CN204568056U - A kind of horizontal interfolded quadrotor - Google Patents
A kind of horizontal interfolded quadrotor Download PDFInfo
- Publication number
- CN204568056U CN204568056U CN201520127184.8U CN201520127184U CN204568056U CN 204568056 U CN204568056 U CN 204568056U CN 201520127184 U CN201520127184 U CN 201520127184U CN 204568056 U CN204568056 U CN 204568056U
- Authority
- CN
- China
- Prior art keywords
- hold
- down arm
- fuselage
- interfolded
- quadrotor
- 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
Links
Landscapes
- Agricultural Machines (AREA)
Abstract
The utility model discloses a kind of horizontal interfolded quadrotor, mainly comprise fuselage, hold-down arm, motor, rotor, alighting gear etc.Wherein, four hold-down arms are distributed in fuselage both sides between two.Two hold-down arms of the same side are staggered installation of up and down.One end of every bar hold-down arm is connected with fuselage by linkage, and the other end is provided with supporting seat.Motor is installed with above supporting seat.Electric machine rotational axis is provided with rotor.Also alighting gear is installed below supporting seat.Launch hold-down arm and alighting gear during the work of this aircraft, kept the position of hold-down arm by lockout mechanism, carry out normal flight; Pack up alighting gear when off working state, by horizontal for hold-down arm interfolded, kept the position of hold-down arm by lockout mechanism, reduce volume easy to carry and transport.
Description
Technical field
the present invention relates to aircraft field, particularly the horizontal interfolded quadrotor of one.
Background technology
Quadrotor compared to other aircraft flight more steadily, can fly in hovering, side to switch rapidly between the state of flight such as inverted flight, takeoff and landing performance and maneuvering performance good, be suitable for very much performing the tasks such as fixed point is scouted, taken photo by plane, aerial mapping, there is military affairs and civil use widely.
Flight support arm and the alighting gear of tradition quadrotor adopt fixing version usually, and this just makes aircraft have larger volume, can bring inconvenience to carrying with transportation.Although some quadrotor also adopts accordion structure, the such as MD4-1000 type aircraft of Germany, its accordion structure adopted is that half hold-down arm folds downwards, and the volume after it is folding is still very large, makes troubles to transport and use.Also some folding schemes improved are had in prior art, the laterally folded scheme of half hold-down arm such as, proposed in patent CN103625641A, its volume after folding reduces to some extent than MD4-1000, but being surrounded on fuselage surrounding after its half hold-down arm is folding, fails to be fully used in the space on the one hand after folding around fuselage, below hold-down arm; On the other hand the equipment such as its capacity weight such as The Cloud Terrace can only be installed on below fuselage in actual applications, can bring defects such as having tunnel vision.Propose a kind of folding quadrotor in patent CN203528812U, its hold-down arm is doubling in opposite directions to the inside, and this just requires fuselage to have longer length to hold two hold-down arms placements, and therefore this quadrotor inherently has larger volume.Propose a kind of folding quadrotor in patent CN302779997S, its hold-down arm is doubling in opposite directions laterally, although this folding mode reduces the transverse width of aircraft, but adds the longitudinal length of aircraft after folding.Therefore, although several folding schemes related in above-mentioned patent reduce the volume of quadrotor all to a certain extent, but all have employed flat-folded scheme, its folding joint is all confined in same plane, do not make full use of the available space around fuselage in maximum.
Summary of the invention
The object of the invention is to overcome the problems referred to above, the horizontal interfolded quadrotor that a kind of structure is simple, volume is little, be convenient for carrying and transport is provided.
For achieving the above object, the method that the present invention adopts is: a kind of horizontal interfolded quadrotor, comprise fuselage, hold-down arm, motor, rotor, alighting gear, it is characterized in that: described hold-down arm is provided with four, article four, hold-down arm is distributed in fuselage both sides between two, two hold-down arms of the same side are staggered installation of up and down, one end of every bar hold-down arm is connected with fuselage, the other end is provided with supporting seat, supporting seat is installed with motor, rotor is fixedly installed on electric machine rotational axis, alighting gear is arranged on the supporting seat on hold-down arm, every bar hold-down arm in four described hold-down arms independently can carry out unitary rotation around the junction of hold-down arm and fuselage, complete expansion or folding movement.
Preferred as one of the present invention, be connected by hinge arrangement with between fuselage at described hold-down arm.
Preferred as one of the present invention, the nearly fuselage end of described hold-down arm is provided with lockout mechanism parts, is fixedly connected with after opening in entirety or folding with the lockout mechanism parts on fuselage.
Preferred as one of the present invention, described lockout mechanism parts comprise the lockout mechanism parts on hold-down arm and the lockout mechanism parts on fuselage; Lockout mechanism parts on described hold-down arm are hold-down arms, the one be installed in the annulus of the nearly fuselage end of hold-down arm, C shape ring or clevis eye or electromagnetism class locking member; Lockout mechanism parts on described fuselage be fuselage is installed for carry out coordinating, be fixedly connected with the lockout mechanism parts on hold-down arm C shape, one in U-shaped draw-in groove or electromagnetism class locking member.
Preferred as one of the present invention, two hold-down arms of described the same side to stagger certain distance in the installation of vertical direction.
Preferred as one of the present invention, described alighting gear be plug-in type or collapsible in one, its one end is fixedly connected with the supporting seat of hold-down arm end, and the other end is for ground supports.
Beneficial effect:
Technical solution of the present invention compares traditional fixed sturcture rotor craft, and volume after folding reduces, and is convenient for carrying and transports.In some flat-folded schemes compared to existing technology, folding joint is all confined to the situation in same plane, technical solution of the present invention adopts the mode of the horizontal interfolded in space, make full use of fuselage side-lower space, improve space availability ratio, volume after folding reduces further, makes to carry and transport convenient.The plug-in type adopted in technical solution of the present invention or collapsible alighting gear are separated with fuselage or also fold after hold-down arm is folding, also make folding rear aircraft volume be reduced further.In addition, the folding mode simple possible that technical solution of the present invention adopts, easy to operate, its hold-down arm can fast folding with fixing, alighting gear can carry out loading and unloading or folding fast, decreases the setup time before equipment use.
Accompanying drawing explanation
Fig. 1 is the front view after horizontal interfolded quadrotor launches;
Fig. 2 is the lateral plan after horizontal interfolded quadrotor launches;
Fig. 3 is that horizontal interfolded quadrotor launches rear isometric view;
Fig. 4 is horizontal interfolded quadrotor folded configuration front view;
Fig. 5 is horizontal interfolded quadrotor folded configuration lateral plan;
Fig. 6 does not add rotor shaft after horizontal interfolded quadrotor folds to survey view.
In figure: 1, fuselage, 2, hold-down arm, 3, motor, 4, rotor, 5, alighting gear, 6, linkage, 7, supporting seat, 8, lockout mechanism, 81, hold-down arm folds C shape groove Lock Part on rear body, 82, hold-down arm launches on rear body C shape groove Lock Part.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, illustrate the present invention further, the present embodiment is implemented under premised on technical solution of the present invention, should understand these embodiments and only be not used in for illustration of the present invention and limit the scope of the invention.
Embodiment 1:
As shown in accompanying drawing 1 to accompanying drawing 6, the invention discloses a kind of horizontal interfolded quadrotor, comprise fuselage 1, hold-down arm 2, motor 3, rotor 4, alighting gear 5, linkage 6, supporting seat 7, lockout mechanism 8.
As shown in Figures 1 and 2, for the front view after horizontal interfolded quadrotor expansion of the present invention and lateral plan, in figure, article four, hold-down arm 2 is distributed in fuselage 1 both sides between two, two hold-down arms about 2 of the same side are staggered installation of, two hold-down arms 2 of the same side to stagger certain distance in the installation of vertical direction, to ensure that all parts is not interfered mutually.One end of every bar hold-down arm 2 is connected with fuselage, and the other end is provided with supporting seat 7, and in the present embodiment, hold-down arm 2 is connected with fuselage 1 by linkage.Article four, the every bar hold-down arm 2 in hold-down arm 2 independently can carry out unitary rotation around end hinge mechanism 6, completes expansion or folding movement.
Supporting seat 7 is installed with motor 3, and rotor 4 is fixedly installed on the S. A. of motor 3.Alighting gear 5 is arranged on the supporting seat 7 on hold-down arm 2, and alighting gear 5 is alighting gear that is collapsible or plug-in, and alighting gear 5 is plug-in alighting gear in the present embodiment.Plug-in type alighting gear 5 one end can be inserted in the pore of supporting seat 7 side of hold-down arm 2 end, and its connection mode is interference fit; The other end is used for ground supports.
Be that horizontal interfolded quadrotor launches rear isometric view as shown in Figure 3, one end that fuselage 1 installs linkage 6 is provided with lockout mechanism parts, and lockout mechanism comprises the lockout mechanism parts on hold-down arm and the lockout mechanism parts on fuselage.Wherein, the lockout mechanism parts on hold-down arm are hold-down arms itself, the one be installed in the annulus of the nearly fuselage end of hold-down arm, C shape ring or clevis eye or electromagnetism class locking member.In the present embodiment, adopt the locking scheme of C shape ring, after hold-down arm 2 entirety is launched, the C shape groove Lock Part 82 that this hold-down arm 2 and hold-down arm launch on rear body is fixedly connected with, and ensures that hold-down arm 2 and fuselage 1 are fixedly linked.
After hold-down arm 2 foldable integral, the C shape groove Lock Part 81 that this hold-down arm 2 and hold-down arm fold on rear body is fixedly connected with, and ensures that hold-down arm 2 and fuselage 1 are fixedly linked.
Technical solution of the present invention compares traditional fixed sturcture rotor craft, and volume after folding reduces, and is convenient for carrying and transports.In some flat-folded schemes compared to existing technology, folding joint is all confined to the situation in same plane, technical solution of the present invention adopts the mode of the horizontal interfolded in space, make full use of fuselage side-lower space, improve space availability ratio, volume after folding reduces further, makes to carry and transport convenient.The plug-in type adopted in technical solution of the present invention or collapsible alighting gear are separated with fuselage or also fold after hold-down arm is folding, also make folding rear aircraft volume be reduced further.In addition, the folding mode simple possible that technical solution of the present invention adopts, easy to operate, its hold-down arm can fast folding with fixing, alighting gear can carry out loading and unloading or folding fast, decreases the setup time before equipment use.
Technological means disclosed in the present invention program is not limited only to the technological means disclosed in above-mentioned technological means, also comprises the technical scheme be made up of above technical characteristic combination in any.The above is the specific embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications are also considered as protection scope of the present invention.
Claims (6)
1. a horizontal interfolded quadrotor, comprise fuselage, hold-down arm, motor, rotor, alighting gear, it is characterized in that: described hold-down arm is provided with four, article four, hold-down arm is distributed in fuselage both sides between two, two hold-down arms of the same side are staggered installation of up and down, one end of every bar hold-down arm is connected with fuselage, the other end is provided with supporting seat, supporting seat is installed with motor, rotor is fixedly installed on electric machine rotational axis, alighting gear is arranged on the supporting seat on hold-down arm, every bar hold-down arm in four described hold-down arms independently can carry out unitary rotation around the junction of hold-down arm and fuselage, complete expansion or folding movement.
2. the horizontal interfolded quadrotor of one according to claim 1, be is characterized in that: be connected by hinge arrangement with between fuselage at described hold-down arm.
3. the horizontal interfolded quadrotor of one according to claim 1, is characterized in that: the nearly fuselage end of described hold-down arm is provided with lockout mechanism parts, is fixedly connected with after opening in entirety or folding with the lockout mechanism parts on fuselage.
4. the horizontal interfolded quadrotor of one according to claim 3, is characterized in that: described lockout mechanism parts comprise the lockout mechanism parts on hold-down arm and the lockout mechanism parts on fuselage; Lockout mechanism parts on described hold-down arm are hold-down arms itself, the one be installed in the annulus of the nearly fuselage end of hold-down arm, C shape ring or clevis eye or electromagnetism class locking member; Lockout mechanism parts on described fuselage be fuselage is installed, C shape for carrying out coordinating, be fixedly connected with the lockout mechanism parts on hold-down arm, one in U-shaped draw-in groove or electromagnetism class locking member.
5. the horizontal interfolded quadrotor of one according to claim 1, is characterized in that: two hold-down arms of described the same side to stagger certain distance in the installation of vertical direction.
