CN205311895U - Unmanned aerial vehicle undercarriage receive and releases structure and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle undercarriage receive and releases structure and unmanned aerial vehicle Download PDFInfo
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- CN205311895U CN205311895U CN201521100131.3U CN201521100131U CN205311895U CN 205311895 U CN205311895 U CN 205311895U CN 201521100131 U CN201521100131 U CN 201521100131U CN 205311895 U CN205311895 U CN 205311895U
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Abstract
The utility model provides an unmanned aerial vehicle undercarriage receive and releases structure and unmanned aerial vehicle, this unmanned aerial vehicle include undercarriage and fuselage, and the undercarriage receive and releases the structure and includes: motor and transmission are connected between motor and undercarriage, are driven the drive mechanism that the rotatory realization undercarriage of undercarriage receive and release by motor drive. The utility model discloses simple structure to receiving and releasing freely of undercarriage can be realized, through to the unmanned aerial vehicle structural adjustment, the requirement of placing that receives under space limitation condition undercarriage has been satisfied.
Description
Technical field
The utility model relates to unmanned air vehicle technique field, particularly relates to a kind of without man-machine landing gear folding structure and without man-machine.
Background technology
At present, unmanned flight's device (is also named without man-machine, hereinafter referred to as without man-machine) fuselage and landing gear (landing gear) assembly structure in, landing gear adopts stretching structure usually, to realize the opening and closing of landing gear, after landing gear is opened, owing to being subject to space constraint, sometimes need to pack up landing gear, but, the existing frame connecting structure that rises and falls then cannot realize the folding and unfolding freely of landing gear, or assembly structure is complicated.
Practical novel content
Main purpose of the present utility model be to provide a kind of structure simple, can freely folding and unfolding landing gear without man-machine landing gear folding structure and without man-machine.
For achieving the above object, the utility model proposes a kind of without man-machine landing gear folding structure, described comprising landing gear and fuselage without man-machine, described landing gear folding structure comprises: motor and be in transmission connection between described motor and landing gear, drive by motor to drive landing gear to rotate the transmission rig realizing landing gear folding and unfolding.
Preferably, described transmission rig comprises: housing, shaft machine, screw mandrel, nut and web member, and wherein, described housing is fixedly connected with described fuselage, and one end of described screw mandrel is in transmission connection by shaft machine and described motor, drives by motor and rotates; Described nut is nested on described screw mandrel and is in transmission connection with wire rod thread, when screw mandrel rotates, nut with screw mandrel be rotated on described screw mandrel slide; Described nut, in the direction of vertical described screw mandrel, extends to two ends and is provided with support bar; One end of described web member is fixedly connected with one end of described landing gear, and the other end of described web member is set on the support bar at described nut two ends, and the both sides of described web member are provided with rotating shaft, and described web member is rotationally connected by the rotating shaft of both sides and described housing.
Preferably, the first connection section that described web member comprises sheet and the 2nd connection section of card channel-shaped being connected with the end of described first connection section, described first connection section and the 2nd connection section shape have angle; Described first connection section is fixedly connected with one end of described landing gear, and described 2nd connection section is fastened on the support bar at described nut two ends; Described rotating shaft is arranged on described first connection section and the two side ends of the 2nd connection section junction.
Preferably, described 2nd connection section comprises the U shape card groove of two parallel settings, described two U shape card grooves are separately positioned on the dual-side of the described end of described first connection section, two U shape slots are in the same side of the first connection section, and the opening direction place plane of described two U shape card grooves and described first connection section form described angle.
Preferably, the both sides of described housing are respectively equipped with the guide rail parallel with described screw mandrel, and the support bar at described nut two ends is shelved on guide rail described in two respectively.
Preferably, described shaft machine respectively rotating shaft and screw mandrel one end with described motor be fixedly connected with.
Preferably, described motor rotating shaft and screw mandrel are coaxially arranged or parallel setting.
