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WO2017206070A1 - Cellule de véhicule aérien sans pilote, et véhicule aérien sans pilote - Google Patents

Cellule de véhicule aérien sans pilote, et véhicule aérien sans pilote Download PDF

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Publication number
WO2017206070A1
WO2017206070A1 PCT/CN2016/084153 CN2016084153W WO2017206070A1 WO 2017206070 A1 WO2017206070 A1 WO 2017206070A1 CN 2016084153 W CN2016084153 W CN 2016084153W WO 2017206070 A1 WO2017206070 A1 WO 2017206070A1
Authority
WO
WIPO (PCT)
Prior art keywords
arm
unmanned aerial
aerial vehicle
segment
vehicle according
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/CN2016/084153
Other languages
English (en)
Chinese (zh)
Inventor
农贵升
唐尹
冯建刚
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SZ DJI Technology Co Ltd
Original Assignee
SZ DJI Technology Co Ltd
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 SZ DJI Technology Co Ltd filed Critical SZ DJI Technology Co Ltd
Priority to CN201680003970.4A priority Critical patent/CN107148383B/zh
Priority to PCT/CN2016/084153 priority patent/WO2017206070A1/fr
Publication of WO2017206070A1 publication Critical patent/WO2017206070A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/061—Frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
    • F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00—UAVs specially adapted for particular uses or applications

