CN205150218U - A wing folding mechanism for managing penetrate unmanned aerial vehicle - Google Patents
A wing folding mechanism for managing penetrate unmanned aerial vehicle Download PDFInfo
- Publication number
- CN205150218U CN205150218U CN201520921343.1U CN201520921343U CN205150218U CN 205150218 U CN205150218 U CN 205150218U CN 201520921343 U CN201520921343 U CN 201520921343U CN 205150218 U CN205150218 U CN 205150218U
- Authority
- CN
- China
- Prior art keywords
- wing
- aerial vehicle
- unmanned aerial
- right flank
- pivot
- 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
- Toys (AREA)
Abstract
Disclose a wing folding mechanism for managing penetrate unmanned aerial vehicle with novel, including the left wing, the pivot is installed to the right -hand member mouth of left wing, the spacing piece in the right side is installed at the rear of pivot, the spacing piece in a left side is installed to the inboard port of left wing, the elastomer is installed on the top of pivot, the elastomer round pin is installed and is expanded the crossing at the wing, right flank fixed orifices and right flank fixed connection are passed through to the bottom of pivot, the right flank is passed through the bearing and is linked to each other with the left wing. This a wing folding mechanism for managing penetrate unmanned aerial vehicle, it needs two pivots to have avoided the conventional art to control the wing, has reduced fuselage weight to can improve the unmanned aerial vehicle performance, and the unmanned aerial vehicle flap expandes the device and practiced thrift the cost, the structure is simpler, and it is more stable work, can prevent to make the wing state change by the fast transient drag that produces of flying speed, the time unmanned aerial vehicle move more steadily.
Description
Technical field
The utility model relates to unmanned air vehicle technique field, is specially a kind of wingfold mechanism penetrating unmanned plane for pipe.
Background technology
Unmanned plane, in individual combat, can provide the activities such as accurate information, supervision, investigation to over-the-horizon target at short notice.Tubular type unmanned plane launch the function systems such as storages, transport and transmitting are bonded together, foldable type unmanned plane have use flexible, easy to carry, adapt to the advantages such as multiple environment.
At present, the domestic unmanned plane wingfold mechanism researched and developed uses a kind of gear engagement mechanism mostly, the Dual-motors Driving miniature gears be connected with movable wing section, miniature gears and the canine tooth crop rotation gears meshing be connected in fixed wing part move, and realize the folding of the relative fixed wing of movable wing and launch to move.This gear engagement mechanism exists that kinematic mechanism is not compact, between cog contact force is comparatively large, higher to motor torque requirement, wing-folding time the problem such as mechanism bumpy motion.
Utility model content
The purpose of this utility model is to provide a kind of wingfold mechanism penetrating unmanned plane for pipe, to solve the problem proposed in above-mentioned background technology.
For achieving the above object, the utility model provides following technical scheme: a kind of wingfold mechanism penetrating unmanned plane for pipe, comprise left wing, the right output port of described left wing is provided with rotating shaft, the rear of described rotating shaft is provided with right limit sheet, the inner side port of described left wing is provided with left limit sheet, the top of described rotating shaft is provided with elastic body, described elastic body pin is arranged on wing and launches crossing, the bottom of described rotating shaft is fixedly connected with right flank by right flank fixed orifice, and described right flank is connected with left wing by bearing.
Preferably, described elastic body is spring structure.
Preferably, described right flank fixed orifice has one at least.
Compared with prior art, the beneficial effects of the utility model are: this is used for the wingfold mechanism that unmanned plane penetrated by pipe, avoid conventional art left and right wing and need two rotating shafts, decrease fuselage weight, thus unmanned plane performance can be improve, and unmanned plane flap expanding unit saves cost, structure is simpler, work more stable, can prevent the transient drag produced soon by flying speed from wing state is changed, time unmanned plane run more steady.
Accompanying drawing explanation
Fig. 1 is the utility model structural representation.
