WO2018090435A1 - Aéronef - Google Patents

Aéronef Download PDF

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Publication number
WO2018090435A1
WO2018090435A1 PCT/CN2016/111920 CN2016111920W WO2018090435A1 WO 2018090435 A1 WO2018090435 A1 WO 2018090435A1 CN 2016111920 W CN2016111920 W CN 2016111920W WO 2018090435 A1 WO2018090435 A1 WO 2018090435A1
Authority
WO
WIPO (PCT)
Prior art keywords
antenna
arm
aircraft
assembly
disposed
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/CN2016/111920
Other languages
English (en)
Chinese (zh)
Inventor
梁贵彬
张永生
王佳迪
陈星元
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 CN201680088323.8A priority Critical patent/CN109562821A/zh
Publication of WO2018090435A1 publication Critical patent/WO2018090435A1/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
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • 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
    • B64U60/00—Undercarriages
    • B64U60/50—Undercarriages with landing legs

Definitions

  • the invention relates to the field of drones, and more particularly to an aircraft.
  • the aircraft can be used in aerial photography, mapping, plant protection, detection, disaster relief and other industries.
  • the structure usually consists of a central frame, a power system, a landing gear, etc., and is carried out by carrying flight control, image transmission and other microcomputer equipment. .
  • the data acquired during the operation of the aircraft will communicate with ground equipment such as remote control, computer, etc. through the antenna amplification signal.
  • the location of the antenna on the aircraft is different, which will affect the optimal signal point of the antenna, which will affect the overall performance of the aircraft. Therefore, the design layout of the antenna in flight is reasonable and directly affects the performance of the aircraft.
  • the antenna is generally placed on the center frame or the landing gear of the aircraft.
  • the antenna is designed on the center frame, and the equipment on the center frame will affect the performance of the antenna.
  • the antenna is designed on the landing gear, and the antenna is connected with the key design on the center frame, which may result in the landing gear not being designed as a quick release method or the quick release method being too complicated to design and inconvenient to use.
  • the present invention provides an aircraft.
  • an aircraft including a center frame, an antenna, and an arm assembly coupled to the center frame;
  • the arm assembly includes a boom, the antenna being disposed on the arm and away from the center frame.
  • the aircraft further includes a connector disposed on the arm, the connector for fixing the antenna to the arm.
  • the connecting member includes a locking sleeve adapted to the arm, and an antenna holder coupled to the locking sleeve, the antenna seat for carrying the antenna.
  • the antenna mount includes a body portion including an accommodation space for accommodating the antenna.
  • the body portion further includes a wire hole located above the accommodating space.
  • the locking sleeve includes a connecting end connected to the antenna base, and a locking end for fixing the locking sleeve to the arm.
  • a plug hole is disposed in the connecting end, and a wiring hole is disposed on the arm corresponding to the plug hole, and a connecting line of the antenna passes through the plug hole and the wiring hole to enter the arm Inside.
  • an elastic member for sealing the plug hole and the wiring hole may be placed in the plug hole.
  • the antenna is located below the arm.
  • the polarization direction of the antenna is perpendicular to the horizontal plane
  • the polarization direction of the antenna is perpendicular to the extending direction of the arm.
  • the antenna is a dipole antenna.
  • the aircraft further includes a landing gear assembly, the arm assembly being foldably coupled to the center frame; the antenna facing the center of the aircraft when the arm assembly is in a stowed state, the antenna being Located inside the landing gear assembly and the arm assembly.
  • an aircraft including a center frame, an antenna, and an arm assembly coupled to the center frame; the arm assembly is foldably coupled to the center frame;
  • the arm assembly includes a robot arm, the antenna is disposed on the arm, and the antenna faces a center of the aircraft when the arm assembly is in a stowed state, so that the antenna is located at the landing gear The assembly and the inside of the arm assembly.
  • the aircraft further includes a connector disposed on the arm, the connector for fixing the antenna to the arm.
  • the connecting member includes a locking sleeve adapted to the arm, and the locking sleeve A connected antenna mount for carrying the antenna.
  • the antenna mount includes a body portion including an accommodation space for accommodating the antenna.