Definitions

  • the present invention relates to the field of aircraft, and more particularly to a frame of an unmanned aerial vehicle and an unmanned aerial vehicle.
  • unmanned aerial vehicles have been widely used in aerial photography, surveillance, exploration, rescue, agricultural plant protection and other fields.
  • the unmanned aerial vehicle In order to perform the mission and the need for its own flight, the unmanned aerial vehicle is usually equipped with a certain number of functional modules, such as a sensor, an inertial measurement unit (IMU), a flight control module, a shooting unit, and the like.
  • functional modules such as a sensor, an inertial measurement unit (IMU), a flight control module, a shooting unit, and the like.
  • IMU inertial measurement unit
  • existing unmanned aerial vehicles especially multi-rotor UAVs, generate vibrations due to the operation of their power units (such as rotors), which in turn affects the functional modules, causing the functional modules to fail to function properly or even be damaged.
  • a frame of an unmanned aerial vehicle includes a fuselage and an arm coupled to the fuselage.
  • the arm is provided with a mounting portion for mounting a power assembly.
  • the frame of the UAV further includes a vibration isolating member disposed on the arm and located between the mounting portion and the fuselage to block vibration of the power assembly.
  • An unmanned aerial vehicle includes a frame and a power assembly.
  • the frame includes a body and an arm coupled to the body.
  • the arm is provided with a mounting portion for the mounting power assembly.
  • the frame of the UAV further includes a vibration isolating member disposed on the arm and located between the mounting portion and the fuselage to block vibration of the power assembly.
  • the rack of the UAV and the UAV are provided with the vibration isolating member to prevent the vibration of the power component from being transmitted to the airframe through the arm, thereby ensuring The components within the fuselage are protected from the shock.
  • FIG. 1 is a perspective view of an unmanned aerial vehicle according to an embodiment of the present invention.
  • FIG. 2 is an exploded view of the arm of the UAV of FIG. 1.
  • FIG. 3 is a further exploded view of the arm of the UAV of FIG. 2.
  • 4 to 6 are schematic views of the assembly of the arm of the UAV of Fig. 3.
  • Fig. 7 is a schematic view of an unmanned aerial vehicle according to a second embodiment of the present invention.
  • Fig. 8 is a schematic view of an unmanned aerial vehicle according to a third embodiment of the present invention.
  • a component when referred to as being “fixed” to another component, it can be directly on the other component or the component can be present.
  • a component When a component is considered to "connect” another component, it can be directly connected to another component or possibly a central component.
  • a component When a component is considered to be “set to” another component, it can be placed directly on another component or possibly with a centered component.
  • the terms “vertical,” “horizontal,” “left,” “right,” and the like, as used herein, are for illustrative purposes only.
  • an unmanned aerial vehicle 100 includes a fuselage 10 , an arm 20 , a vibration isolating member 30 , a power assembly 40 , and a stand 50 .
  • the UAV 100 is a quadrotor unmanned aerial vehicle, so the power assembly 40 is a rotor assembly and the number is four, and the four power components 40 are supported by the corresponding arm 20 . And distributed in a rectangular area around the body 10, and each of the power components 40 is located at one vertex of the rectangle.
  • the adjacent power components 40 have different rotational directions during operation, and the opposite rotational directions of the power components 40 are the same.
  • the number of the power components 40 can be appropriately changed according to different requirements.
  • the number of the power components 40 can be two, three, six, eight, sixteen, etc., even The number of power components 40 can be only one.
  • the airframe 10 is a carrier of the unmanned aerial vehicle 100, and an electrical installation portion may be disposed on or in the body 10.
  • the electrical installation portion may mount and carry a sensor, a circuit board, a processor, and a communication module. And electronic components such as batteries.
  • the outer casing (not numbered) of the fuselage 10 is streamlined to reduce air resistance during flight.
  • the outer casing of the fuselage 10 may have other shapes, such as a polygon, a circle, an ellipse, and the like. It can be understood that the outer casing of the fuselage 10 can also be omitted, and the fuselage 10 is formed only by the bracket overlapping.
  • the body 10 includes an upper casing 11 and a lower casing 12, and the upper casing 11 and the lower casing 12 are spliced and joined to each other to form an integral casing of the body 10.
  • the upper case 11 and the lower case 12 can be connected to each other by means of snapping, fastener connection, gluing or the like.
  • a cavity (not shown) is formed between the upper casing 11 and the lower casing 12, and the sensor, the circuit board, the processor, the communication module, and the battery are housed in the cavity.
  • the arm 20 is used to support the power assembly 40 and distribute the power assembly 40 around the fuselage 10 in a predetermined pattern.
  • the number of the arms 20 corresponds to the number of the power components 40, and is four.
  • the number of the arms 20 may be different from the number of the power components 40.
  • each of the arms 20 can support two or more of the power assemblies 40.
  • each of the arms 20 can form two or more branches, each of which can support one The power assembly 40.
  • each of the arms 20 may not include a branch. As long as the arms 20 and the power assembly 40 are sized, a plurality of the power components 40 may be disposed on each of the arms 20. .
  • the arm 20 is connected to the side of the body 10 , and the plurality of the arms 20 are radially connected to the circumference of the body 10 .
  • the angles between the adjacent arms 20 are the same.
  • Each of the arms 20 includes a first section 21 and a second section 22.
  • the first section 21 is coupled to the fuselage 10, and the second section 22 supports the corresponding power assembly 40.
  • the vibration isolating member 30 is disposed between the first segment 21 and the second segment 22 .
  • the first segment 21 and the second segment 22 are separated by the isolating member 30. In other words, the first segment 21 and the second segment 22 are not in direct contact.
  • a limiting portion 211 is protruded from an end surface 210 of each of the first segments 21 facing away from the fuselage 10 , and the limiting portion 211 includes a supporting member 2111 and a stopping member 2112 .