Preferably, described motor rotating shaft is vertical with described screw mandrel is arranged.
In addition, the utility model also proposes a kind of without man-machine, comprising landing gear and fuselage, also comprise: for connecting described landing gear and fuselage and realize the landing gear folding structure of folding and unfolding landing gear, described landing gear folding structure is as above without man-machine landing gear folding structure.
The one that the utility model proposes is without man-machine landing gear folding structure and without man-machine, this landing gear folding structure comprises: motor and be in transmission connection between motor and landing gear, rotate, by the dynamic landing gear of motor driven belts, the transmission rig realizing landing gear folding and unfolding, its structure is simple, and the folding and unfolding freely of landing gear can be realized, thus by without man-machine structural adjustment, meeting the placement requirement by landing gear when space constraint.
Accompanying drawing explanation
Fig. 1 is that the utility model embodiment is without man-machine sectional perspective structural representation;
Fig. 2 is that the utility model embodiment is without man-machine landing gear folding structure decomposing schematic representation;
Fig. 3 is web member perspective view in the utility model embodiment;
Fig. 4 is the horizontal collapsed state schematic diagram of landing gear in the utility model embodiment;
Fig. 5 is that in the utility model embodiment, view vertically opened by landing gear;
Fig. 6 be in Fig. 5 fore shell remove after view;
Fig. 7 is the structural representation of rear shell in the utility model embodiment;
Fig. 8 is the perspective view of the utility model embodiment transfer axial organ.
The realization of the utility model object, functional characteristics and advantage will in conjunction with the embodiments, are described further with reference to accompanying drawing.
Embodiment
It is to be understood that specific embodiment described herein is only in order to explain the utility model, and it is not used in restriction the utility model.
With reference to shown in Fig. 1, the one that the better embodiment of the utility model proposes is without man-machine, and this comprises landing gear 2 and fuselage 1 without man-machine, also comprises and with fuselage 1 and realize the landing gear folding structure 3 of folding and unfolding landing gear 2 for connecting described landing gear 2.
Specifically, shown in composition graphs 2, Fig. 3 and Fig. 4, described landing gear folding structure 3 comprises: motor 31 and the transmission rig being in transmission connection between described motor 31 and landing gear 2, driving by motor 31, and this transmission rig drives landing gear 2 to rotate and realizes landing gear 2 folding and unfolding.
Described transmission rig comprises: housing 32, the shaft machine 33 being placed in outside housing 32 and the screw mandrel 34 being placed in housing 32, nut 35 and web member 36, wherein, described housing 32 is fixedly connected with described fuselage 1, and this housing 32 comprises fore shell 322 and detains the rear shell 323 closed with fore shell 322.
Described screw mandrel 34 is shelved in described housing 32, and one end of described screw mandrel 34 is in transmission connection by shaft machine 33 and described motor 31, drives rotation by motor 31; Described nut 35 is nested on described screw mandrel 34 and is in transmission connection with screw mandrel 34 screw thread, when screw mandrel 34 rotates, nut 35 with screw mandrel 34 be rotated on described screw mandrel 34 slide.
Described nut 35, in the direction of vertical described screw mandrel 34, extends to two ends and is provided with support bar 351.
One end of described web member 36 is fixedly connected with one end of the landing gear 2 outside housing 32, the other end of described web member 36 is set on the support bar 351 at described nut 35 two ends, the both sides of described web member 36 are provided with rotating shaft 361, and described web member 36 is rotationally connected with described housing 32 by the rotating shaft 361 of both sides.
When motor 31 drive shaft device 33 drives screw mandrel 34 to rotate, nut 35 with screw mandrel 34 be rotated on screw mandrel 34 slide, the web member 36 being connected on nut 35 and be rotatably connected on housing 32 rotates taking rotating shaft 361 as axis, like this, the nut 35 of slip can drive web member 36 to swing at the vertical plane of down-feed screw 34.