  • the body portion further includes a wire hole located above the accommodating space.
  • the locking sleeve includes a connecting end connected to the antenna base, and a locking end for fixing the locking sleeve to the arm.
  • a plug hole is disposed in the connecting end, and a wiring hole is disposed on the arm corresponding to the plug hole, and a connecting line of the antenna passes through the plug hole and the wiring hole to enter the arm Inside.
  • an elastic member for sealing the plug hole and the wiring hole may be placed in the plug hole.
  • the antenna is located below the arm; or
  • the polarization direction of the antenna is perpendicular to the horizontal plane
  • the polarization direction of the antenna is perpendicular to the extending direction of the arm.
  • the antenna is a dipole antenna.
  • the technical solution provided by the embodiment of the present invention may include the following effects: the aircraft sets the antenna on the arm, and the setting away from the center frame of the aircraft avoids other components from affecting the performance of the antenna, and ensures that the stand is easily disassembled.
  • FIG. 1 is a schematic view of an aircraft shown in an embodiment of the present invention.
  • FIG. 2 is a schematic view showing the connection between the arm of the aircraft and the connecting member according to an embodiment of the invention.
  • FIG 3 is an exploded view of an arm and a connecting member of an aircraft according to an embodiment of the present invention.
  • FIG. 4 is a schematic view showing the stowed state of an arm assembly of an aircraft according to an embodiment of the present invention.
  • Embodiment 1 is a diagrammatic representation of Embodiment 1:
  • an aircraft 100 shown in this embodiment includes a center frame 1 , an antenna 3 , and an arm assembly 2 connected to the center frame 1 , wherein the center frame 1 is provided with electrical equipment. And metal parts, etc.
  • the arm assembly 2 is foldably or non-foldably connected to the center frame 1.
  • the arm assembly 2 includes a robot arm 21 that is disposed on the arm 21 and away from the center frame 1 .
  • the antenna 3 is disposed on the arm 21 to move the antenna 3 away from electrical equipment, metal parts, and the like in the center frame 1 to avoid interference of signals of the antenna 3, such as electrical equipment and metal parts.
  • the antenna 3 is disposed away from the center frame 1, in the middle of the arm 21 or toward the middle of the arm 21.
  • the present invention provides the antenna 3 of the aircraft 100 on the arm 21 of the arm assembly 2, and the antenna 3 is available at a position away from the center frame 1 without interference from electrical equipment and metal parts. Better performance.
  • the aircraft 100 further includes a connector 4 disposed on the arm 21 for fixing the antenna 3 to the arm 21.
  • the antenna 3 can be directly fixed on the arm 21, for example, the antenna 3 is glued to the arm 21; the antenna can also be connected through a connecting member 4. 3 is fixed to the arm 21.
  • the connecting member 4 includes a locking sleeve 41 adapted to the arm 21 and an antenna holder 42 coupled to the locking sleeve 41.
  • the antenna mount 42 is used to carry the antenna 3.
  • the locking sleeve 41 is detachably or non-detachably connected to the arm 21 .
  • the locking sleeve 41 and the arm 21 are in a snap-fit connection, and the locking sleeve 41 and the arm 21 can also be fixedly connected by bolts or screws.
  • the antenna mount 42 includes a body portion 421, and the body portion 421 includes The accommodating space 423 of the antenna 3 is accommodated. That is, the accommodating space 423 is disposed in the antenna base 42 for carrying the antenna 3.
  • the antenna 3 can also be directly placed in the accommodating space 423, and a baffle 424 is disposed on the body portion 412 for fixing the antenna 3 to the accommodating portion.
  • the baffle 424 can be disposed at an upper portion of the accommodating space 423.
  • the antenna 3 can also be embedded in the accommodating space 423.
  • the body portion 421 further includes a wire hole 422 located above the accommodating space 423, and the wire hole 422 is allowed to pass through the connecting line 31 of the antenna 3.
  • the locking sleeve 41 includes a connecting end 412 connected to the antenna base 42, and a locking end 411 for fixing the locking sleeve 41 to the arm 21.
  • the locking end 411 can fix the locking sleeve 41 to the arm 21 by means of a screw 6.
  • a screw hole is opened in the locking end 411, and the screw 6 is screwed through the screw hole to lock the locking end 411.
  • a plug hole 413 is defined in the connecting end 412, and a wiring hole (not shown) is disposed on the arm 21 corresponding to the plug hole 413.
  • the connecting line 31 of the antenna 3 passes through the plug hole 413 and the wiring hole into the arm 21.
