CN205239901U - Many rotor unmanned aerial vehicle and frame thereof - Google Patents
Many rotor unmanned aerial vehicle and frame thereof Download PDFInfo
- Publication number
- CN205239901U CN205239901U CN201520647626.1U CN201520647626U CN205239901U CN 205239901 U CN205239901 U CN 205239901U CN 201520647626 U CN201520647626 U CN 201520647626U CN 205239901 U CN205239901 U CN 205239901U
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- cantilever
- unmanned aerial
- fuselage
- wing unmanned
- rotor wing
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Abstract
The utility model discloses a many rotor unmanned aerial vehicle and frame thereof, its size is less, and the cost of manufacture is lower. A many rotor unmanned aerial vehicle's frame includes the fuselage, the fuselage is equipped with all around a plurality of cantilevers of radial extension, a plurality of cantilevers are divided into two sets ofly at least, and each tip of organizing the cantilever lies in different horizontal planes, make the tip distribution of a plurality of cantilevers two -layer for at least, and the dislocation corresponds between the cantilever of adjacent layer. Many rotor unmanned aerial vehicle include the frame.
Description
Technical field
The utility model relates to unmanned plane technical field, particularly relates to a kind of many rotor wing unmanned aerial vehicles and machine thereofFrame.
Background technology
The cantilever of existing many rotor wing unmanned aerial vehicles is all in the same plane, in order to prevent the spiral shell on cantileverRevolve in the oar course of work and interfere, many rotor wing unmanned aerial vehicles jib-length is done greatly, weight also thereforeGreatly, reduce flexibility and the mobility of many rotor wing unmanned aerial vehicles, in addition, many rotors of different rotor quantityThe rack section of unmanned plane all needs mould is set respectively, and cost of manufacture is higher.
The fuselage of existing many rotor wing unmanned aerial vehicles and cantilever are all package assemblies, for example, be welded and fixed, boltFix etc., its bonding strength is lower, installation process complexity, and precision is poor.
The cantilever of existing many rotor wing unmanned aerial vehicles is all structures of even thickness, therefore, and in order to ensure cantileverIntensity, the portion size that cantilever is connected with fuselage is suitable, near size cantilever end is excessive,Considerably beyond needing, increase cost of manufacture and the complete machine weight of many rotor wing unmanned aerial vehicles, reduce and revolved moreThe flying quality of wing unmanned plane.
Normally fixed structure of the undercarriage of existing many rotor wing unmanned aerial vehicles, can not carry out folding, very notBe convenient to transport, and undercarriage is rigid structure normally, when many rotor wing unmanned aerial vehicle landing, can be subject toVery large impact, easily damages.
Utility model content
The purpose of this utility model is to overcome the deficiencies in the prior art, provide a kind of many rotor wing unmanned aerial vehicles andIts frame, its size is less, and cost of manufacture is lower.
The purpose of this utility model is achieved in that
A frame for many rotor wing unmanned aerial vehicles, comprises fuselage, and fuselage surrounding is provided with radially extend multiple outstandingArm, described multiple cantilevers are divided at least two groups, and the end of respectively organizing cantilever is positioned on different horizontal planes, makesThe end of multiple cantilevers is distributed as at least two-layer, and between the cantilever of adjacent layer, dislocation is corresponding.
In order to meet most of users' needs, preferably, the quantity of described cantilever is eight, and eight outstandingArm is divided into two groups, and wherein one group of cantilever along continuous straight runs extends, and forms horizontal arm layer, and another organizes cantilever edgeOblique upper extends, and forms and tiltedly sticks up arm layer. User can be as required, selection level arm layer and/or tiltedly stick up arm layerThe parts such as screw are installed, are formed different types of many rotor wing unmanned aerial vehicles.
In order to ensure the bonding strength of fuselage, cantilever, preferably, described fuselage and cantilever adopt magnesium alloyMaterial casting is integrated. The frame of integrative-structure reduced assembling process, and improved frameMake precision. Magnesium alloy materials is compared with charcoal fibrous material, and proportion is close, low price many, andMagnesium alloy rigidity is strong, and shock absorption is good, and is beneficial to compacting decorative pattern.
For in ensureing cantilever intensity, reduce weight and the cost of manufacture of cantilever, preferably, instituteState cantilever and be tapered taper from inside to outside. Therefore, reduced the complete machine weight of many rotor wing unmanned aerial vehicles,Improve the flying quality of many rotor wing unmanned aerial vehicles.
