CN208181404U - Landing gear structure and unmanned plane - Google Patents

Landing gear structure and unmanned plane Download PDF

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Publication number
CN208181404U
CN208181404U CN201820604746.7U CN201820604746U CN208181404U CN 208181404 U CN208181404 U CN 208181404U CN 201820604746 U CN201820604746 U CN 201820604746U CN 208181404 U CN208181404 U CN 208181404U
Authority
CN
China
Prior art keywords
landing gear
mounting portion
gear structure
undercarriage
plug division
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.)
Active
Application number
CN201820604746.7U
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Chinese (zh)
Inventor
王坤殿
于建方
张圣鑫
陈旭东
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
SZ DJI 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.)
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Publication date
Application filed by Shenzhen Dajiang Innovations Technology Co Ltd filed Critical Shenzhen Dajiang Innovations Technology Co Ltd
Priority to CN201820604746.7U priority Critical patent/CN208181404U/en
Priority to PCT/CN2018/106178 priority patent/WO2019205460A1/en
Priority to CN201880016623.4A priority patent/CN110896627A/en
Application granted granted Critical
Publication of CN208181404U publication Critical patent/CN208181404U/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C25/00Alighting gear
    • B64C25/02Undercarriages
    • B64C25/04Arrangement or disposition on aircraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C25/00Alighting gear
    • B64C25/02Undercarriages
    • B64C25/08Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/02Unmanned aerial vehicles; Equipment therefor characterized by type of aircraft
    • B64C2201/021Airplanes, i.e. having wings and tail planes

Abstract

A kind of landing gear structure and unmanned plane.Landing gear structure (100) includes undercarriage (10) and Quick-dismantle component (20);Undercarriage (10) includes main part (14) and the plug division (11) for being set to main part (14), Quick-dismantle component (20) includes the first mounting portion (21) for connecting with outer body structure and the second mounting portion (22) connecting with the first mounting portion (21), and the second mounting portion (22) is equipped with the slot (23) and fixing piece (24) matched with plug division (11);Plug division (11) is inserted in slot (23), and fixed by fixing piece (24) and the second mounting portion (22).Undercarriage is plugged in the slot of Quick-dismantle component by plug division, is connect by fixing piece with Quick-dismantle component, is connect by the first mounting portion of Quick-dismantle component with outer body structure, and then undercarriage is installed in outer body structure.Simple structure, high reliability, and be easy to dismount.

