage associé
US20220402607A1 (en) Foldable multi-rotor aerial vehicle
US11305875B2 (en) Mult-functional compartment
US20170247106A1 (en) Drone provided with foldable drone supports
WO2016169035A1 (fr) Suspension à la cardan et véhicule aérien sans pilote utilisant cette dernière
WO2018120890A1 (fr) Véhicule aérien sans pilote
WO2019024541A1 (fr) Bras et véhicule aérien sans pilote
WO2019056865A1 (fr) Dispositif de panoramique-inclinaison et véhicule aérien sans pilote le comprenant
CN107539466B (zh) 一种用于全景拍摄的无人机
WO2019128401A1 (fr) Train d'atterrissage et véhicule aérien sans pilote équipé de celui-ci
CN104859857A (zh) 一种单镜头全景无人机系统
CN108146618B (zh) 起落架及具有此起落架的无人飞行器
WO2019062139A1 (fr) Véhicule aérien sans pilote
WO2019007130A1 (fr) Train d'atterrissage et véhicule aérien sans pilote le comprenant
WO2019173990A1 (fr) Mécanisme de montage, train d'atterrissage, bâti et véhicule aérien sans pilote
WO2019062140A1 (fr) Véhicule aérien sans pilote
WO2019100821A1 (fr) Véhicule aérien sans pilote
CN201380965Y (zh) 小型无人飞机上的航拍云台
WO2017107493A1 (fr) Pied de support d'aéronef, aéronef et procédé de commande
WO2018095238A1 (fr) Véhicule aérien sans pilote et son dispositif de train de roulement
WO2018223742A1 (fr) Tête à berceau, dispositif de prise de vues pourvu de ladite tête à berceau et véhicule aérien sans pilote
CN109278981B (zh) 一种微型可折叠三维实景建模无人机
WO2023237076A1 (fr) Mécanisme de photographie, véhicule aérien sans pilote et procédé de commande pour véhicule aérien sans pilote
CN109573034B (zh) 收放机构和无人机
WO2019119939A1 (fr) Véhicule aérien sans pilote

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 17873353

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 17873353

Country of ref document: EP

Kind code of ref document: A1