CN203047531U - Multi-rotor unmanned aerial vehicle - Google Patents

Multi-rotor unmanned aerial vehicle Download PDF

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Publication number
CN203047531U
CN203047531U CN2012206043967U CN201220604396U CN203047531U CN 203047531 U CN203047531 U CN 203047531U CN 2012206043967 U CN2012206043967 U CN 2012206043967U CN 201220604396 U CN201220604396 U CN 201220604396U CN 203047531 U CN203047531 U CN 203047531U
Authority
CN
China
Prior art keywords
horn
housing
rotor
unmanned vehicle
actuating device
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.)
Expired - Lifetime
Application number
CN2012206043967U
Other languages
Chinese (zh)
Inventor
汪滔
赵涛
陈少杰
欧志刚
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.)
Shenzhen Dajiang Innovations Technology Co Ltd
Original Assignee
Shenzhen Dajiang Innovations 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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=48730514&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=CN203047531(U) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Priority to CN2012206043967U priority Critical patent/CN203047531U/en
Application filed by Shenzhen Dajiang Innovations Technology Co Ltd filed Critical Shenzhen Dajiang Innovations Technology Co Ltd
Publication of CN203047531U publication Critical patent/CN203047531U/en
Application granted granted Critical
Priority to JP2015542149A priority patent/JP2016505435A/en
Priority to DE202013012541.1U priority patent/DE202013012541U1/en
Priority to DE202013012545.4U priority patent/DE202013012545U1/en
Priority to DE202013012543.8U priority patent/DE202013012543U1/en
Priority to DE202013012547.0U priority patent/DE202013012547U1/en
Priority to DE202013012544.6U priority patent/DE202013012544U1/en
Priority to DE202013012546.2U priority patent/DE202013012546U1/en
Priority to EP13795150.5A priority patent/EP2763896B1/en
Priority to PCT/CN2013/087053 priority patent/WO2014075609A1/en
Priority to US14/092,653 priority patent/US9016617B2/en
Priority to US14/515,357 priority patent/US9221536B2/en
Priority to US14/534,127 priority patent/US9221537B2/en
Priority to US14/836,344 priority patent/US9233754B1/en
Priority to US14/947,923 priority patent/US9321530B2/en
Priority to US14/954,427 priority patent/US9284049B1/en
Priority to US15/012,006 priority patent/US9394048B2/en
Priority to US15/175,473 priority patent/US10155584B2/en
Priority to US15/947,650 priority patent/US10189562B2/en
Priority to US16/005,309 priority patent/US10196137B2/en
Priority to US16/027,178 priority patent/US10272994B2/en
Priority to US16/353,999 priority patent/US10472056B2/en
Priority to US16/679,984 priority patent/US11338912B2/en
Priority to US17/664,629 priority patent/US20220281592A1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Abstract

The utility model is applicable to the field of multi-rotor unmanned aerial vehicles and provides a multi-rotor unmanned aerial vehicle. The multi-rotor unmanned aerial vehicle comprises a hollow shell, a circuit module which is contained in the shell, arms which are connected with the shell, power devices which are arranged on the arms and are used for driving the aerial vehicle to fly, a containing position which is arranged on the shell and is used for containing a power supply, and a connecting device which is used for electrically connecting the power supply with the power devices, wherein each power device comprises at least three rotor wing and a rotor wing driving device; the rotor wings are connected to the corresponding rotor wing driving device; and each rotor wing driving device is fixedly connected to the corresponding arm. According to the multi-rotor unmanned aerial vehicle, the power supply and the circuit module can be pre-arranged in the shell, and a user does not need to self-assemble and self-debug the aerial vehicle, so that requirements on the profession of the user are greatly reduced, errors in installation of the aerial vehicle by the user are eliminated, and the aerial vehicle is high in reliability.