Description

Landing gear structure and unmanned plane
Technical field
The utility model relates to air vehicle technique field, in particular to a kind of landing gear structure and unmanned plane.
Background technique
Undercarriage is as the important mechanism on unmanned machine equipment, it is necessary to which the design with unmanned plane entirety is adapted, simultaneously Also to meet safe and reliable requirement.
And at present the undercarriage of common unmanned plane usually have there are two problem, first is that structure is sturdy and durable, second is that structure Lightweight.Some undercarriages strengthen structure but also increase weight, and some undercarriages alleviate weight but also weaken Structure, often attends to one thing and lose sight of another.The complexity that existing quick-disassembly structure is often done, further increase that weight also makes mechanism can It is reduced by property.Or the undercarriage having brings inconvenience to packaging transhipment at all without quick-disassembly structure.
Utility model content
It is reliable and can be with the landing gear structure and unmanned plane of fast assembling-disassembling that the utility model provides a kind of structure.
According to the utility model embodiment in a first aspect, providing a kind of landing gear structure, comprising: undercarriage and Quick Release group Part;
The undercarriage includes main part and set on the plug division of the main part, the Quick-dismantle component include for it is outer First mounting portion of portion's main structure connection and the second mounting portion connecting with first mounting portion, second mounting portion are set There is the slot and fixing piece matched with the plug division;
The plug division is inserted in the slot, and is fixed by the fixing piece and second mounting portion.
Further, first mounting portion includes the socket part for being socketed on the outer body structure, the socket part Lateral wall be connected with second mounting portion.
Further, second mounting portion includes two limiting sections and the connection between described two limiting sections Portion;The limiting section is installed with the fixing piece, and the interconnecting piece offers the slot.
Further, described two limiting sections and the interconnecting piece interval are arranged.
Further, the spacing distance between described two limiting sections is equal to the width of the plug division.
Further, the side wall of described two limiting sections offers connecting hole, the connection of described two limiting sections Hole is coaxial arrangement, and is equipped with the fixing piece in two connecting holes.
Further, the fixing piece is bulb plunger.
Further, the plug division is symmetrically arranged with arc-shaped recess portion close to the both side ends of described two limiting sections, Cooperate with the fixing piece.
Further, the side of the interconnecting piece is equipped with the reinforcement wing plate connecting with first mounting portion.
Further, the undercarriage is sweepback undercarriage.
Further, the main part offers multiple hollow-out parts along its length.
According to the second aspect of the utility model embodiment, a kind of unmanned plane is provided, including fuselage, be set to the fuselage Horn and any of the above-described embodiment landing gear structure, the first mounting portion of the Quick-dismantle component of the landing gear structure with The horn connection.
The landing gear structure of the utility model, undercarriage by plug division be plugged in Quick-dismantle component the second mounting portion insert It in slot, is fixedly connected by fixing piece with the second mounting portion, to be connect with Quick-dismantle component, then the first peace for passing through Quick-dismantle component Dress portion is connect with outer body structure, and then undercarriage is installed in outer body structure.Simple structure, high reliability, and It is easy to dismount.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of landing gear structure shown in the utility model embodiment.
Fig. 2 is a kind of decomposition diagram of landing gear structure shown in the utility model embodiment.
Fig. 3 is a kind of perspective exploded view of landing gear structure shown in the utility model embodiment.
Fig. 4 is a kind of stereoscopic schematic diagram of unmanned plane shown in the utility model embodiment.
Fig. 5 is a kind of side view of unmanned plane shown in the utility model embodiment.
Fig. 6 is a kind of front view of unmanned plane shown in the utility model embodiment.
Fig. 7 is a kind of hatchcover of unmanned plane shown in the utility model embodiment and the enlarged diagram of fuselage.
Specific embodiment
Example embodiments are described in detail here, and the example is illustrated in the accompanying drawings.Following description is related to When attached drawing, unless otherwise indicated, the same numbers in different drawings indicate the same or similar elements.Following exemplary embodiment Described in embodiment do not represent all embodiments consistent with the utility model.On the contrary, they be only with such as The example of the consistent device and method of some aspects be described in detail in the appended claims, the utility model.
It is only to be not intended to be limiting this reality merely for for the purpose of describing particular embodiments in the term that the utility model uses With novel.In the "an" of the utility model and singular used in the attached claims, " described " and "the" Most forms are intended to include, unless the context clearly indicates other meaning.It is also understood that term used herein " and/ Or " refer to and include that one or more associated any or all of project listed may combine.
It should be appreciated that " first " " second " and similar word used in present specification and claims It is not offered as any sequence, quantity or importance, and is used only to distinguish different component parts.Equally, "one" or The similar word such as " one " does not indicate that quantity limits yet, but indicates that there are at least one.Unless otherwise noted, " front ", " after The similar word such as portion ", " lower part " and/or " top " is not limited to a position or a kind of sky only to facilitate explanation Between orient.The similar word such as " comprising " or "comprising" means to appear in element or object before " comprising " or "comprising" Cover the element for appearing in " comprising " or "comprising" presented hereinafter or object and its equivalent, it is not excluded that other elements or Object." connection " either the similar word such as " connected " is not limited to physics or mechanical connection, and may include Electrical connection, it is either direct or indirect.
It is reliable and can be with the landing gear structure and unmanned plane of fast assembling-disassembling that the utility model provides a kind of structure.It ties below Attached drawing is closed, the landing gear structure and unmanned plane of the utility model are described in detail.In the absence of conflict, following reality The feature applied in example and embodiment can be combined with each other.
Referring to shown in Fig. 1 to Fig. 3, the utility model embodiment provides a kind of landing gear structure 100, for being mounted on outside Main structure, in the present embodiment, outer body structure can be the horn of unmanned plane.The landing gear structure 100 includes: to rise and fall Frame 10 and Quick-dismantle component 20, undercarriage 10 and Quick-dismantle component 20 are detachably connected.
Wherein, the undercarriage 10 is including main part 14 and set on the plug division 11 of the main part 14, the Quick Release group Part 20 includes the first mounting portion 21 for connecting with outer body structure and the second peace connecting with first mounting portion 21 Dress portion 22, second mounting portion 22 are equipped with the slot 23 and fixing piece 24 matched with the plug division 11.The undercarriage 10 plug division 11 is inserted in the slot 23 of the second mounting portion 22 of the Quick-dismantle component 20, and by the fixing piece 24 with Second mounting portion 22 is fixed.
As seen from the above-described embodiment, the landing gear structure 100 of the utility model, undercarriage 10 are plugged in by plug division 11 In the slot 23 of second mounting portion 22 of Quick-dismantle component 20, then passes through fixing piece 24 and be fixedly connected with the second mounting portion 22, thus It connect with Quick-dismantle component 20, is then connect by the first mounting portion 21 of Quick-dismantle component 20 with outer body structure, and then will rise Frame 10 is fallen to be installed in outer body structure.When undercarriage 10 needs to disassemble, as long as by the plug division 11 of undercarriage 10 from Quick Release It is extracted in the slot 23 of second mounting portion 22 of component 20, completes the decomposition of undercarriage 10 and outer body structure.Structure is simple High reliablity, and be easy to dismount.
In an optional embodiment, the first mounting portion 21 of the Quick-dismantle component 20 includes being socketed on the external master The socket part 212 of body structure, the lateral wall of the socket part 212 are connected with second mounting portion 22.In the present embodiment, One mounting portion 21 is sleeve member, and the side wall of socket part 212 opens up the portion of having the gap 213, and socket part 212 can be made to have certain stretch Contracting surplus is more convenient for being socketed in outer body structure.
In the present embodiment, outer body structure is the horn of unmanned plane, offers multiple hole locations, the set on the horn The mounting hole 214 (in figure by taking two mounting holes 214 as an example) matched with the hole location can also be arranged in the lateral wall of socket part 212, After socket part 212 is set on horn, socket part 212 is adjusted and arrives suitable position, (such as the spiral shell of fastener 215 can be passed through Nail) it is threaded through in corresponding hole location and mounting hole 214, realize that socket part 212 is fixed to each other with outer body structure, and then will be fast The first mounting portion 21 for tearing component 20 open is mounted in outer body structure, and is also convenient for through such a connection manner by Quick Release Component 20 is dismantled with outer body structure.Certainly, the first mounting portion 21 of Quick-dismantle component 20 can also be connected by other Mode (may be a fixed connection, may be a detachable connection) is attached with outer body structure, and the utility model is to this With no restriction.
In an optional embodiment, the second mounting portion 22 of the Quick-dismantle component 20 includes two limiting sections 25 and position Interconnecting piece 26 between described two limiting sections 25.The limiting section 25 is installed with the fixing piece 24, the interconnecting piece 26 Offer the slot 23.In the present embodiment, described two limiting sections 25 are arranged with the interconnecting piece 26 interval, insert in processing Fillet can be formed in the bottom of slot 23 when slot 23, plug division 11 can be interfered to be plugged into slot 23, institute can be passed through in technique State the interval mill off fillet between two limiting sections 25 and the interconnecting piece 26, be plugged into slot 23 conducive to plug division 11 and with Slot 23 is fitted close, while convenient for the position of plug division 11 from gap location between limiting section 25 and interconnecting piece 26, with Just plug division 11 is inserted into slot 23.And the spacing distance between described two limiting sections 25 is equal to the plug division 11 Width can play the role of guiding to plug division 11, be more convenient for for being inserted into slot 23 plug division 11.Certainly, in other examples In son, two limiting sections 25 and the interconnecting piece 26 can also be integrally formed setting.In addition, main part 14 and the institute of undercarriage 10 The width for stating the position that plug division 11 is closed on is greater than the width of plug division 11, when plug division 11 is inserted into the slot 23 of interconnecting piece 26 After grafting in place, main part 14 can be abutted against with limiting section 25, keep the installation of undercarriage 10 more secured.
In an optional embodiment, the side wall of described two limiting sections 25 offers connecting hole 251, described two The connecting hole 251 of limiting section 25 is coaxial arrangement, and is equipped with the fixing piece 24 in two connecting holes 251. In the present embodiment, the fixing piece 24 is bulb plunger, two side ends of the plug division 11 close to described two limiting sections 25 Portion is symmetrically arranged with the arc-shaped recess portion 12 cooperated with the fixing piece 24 using bulb plunger.Further, in order to enhance second The structural strength of mounting portion 22, the side of the interconnecting piece 26 are equipped with the reinforcement wing plate 27 connecting with first mounting portion 21.