  • the connecting line 31 of the antenna 3 is placed in the arm 21 to protect the connecting line 31 from damage, and the wiring disorder is prevented from affecting the appearance of the aircraft. It is true that in other embodiments, the connecting wire 31 can also be directly attached to the arm 21 or the connecting wire 31 can be fixed to the arm 21 using a fixing member.
  • an elastic member 43 for sealing the plug hole 413 and the wiring hole may be placed in the plug hole 413.
  • the elastic member 43 can be a silicone plug, and the connecting wire 31 of the antenna 3 can pass through the silicone plug. That is, the connecting wire 31 passes through the silicone plug into the arm 21, and the silicone plug is placed in the plug hole 413 and the wiring hole.
  • the silicone plug further protects the connecting line 31.
  • the antenna 3 when the arm 21 is opened, the antenna 3 is located below the arm 21.
  • the number of the antennas 3 is two or more, and is respectively disposed on different arms 21.
  • the polarization direction of the antenna 3 is set to be perpendicular to the horizontal plane, below the arm 21.
  • the antenna 3 is disposed under the arm 21 to ensure that the antenna 3 faces the center of the entire aircraft 100 when the arm assembly 2 is folded and folded, and the outer arm assembly 2 can protect the antenna 3 and make the antenna 3 Free from collisions, etc., which facilitates packaging, handling, and movement.
  • the performance achieved when the polarization direction of the antenna 3 is perpendicular to the horizontal plane is optimal.
  • the extending direction of the antenna 3 overlaps with the polarization direction of the antenna 3. Therefore, in the present embodiment, the extending direction of the antenna 3 provided on the arm 21 is perpendicular to the ground.
  • the antenna 3 when the arm assembly 2 is opened, the antenna 3 can also be located above the arm 21, and when the arm assembly 3 is folded and folded, the antenna 3 is folded or rotated so that It is oriented toward the center of the aircraft 100 to avoid damage to the outside of the arm 21.
  • the polarization direction of the antenna 3 is perpendicular to the extending direction of the arm 21.
  • the arm 21 When the arm 21 is deployed, it is substantially parallel to the horizontal plane, so that the angle between the antenna 3 and the horizontal plane disposed on the arm 21 and perpendicular to the arm 21 is also close to ninety degrees.
  • the polarization direction of the antenna 3 is perpendicular to the extending direction of the arm 21, and it is easy to align when the antenna 3 is mounted, and the appearance of the aircraft 100 is also beautified. It is true that when the arm assembly 2 and the center frame 1 are non-foldable, the angle between the polarization direction of the antenna 3 and the horizontal plane is also close to ninety degrees, which also has the above effects.
  • the extending direction of the antenna 3 overlaps with the polarization direction of the antenna 3. Therefore, in the present embodiment, the extending direction of the antenna 3 is perpendicular to the arm 21 .
  • the aircraft 100 further includes a landing gear assembly 5, and the arm assembly 2 of the aircraft 100 is foldably coupled to the center frame 1.
  • the antenna 3 is located inside the landing gear assembly 5 and the arm assembly 2, and the landing gear assembly 5 and the arm assembly 2 can protect the antenna 3 and prevent the antenna 3 from being subjected to damage. That is, the arm assembly 2 is foldably connected to the center frame 1, and when the arm assembly 2 is in the stowed state, the antenna 3 faces the center of the aircraft 100, so that the antenna 3 is located The drop frame assembly 5 and the inside of the arm assembly 2 are protected to protect the antenna 3 from damage.
  • the antenna is a dipole antenna, and may also be, for example, an IFA (Inverted F-shaped Antenna), a PIFA (Planar Inverted F-shaped Antenna), a loop antenna, Slot antennas, etc.
  • the loop antenna is a metal guide
  • the wire is wound into a certain shape, such as a circle, a square, a triangle, etc., with the ends of the conductor as the output end.
  • the aircraft 100 is a multi-rotor aircraft 100, including one of a quadrotor aircraft, a six-rotor aircraft, or an eight-rotor aircraft.
  • Embodiment 2 is a diagrammatic representation of Embodiment 1:
  • the present invention provides a further description of an aircraft 100 by another embodiment.
  • the aircraft 100 includes a center frame 1, an antenna 3, and a boom assembly 2 connected to the center frame 1.
  • the arm assembly 2 is foldably connected to the center frame 1.
  • the arm assembly 2 includes a robot arm 21, and the antenna 3 is disposed on the arm 21, and when the arm assembly 2 is in a stowed state, the antenna faces the center of the aircraft, so that the antenna 3 is located inside the landing gear assembly 5 and the arm assembly 2.