Description

Many rotors unmanned vehicle
Technical field
The utility model belongs to many rotors unmanned vehicle field, relates in particular to a kind of many rotors unmanned vehicle.
Background technology
Present many rotors unmanned vehicle, its fuselage, power system, flight control system is separated, and power system, flight control system need expose and be installed on the fuselage, are not easy to transportation and storage.The user needs voluntarily to power system, and flight control system etc. are installed, debugged, to user's requirement height.Just in case user installation is wrong, can cause the phenomenon of infringement aircraft such as aircraft bombing, reliability is relatively poor, uses inconvenient.
In addition, the joint that need connect during installation is more, but it adopts the adaptor union jointing of plug mostly, may install not in placely during user installation, and the vibration that aircraft produces in flight course may cause joint to come off, and can't guarantee aircraft safety flight.
The utility model content
The purpose of this utility model is to overcome poor reliability, uses inconvenient deficiency, and a kind of many rotors unmanned vehicle is provided, and its reliability height is easy to use.
The utility model is achieved in that a kind of many rotors unmanned vehicle, this unmanned vehicle comprises hollow housing, be contained in circuit module, the horn that links to each other with described housing in the described housing, be arranged on described horn the engine installation that is used for driving aircraft flight, be arranged on described housing be used for hold power supply hold the position, for the connecting device that described power supply is electrically connected with described engine installation; Described engine installation comprises rotor and rotor actuating device, and described rotor is connected in described rotor actuating device, and described rotor actuating device is fixedly connected on described horn, and described rotor is at least three.
Particularly, described horn is one-body molded with described housing or captive joint, and described horn is at least three.
Perhaps, flexibly connect between described horn and the described housing, described horn is at least three.
Particularly, offer on the described horn for the installation position that described engine installation is installed, an end of described rotor actuating device is fixed in the installation position, and the other end connects described rotor.
Alternatively, described horn is 4, and described rotor is 4.
Particularly, described rotor actuating device is electrically connected with the electric mode transfer piece for the described rotor actuating device of control, and described electric mode transfer piece is arranged at the below of described rotor actuating device and is positioned at described horn.
Particularly, described housing or described horn are provided with indicator lamp.
Particularly, the described position that holds is arranged on described housing outer surface or described enclosure interior.
Particularly, described housing comprises upper shell and the lower house of involutory setting up and down, and described horn comprises last horn housing and the following horn housing of involutory setting up and down; The described horn housing of going up is one-body molded with described upper shell or captive joint, and described time horn housing is one-body molded with described lower house or captive joint.
Particularly, the lower end of described housing is connected with foot rest.
Many rotors unmanned vehicle provided by the utility model, it can be preset in power supply, circuit module etc. in the housing, the user need not to assemble voluntarily, debug aircraft, convenient for users to use, greatly reduce the requirement to user's specialty degree, avoid user installation wrong situation, the reliability height of aircraft to occur, and reduced the risk that adaptor union gets loose, further improved the reliability of aircraft.
Description of drawings
Fig. 1 is the three-dimensional assembly drowing after many rotors unmanned vehicle of providing of the utility model embodiment is removed rotor;
Fig. 2 is the three-dimensional assembly drowing after many rotors unmanned vehicle of providing of the utility model embodiment is removed upper shell;
Fig. 3 is another the three-dimensional assembly drowing after many rotors unmanned vehicle of providing of the utility model embodiment is removed upper shell.
The specific embodiment
In order to make the purpose of this utility model, technical scheme and advantage clearer, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein only in order to explaining the utility model, and be not used in restriction the utility model.
A kind of many rotors unmanned vehicle that the utility model embodiment provides can be used for taking photo by plane, the investigation of ground mapping, the condition of a disaster and rescue, aerial monitoring, polling transmission line etc.