  • the support member 2111 is a protrusion formed on the end surface 210 of the first segment 21.
  • the support member 2111 is a cylindrical protrusion. It can be understood that the support member 2111 can also be Prism or other shaped studs.
  • the cross-sectional dimension of the support member 2111 is smaller than the size of the end surface 210 of the first segment 21 such that at least a portion of the end surface 210 protrudes from the circumferential side of the first segment 21.
  • the stopper 2112 is a flange formed at the end of the support member 2111. In the embodiment, the stopper 2112 protrudes substantially perpendicularly from the circumferential side of the support member 2111. 2112 is a continuous annular flange. It can be understood that in other embodiments, the stopper 2112 may also be discontinuous. For example, the stopper 2112 may be composed of a plurality of arcuate flanges.
  • the support member 2111 and the stopper 2112 are integrally formed, and the support member 2111 is integrally formed with the first segment 21. It can be understood that the support member 2111, the stopper member 2112 and the first segment 21 can also be separately formed and assembled by the above-mentioned structure, and the connection can be a snap connection, a glue connection, a welding, etc. , no longer repeat them one by one.
  • the first segment 21 is a hollow structure, and the inside thereof communicates with the internal space of the body 10.
  • the first segment 21 includes a plurality of splice portions, and the plurality of splice portions are spliced to form the first segment 21 .
  • the first segment 21 includes a first splicing portion 21a and a second splicing portion 21b, and the first splicing portion 21a and the second splicing portion 21b are spliced to each other to form the first segment 21.
  • the first joint portion 21a is integrally formed with the upper casing 11 of the body 10
  • the second joint portion 21b is integrally formed with the lower casing 12 of the body 10.
  • the upper case 11 and the lower case 12 are spliced and joined to each other to form an integral outer casing of the body 10.
  • first splicing portion 21a and the second splicing portion 21b can be connected to each other by means of snapping, fastener connection, gluing or the like. It can be understood that the first segment 21 may further include other splicing portions than the first splicing portion 21a and the second splicing portion 21b, and details are not described herein.
  • the second section 22 is a hollow structure whose end facing the first section 21 is an open end.
  • the second segment 22 includes a third splicing portion 22a and a fourth splicing portion 22b that can be spliced to each other.
  • the third joint portion 22a includes a first arm portion 221 and a first mounting portion 222 connected to the first arm portion 221, and the fourth joint portion 22b includes a second arm portion 223 and the second arm portion
  • the second mounting portion 224 is connected to the portion 223.
  • the first arm portion 221 and the second arm portion 223 together constitute an integral arm portion 201 of the arm 20
  • the first mounting portion 222 and the second mounting portion 224 together constitute an integral mounting portion 202 of the arm 20 .
  • the arm portion 201 can be coupled to the first segment 21, the arm portion 201 having a length such that the corresponding power assembly 40 can be supported at a predetermined position.
  • the length of the second segment 22 is greater than the length of the first segment 21 .
  • the arm portion 201 has a substantially truncated cone shape, and a cross-sectional dimension of the end portion of the arm portion 201 away from the body 10 is smaller than a cross-sectional dimension toward an end of the first segment 21 .
  • the inner surface of the arm portion 201 is substantially tapered, and the inner dimension of the arm portion 201 is gradually reduced from a side close to the first segment 21 toward a side away from the body 10.
  • a plurality of first latching protrusions 2211 are formed on an inner surface of the first arm portion 221 at an end adjacent to the first segment 21 .
  • the number of the first latching protrusions 2211 is two, and the two first latching protrusions 2211 are parallel and spaced apart from each other.
  • the first latching protrusion 2211 is along The first arm portions 221 are arranged in the longitudinal direction.
  • the first engaging protrusions 2211 are all semi-annular protrusions.
  • the number of the first latching protrusions 2211 may be changed to one, three, four, and the like; in addition, at least one of the first latching protrusions 2211 may also have Multi-section arc-shaped protrusions.
  • An inner surface of the first arm portion 221 is further formed with a first connecting post 2212, and the first connecting post 2212 extends from a surface of the first arm portion 221 toward the second arm portion 223, the first A connecting hole 2212a is formed in the connecting post 2212 toward the end surface of the second arm portion 223.
  • the number of the first connecting posts 2212 is two, and the connecting holes 2212a are threaded holes.
  • the first mounting portion 222 is located at an end of the first arm portion 221 facing away from the body 10 .
  • the first mounting portion 222 is provided with a through hole 2221 , and the through hole 2221 can pass through a part of the structure of the power assembly 40 .
  • the second arm portion 223 has a structure substantially similar to the first arm portion 221, and includes a second snap-in protrusion (not labeled) corresponding to the first snap-in protrusion 2211 and The first connecting post 2212 corresponds to the second connecting post 2232.
  • the second snap-in protrusion is substantially similar to the structure of the first latching protrusion 2211 and will not be described in detail.
  • the second arm portion 223 defines a through hole 2233 corresponding to the second connecting post 2232 , and the through hole 2233 extends from the outer surface of the second arm portion 223 to the corresponding second connecting post 2232 The end surface of the first arm portion 221 is faced.
  • the second mounting portion 224 is located at an end of the second arm portion 223 that faces away from the body 10.
  • the first mounting portion 222 and the second mounting portion 224 together form a mounting groove structure for mounting the power assembly 40.
  • the mounting groove structure is in communication with the interior of the first section 21.
  • the second mounting portion 224 is provided with a fixing structure 2241 for fixing the power assembly 40.
  • the vibration isolating member 30 is for eliminating the influence of the vibration of the power assembly 40 on the body 10.
  • the vibration isolating member 30 is made of an elastic material.
  • the material of the vibration isolating member 30 may be soft rubber, rubber, silica gel or the like.
  • the vibration isolating member 30 has a substantially sleeve shape, and a sleeve hole 301 is formed inside thereof.