  • the arm assembly 2 of the aircraft 100 can be opened or stowed relative to the center frame 1, and the antenna 3 is disposed on the arm 21, and the antenna 3 can be retracted with the arm 21, and
  • the antenna 3 is located inside the landing gear assembly 5 and the arm assembly 2 when the arm assembly 2 is in the stowed state. Since the outer side of the antenna 3 has the landing gear assembly 5 and the arm assembly 2, the landing gear assembly 5 and the arm assembly 2 can protect the antenna 3 when transporting or packaging the aircraft 100. The antenna 3 is protected from collision or the like, and the damage of the external force to the antenna 3 is reduced. Since the antenna 3 is disposed on the arm 21, the landing gear assembly can be designed as a quick release structure, which further reduces the packaging volume of the aircraft and is more advantageous for mobile handling.
  • the antenna 3 when the arm 21 is opened, the antenna 3 is located below the arm 21, and when the arm assembly 2 is in the stowed state, the antenna 3 faces the center or orientation of the aircraft. It tends to the center of the aircraft.
  • the outer arm assembly 2 protects the antenna 3 and protects the antenna 3 from collisions and the like, thereby facilitating packaging, handling, and movement.
  • the polarization direction of the antenna 3 is set to be perpendicular to the horizontal plane, and the achieved performance of the antenna 3 is optimal at this time. It can be understood that when the arm assembly 2 is opened, the antenna 3 can also be located above the arm 21, and when the arm assembly 3 is folded and folded, the antenna 3 is folded or rotated so that It is oriented toward the center of the aircraft 100 to avoid damage to the outside of the arm 21.
  • the polarization direction of the antenna 3 is perpendicular to the direction in which the arm 21 extends.
  • the performance achieved by the antenna 3 is optimal. Therefore, the arrangement of the antenna 3 in the present embodiment optimizes the performance of the antenna 3 while protecting the antenna 3.
  • the arm 21 When the arm 21 is deployed, it is substantially parallel to the horizontal plane, so that the angle between the antenna 3 and the horizontal plane disposed on the arm 21 and perpendicular to the arm 21 is also close to ninety degrees.
  • the polarization direction of the antenna 3 is perpendicular to the extending direction of the arm 21, and it is easy to align when the antenna 3 is mounted, and the appearance of the aircraft 100 is also beautified.
  • the aircraft 100 in this embodiment further includes the following technical features.
  • the technical features described below are the same as or similar to those in the previous embodiment, and the technical effects obtained are the same or similar, and belong to the same inventive concept. Only the relationship between the technical features and technical features of the aircraft 100 will be described below, and the effects between the specific effects or technical features will not be described. For details, refer to the description of the embodiment of the aircraft 100.
  • the aircraft 100 further includes:
  • a connector 4 is provided on the arm 21 for fixing the antenna 3 to the arm 21.
  • the connecting member 4 includes a locking sleeve 41 adapted to the arm 21 and an antenna holder 42 connected to the locking sleeve 41 for carrying the antenna 3.
  • the antenna holder 42 includes a body portion 421 including an accommodation space 423 for accommodating the antenna 3.
  • the body portion 421 further includes a wire hole 422 located above the accommodating space 423.
  • the locking sleeve 41 includes a connecting end 412 connected to the antenna base 42 and a locking end 411 for fixing the locking sleeve 41 to the arm 21 .
  • a plug hole 413 is disposed in the connecting end 412, and a wire hole is disposed on the arm 21 corresponding to the plug hole 413.
  • the connecting wire 31 of the antenna 3 passes through the plug hole 413 and the wiring hole. Inside the arm 21 .
  • An elastic member 43 for sealing the plug hole 413 and the wiring hole may be placed in the plug hole 413.
  • the antenna is a dipole antenna.
  • the aircraft 100 is a multi-rotor aircraft 100, including one of a quadrotor aircraft, a six-rotor aircraft, or an eight-rotor aircraft.
  • the aircraft 100 has the antenna 3 disposed on the arm 21, which solves the interference problem and can obtain a more performance effect than the antenna 3 is disposed on the center frame 1.
  • the antenna is placed under the arm to avoid antenna damage when applied to an aircraft that is capable of folding the arm assembly.
  • Some aircraft with the retractable landing gear assembly 5, using the antenna 3 design on the arm 21, can design the retractable landing gear assembly as a quick-release structure, which can further reduce the packaging volume of the aircraft and facilitate the movement. Handling.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Details Of Aerials (AREA)