In figure: 1, left wing, 2, rotating shaft, 3, left limit sheet, 4, elastic body, 5, elastic body pin, 6, right flank, 7, right limit sheet, 8, right flank fixed orifice, 9 supports.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the utility model embodiment, be clearly and completely described the technical scheme in the utility model embodiment, obviously, described embodiment is only the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.
Refer to Fig. 1, the utility model provides a kind of technical scheme: a kind of wingfold mechanism penetrating unmanned plane for pipe, comprise left wing 1, the right output port of described left wing 1 is provided with rotating shaft 2, the rear of described rotating shaft 2 is provided with right limit sheet 7, the inner side port of described left wing 1 is provided with left limit sheet 3, the top of described rotating shaft 2 is provided with elastic body 4, described elastic body 4 is spring structure, described elastic body pin 5 is arranged on wing and launches crossing, the bottom of described rotating shaft 2 is fixedly connected with right flank 6 by right flank fixed orifice 8, described right flank fixed orifice 8 has one, described right flank 6 is connected with left wing 1 by bearing.
Working process: before unmanned plane is launched, being positioned at tubulose penetrates within cylinder, two wings are not at same horizontal surface, interfolded, due to elastic body 4 torsion, wing has the trend of opening, after unmanned plane is launched outgoing cylinder, the torsion of elastic body 4 and pressure, wing is opened rapidly, bilateral wing is subject to equal application force and outwards launches simultaneously, arrive maximal degree angular region when adjusting back, 5. spring pin ejects, wing is stoped again to fold, now left limit sheet 3 is engaged with right flank 6, right limit sheet 7 is engaged with left wing 1, ensure that both sides wing locks mutually, improve fuselage stability.
Although illustrate and described embodiment of the present utility model, for the ordinary skill in the art, be appreciated that and can carry out multiple change, amendment, replacement and modification to these embodiments when not departing from principle of the present utility model and spirit, scope of the present utility model is by claims and equivalents thereof.
Claims (3)
1. penetrate the wingfold mechanism of unmanned plane for pipe for one kind, comprise left wing (1), it is characterized in that: the right output port of described left wing (1) is provided with rotating shaft (2), the rear of described rotating shaft (2) is provided with right limit sheet (7), the inner side port of described left wing (1) is provided with left limit sheet (3), the top of described rotating shaft (2) is provided with elastic body (4), elastic body pin (5) is arranged on wing and launches crossing, the bottom of described rotating shaft (2) is fixedly connected with right flank (6) by right flank fixed orifice (8), described right flank (6) is connected with left wing (1) by bearing.
2. a kind of wingfold mechanism penetrating unmanned plane for pipe according to claim 1, is characterized in that: described elastic body (4) is spring structure.
3. a kind of wingfold mechanism penetrating unmanned plane for pipe according to claim 1, is characterized in that: described right flank fixed orifice (8) has one at least.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520921343.1U CN205150218U (en) | 2015-11-18 | 2015-11-18 | A wing folding mechanism for managing penetrate unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520921343.1U CN205150218U (en) | 2015-11-18 | 2015-11-18 | A wing folding mechanism for managing penetrate unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205150218U true CN205150218U (en) | 2016-04-13 |
Family
ID=55685936
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520921343.1U Active CN205150218U (en) | 2015-11-18 | 2015-11-18 | A wing folding mechanism for managing penetrate unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205150218U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108146613A (en) * | 2017-12-28 | 2018-06-12 | 西安特种飞行器工程研究院有限公司 | A kind of unmanned plane with retaining mechanism |
| CN108177783A (en) * | 2017-12-28 | 2018-06-19 | 陕西中科博亿电子科技有限公司 | A kind of training type unmanned plane |
| CN108189999A (en) * | 2017-12-28 | 2018-06-22 | 宝鸡特种飞行器工程研究院有限公司 | A kind of split type unmanned plane |
| CN108190003A (en) * | 2017-12-28 | 2018-06-22 | 陕西中科博亿电子科技有限公司 | A kind of unmanned plane with buffer gear |
| CN109367760A (en) * | 2018-09-21 | 2019-02-22 | 北京大翔航空科技有限公司 | A kind of light-duty unmanned plane wing-folding unfolding mechanism |
| CN110834715A (en) * | 2019-10-21 | 2020-02-25 | 中国运载火箭技术研究院 | Missile-borne unmanned aerial vehicle's folding wing |
-
2015
- 2015-11-18 CN CN201520921343.1U patent/CN205150218U/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108146613A (en) * | 2017-12-28 | 2018-06-12 | 西安特种飞行器工程研究院有限公司 | A kind of unmanned plane with retaining mechanism |
| CN108177783A (en) * | 2017-12-28 | 2018-06-19 | 陕西中科博亿电子科技有限公司 | A kind of training type unmanned plane |
| CN108189999A (en) * | 2017-12-28 | 2018-06-22 | 宝鸡特种飞行器工程研究院有限公司 | A kind of split type unmanned plane |
| CN108190003A (en) * | 2017-12-28 | 2018-06-22 | 陕西中科博亿电子科技有限公司 | A kind of unmanned plane with buffer gear |
| CN108189999B (en) * | 2017-12-28 | 2022-04-26 | 宝鸡特种飞行器工程研究院有限公司 | Split type unmanned aerial vehicle |
| CN108190003B (en) * | 2017-12-28 | 2022-07-15 | 陕西中科博亿电子科技有限公司 | Unmanned aerial vehicle with buffer gear |
| CN108146613B (en) * | 2017-12-28 | 2022-07-15 | 西安特种飞行器工程研究院有限公司 | Unmanned aerial vehicle with locking mechanism |
| CN109367760A (en) * | 2018-09-21 | 2019-02-22 | 北京大翔航空科技有限公司 | A kind of light-duty unmanned plane wing-folding unfolding mechanism |
| CN110834715A (en) * | 2019-10-21 | 2020-02-25 | 中国运载火箭技术研究院 | Missile-borne unmanned aerial vehicle's folding wing |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205150218U (en) | A wing folding mechanism for managing penetrate unmanned aerial vehicle | |
| CN103129735B (en) | Three sections of twofold wings | |
| US10513332B2 (en) | Tiltwing aircraft | |
| CN106428525B (en) | A kind of variable sweep angle ejection tandem arrangement rotor flying robot | |
| CN106585984B (en) | Rolling type ornithopter | |
| CN200995782Y (en) | Airplane | |
| CN201604793U (en) | Lifting area-variable fixed wing unmanned aerocraft | |
| CN109606675A (en) | A kind of bionic flying micro-robot based on single crank double rocker mechanism | |
| RU2012132327A (en) | Convert | |
| CN105270619A (en) | Oil-drive variable-pitch quad-rotor unmanned aerial vehicle | |
| CN105059536A (en) | Rotor wing device with variable pitch and multi-rotor-wing aircraft | |
| US10486806B2 (en) | Pivot systems for tiltwing aircraft | |
| CN106143899A (en) | Displacement rotor and include multi-rotor aerocraft and the flying method thereof of this displacement rotor | |
| CN112265631B (en) | Box-type folding wing unmanned aerial vehicle layout capable of realizing modular assembly with variable aspect ratio | |
| CN105059537A (en) | UAV (unmanned aerial vehicle) | |
| CN107600415B (en) | Tilting type high-mobility unmanned aerial vehicle adopting cross-pitch-variable rotor wing structure | |
| CN102963526A (en) | Cycloidal propeller aerial vehicle | |
| CN204433050U (en) | The hardware platform of dynamic four rotor unmanned aircrafts of oil | |
| CN106458317A (en) | Actuator for flight control surface | |
| CN206068131U (en) | The foldable assembly of unmanned plane | |
| CN204452933U (en) | The many rotor wing unmanned aerial vehicles of belt-driving | |
| CN203143002U (en) | Connective wing synchronous variable sweep-mobile mechanism | |
| CN104443353A (en) | Wing-changeable airplane | |
| CN106986005B (en) | Tilting structure of oil-driven tilting rotary wing aircraft | |
| CN203767065U (en) | Wing folding mechanism of unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |