CN205256650U - Rotor beta structure - Google Patents
Rotor beta structure Download PDFInfo
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- CN205256650U CN205256650U CN201521007464.1U CN201521007464U CN205256650U CN 205256650 U CN205256650 U CN 205256650U CN 201521007464 U CN201521007464 U CN 201521007464U CN 205256650 U CN205256650 U CN 205256650U
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- fuselage
- rotor
- support bar
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Abstract
The utility model relates to a rotor beta structure, including fuselage, bracing piece, rotor, motor and gallows, the fuselage be regular octagon disc construction, and a bracing piece is installed to eight apex angles of fuselage cantilever type respectively, and a hinge shaft base has been made respectively to eight apex angles of fuselage, and spacing wobbling pendulum rod cover is adorned to this hinge shaft base hinge, and this pendulum rod overlaps the coaxial fixed mounted bracing piece, rotate the installation and adjust and have a hasp on the fuselage of apex angle upper end, have one and the spacing lug of hasp complex in the outer solid dress / system of pendulum rod cover. The utility model discloses the overall arrangement is good, and the self stability is high, but possesses the VTOL, has light in weight, collapsible, folds method easy operation, convenient to carry moreover.
Description
Technical field
The utility model belongs to unmanned plane field, especially a kind of rotor foldable structure.
Background technology
In recent years, be accompanied by the ripe gradually of UAV technology, and the progress of supporting control appliance had possessed technicalThe feasibility of multiple application. At present, the structure of unmanned plane itself is generally stationary structure, and agent structure is fixed, and takies skyBetween larger, while especially going out to execute the task, carry comparatively inconvenience, carry inconvenience.
Utility model content
The purpose of this utility model is to overcome the deficiencies in the prior art part, provides a kind of reasonable in design, simple in structure, stableReliably, portable rotor foldable structure.
The utility model solves its technical problem and takes following technical scheme to realize:
A kind of rotor foldable structure, comprises fuselage, support bar, rotor, motor and suspension bracket, and fuselage is that octagon is plate shapedStructure, eight drift angles of fuselage respectively cantilevered are provided with a support bar, it is characterized in that: eight drift angles of fuselage are shaped with respectivelyA hinged block, this hinged block hinge fills the fork cover of spacing swing, and this fork cover is coaxially fixedly mounted with support bar; At the machine of drift angle upper endRotating with it to install to regulate has a snap close, is fixedly mounted with/is shaped with one and the spacing block set of snap fit fork cover is outer.
And the equal drive installation of cantilever end of support bar has a rotor.
And, be set with a position-limited hoop at support bar middle part.
Advantage of the present utility model and good effect are:
The utility model layout is good, and self stability is high, and possessing can VTOL, have lightweight, collapsible, and foldingFolded method is simple to operate, easy to carry.
Brief description of the drawings
Fig. 1 is the structural front view of the utility model deployed condition;
Fig. 2 is the structural representation of the utility model folded state;
Fig. 3 is foldable structure partial enlarged drawing (deployed condition);
Fig. 4 is foldable structure partial enlarged drawing (folded state).
Detailed description of the invention
Below in conjunction with accompanying drawing and by specific embodiment, the utility model is described in further detail, and following examples are descriptive,Not determinate, can not limit protection domain of the present utility model with this.
A kind of rotor foldable structure, comprises fuselage 1, support bar 3, rotor 4, motor 5 and suspension bracket 2, and fuselage is positive eight limitsShape disk construction, eight drift angles of fuselage respectively cantilevered are provided with a support bar, and support bar can upper and lower rotation; SupportThe equal drive installation of cantilever end of bar has a rotor, and each rotor lower end is coaxially installed with a motor; Select corresponding merit according to loading capacityThe motor of rate;
For the ease of dwindling unmanned plane volume, eight drift angles of fuselage are shaped with respectively a hinged block 14, this hinged block hinge loads onto,The fork cover 11 that lower limit swings, this fork cover is coaxially fixedly mounted with support bar 3, thereby drives the spacing swing of support bar;
The stability of deployed condition when ensureing work, on the fuselage of drift angle upper end, rotating to install to regulate has a snap close 10, andAnd, fork cover outer be fixedly mounted with/be shaped with one with the spacing block set 13 of snap fit, after support bar launches, rotation snap close is spacing to fasteningThereby the attitude of projection lock support support bar.
Fuselage lower end is coaxially fixed with a suspension bracket 2, and this suspension bracket is shaped with the bolt mounting holes for self-contained battery;
Shown in accompanying drawing, be hinged with one end of two supports 6 in the fuselage lower end symmetry of the both lateral sides of suspension bracket, support anotherOne end is fixed with a cross bar 7, can make fuselage stable support on the ground.
The rotor of the present embodiment is folding rotor, is set with a position-limited hoop 12 at support bar middle part, and when folding, two fins can be foldedPut to insert in position-limited hoop and be fixed.
The suspension bracket of aircraft lower end is used for installing airborne task device, and the lower end of suspension bracket shown in the present embodiment is provided with and can multi-angle turnsMoving The Cloud Terrace 8, The Cloud Terrace lower end is provided with video camera 9. Video camera can be selected thermal camera, visible light camera and laserThe multiple optical pickocff such as range finder.