  • the sleeve hole 301 is a circular hole, and the inner diameter of the sleeve hole 301 is matched with the outer diameter of the support member 2111, and the inner diameter of the sleeve hole 301 is smaller than the stop.
  • An abutting portion 31 is formed on a circumferential side surface of the vibration isolating member 30.
  • the abutting portion 31 is a plurality of flanges that are convex with respect to the circumferential side surface of the vibration isolating member 30, and the plurality of flanges are spaced along the central axis of the sleeve hole 301.
  • the outer diameters of the flanges are different from each other, and the outer diameter of the flanges is sequentially decreased along the direction in which the vibration isolating members 30 face away from the body 10.
  • the decreasing extent of the outer diameter dimension of the flange is adapted to the taper of the inner surface of the arm portion 201.
  • the outer diameter of the flange farthest from the fuselage 10 is larger than the outer diameter of the stopper 2112.
  • the number of the flanges is three, and the separation distance between the flanges is matched with the thickness of the first locking protrusion 2211 and the second locking protrusion;
  • the thickness of the flange is adapted to the spacing of the first latching projections 2211 and the spacing of the second latching projections. In other words, the flange can be clamped to and engaged with the first engaging projection 2211 and the second engaging projection.
  • the number of the flanges can also be changed according to requirements, for example, four, five, six, etc., and even the flanges can be one of the whole.
  • the shock absorbing member 30 is sleeved on the support member 2111 , and the stopper member 2112 can resist the end of the vibration isolation member 30 facing away from the body 10 .
  • the protrusion and the abutting portion 31 of the vibration isolating member 30 abut each other, specifically, the flange is engaged with the space between the second locking protrusions, and the second card is inserted into the convex card.
  • the flange closest to the fuselage 10 is located between the fuselage 10 and the fourth joint portion 22b; the third joint portion 22a is from the machine
  • the upper portion of the body 10 is sleeved on the vibration isolating member 30, and the first engaging projection 2211 and the abutting portion 31 of the vibration isolating member 30 abut each other. Specifically, the flange is engaged.
  • the second splicing portion 22a and the fourth splicing portion 22b are mutually engaged to form the second segment 22, and the second segment 22 is internally connected to the first segment 21, the machine
  • the electronic component in the body 10 can be electrically connected to the power component 40 through a conductive line (not shown) disposed in the first segment 21 and the second segment 22; the first connecting post 2212 and The second connecting portion 2232 is aligned with each other, and the third joint portion 22a and the fourth joint portion 22b are fixedly connected to each other by a connecting member 60.
  • the connecting member 60 is a bolt, which can The first connecting post 2212 is threaded so that the arm 20 clamps the shock absorbing member 30; the vibration isolating member 30 is located between the body 10 and the arm 20, thereby avoiding The direct contact between the fuselage 10 and the arm 20 is such that the isolating member 30 can eliminate the influence of vibrations from the arm 20 on the fuselage 10.
  • the power assembly 40 is configured to provide flight power to the UAV 100.
  • the power assembly 40 includes a motor 41 and a propeller 42.
  • the motor 41 includes a stator 411 and a rotor 412 rotatable relative to the stator 411.
  • the stator 411 is fixed on the second mounting portion 224 of the fourth joint portion 22b, and the rotor 412 and a portion of the stator 411 pass through the third joint portion 22a.
  • the motor 41 may be any suitable type of motor such as a brushless motor or a brushed motor.
  • the motor 41 can be electrically connected to electronic components (such as a flight control, a power source, etc.) of the body 10.
  • the propeller 42 is coupled to the rotor 412 and is rotatable by the rotation 412.
  • the propeller 42 can be a foldable paddle.
  • the stand 50 is a support structure when the UAV 100 is landing.
  • the stand 50 is coupled to the bottom of the body 10 and extends away from the body 10 by a predetermined distance.
  • the number of the stand 50 is two.
  • the connection angle of the stand 50 relative to the body 10 can be adjusted, and when the UAV 100 is in a flight state, the stand 50 can be retracted relative to the body 10.
  • the antenna 50 (not shown) of the UAV 100 is disposed inside or outside the stand 50, such that the antenna can be remote from the electronic components in the body 10, avoiding the The interference of the electronic component to the antenna.
  • the unmanned aerial vehicle 100 isolates the arm 20 and the body 10 by the vibration isolating member 30, so that the vibration isolating member 30 can eliminate vibration from the arm 20 to the body 10.
  • the effect is that the functional modules in the fuselage 10 are prevented from being abnormally affected or damaged by the vibration.
  • FIG. 7 a schematic diagram of an unmanned aerial vehicle 200 according to a second embodiment of the present invention is shown.
  • the UAV 200 has a structure similar to that of the UAV 100 described in the first embodiment. Furthermore, the length of the first section 21' of the arm 20' of the UAV 200 is greater than the length of the second section 22', so that the isolation member 30' is closer than the first embodiment.
  • the weight of the second segment 22' can be reduced due to being disposed closer to the power assembly 40', so the second segment 22' and the power assembly 40' function The torque on the vibration isolating member 30' becomes smaller. Therefore, the arm 20' of the UAV 200 is less prone to chattering.
  • FIG. 8 a schematic diagram of an unmanned aerial vehicle 300 according to a third embodiment of the present invention is shown.
  • the UAV 300 has a structure similar to the UAV 100 described in the first embodiment.
  • the vibration isolation member 30" of the UAV 300 is disposed between the arm 20" and the airframe 10".
  • the UAV 300 can also avoid the functions in the airframe 10".
  • the module is affected by the vibration of the power assembly 40'' and functions abnormally or is damaged.
  • the specific structure of the vibration isolating member 30 ′′ and the connection between the vibration isolating member 30 ′′ and the arm 20 ′′ may be the same as the vibration isolating member 30 described in the first embodiment, and no longer A detailed description.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)
  • Insulating Bodies (AREA)
  • Vibration Prevention Devices (AREA)