As depicted in figs. 1 and 2, above-mentioned many rotors unmanned vehicle comprise hollow housing 11, be contained in circuit module 3, the horn 12 that links to each other with housing 11 in the housing 11, be arranged on horn 12 the engine installation 2 that is used for driving aircraft flight, be arranged on housing 11 be used for hold the holding position (figure a mark), be arranged at housing 11 of power supply (not shown), horn 12 interior for the connecting device (not shown) that power supply is electrically connected with engine installation 2; Horn 12 can be the suitable shapes such as arm shape of hollow, its can with the intracavity inter-connection of housing 11.Engine installation 2 can be fixedly connected on horn 12.Circuit module 3 is as the critical component of aircraft, can realize each associated components such as is controlled at function.Power supply can be battery.Circuit module 3 comprises IMU(Inertial Measuring Unit, Inertial Measurement Unit) module, main control module 34 etc.
Engine installation 2 comprises rotor 21 and rotor actuating device 22, and rotor 21 is fixedly connected on rotor actuating device 22, and rotor actuating device 22 is fixedly connected on horn 12, and rotor 21 is at least three.Rotor 21 can be two oars, three oars etc., and its function is exactly under the driving of rotor actuating device 22, drives this aircraft flight.Be set with electric mode transfer piece 34 in housing 11 or the horn 12.In this enforcement, electric mode transfer piece 34 is fixedly set in the horn 12, and it can be electrically connected on circuit module 3 by connection cable.
Because outside circuit module 3, battery, connection cable etc. need not to be exposed to; can in factory, circuit module 3, battery, connection cable etc. be assembled in housing 11, the horn 12; parts such as housing 11,12 pairs of circuit modules 3 of horn, battery, connection cable have protective effect; aircraft has good intensity and rigidity, can be adapted to transportation and storage well.The user need not to assemble voluntarily, debug aircraft, can reach the effect of " in one's hands namely use ", convenient for users to use, greatly reduce the requirement to user's specialty degree, avoid user installation wrong situation to occur, thereby avoided the situation of infringement aircraft such as aircraft bombing, the reliability height of aircraft.Because the user need not circuit module 3, rotor 21, rotor actuator 22, horn 12 etc. are assembled, so but cable connect and need not all to adopt the adaptor union of plug to connect, the part cable can be connected as one by the mode of welding.And, even but the adaptor union of plug cable is connected, when in factory, assembling, the specialty the skilled worker adaptor union can be in place, thereby reduced the risk that adaptor union gets loose, further improved the reliability of aircraft.Connection cable can be connected in electric mode transfer piece 34 and circuit module 3 by modes such as welding or adaptor unions.Be appreciated that ground, owing to the connection cables in housing 11, the horn 12 need not frequent dismounting, can connect the reliability height to cable by modes such as welding or adaptor unions.
Horn 12 and housing 11 are one-body molded or captive joint, and horn 12 is at least three.Horn 12 can adopt the integrally manufactured moulding of suitable method such as injection moulding with housing 11 one-body molded finger horns 12 with housing 11.Certainly, horn 12 also can be distinguished moulding with housing 11, and by mode captive joints such as locking piece locking or welding.Locking piece can be screw etc.
That is to say, according to above-mentioned description, integrated structure specifically can also following description: many rotors unmanned vehicle comprise engine installation 2, hollow housing assembly (among the figure mark), housing unit be provided with for hold the holding position (figure a mark), be contained in the interior circuit module 3 of housing unit of power supply (not shown), for connecting device (not shown), electric mode transfer piece 34 that power supply is electrically connected with engine installation 2.
Housing unit comprises housing 11 and from housing 11 outward extending horns 12, horn 12 is provided with engine installation 2, and engine installation 2 comprises rotor 21 and rotor actuating device 22.
Circuit module 3 and electric mode transfer piece 34 are placed on housing unit inside.Except the description of said structure, also can flexibly connect between horn 12 and the housing 11, horn 12 is at least three.In concrete the application, but horn 12 unitary rotation be connected on the housing 11, horn 12 housing 11 relatively folds.When not using, can horn 12 is folding, so that deposit and carry.In use, horn 12 can be launched and fixes.
Offer on the horn 12 for the installation position 120 that engine installation 2 is installed, an end of rotor actuating device 22 is fixed in the installation position 120, and the other end connects rotor 21.Rotor actuating device 22 can be motor, and rotor 21 can be fixedly connected in the rotating shaft 221 of motor.