Owing to landing gear 2 is fixedly connected with web member 36, thus, drive landing gear 2 to rotate at vertical plane, reach the object of folding and unfolding landing gear 2. As shown in Figure 4, landing gear 2 vertically opens state as shown in Figure 5, Figure 6 to landing gear 2 collapsed state.
More specifically, shown in composition graphs 3, the first connection section 362 that described web member 36 comprises sheet and the 2nd connection section 363 of card channel-shaped being connected with the end of described first connection section 362, described first connection section 362 and the 2nd connection section 363 shape have angle, preferably, this angle can be an obtuse angle; Described first connection section 362 is fixedly connected with one end of described landing gear 2, and described 2nd connection section 363 is fastened on the support bar 351 at described nut 35 two ends; Described rotating shaft 361 is arranged on described first connection section 362 and the two side ends of the 2nd connection section 363 junction.
Mode is implemented as one, described 2nd connection section 363 comprises the U shape card groove 3631 of two parallel settings, described two U shape card grooves 3631 are separately positioned on the dual-side of the described end of described first connection section 362, and two U shape card groove 3631 be positioned at the same side of the first connection section 362, opening direction place plane and described first connection section 362 of described two U shape card grooves 3631 form described angle.
Further, implement mode as one, shown in composition graphs 7, it is also possible to nut 35 is shelved on housing 32, the guide rail 323 parallel with described screw mandrel 34 is set respectively in the both sides of housing 32, that is, fore shell and rear shell arranges a chute respectively as guide rail 323.
The support bar 351 at nut 35 two ends is shelved on guide rail 323 described in two respectively. Thus, screw mandrel 34 rotarily drive nut 35 slide time, nut 35 can slidably reciprocate along the guide rail 323 on housing 32 so that is connected on nut 35 and the web member 36 that is rotatably connected on housing 32 is that axis rotates taking coupling shaft, drives landing gear 2 to rotate and realizes folding and unfolding.
In the present embodiment, described shaft machine 33 respectively rotating shaft and screw mandrel 34 one end with described motor 31 be fixedly connected with, and motor 31 rotating shaft, shaft machine 33 and screw mandrel 34 are coaxially arranged. Certainly in other embodiments, according to installing in the application the reserving space without man-machine landing gear folding structure, can motor 31 be placed on housing 32, like this, the rotating shaft of motor 31 setting parallel with screw mandrel 34, shaft machine now is different from the shaft machine 33 shown in accompanying drawing 8, and shaft machine now can comprise the first cylindrical gear intermeshing, that be fixedly connected with respectively and the 2nd cylindrical gear being fixedly connected with screw mandrel 34 one end with the rotating shaft of motor 31.
It should be noted that, in another embodiment, motor 31 can not be horizontal positioned, it can be vertical placement, now motor 31 rotating shaft is vertical with screw mandrel 34 to be arranged, and shaft machine now can comprise the first bevel gear intermeshing, that be fixedly connected with respectively and the three cylinders gear being fixedly connected with screw mandrel 34 one end with the rotating shaft of motor 31. Such that it is able to meet different spaces to place requirement.
In above-described embodiment, motor 31 rotating shaft can be connected by being screwed with shaft machine 33, it is also possible to is fastenedly connected by the gear teeth 331, as shown in Figure 8.Certainly, in other embodiments, it is also possible to adopt gear transmission structure to replace shaft machine 33, it is achieved motor 31 drives the transmission of power.
The present embodiment passes through such scheme, the landing gear folding structure 3 adopting motor 31 and transmission rig to form, can realize the folding and unfolding freely of landing gear 2, and its structure is simple, by to without man-machine structural adjustment, meeting the placement requirement by landing gear when space constraint 2.
Landing gear folding structure 3 described in above-described embodiment is the one of the present embodiment proposition without man-machine landing gear folding structure 3, does not repeat them here.
These are only preferred embodiment of the present utility model; not thereby patent scope of the present utility model is limited; every utilize the utility model specification sheets and accompanying drawing content to do equivalent structure or equivalence stream claim a journey conversion; or directly or indirectly it is used in other relevant technical fields, all it is included in scope of patent protection of the present utility model with reason.
Claims (9)
1. one kind without man-machine landing gear folding structure, described comprise landing gear and fuselage without man-machine, it is characterized in that, described landing gear folding structure comprises: motor and be in transmission connection between described motor and landing gear, drive by motor to drive landing gear to rotate the transmission rig realizing landing gear folding and unfolding.
2. according to claim 1 without man-machine landing gear folding structure, it is characterized in that, described transmission rig comprises: housing, shaft machine, screw mandrel, nut and web member, wherein, described housing is fixedly connected with described fuselage, one end of described screw mandrel is in transmission connection by shaft machine and described motor, drives by motor and rotates; Described nut is nested on described screw mandrel and is in transmission connection with wire rod thread, when screw mandrel rotates, nut with screw mandrel be rotated on described screw mandrel slide; Described nut, in the direction of vertical described screw mandrel, extends to two ends and is provided with support bar; One end of described web member is fixedly connected with one end of described landing gear, and the other end of described web member is set on the support bar at described nut two ends, and the both sides of described web member are provided with rotating shaft, and described web member is rotationally connected by the rotating shaft of both sides and described housing.
3. according to claim 2 without man-machine landing gear folding structure, it is characterized in that, the first connection section that described web member comprises sheet and the 2nd connection section of card channel-shaped being connected with the end of described first connection section, described first connection section and the 2nd connection section shape have angle; Described first connection section is fixedly connected with one end of described landing gear, and described 2nd connection section is fastened on the support bar at described nut two ends; Described rotating shaft is arranged on described first connection section and the two side ends of the 2nd connection section junction.
4. according to claim 3 without man-machine landing gear folding structure, it is characterized in that, described 2nd connection section comprises the U shape card groove of two parallel settings, described two U shape card grooves are separately positioned on the dual-side of the described end of described first connection section, two U shape slots are in the same side of the first connection section, and the opening direction place plane of described two U shape card grooves and described first connection section form described angle.
5. according to claim 2,3 or 4 without man-machine landing gear folding structure, it is characterised in that, the both sides of described housing are respectively equipped with the guide rail parallel with described screw mandrel, and the support bar at described nut two ends is shelved on guide rail described in two respectively.
6. according to claim 5 without man-machine landing gear folding structure, it is characterised in that, described shaft machine respectively rotating shaft and screw mandrel one end with described motor be fixedly connected with.
7. according to claim 6 without man-machine landing gear folding structure, it is characterised in that, described motor rotating shaft and screw mandrel are coaxially arranged or parallel setting.
8. according to claim 6 without man-machine landing gear folding structure, it is characterised in that, described motor rotating shaft is vertical with described screw mandrel to be arranged.