Abstract

La présente invention concerne un aéronef (100), comprenant un cadre central (1), une antenne (3), et un ensemble bras (2) relié au cadre central. L'ensemble bras comprend des bras (21). L'antenne est disposée sur une position sur le bras à une certaine distance du cadre central. L'aéronef comprend en outre un connecteur (4) disposé sur le bras. Le connecteur est utilisé pour fixer l'antenne sur le bras. Selon l'aéronef, l'antenne est disposée sur le bras à une certaine distance du cadre central de l'aéronef pour éviter que d'autres composants affectent les performances de l'antenne et pour faciliter le détachement d'un cadre de jambe.
PCT/CN2016/111920 2016-11-18 2016-12-24 Aéronef Ceased WO2018090435A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201680088323.8A CN109562821A (zh) 2016-11-18 2016-12-24 飞行器

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201621247756.7U CN206218204U (zh) 2016-11-18 2016-11-18 飞行器
CN201621247756.7 2016-11-18

Publications (1)

Publication Number Publication Date
WO2018090435A1 true WO2018090435A1 (fr) 2018-05-24

Family

ID=58791648

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2016/111920 Ceased WO2018090435A1 (fr) 2016-11-18 2016-12-24 Aéronef

Country Status (2)

Country Link
CN (2) CN206218204U (fr)
WO (1) WO2018090435A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN206893798U (zh) 2017-07-10 2018-01-16 深圳市道通智能航空技术有限公司 一种天线及无人机
CN107512391B (zh) * 2017-08-23 2020-07-24 佛山长光智能制造研究院有限公司 基于系留线缆供电的旋翼无人飞行器
CN109415127B (zh) * 2017-12-01 2022-03-04 深圳市大疆灵眸科技有限公司 连接组件以及拍摄设备
CN109774948A (zh) * 2019-02-13 2019-05-21 山东蜂巢航空科技有限公司 一种可挂载多种载荷的油电混合多旋翼无人机
WO2024124569A1 (fr) * 2022-12-16 2024-06-20 深圳市闪至科技有限公司 Engin volant sans pilote embarqué

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2455374A (en) * 2008-06-16 2009-06-10 Middlesex University Higher Ed Unmanned aerial vehicle comprising a triangular array of rotors
CN204660021U (zh) * 2015-03-12 2015-09-23 上海良相智能化工程有限公司 一种六旋翼无人侦察直升机系统
CN204776013U (zh) * 2015-06-04 2015-11-18 东莞中寰智能航空科技有限公司 一种六轴无人机
CN205186516U (zh) * 2015-10-26 2016-04-27 贵州斯凯威科技有限公司 一种具有运输功能的无人机
CN105752340A (zh) * 2016-04-07 2016-07-13 广州极飞电子科技有限公司 无人飞行器

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9731811B2 (en) * 2013-12-13 2017-08-15 Aai Corporation Payload shroud for air vehicle
WO2015196418A1 (fr) * 2014-06-26 2015-12-30 深圳市大疆创新科技有限公司 Aéronef et ensemble de protection des lignes de signaux de celui-ci
CN205652331U (zh) * 2016-04-14 2016-10-19 深圳市大疆创新科技有限公司 无人飞行器的机架及多旋翼无人飞行器

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2455374A (en) * 2008-06-16 2009-06-10 Middlesex University Higher Ed Unmanned aerial vehicle comprising a triangular array of rotors
CN204660021U (zh) * 2015-03-12 2015-09-23 上海良相智能化工程有限公司 一种六旋翼无人侦察直升机系统
CN204776013U (zh) * 2015-06-04 2015-11-18 东莞中寰智能航空科技有限公司 一种六轴无人机
CN205186516U (zh) * 2015-10-26 2016-04-27 贵州斯凯威科技有限公司 一种具有运输功能的无人机
CN105752340A (zh) * 2016-04-07 2016-07-13 广州极飞电子科技有限公司 无人飞行器

Also Published As

Publication number Publication date
CN109562821A (zh) 2019-04-02
CN206218204U (zh) 2017-06-06

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