Described rotor actuating device 22 is electrically connected with the electric mode transfer piece 34 for the described rotor actuating device 22 of control.Described electric mode transfer piece 34 is electrically connected on described circuit module.Electricity mode transfer piece 34 can be arranged in the housing 11, also can be arranged at the below of described rotor actuating device 22 and be positioned at horn 12.
Horn 12 is 4, and rotor 21 is 4.The quantity that rotor actuating device 22 and rotor 21 arrange can equate with the quantity that horn 12 arranges.Certainly, the quantity of horn 12 and rotor 21 also can arrange according to actual conditions.
4 horns 12 are arranged with " X " shape or " ten " font and are connected in housing 11.In concrete the application, horn 12 can be the center of circle with the center shaft of housing 11, and the number of horn 12 on every side that circumferentially is distributed in housing 11 can be adjusted as required.
Housing 11 or horn 12 are provided with the indicator lamp (not shown).In concrete the application, can offer the light inlet window (not shown) in the lower end of horn 12, light inlet window place captive joint is useful on the transmission element 13 of capping light inlet window, and indicator lamp is arranged at the light inlet window place, and indicator lamp can be LED, and its brightness height, power consumption are little, and the life-span is long.Made things convenient for the flight at night of this aircraft.
Hold the position and be arranged on housing 11 outside faces or housing 11 inside.In concrete the application, holding the position can be formed by the structure of being located at housing 11 outside faces, the lid (among the figure mark) that has been rotatably connected on the housing 11, lid can be connected in housing 11 by buckle structure so that the user will hold that battery in the position takes out charging or with arranging batteries in holding plane.Certainly hold the position and also can be formed by the structure of being located at housing 11 inwalls, housing 11 is provided with switch door (not shown), and the user need open switch dismantled and assembled battery behind the door.
Housing 11 comprises upper shell and the lower house of involutory setting up and down, horn 12 comprises last horn housing and the following horn housing of involutory setting up and down, last horn housing and upper shell are one-body molded or be fixedly connected on upper shell, and following horn housing and lower house are one-body molded or be fixedly connected on lower house.In concrete the application, between upper shell and the lower house, go up between horn housing and the following horn housing and can captive joint by locking piece, locking piece can be screw or buckle etc.So that the maintenance of aircraft, when needs are safeguarded, only need with upper shell and go up the horn housing from lower house and down the horn housing remove, just can intuitively all devices in the housing 11 be observed and safeguard.In concrete the application, upper shell and lower house are also can be respectively assembled by two or polylith housing parts 11, and the inboard of upper shell and lower house can convex with reinforced rib, with its structural strength of further raising.
As shown in figures 1 and 3, the lower end of housing 11 is connected with foot rest 4, and foot rest 4 can be fixedly connected on the lower end of lower house by fastener, and fastener can be screw etc.Foot rest 4 can be used for support housing 11, carries The Cloud Terrace 5, pick up camera 6 etc.Certainly, be appreciated that ground, also foot rest 4 can be set, utilize the lower end of lower house to be supported on the ground, also belong to protection domain of the present utility model.
As depicted in figs. 1 and 2, the main control module 33 on the circuit module 3, IMU(Inertial MeasuringUnit, Inertial Measurement Unit) can be arranged in the lower house.Electricity mode transfer piece 34 is electrically connected on rotor actuating device 22, and electric mode transfer piece 34 can be arranged in the hollow cavity of horn 12, so that electric mode transfer piece 34 is electrically connected on rotor actuating device 22.The control signal of electricity mode transfer piece 34 is provided by main control module 33, and electric mode transfer piece 34 and main control module 33 are electrically connected on battery.
Be set with radio receiver 31 in the housing 11, to receive remote signal.
Also be provided with on the radio receiver 31 to sign indicating number button 311 with to sign indicating number indicator lamp 312, so that the debugging aircraft is connected with remote controller.
Need to prove that the front end in the present embodiment, position term such as upper and lower are that conventional operation attitude with aircraft is reference, and do not will be understood that it is restrictive.
Below only be preferred embodiment of the present utility model, not in order to limiting the utility model, all any modifications of within spirit of the present utility model and principle, doing, be equal to and replace or improvement etc., all should be included within the protection domain of the present utility model.

Claims (10)

1. rotor unmanned vehicle more than a kind, it is characterized in that, this unmanned vehicle comprises hollow housing, be contained in circuit module, the horn that links to each other with described housing in the described housing, be arranged on described horn the engine installation that is used for driving aircraft flight, be arranged on described housing be used for hold power supply hold the position, for the connecting device that described power supply is electrically connected with described engine installation;
Described engine installation comprises rotor and rotor actuating device, and described rotor is fixedly connected on described rotor actuating device, and described rotor actuating device is connected in described horn, and described rotor is at least three.
2. many rotors unmanned vehicle according to claim 1 is characterized in that, described horn is one-body molded with described housing or captive joint, and described horn is at least three.
3. many rotors unmanned vehicle according to claim 1 is characterized in that, flexibly connects between described horn and the described housing, and described horn is at least three.
4. according to claim 2 or 3 described many rotors unmanned vehicles, it is characterized in that offer on the described horn for the installation position that described engine installation is installed, an end of described rotor actuating device is fixed in the installation position, the other end connects described rotor.
5. according to claim 2 or 3 described many rotors unmanned vehicles, it is characterized in that described horn is 4, described rotor is 4.
6. many rotors unmanned vehicle according to claim 4, it is characterized in that, described rotor actuating device is electrically connected with the electric mode transfer piece for the described rotor actuating device of control, and described electric mode transfer piece is arranged at the below of described rotor actuating device and is positioned at described horn.
7. many rotors unmanned vehicle according to claim 1 is characterized in that, described housing or described horn are provided with indicator lamp.
8. many rotors unmanned vehicle according to claim 1 is characterized in that, the described position that holds is arranged on described housing outer surface or described enclosure interior.
9. many rotors unmanned vehicle according to claim 1 is characterized in that, described housing comprises upper shell and the lower house of involutory setting up and down, and described horn comprises last horn housing and the following horn housing of involutory setting up and down; The described horn housing of going up is one-body molded with described upper shell or captive joint, and described horn housing down is one-body molded or captive joint with the described horn housing that descends.
10. as each described many rotors unmanned vehicle in the claim 1 to 3, it is characterized in that the lower end of described housing is connected with foot rest.
CN2012206043967U 2012-11-15 2012-11-15 Multi-rotor unmanned aerial vehicle Expired - Lifetime CN203047531U (en)

Priority Applications (24)

Application Number Priority Date Filing Date Title
CN2012206043967U CN203047531U (en) 2012-11-15 2012-11-15 Multi-rotor unmanned aerial vehicle
PCT/CN2013/087053 WO2014075609A1 (en) 2012-11-15 2013-11-13 A multi-rotor unmanned aerial vehicle
EP13795150.5A EP2763896B1 (en) 2012-11-15 2013-11-13 A multi-rotor unmanned aerial vehicle
DE202013012543.8U DE202013012543U1 (en) 2012-11-15 2013-11-13 Unmanned aerial vehicle with multiple rotors
DE202013012541.1U DE202013012541U1 (en) 2012-11-15 2013-11-13 Unmanned aerial vehicle with multiple rotors
DE202013012545.4U DE202013012545U1 (en) 2012-11-15 2013-11-13 Unmanned aerial vehicle with multiple rotors
JP2015542149A JP2016505435A (en) 2012-11-15 2013-11-13 Multi-rotor unmanned aerial vehicle
DE202013012547.0U DE202013012547U1 (en) 2012-11-15 2013-11-13 Unmanned aerial vehicle with multiple rotors
DE202013012544.6U DE202013012544U1 (en) 2012-11-15 2013-11-13 Unmanned aerial vehicle with multiple rotors
DE202013012546.2U DE202013012546U1 (en) 2012-11-15 2013-11-13 Unmanned aerial vehicle with multiple rotors
US14/092,653 US9016617B2 (en) 2012-11-15 2013-11-27 Unmanned aerial vehicle and operations thereof
US14/515,357 US9221536B2 (en) 2012-11-15 2014-10-15 Unmanned aerial vehicle and operations thereof
US14/534,127 US9221537B2 (en) 2012-11-15 2014-11-05 Unmanned aerial vehicle and operations thereof
US14/836,344 US9233754B1 (en) 2012-11-15 2015-08-26 Unmanned aerial vehicle and operations thereof
US14/947,923 US9321530B2 (en) 2012-11-15 2015-11-20 Unmanned aerial vehicle and operations thereof
US14/954,427 US9284049B1 (en) 2012-11-15 2015-11-30 Unmanned aerial vehicle and operations thereof
US15/012,006 US9394048B2 (en) 2012-11-15 2016-02-01 Unmanned aerial vehicle and operations thereof
US15/175,473 US10155584B2 (en) 2012-11-15 2016-06-07 Unmanned aerial vehicle and operations thereof
US15/947,650 US10189562B2 (en) 2012-11-15 2018-04-06 Unmanned aerial vehicle and operations thereof
US16/005,309 US10196137B2 (en) 2012-11-15 2018-06-11 Unmanned aerial vehicle and operations thereof
US16/027,178 US10272994B2 (en) 2012-11-15 2018-07-03 Unmanned aerial vehicle and operations thereof
US16/353,999 US10472056B2 (en) 2012-11-15 2019-03-14 Unmanned aerial vehicle and operations thereof
US16/679,984 US11338912B2 (en) 2012-11-15 2019-11-11 Unmanned aerial vehicle and operations thereof
US17/664,629 US20220281592A1 (en) 2012-11-15 2022-05-23 Unmanned aerial vehicle and operations thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN2012206043967U CN203047531U (en) 2012-11-15 2012-11-15 Multi-rotor unmanned aerial vehicle

Publications (1)

Publication Number Publication Date
CN203047531U true CN203047531U (en) 2013-07-10

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ID=48730514

Family Applications (1)

Application Number Title Priority Date Filing Date
CN2012206043967U Expired - Lifetime CN203047531U (en) 2012-11-15 2012-11-15 Multi-rotor unmanned aerial vehicle

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WO2017147764A1 (en) * 2016-02-29 2017-09-08 深圳市大疆创新科技有限公司 Power supply component, unmanned aerial vehicle and remotely controlled moving device
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CN107697308A (en) * 2017-11-08 2018-02-16 沈阳旋飞航空技术有限公司 A kind of drive mechanism of the dynamic unmanned plane of oil
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CN108602558A (en) * 2015-12-21 2018-09-28 空客直升机德国有限公司 Multi-rotor aerocraft
CN108715226A (en) * 2018-08-07 2018-10-30 濉溪淮匠机械设备有限责任公司 A kind of more rotor plant protection drones
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CN108974345A (en) * 2013-11-13 2018-12-11 深圳市大疆创新科技有限公司 More rotor unmanned aircrafts
CN109625256A (en) * 2018-11-18 2019-04-16 南京信息工程大学 A kind of surprise rotor wing unmanned aerial vehicle
WO2019140640A1 (en) * 2018-01-19 2019-07-25 深圳市大疆创新科技有限公司 Arm assembly and unmanned aerial vehicle
US10507914B2 (en) 2013-03-15 2019-12-17 Flir Detection, Inc. Spooler for unmanned aerial vehicle system
US11141673B1 (en) 2016-09-28 2021-10-12 Traxxas Lp Model rotorcraft with light pipe support members

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Date Code Title Description
C14 Grant of patent or utility model
GR01 Patent grant
CX01 Expiry of patent term

Granted publication date: 20130710

CX01 Expiry of patent term
IP01 Partial invalidation of patent right

Commission number: 5W112913

Conclusion of examination: On the basis of claims 1-8 of the invalidation request No. 27407, which has been examined and decided to remain valid, claims 1-4 of the utility model patent No. 201220604396.7 and claims 7 with the additional technical feature of "the accommodation position is set inside the housing" are declared invalid. The present patent shall remain valid on the basis of claim 5, claim 6, claim 7 with the additional technical feature of "the accommodation is set on the outer surface of the shell", and claim 8

Decision date of declaring invalidation: 20180205

Decision number of declaring invalidation: 34860

Denomination of utility model: Multi-rotor unmanned aerial vehicle

Granted publication date: 20130710

Patentee: SZ DJI TECHNOLOGY Co.,Ltd.

IP01 Partial invalidation of patent right