9. one kind without man-machine, comprise landing gear and fuselage, it is characterized in that, also comprise: for connecting described landing gear and fuselage and realize the landing gear folding structure of folding and unfolding landing gear, described landing gear folding structure be according to any one of claim 1-8 without man-machine landing gear folding structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521100131.3U CN205311895U (en) | 2015-12-24 | 2015-12-24 | Unmanned aerial vehicle undercarriage receive and releases structure and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521100131.3U CN205311895U (en) | 2015-12-24 | 2015-12-24 | Unmanned aerial vehicle undercarriage receive and releases structure and unmanned aerial vehicle |
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| CN205311895U true CN205311895U (en) | 2016-06-15 |
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| CN201521100131.3U Active CN205311895U (en) | 2015-12-24 | 2015-12-24 | Unmanned aerial vehicle undercarriage receive and releases structure and unmanned aerial vehicle |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106043664A (en) * | 2016-06-22 | 2016-10-26 | 宁波蓝飞鹂航空科技有限公司 | Novel folding deformable aircraft |
| WO2017219295A1 (en) * | 2016-06-22 | 2017-12-28 | SZ DJI Technology Co., Ltd. | Systems and methods of aircraft walking systems |
| CN107521675A (en) * | 2016-06-22 | 2017-12-29 | 北京臻迪机器人有限公司 | A kind of foot rest structure using turbine worm folding |
| CN107914891A (en) * | 2016-10-09 | 2018-04-17 | 比亚迪股份有限公司 | Unmanned plane |
| CN107985564A (en) * | 2017-12-28 | 2018-05-04 | 深圳市道通智能航空技术有限公司 | Undercarriage and the unmanned vehicle with the undercarriage |
| CN108284946A (en) * | 2017-01-09 | 2018-07-17 | 昊翔电能运动科技(昆山)有限公司 | Single steering engine drives the structure of undercarriage control and the unmanned plane using the structure |
| CN108713275A (en) * | 2017-02-24 | 2018-10-26 | 深圳市大疆创新科技有限公司 | RTK antenna installation stents and unmanned vehicle |
| CN109895999A (en) * | 2019-03-21 | 2019-06-18 | 北京航空航天大学 | A kind of undercarriage control device for lightweight aircraft |
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2015
- 2015-12-24 CN CN201521100131.3U patent/CN205311895U/en active Active
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043664B (en) * | 2016-06-22 | 2019-10-18 | 宁波创彩颜料有限公司 | A kind of novel folding morphing aircraft |
| WO2017219295A1 (en) * | 2016-06-22 | 2017-12-28 | SZ DJI Technology Co., Ltd. | Systems and methods of aircraft walking systems |
| CN107521675A (en) * | 2016-06-22 | 2017-12-29 | 北京臻迪机器人有限公司 | A kind of foot rest structure using turbine worm folding |
| CN106043664A (en) * | 2016-06-22 | 2016-10-26 | 宁波蓝飞鹂航空科技有限公司 | Novel folding deformable aircraft |
| CN107521675B (en) * | 2016-06-22 | 2022-03-25 | 北京臻迪机器人有限公司 | Foot rest structure opened and closed by turbine worm |
| US11124292B2 (en) | 2016-06-22 | 2021-09-21 | SZ DJI Technology Co., Ltd. | Systems and methods of aircraft walking systems |
| CN107914891A (en) * | 2016-10-09 | 2018-04-17 | 比亚迪股份有限公司 | Unmanned plane |
| CN107914891B (en) * | 2016-10-09 | 2020-03-31 | 比亚迪股份有限公司 | Unmanned plane |
| CN108284946A (en) * | 2017-01-09 | 2018-07-17 | 昊翔电能运动科技(昆山)有限公司 | Single steering engine drives the structure of undercarriage control and the unmanned plane using the structure |
| CN108713275A (en) * | 2017-02-24 | 2018-10-26 | 深圳市大疆创新科技有限公司 | RTK antenna installation stents and unmanned vehicle |
| WO2019128401A1 (en) * | 2017-12-28 | 2019-07-04 | 深圳市道通智能航空技术有限公司 | Undercarriage and unmanned aerial vehicle provided with same |
| CN107985564A (en) * | 2017-12-28 | 2018-05-04 | 深圳市道通智能航空技术有限公司 | Undercarriage and the unmanned vehicle with the undercarriage |
| CN109895999A (en) * | 2019-03-21 | 2019-06-18 | 北京航空航天大学 | A kind of undercarriage control device for lightweight aircraft |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191210 Address after: Room 812, enterprise service center, No. 17, section 3, west section of Changjiang North Road, Lingang Economic Development Zone, Yibin City, Sichuan Province Patentee after: Sichuan Yidian Aviation Technology Co., Ltd Address before: Baoan District Shiyan street Shenzhen city Guangdong province 518108 Songbai road Tangtou junctions electric science and Technology Park Patentee before: Shenzhen Yidian Aviation Technology Co., Ltd. |
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| TR01 | Transfer of patent right |