Fuselage and suspension bracket all adopt carbon fibre composite to make, and have lightweight feature, can improve unmanned plane load.
Although disclose for the purpose of illustration embodiment of the present utility model and accompanying drawing, it will be appreciated by those skilled in the art that:Not departing from the spirit and scope of the utility model and claims, various replacements, variation and amendment are all possible,Therefore, scope of the present utility model is not limited to embodiment and the disclosed content of accompanying drawing.
Claims (3)
1. a rotor foldable structure, comprises fuselage, support bar, rotor, motor and suspension bracket, and fuselage is octagon flat boardShape structure, eight drift angles of fuselage respectively cantilevered are provided with a support bar, it is characterized in that: eight drift angles of fuselage are made respectivelyHave a hinged block, this hinged block hinge fills the fork cover of spacing swing, and this fork cover is coaxially fixedly mounted with support bar; In drift angle upper endOn fuselage, rotating to install to regulate has a snap close, is fixedly mounted with/is shaped with one and the spacing block set of snap fit fork cover is outer.
2. rotor foldable structure according to claim 1, is characterized in that: the equal drive installation of cantilever end of support bar has oneRotor.
3. rotor foldable structure according to claim 1, is characterized in that: be set with a position-limited hoop at support bar middle part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521007464.1U CN205256650U (en) | 2015-12-07 | 2015-12-07 | Rotor beta structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521007464.1U CN205256650U (en) | 2015-12-07 | 2015-12-07 | Rotor beta structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205256650U true CN205256650U (en) | 2016-05-25 |
Family
ID=55998195
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521007464.1U Active CN205256650U (en) | 2015-12-07 | 2015-12-07 | Rotor beta structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205256650U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081057A (en) * | 2016-06-21 | 2016-11-09 | 广州市红鹏直升机遥感科技有限公司 | A kind of stable multiaxis unmanned plane |
| CN106184728A (en) * | 2016-07-08 | 2016-12-07 | 武汉科技大学 | A kind of rotary telescopic variable-torque quadrotor |
| CN106585953A (en) * | 2016-12-27 | 2017-04-26 | 歌尔科技有限公司 | Unmanned aerial vehicle |
| CN107108012A (en) * | 2016-10-27 | 2017-08-29 | 深圳市大疆创新科技有限公司 | The horn and unmanned vehicle of connection component, unmanned vehicle |
| CN107323661A (en) * | 2017-07-03 | 2017-11-07 | 湖北龙翼机器人有限公司 | A kind of axle aircraft of multifunctional portable six |
| CN108240533A (en) * | 2016-12-26 | 2018-07-03 | 中山日高精密工业有限公司 | Multi-functional special cantilever pan tilt structure |
| CN108602553A (en) * | 2016-12-27 | 2018-09-28 | 深圳市大疆创新科技有限公司 | multi-rotor unmanned aerial vehicle |
-
2015
- 2015-12-07 CN CN201521007464.1U patent/CN205256650U/en active Active
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081057A (en) * | 2016-06-21 | 2016-11-09 | 广州市红鹏直升机遥感科技有限公司 | A kind of stable multiaxis unmanned plane |
| CN106081057B (en) * | 2016-06-21 | 2018-05-25 | 广州市红鹏直升机遥感科技有限公司 | A kind of multiaxis unmanned plane of stabilization |
| CN106184728A (en) * | 2016-07-08 | 2016-12-07 | 武汉科技大学 | A kind of rotary telescopic variable-torque quadrotor |
| CN107108012A (en) * | 2016-10-27 | 2017-08-29 | 深圳市大疆创新科技有限公司 | The horn and unmanned vehicle of connection component, unmanned vehicle |
| CN107108012B (en) * | 2016-10-27 | 2019-04-09 | 深圳市大疆创新科技有限公司 | The horn and unmanned vehicle of connection component, unmanned vehicle |
| CN108240533A (en) * | 2016-12-26 | 2018-07-03 | 中山日高精密工业有限公司 | Multi-functional special cantilever pan tilt structure |
| CN106585953A (en) * | 2016-12-27 | 2017-04-26 | 歌尔科技有限公司 | Unmanned aerial vehicle |
| CN108602553A (en) * | 2016-12-27 | 2018-09-28 | 深圳市大疆创新科技有限公司 | multi-rotor unmanned aerial vehicle |
| CN108602553B (en) * | 2016-12-27 | 2022-01-25 | 深圳市大疆创新科技有限公司 | Multi-rotor unmanned aerial vehicle |
| US11597513B2 (en) | 2016-12-27 | 2023-03-07 | SZ DJI Technology Co., Ltd. | Multi-rotor unmanned aerial vehicle |
| CN106585953B (en) * | 2016-12-27 | 2023-07-21 | 歌尔科技有限公司 | Unmanned aerial vehicle |
| CN107323661A (en) * | 2017-07-03 | 2017-11-07 | 湖北龙翼机器人有限公司 | A kind of axle aircraft of multifunctional portable six |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |