CN201800914U - Unmanned aerial vehicle platform wing - Google Patents
Unmanned aerial vehicle platform wing Download PDFInfo
- Publication number
- CN201800914U CN201800914U CN201020518656XU CN201020518656U CN201800914U CN 201800914 U CN201800914 U CN 201800914U CN 201020518656X U CN201020518656X U CN 201020518656XU CN 201020518656 U CN201020518656 U CN 201020518656U CN 201800914 U CN201800914 U CN 201800914U
- Authority
- CN
- China
- Prior art keywords
- wing
- aerial vehicle
- pin
- latch
- vehicle body
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Catching Or Destruction (AREA)
Abstract
An unmanned aerial vehicle platform wing comprises wing skin in a honeycomb type thin casing structure made of composites. A girder type pin is arranged in the middle of a connection position of the wing with an aerial vehicle body, a front pin is arranged at the front end of the connection position of the wing with the aerial vehicle body, and a rear pin is arranged at the rear end of the connection position of the wing with the aerial vehicle body. Before operation, an aerial vehicle can take off normally since the wing and the aerial vehicle body are connected through the girder type pin, the front pin and the rear pin, the wing skin in the honeycomb type thin casing structure made of composites enhances impact resistance of the wing and rigidity of the wing at the same time, and the wing is difficult to deform, and has the advantages of simple structure, high strength, convenience in maintenance and low cost.
Description
Technical field
The utility model relates to the wing field of aircraft, is specifically related to a kind of unmanned plane platform wing.
Background technology
Present wing structure complexity, wing cover is smooth, and wing is connected loaded down with trivial details with fuselage, and wing intensity is low, has the inconvenient shortcoming of maintenance.
Summary of the invention
In order to overcome the shortcoming of above-mentioned prior art, the utility model provides a kind of unmanned plane platform wing, and is simple in structure, intensity is high, has advantage easy to maintenance, that cost is low.
In order to achieve the above object, the technical scheme taked of the utility model is:
A kind of unmanned plane platform wing, comprise wing cover 1, wing cover 1 is a cell type composite material thin shell structure, middle part in the junction of wing and fuselage disposes fall crossbeam type latch 2, latch 3 before the front-end configuration of the junction of wing and fuselage has, the backend arrangement in the junction of wing and fuselage has back latch 4.
Principle of work of the present utility model is:
During work, by fall crossbeam type latch 2, preceding latch 3 and back latch 4 wing is connected with fuselage, aircraft gets final product normal flight, and wing cover 1 is a cell type composite material thin shell structure, and increase wing rigidity is not yielding in the time of the anti-impact force of reinforcement wing.
The utility model has the advantages that: because wing is connected with technology simply, reduces manufacturing cost and improve the work forming efficiency, simultaneously easy to maintenance; Owing to utilize shell theory to increase mechanism intensity, and be distributed in the interior external carbuncle of whole wing, increase the wing rigidity when anti-impact force is strengthened by the shell transmission, not yielding, so intensity is big.
Description of drawings
Fig. 1 is a birds-eye view of the present utility model.
Fig. 2 is a lateral plan of the present utility model.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is done detailed description.
See figures.1.and.2, a kind of unmanned plane platform wing, comprise wing cover 1, wing cover 1 is a cell type composite material thin shell structure, middle part in the junction of wing and fuselage disposes fall crossbeam type latch 2, latch 3 before the front-end configuration of the junction of wing and fuselage has, the backend arrangement in the junction of wing and fuselage has back latch 4.
Principle of work of the present utility model is:
During work, by fall crossbeam type latch 2, preceding latch 3 and back latch 4 wing is connected with fuselage, aircraft gets final product normal flight, and wing cover 1 is a cell type composite material thin shell structure, and increase wing rigidity is not yielding in the time of the anti-impact force of reinforcement wing.
In the accompanying drawing: 1 is wing cover; 2 is the fall crossbeam type latch; 3 is front latch; 4 is rear latch.
Claims (1)
1. unmanned plane platform wing, it is characterized in that, comprise wing cover (1), wing cover (1) is a cell type composite material thin shell structure, middle part in the junction of wing and fuselage disposes fall crossbeam type latch (2), front-end configuration in the junction of wing and fuselage has preceding latch (3), and the backend arrangement in the junction of wing and fuselage has back latch (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020518656XU CN201800914U (en) | 2010-09-07 | 2010-09-07 | Unmanned aerial vehicle platform wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020518656XU CN201800914U (en) | 2010-09-07 | 2010-09-07 | Unmanned aerial vehicle platform wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201800914U true CN201800914U (en) | 2011-04-20 |
Family
ID=43870432
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201020518656XU Expired - Fee Related CN201800914U (en) | 2010-09-07 | 2010-09-07 | Unmanned aerial vehicle platform wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201800914U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104249811A (en) * | 2014-08-29 | 2014-12-31 | 中国运载火箭技术研究院 | Aircraft wing suitable for shuttling back and forth aerosphere |
| CN105383683A (en) * | 2015-11-12 | 2016-03-09 | 中国人民解放军国防科学技术大学 | Three-section and impact resisting type UAV (Unmanned Aerial Vehicle) wing |
| CN106585948A (en) * | 2017-02-10 | 2017-04-26 | 哈尔滨工业大学 | Amphibious unmanned aerial vehicle |
| CN106741828A (en) * | 2017-01-10 | 2017-05-31 | 江苏奥派交通装备股份有限公司 | A kind of lightweight low-cost unmanned target drone |
-
2010
- 2010-09-07 CN CN201020518656XU patent/CN201800914U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104249811A (en) * | 2014-08-29 | 2014-12-31 | 中国运载火箭技术研究院 | Aircraft wing suitable for shuttling back and forth aerosphere |
| CN104249811B (en) * | 2014-08-29 | 2017-01-25 | 中国运载火箭技术研究院 | Aircraft wing suitable for shuttling back and forth aerosphere |
| CN105383683A (en) * | 2015-11-12 | 2016-03-09 | 中国人民解放军国防科学技术大学 | Three-section and impact resisting type UAV (Unmanned Aerial Vehicle) wing |
| CN105383683B (en) * | 2015-11-12 | 2017-08-18 | 中国人民解放军国防科学技术大学 | A kind of three-stage shock resistance type unmanned plane wing |
| CN106741828A (en) * | 2017-01-10 | 2017-05-31 | 江苏奥派交通装备股份有限公司 | A kind of lightweight low-cost unmanned target drone |
| CN106585948A (en) * | 2017-02-10 | 2017-04-26 | 哈尔滨工业大学 | Amphibious unmanned aerial vehicle |
| CN106585948B (en) * | 2017-02-10 | 2019-10-29 | 哈尔滨工业大学 | A kind of empty amphibious unmanned vehicle of water |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201800914U (en) | Unmanned aerial vehicle platform wing | |
| CN202609086U (en) | Downwards-throwing popup type parachute opening device of unmanned plane | |
| CN203666965U (en) | Thermal protection mechanism of hypersonic aircraft | |
| CN204776007U (en) | Many rotors of agricultural plant protection unmanned vehicles | |
| CN203323620U (en) | Rain-increasing hail-suppressing rocket projectile recycling device | |
| CN204527638U (en) | Coaxial anti-paddle multiaxis plant protection unmanned plane | |
| CN201086825Y (en) | Wing shaped airplane | |
| CN204433031U (en) | Portable fast assembling-disassembling unmanned plane | |
| CN205203134U (en) | Aircraft bonnet assembly before carbon fiber | |
| CN206031756U (en) | Unmanned aerial vehicle wing | |
| CA2893350C (en) | Tail gas balance system used for an unmanned helicopter | |
| CN211253048U (en) | Unmanned aerial vehicle powered by hydrogen fuel cell | |
| CN204250346U (en) | A kind of anti-rollover airframe steel framework structure | |
| CN203780794U (en) | Lightweight wing tip structure for protecting wing | |
| CN203727648U (en) | Unmanned annunciator | |
| CN102765471B (en) | Wing surface root rib and capsule section longitudinal beam integrated structure of guided missile | |
| CN202379089U (en) | Novel unmanned aerial vehicle | |
| CN203638095U (en) | Unmanned mapping machine | |
| CN204926211U (en) | Ejection seat parameter record appearance | |
| CN202703884U (en) | Integration structure of missile airfoil rib and cabin longitudinal beam | |
| KR101883986B1 (en) | Reconfigurable Modular Prefabricated UAV | |
| CN204776002U (en) | Undercarriage is receive and release in unmanned aerial vehicle pneumatics | |
| CN202115699U (en) | Fighter plane with inflated wings for aircraft carrier | |
| CN203043552U (en) | Mechanical arm of model airplane central spiral frame | |
| CN203255352U (en) | Unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110420 Termination date: 20130907 |