Abstract

L'invention concerne une cellule d'un véhicule aérien sans pilote, et un véhicule aérien sans pilote (100, 200, 300) comprenant un corps (10, 10', 10") et un bras (20, 20', 20") relié au corps (10, 10', 10"). Le bras (20, 20', 20") comprend une partie de montage (202) pour monter un ensemble d'alimentation (40, 40'). La cellule du véhicule aérien sans pilote comprend en outre un élément d'isolation de choc (30, 30', 30"). L'élément d'isolation de choc (30, 30', 30") est disposé sur le bras (20, 20', 20") et situé entre la partie de montage (202) et le corps (10, 10', 10") pour isoler le choc de l'ensemble d'alimentation (40, 40').
PCT/CN2016/084153 2016-05-31 2016-05-31 Cellule de véhicule aérien sans pilote, et véhicule aérien sans pilote Ceased WO2017206070A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201680003970.4A CN107148383B (zh) 2016-05-31 2016-05-31 无人飞行器的机架及无人飞行器
PCT/CN2016/084153 WO2017206070A1 (fr) 2016-05-31 2016-05-31 Cellule de véhicule aérien sans pilote, et véhicule aérien sans pilote

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2016/084153 WO2017206070A1 (fr) 2016-05-31 2016-05-31 Cellule de véhicule aérien sans pilote, et véhicule aérien sans pilote

Publications (1)

Publication Number Publication Date
WO2017206070A1 true WO2017206070A1 (fr) 2017-12-07

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108394545A (zh) * 2018-03-27 2018-08-14 傲飞创新科技（深圳）有限公司 拼接式无人机机身
US20200283118A1 (en) * 2018-01-19 2020-09-10 SZ DJI Technology Co., Ltd. Unmanned aerial vehicle
CN108275258B (zh) * 2018-03-07 2024-05-24 天津凤凰智能科技有限公司 一种固定结构及多旋翼无人机

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109436349B (zh) * 2018-12-29 2024-06-11 深圳市道通智能航空技术股份有限公司 一种风扇组件、惯性测量组件以及无人飞行器
CN110329525B (zh) * 2019-06-28 2025-02-14 深圳市道通智能航空技术股份有限公司 一种无人机及其组装方法
FR3112328B1 (fr) * 2020-07-09 2022-07-08 Diodon Drone Tech Aéronef sans pilote télécommandé comprenant une structure gonflable

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