Under normal conditions, the ball head of the bulb plunger is the side wall that part protrudes from limiting section 25, when undercarriage 10 Plug division 11 when being inserted into the slot 23 of interconnecting piece 26, the ball head of the first squeeze bulb plunger in plug division 11 is by the ball head Be pressed onto the connecting hole 251 of 25 side wall of limiting section, when the arc-shaped recess portion 12 of plug division 11 be moved to it is corresponding with the connecting hole 251 Position when, the ball head of bulb plunger gradually pops up the connecting hole 251 until engaging completely with arc-shaped recess portion 12 so that insert The two sides of socket part 11 engage with corresponding fixing piece 24, and then realize the second mounting portion of undercarriage 10 and Quick-dismantle component 20 21 are fixed to each other.When needing to dismantle undercarriage 10, as long as plug division 11 to be extracted to the slot 23 of interconnecting piece 26, thus real The fast assembling-disassembling of undercarriage 10 Yu Quick-dismantle component 20 is showed.
In an optional embodiment, in order to guarantee the structural strength and lightweight requirements of undercarriage 10, institute simultaneously Undercarriage 10 is stated using the carbon fibre material of 4mm thickness, ensure that the structural strength of undercarriage 10.Whole undercarriage 10 is in sweepback Shape full of innervation and has good aeroperformance.The main part 14 of undercarriage 10 offers multiple hollow outs along its length Portion 13, it is ensured that light-weighted requirement.Each component of Quick-dismantle component 20 can use aluminum alloy materials, can equally guarantee to tie Structure intensity and light-weighted requirement.
Referring to fig. 4 and shown in Fig. 5, the utility model embodiment also provides a kind of unmanned plane 200, can be fixed-wing nobody The model plane equipment such as machine, multi-rotor unmanned aerial vehicle, VTOL fixed-wing unmanned plane, mixing wing unmanned plane.Example shown in the figure In, unmanned plane 200 is VTOL fixed-wing unmanned plane, and unmanned plane 200 includes fuselage 91, the horn for being set to the fuselage 91 92, fixed-wing 93 and it is installed in the landing gear structure 100 of horn 92.Optionally, the tail portion of fuselage 91 is additionally provided with propeller 94 As the power device of fixed-wing 93, fixed-wing 93 is removably mounted on fuselage 91.It should be noted that above-described embodiment With the description as described in the landing gear structure 10 in embodiment, it is equally applicable to the unmanned plane 200 of the utility model.Described The first mounting portion 21 for falling the Quick-dismantle component 20 of frame structure 100 is connect with the horn 92.
The undercarriage 10 of the unmanned plane 200 of the utility model, landing gear structure 100 is plugged in Quick Release group by plug division 11 In the slot 23 of second mounting portion 22 of part 20, then pass through fixing piece 24 and be fixedly connected with the second mounting portion 22, thus and Quick Release Component 20 connects, and is then connect by the first mounting portion 21 of Quick-dismantle component 20 with the horn 92 of unmanned plane 200, and then will rise and fall Frame 10 is installed on horn 92.When undercarriage 10 needs to disassemble, as long as by the plug division 11 of undercarriage 10 from Quick-dismantle component 20 It is extracted in the slot 23 of second mounting portion 22, completes the decomposition of undercarriage 10 and horn 92.Simple structure, high reliability, and easily In dismounting.
In conjunction with described in fig. 4 to fig. 6, in an optional embodiment, the quantity of the horn 92 is two, is symmetrical arranged In being all provided on the two sides of fuselage 91, each horn 92 there are two landing gear structure 100, two landing gear structures 100 are one in front and one in back Ground is arranged on corresponding horn 92, also, the landing gear structure 100 being arranged on two horns 92 is with respect to the axial direction of fuselage 91 It is inclined outwardly setting, it is whole to be arranged in outer "eight" shape, complete machine can be added significantly to when unmanned plane 200 is put it on the ground Stability.
Referring to described in Fig. 7, in an optional embodiment, the top of the fuselage 91, which is equipped with, is used for accommodating electric element Accommodating chamber, the opening of the accommodating chamber 20 is removably covered with hatchcover 95, and the inner wall of hatchcover 95 is equipped with liner plate 96, liner plate 96 Part protrudes from hatchcover 95.Hatchcover 95 covers the accommodating chamber after being attached to fuselage 91, electronic component can be enclosed in machine The inside of body 91.Electronic component may include the elements such as battery, GPS module, 4G module, satellite modules, main control module.It is optional Ground, can be detachably connected using hasp structures such as snap fasteners between hatchcover 95 and fuselage 91.
The liner plate 96 that hatchcover 95 is protruded from by the inner wall setting unit in hatchcover 95, can increase hatchcover 95 and fuselage 91 Between connection area.After hatchcover 95 is connect with fuselage 91, the part that liner plate 96 protrudes from hatchcover 95 can be filled in hatchcover Gap location between 95 and fuselage 91 forms backstop, and then guarantees between hatchcover 95 and fuselage 91 after mounting without offset, to keep away Exempt from hatchcover 91 and is detached from fuselage 91 in 200 flight course of unmanned plane.
The above is only the preferred embodiment of the utility model, not does in any form to the utility model Limitation, although the utility model has been disclosed with preferred embodiment as above, is not intended to limit the utility model, any to be familiar with Professional and technical personnel, in the range of not departing from technical solutions of the utility model, when in the technology using the disclosure above Hold the equivalent embodiment for being modified or being modified to equivalent variations, but all without departing from technical solutions of the utility model Hold, any simple modification, equivalent change and modification made by the above technical examples according to the technical essence of the present invention, still It is within the scope of the technical solutions of the present invention.
This patent document disclosure includes material protected by copyright.The copyright is all for copyright holder.Copyright Owner does not oppose the patent document in the presence of anyone replicates the proce's-verbal of Patent&Trademark Office and archives or should Patent discloses.