6. the horizontal interfolded quadrotor of one according to claim 1, is characterized in that: described alighting gear be plug-in type or collapsible in one, its one end is fixedly connected with the supporting seat of hold-down arm end, the other end be used for ground supports.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520127184.8U CN204568056U (en) | 2015-03-05 | 2015-03-05 | A kind of horizontal interfolded quadrotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520127184.8U CN204568056U (en) | 2015-03-05 | 2015-03-05 | A kind of horizontal interfolded quadrotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204568056U true CN204568056U (en) | 2015-08-19 |
Family
ID=53860730
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520127184.8U Active CN204568056U (en) | 2015-03-05 | 2015-03-05 | A kind of horizontal interfolded quadrotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204568056U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691749A (en) * | 2015-03-05 | 2015-06-10 | 葛讯 | Transversely staggered four-rotor aircraft |
| CN107985581A (en) * | 2017-12-29 | 2018-05-04 | 江苏方阔航空科技有限公司 | A kind of dynamic rotor structure of new type foldable oil |
-
2015
- 2015-03-05 CN CN201520127184.8U patent/CN204568056U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691749A (en) * | 2015-03-05 | 2015-06-10 | 葛讯 | Transversely staggered four-rotor aircraft |
| CN107985581A (en) * | 2017-12-29 | 2018-05-04 | 江苏方阔航空科技有限公司 | A kind of dynamic rotor structure of new type foldable oil |
| CN107985581B (en) * | 2017-12-29 | 2023-11-28 | 南京瑞蓝世光电传感技术研究院有限公司 | Novel folding oil moves rotor structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104691749A (en) | Transversely staggered four-rotor aircraft | |
| CN111655578B (en) | Fixed wing vertical take-off and landing hybrid UAV | |
| US10293933B2 (en) | Rotating wing assemblies for tailsitter aircraft | |
| CN109502006B (en) | Unmanned aerial vehicle frame, unmanned aerial vehicle and using method thereof | |
| US10414483B2 (en) | Tiltrotor articulated wing extension | |
| CN106573678B (en) | Aircraft suitable for vertical take-off and horizontal flight | |
| EP3632793B1 (en) | Unmanned aerial vehicle and landing gear thereof | |
| US20200180756A1 (en) | Propeller-Hub Assembly With Folding Blades For VTOL Aircraft | |
| US20170217585A1 (en) | Aircraft with wing-borne flight mode and hover flight mode | |
| US10106274B2 (en) | Tail sitter vehicle with aerial and ground refueling system | |
| CN102556336A (en) | Wing fast unfolding device for folding-wing unmanned plane | |
| CN107618651B (en) | Multi-rotor unmanned aerial vehicle horn remote control retraction device | |
| CN207466961U (en) | The collapsible undercarriage and its foldable structure of balloon borne near space solar energy unmanned plane | |
| KR20180042405A (en) | Folding wing unmanned aircraft | |
| US20200290719A1 (en) | Frame assembly of unmanned aerial vehicle, and unmanned aerial vehicle | |
| KR101731054B1 (en) | Drone | |
| CN104986324A (en) | Rotary locking mechanism and plant protection unmanned aerial vehicle with the same | |
| CN107187592A (en) | A kind of many rotors of combined type are tethered at UAS | |
| WO2018152792A1 (en) | Foldable frame, frame assembly and unmanned aerial vehicle | |
| CN205931230U (en) | Frame subassembly and use unmanned aerial vehicle of this frame subassembly | |
| CN104691737A (en) | Support arm assembly for multi-rotor aircrafts, rack and aircraft | |
| CN204568056U (en) | A kind of horizontal interfolded quadrotor | |
| CN210852883U (en) | Four rotor unmanned aerial vehicle of collapsible arm | |
| CN210455176U (en) | Folding horn and unmanned vehicles | |
| CN210310861U (en) | Automatic expansion undercarriage |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20180226 Address after: Nanjing Baixia High-tech Industrial Park in Jiangsu province 210000 Building No. 4 Room 305 Patentee after: Nanjing Tao - Aviation Technology Co. Ltd. Address before: Nanjing Baixia High-tech Industrial Park in Jiangsu province 210000 Building No. 4 Room 305 Patentee before: Ge Xun |