For in ensureing cantilever intensity, reduce weight and the cost of manufacture of cantilever, preferably, instituteThe cross section of stating cantilever is inverted U, makes the bottom of cantilever be formed for holding the cavity of wire, described machineThe first wire is set to be with it communicated with the cavity on cantilever by hole. Cavity, the first wire can by holeBe convenient to conducting wire, and the two side of U-shaped cantilever can form the protection to wire.
For the ease of mounted motor, and the bonding strength of guarantee motor cabinet and cantilever, preferably, described outstandingThe end of arm is one-body molded " ┏ " type motor cabinet, the second wire is set logical on the riser of described motor cabinetVia hole is communicated with the cavity on cantilever, privates is set by hole and second on the transverse slat of described motor cabinetWire is by hole correspondence. The second wire can be so that conducting wire by hole by hole, privates.
A kind of many rotor wing unmanned aerial vehicles, comprise any one above-mentioned frame.
In order to protect the Circuits System in fuselage, preferably, the end of described cantilever be provided with screw andThe drive motors of screw, the upper end of described fuselage arranges upper end cover sealing, and the lower end of described fuselage arrangesBottom end cover sealing, the fuselage of formation hermetically-sealed construction, is provided with the power supply of drive motors and controls system in fuselageSystem.
For the ease of folding, the transport of undercarriage, preferably, also comprise and be fixed on rising and falling of fuselage belowFrame, described undercarriage comprises two H type framves, and the middle part of the crossbeam of two H type framves is hinged, and formation can be receivedThe undercarriage of folding.
Suffered impulsive force while landing in order to reduce many rotor wing unmanned aerial vehicles, preferably, described two H type framvesVertical rod bottom be equipped with resiliency supported leg.
Owing to having adopted technique scheme, the utlity model has following beneficial effect:
The end of many rotor wing unmanned aerial vehicles cantilever is distributed as at least two-layer, dislocation correspondence between the cantilever of adjacent layer,Greatly dwindle the radius of many rotor wing unmanned aerial vehicles, between the screw on each layer of cantilever, can not interfere,And, with respect to all upper many rotor wing unmanned aerial vehicles that upper and lower screw is installed of each cantilever, these many rotorsThe screw area coverage of unmanned plane is larger, has greatly promoted flight performance.
Owing to having dwindled the radius of many rotor wing unmanned aerial vehicles, the length of many rotor wing unmanned aerial vehicles cantilever is shorter, weightAlso therefore lighter, greatly promote flexibility and the mobility of many rotor wing unmanned aerial vehicles, in addition, user canSelect as required one or more layers cantilever wherein that screw is installed, the scope of application is extensive, and producer is comeSay, the rack section of many rotor wing unmanned aerial vehicles of these specifications only needs a width mould to make, cost of manufactureLower.
Brief description of the drawings
Fig. 1 is the structural representation of many rotor wing unmanned aerial vehicles;
Fig. 2 is the schematic top plan view of Fig. 1;
Fig. 3 is the structural representation of frame;
Fig. 4 is the structural representation of undercarriage;
Fig. 5 is that the inclined shaft of many rotor wing unmanned aerial vehicles measures intention.
Reference numeral
In accompanying drawing, 1 is fuselage, and 2 is cantilever, and 3 is the first wire by hole, and 4 is motor cabinet, and 5 is theTwo wires are by hole, and 6 for privates is by hole, and 7 is screw, and 8 is drive motors, and 9 is levelArm layer, 10 for tiltedly sticking up arm layer, and 11 is upper end cover, and 12 is bottom end cover, and 13 is H type frame, 14 is elasticitySupporting leg.
Detailed description of the invention
Referring to Fig. 3, it is a kind of preferred embodiment of the frame of many rotor wing unmanned aerial vehicles
Comprise fuselage 1 cylindraceous, fuselage 1 surrounding is provided with the multiple cantilevers 2 that radially extend, described fuselage1 adopts magnesium alloy materials casting to be integrated with cantilever 2. Described cantilever 2 is from inside to outside and is taperedTaper. The cross section of described cantilever 2 is inverted U, makes the bottom of cantilever 2 be formed for holding wireCavity, the first wire is set on described fuselage 1 and is communicated with the cavity on cantilever 2 by hole 3. DescribedThe end of cantilever 2 is one-body molded " ┏ " type motor cabinet 4, on the riser of described motor cabinet 4, arranges secondWire is communicated with the cavity on cantilever 2 by hole 5, on the transverse slat of described motor cabinet 4, privates is setCorresponding by hole 5 with the second wire by hole 6.
Described multiple cantilever 2 is divided at least two groups, and the end of respectively organizing cantilever 2 is positioned on different horizontal planes,The end of multiple cantilevers 2 is distributed as at least two-layer, between the cantilever 2 of adjacent layer, dislocation is corresponding. This realityExecute in example, the quantity of described cantilever 2 is eight, and eight cantilevers 2 are divided into two groups, wherein one group of cantilever 2Along continuous straight runs extends, and forms horizontal arm layer 9, and another group cantilever 2 extends along oblique upper, forms and tiltedly sticks up armLayer 10. Frame radius is 0.65m.
Referring to Fig. 1 to Fig. 5, it is a kind of preferred embodiment of many rotor wing unmanned aerial vehicles
Referring to Fig. 3, comprise frame, referring to Fig. 1, Fig. 2, Fig. 5, the end of described cantilever 2 is provided with spiral shellThe drive motors 8 that revolves oar 7 and screw 7, the upper end of described fuselage 1 arranges upper end cover 11 and seals,The lower end of described fuselage 1 arranges bottom end cover 12 and seals, and forms the fuselage 1 of hermetically-sealed construction, in the present embodiment,In described fuselage 1, be provided with screw base, described upper end cover 11, bottom end cover 12 are provided with screw hole, upper end cover11, bottom end cover 12 is fixedly connected with by screw with the screw base in fuselage 1. In described fuselage 1, be provided withThe power supply of drive motors 8 and control system, the guiding of connection power supply, control system and drive motors 8Extend through the first wire passes through hole 5 and privates by the cavity on hole 3, cantilever 2, the second wireBy hole 6. The radius of many rotor wing unmanned aerial vehicles is about 2m.
Referring to Fig. 4, also comprise the undercarriage that is fixed on fuselage below, described undercarriage comprises two H typesThe middle part of the crossbeam of 13, two H type framves 13 of frame is by bolted splice, and formation is folding in the horizontal directionUndercarriage, general car trunk can hold. On the column of two H type framves 13, be respectively equipped with useIn the L-type notch part that supports fuselage 1, for the radially spacing and axial limiting to fuselage 1, L-type notch partBe bolted to connection with fuselage. The vertical rod bottom of described two H type framves 13 is equipped with resiliency supported leg14. Described resiliency supported leg 14 is slidably matched with the vertical rod of H type frame 13, and Compress Spring conduct is setBuffering.
Finally explanation, above preferred embodiment only in order to the technical solution of the utility model to be described but notRestriction, although the utility model is described in detail by above preferred embodiment, thisThose skilled in the art should be appreciated that and can make various changes to it in the form and details,And do not depart from the utility model claims limited range.
Claims (10)
1. the frame of rotor wing unmanned aerial vehicle more than a kind, comprise fuselage, fuselage surrounding is provided with the multiple cantilevers that radially extend, it is characterized in that: described multiple cantilevers are divided at least two groups, the end of each group cantilever is positioned on different horizontal planes, the end of multiple cantilevers is distributed as at least two-layer, between the cantilever of adjacent layer, dislocation is corresponding.
2. the frame of many rotor wing unmanned aerial vehicles according to claim 1, is characterized in that: the quantity of described cantilever is eight, and eight cantilevers are divided into two groups, wherein one group of cantilever along continuous straight runs extends, form horizontal arm layer, another group cantilever extends along oblique upper, forms and tiltedly sticks up arm layer.
3. the frame of many rotor wing unmanned aerial vehicles according to claim 1, is characterized in that: described fuselage and cantilever adopt magnesium alloy materials casting to be integrated.
4. the frame of many rotor wing unmanned aerial vehicles according to claim 1, is characterized in that: described cantilever is tapered taper from inside to outside.
5. the frame of many rotor wing unmanned aerial vehicles according to claim 1, is characterized in that: the cross section of described cantilever is inverted U, makes the bottom of cantilever be formed for holding the cavity of wire, the first wire is set on described fuselage and is communicated with the cavity on cantilever by hole.
6. the frame of many rotor wing unmanned aerial vehicles according to claim 1, it is characterized in that: the end of described cantilever is one-body molded " ┏ " type motor cabinet, the second wire is set on the riser of described motor cabinet and is communicated with the cavity on cantilever by hole, privates is set corresponding by hole with the second wire by hole on the transverse slat of described motor cabinet.
7. a rotor wing unmanned aerial vehicle more than, is characterized in that: comprise the arbitrary described frame of claim 1 to 6.
8. many rotor wing unmanned aerial vehicles according to claim 7, it is characterized in that: the end of described cantilever is provided with the drive motors of screw and described screw, the upper end of described fuselage arranges upper end cover sealing, the lower end of described fuselage arranges bottom end cover sealing, form the fuselage of hermetically-sealed construction, power supply and the control system of described drive motors is installed in fuselage.
9. many rotor wing unmanned aerial vehicles according to claim 8, is characterized in that: also comprise the undercarriage that is fixed on fuselage below, described undercarriage comprises two H type framves, and the middle part of the crossbeam of two H type framves is hinged, forms foldable undercarriage.
10. many rotor wing unmanned aerial vehicles according to claim 9, is characterized in that: the vertical rod bottom of described two H type framves is equipped with resiliency supported leg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520647626.1U CN205239901U (en) | 2015-08-25 | 2015-08-25 | Many rotor unmanned aerial vehicle and frame thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520647626.1U CN205239901U (en) | 2015-08-25 | 2015-08-25 | Many rotor unmanned aerial vehicle and frame thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205239901U true CN205239901U (en) | 2016-05-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520647626.1U Expired - Fee Related CN205239901U (en) | 2015-08-25 | 2015-08-25 | Many rotor unmanned aerial vehicle and frame thereof |
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| Country | Link |
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| CN (1) | CN205239901U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106927014A (en) * | 2017-03-14 | 2017-07-07 | 上海帆煜自动化科技有限公司 | A kind of lightweight unmanned plane of high-strength corrosion-resisting |
| CN107539455A (en) * | 2016-06-29 | 2018-01-05 | 北京臻迪机器人有限公司 | A kind of unmanned plane frame upper bracket |
| CN108394545A (en) * | 2018-03-27 | 2018-08-14 | 傲飞创新科技（深圳）有限公司 | Spliced unmanned aerial vehicle fuselage |
| WO2018172815A1 (en) * | 2017-03-22 | 2018-09-27 | Aerones, Sia | A multicopter frame |
| CN109592024A (en) * | 2016-07-05 | 2019-04-09 | 金福珍 | A kind of Intelligent unattended machine |
| CN113002764A (en) * | 2019-12-18 | 2021-06-22 | 上海峰飞航空科技有限公司 | Multi-rotor aircraft with multi-axis staggered layout |
-
2015
- 2015-08-25 CN CN201520647626.1U patent/CN205239901U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107539455A (en) * | 2016-06-29 | 2018-01-05 | 北京臻迪机器人有限公司 | A kind of unmanned plane frame upper bracket |
| CN109592024A (en) * | 2016-07-05 | 2019-04-09 | 金福珍 | A kind of Intelligent unattended machine |
| CN109592024B (en) * | 2016-07-05 | 2022-02-11 | 武汉慧农无人机科技有限公司 | Intelligent unmanned aerial vehicle |
| CN106927014A (en) * | 2017-03-14 | 2017-07-07 | 上海帆煜自动化科技有限公司 | A kind of lightweight unmanned plane of high-strength corrosion-resisting |
| WO2018172815A1 (en) * | 2017-03-22 | 2018-09-27 | Aerones, Sia | A multicopter frame |
| CN108394545A (en) * | 2018-03-27 | 2018-08-14 | 傲飞创新科技（深圳）有限公司 | Spliced unmanned aerial vehicle fuselage |
| CN108394545B (en) * | 2018-03-27 | 2024-03-26 | 傲飞创新科技（深圳）有限公司 | Spliced unmanned aerial vehicle fuselage |
| CN113002764A (en) * | 2019-12-18 | 2021-06-22 | 上海峰飞航空科技有限公司 | Multi-rotor aircraft with multi-axis staggered layout |
| CN113002764B (en) * | 2019-12-18 | 2023-09-05 | 上海峰飞航空科技有限公司 | Multi-rotor aircraft with multi-axis staggered layout |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160518 Termination date: 20180825 |