Claims (12)

1. a kind of landing gear structure characterized by comprising undercarriage and Quick-dismantle component;
The undercarriage includes main part and set on the plug division of the main part, the Quick-dismantle component include for outside master First mounting portion of body structure connection and the second mounting portion for connect with first mounting portion, second mounting portion equipped with The slot and fixing piece that the plug division matches;
The plug division is inserted in the slot, and is fixed by the fixing piece and second mounting portion.
2. landing gear structure according to claim 1, which is characterized in that first mounting portion includes being socketed on outside described The socket part of portion's main structure, the lateral wall of the socket part are connected with second mounting portion.
3. landing gear structure according to claim 1, which is characterized in that second mounting portion include two limiting sections and Interconnecting piece between described two limiting sections;The limiting section is installed with the fixing piece, and the interconnecting piece opens up State slot.
4. landing gear structure according to claim 3, which is characterized in that described two limiting sections and the interconnecting piece interval Setting.
5. landing gear structure according to claim 3, which is characterized in that the spacing distance etc. between described two limiting sections Width in the plug division.
6. landing gear structure according to claim 3, which is characterized in that the side wall of the described two limiting sections company of offering Hole is connect, the connecting hole of described two limiting sections is coaxial arrangement, and is equipped with the fixation in two connecting holes Part.
7. landing gear structure according to claim 3, which is characterized in that the fixing piece is bulb plunger.
8. landing gear structure according to claim 7, which is characterized in that the plug division is close to described two limiting sections Both side ends are symmetrically arranged with arc-shaped recess portion, cooperate with the fixing piece.
9. landing gear structure according to claim 3, which is characterized in that the side of the interconnecting piece is equipped with and described first The reinforcement wing plate of mounting portion connection.
10. landing gear structure according to claim 1, which is characterized in that the undercarriage is sweepback undercarriage.
11. landing gear structure according to claim 1, which is characterized in that the main part offers along its length Multiple hollow-out parts.
12. a kind of unmanned plane, which is characterized in that including fuselage, be set to the horn and according to claim 1 of the fuselage Landing gear structure described in any one of~11, the first mounting portion and the horn of the Quick-dismantle component of the landing gear structure connect It connects.
CN201820604746.7U 2018-04-24 2018-04-24 Landing gear structure and unmanned plane Active CN208181404U (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
CN201820604746.7U CN208181404U (en) 2018-04-24 2018-04-24 Landing gear structure and unmanned plane
PCT/CN2018/106178 WO2019205460A1 (en) 2018-04-24 2018-09-18 Landing gear structure and unmanned aerial vehicle
CN201880016623.4A CN110896627A (en) 2018-04-24 2018-09-18 Undercarriage structure and unmanned aerial vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201820604746.7U CN208181404U (en) 2018-04-24 2018-04-24 Landing gear structure and unmanned plane

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Publication Number Publication Date
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CN201880016623.4A Pending CN110896627A (en) 2018-04-24 2018-09-18 Undercarriage structure and unmanned aerial vehicle

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109795677A (en) * 2019-03-22 2019-05-24 西北工业大学 A kind of unmanned plane fast assembling-disassembling landing gear structure
CN110896627A (en) * 2018-04-24 2020-03-20 深圳市大疆创新科技有限公司 Undercarriage structure and unmanned aerial vehicle

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0921960D0 (en) * 2009-12-16 2010-02-03 Airbus Operations Ltd Landing gear with noise reduction apparatus
CN205096426U (en) * 2015-09-28 2016-03-23 东莞市真泽电子有限公司 Disjunctor formula double stretching cup
CN105691599B (en) * 2016-01-20 2018-10-16 广东司马航模实业有限公司 A kind of undercarriage disassembly and assembly structure of aircraft
CN205770127U (en) * 2016-06-15 2016-12-07 比亚迪股份有限公司 Landing gear assembly and unmanned plane
CN205872445U (en) * 2016-08-10 2017-01-11 北方天途航空技术发展(北京)有限公司 Unmanned aerial vehicle foot rest and unmanned aerial vehicle
CN107792352A (en) * 2016-08-29 2018-03-13 天津中翔腾航科技股份有限公司 A kind of six rotor wing unmanned aerial vehicles
CN206243458U (en) * 2016-12-07 2017-06-13 天津航天中为数据系统科技有限公司 A kind of new multi-rotor unmanned aerial vehicle linkage undercarriage
CN106628125A (en) * 2016-12-28 2017-05-10 中国航天电子技术研究院 Quick-disassembling energy absorption undercarriage for multi-rotor unmanned aerial vehicle
CN206926808U (en) * 2017-06-23 2018-01-26 歌尔科技有限公司 Unmanned plane undercarriage
CN107647540A (en) * 2017-09-18 2018-02-02 东莞市联洲知识产权运营管理有限公司 A kind of Intelligent bracelet of easy installation and removal
CN208181404U (en) * 2018-04-24 2018-12-04 深圳市大疆创新科技有限公司 Landing gear structure and unmanned plane

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110896627A (en) * 2018-04-24 2020-03-20 深圳市大疆创新科技有限公司 Undercarriage structure and unmanned aerial vehicle
CN109795677A (en) * 2019-03-22 2019-05-24 西北工业大学 A kind of unmanned plane fast assembling-disassembling landing gear structure

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WO2019205460A1 (en) 2019-10-31

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