CN201604793U - Lifting area-variable fixed wing unmanned aerocraft - Google Patents
Lifting area-variable fixed wing unmanned aerocraft Download PDFInfo
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- CN201604793U CN201604793U CN2009203149239U CN200920314923U CN201604793U CN 201604793 U CN201604793 U CN 201604793U CN 2009203149239 U CN2009203149239 U CN 2009203149239U CN 200920314923 U CN200920314923 U CN 200920314923U CN 201604793 U CN201604793 U CN 201604793U
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- lifting area
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Abstract
The utility model relates to a lifting area-variable fixed wing unmanned aerocraft which comprises an aerocraft body (1), fixed wings (2) symmetrically arranged on two sides of the aerocraft body and tail wings symmetrically arranged at the tail part of the aerocraft body. Each fixed wing (2) comprises an inner side wing (21) connected with the aerocraft body (1) and an outer side wing (22) connected with the inner side wing (21); and the inner side wing (21) and the aerocraft body (1) as well as the inner side wing (21) and the outer side wing (22) are connected through a folding mechanism (4). The utility model solves the technical problems that the prior fixed wing unmanned aerocraft has narrow cruising speed variation amplitude and can not simultaneously fly at high and low speeds. The utility model greatly improves the flying speed range of the lifting area-variable fixed wing unmanned aerocraft and can improve 60 percent of speed range relative to the conventional configuration, so that the aerocraft has longer cruising duration and can obtain higher flying speed.
Description
Technical field
The utility model relates to a kind of unmanned vehicle, relates in particular to the variable fixed-wing aircraft of a kind of lifting area.
Background technology
At present, existing unmanned fixed-wing aircraft is because aerodynamic arrangement's relative fixed, thereby its flight characteristics also is relative mono-, aerodynamic arrangement is fit to the main suitable high-performance cruise flight of high speed characteristics, what aerodynamic arrangement was fit to low-speed characteristic can't carry out high-speed flight, their cruising speed variation range is subjected to the restriction of aerodynamic arrangement, is difficult to take into account simultaneously high speed, low speed task.
Summary of the invention
Narrow in order to solve existing fixed wing unmanned vehicle flight cruise velocity variations amplitude, can't take into account the technical matters of high speed, low-speed operations simultaneously, the utility model provides a kind of variable fixed-wing unmanned vehicle of lifting area that can significantly widen the speed range of fixed-wing unmanned vehicle cruising flight.
Technical solution of the present utility model is:
The fixed-wing unmanned vehicle that a kind of lifting area is variable, comprise fuselage 1, be symmetricly set on the fixed wing 2 of fuselage both sides and the empennage that is symmetricly set on afterbody, its special character is: described fixed wing 2 comprise with fuselage 1 bonded assembly inboard wing 21 and with inboard wing 21 bonded assembly ala lateralises 22, between described inboard wing 21 and the fuselage 1 and inboard wing 21 be connected by fold mechanism 4 with ala lateralis 22.
Above-mentioned fold mechanism 4 comprises push-pull mechanism 41 and parallelogram linkage 42, the last waling stripe 421 and the ala lateralis 22 of described parallelogram linkage 42 are connected, waling stripe 422 is connected with fuselage 1 under it, the upside connecting rod 423 and the inboard wing 21 of described parallelogram linkage 42 are connected, one end of described push-pull mechanism 41 is connected with fuselage 1, and its other end is connected with upside connecting rod 423 middle parts of parallelogram linkage 42.
Above-mentioned push-pull mechanism 41 is Hydraulic Pump or linear electric motors.
Advantage of the present utility model: the variable fixed-wing unmanned vehicle of the utility model lifting area is designed to fixed wing folding, and being provided with fold mechanism folds and the operation that launches wing, improved the flying speed scope of fixed-wing unmanned vehicle greatly, normal arrangement can improve 60% speed range relatively, make aircraft have long cruise duration, and can obtain higher flying speed.
Description of drawings
Fig. 1 is a structural representation of the present utility model;
The scheme drawing that Fig. 2 launches for the utility model fixed-wing:
Fig. 3 is the folding scheme drawing of the utility model fixed-wing;
Wherein: 1-fuselage, 2-fixed wing, 21-inboard wing, 22-ala lateralis, 4-fold mechanism, 41-push-pull mechanism, 42-parallelogram linkage, the last waling stripe of 421-, waling stripe under the 422-, 423-upside connecting rod, 424-downside connecting rod.
The specific embodiment
Referring to Fig. 1, the fixed-wing unmanned vehicle that the utility model lifting area is variable, comprise fuselage 1, be symmetricly set on the fixed wing 2 of fuselage both sides and the empennage that is symmetricly set on afterbody, fixed wing 2 comprise with fuselage 1 bonded assembly inboard wing 21 and with inboard wing 21 bonded assembly ala lateralises 22, between inboard wing 21 and the fuselage 1 and inboard wing 21 be connected by fold mechanism 4 with ala lateralis 22, fold mechanism 4 comprises push-pull mechanism 41 and parallelogram linkage 42, the last waling stripe 421 and the ala lateralis 22 of parallelogram linkage 42 are connected, waling stripe 422 is connected with fuselage 1 under it, the upside connecting rod 423 and the inboard wing 21 of parallelogram linkage 42 are connected, one end and the fuselage 1 of push-pull mechanism 41 are hinged, and upside connecting rod 423 middle parts of its other end and parallelogram linkage 42 are hinged; Push-pull mechanism 41 can adopt Hydraulic Pump or linear electric motors, changes the position of parallelogram linkage by the extension elongation that changes control stalk.
The utility model passes through the changeable fixed-wing unmanned vehicle of control push-pull mechanism in flight course.Is collapsible with aircraft wing according to its characteristics design under friction speed, and the utilization fold mechanism folds in flight course and stretches.When wing is stretched to big wing, have big lifting area, bigger 1ift-drag ratio is provided, cruise with lower tractive power, can increase cruising radius.Behind wing-folding, wing area and full machine profit are invaded area and are reduced, and the resistance of aircraft reduces, and can realize higher flying speed under equal thrust.
Claims (3)
1. fixed-wing unmanned vehicle that lifting area is variable, comprise fuselage (1), be symmetricly set on the fixed wing (2) of fuselage both sides and the empennage that is symmetricly set on afterbody, it is characterized in that: described fixed wing (2) comprise with fuselage (1) bonded assembly inboard wing (21) and with inboard wing (21) bonded assembly ala lateralis (22), between described inboard wing (21) and the fuselage (1) and inboard wing (21) be connected by fold mechanism (4) with ala lateralis (22).
2. the fixed-wing unmanned vehicle that lifting area according to claim 1 is variable, it is characterized in that: described fold mechanism 4 comprises push-pull mechanism (41) and parallelogram linkage (42), the last waling stripe (421) of described parallelogram linkage (42) is connected with ala lateralis (22), waling stripe (422) is connected with fuselage (1) under it, the upside connecting rod (423) of described parallelogram linkage (42) is connected with inboard wing (21), one end of described push-pull mechanism (41) is connected with fuselage (1), and its other end is connected with upside connecting rod (423) middle part of parallelogram linkage (42).
3. the fixed-wing unmanned vehicle that lifting area according to claim 2 is variable is characterized in that: described push-pull mechanism (41) is Hydraulic Pump or linear electric motors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203149239U CN201604793U (en) | 2009-11-17 | 2009-11-17 | Lifting area-variable fixed wing unmanned aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203149239U CN201604793U (en) | 2009-11-17 | 2009-11-17 | Lifting area-variable fixed wing unmanned aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201604793U true CN201604793U (en) | 2010-10-13 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009203149239U Expired - Fee Related CN201604793U (en) | 2009-11-17 | 2009-11-17 | Lifting area-variable fixed wing unmanned aerocraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN201604793U (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102991668A (en) * | 2011-09-16 | 2013-03-27 | 赵文志 | Airplane |
| CN103847954A (en) * | 2014-01-29 | 2014-06-11 | 江村 | Telescopic wing |
| CN104853988A (en) * | 2013-01-10 | 2015-08-19 | 深圳市大疆创新科技有限公司 | Transformable aerial vehicle |
| CN104943850A (en) * | 2014-03-27 | 2015-09-30 | 杨文建 | Main wing retractable type fixed wing airplane |
| CN105398564A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Flexible aircraft control method based on wing structure transformation |
| CN105539807A (en) * | 2016-01-15 | 2016-05-04 | 杨汉波 | Deformable airplane with front-rear double propeller and front-rear double wing |
| CN105620721A (en) * | 2016-01-30 | 2016-06-01 | 邢永安 | Small wing face folding mechanism of unmanned aerial vehicle |
| CN107031819A (en) * | 2015-11-18 | 2017-08-11 | 空中客车德国运营有限责任公司 | Folding wing for aircraft and the aircraft with folding wing |
| CN107140218A (en) * | 2017-05-19 | 2017-09-08 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of unmanned air-refueling device and oiling method |
| US9896195B2 (en) | 2014-06-26 | 2018-02-20 | SZ DJI Technology Co., Ltd. | Aerial vehicle and a signal line protection assembly thereof |
| CN103786871B (en) * | 2012-10-30 | 2020-02-11 | 波音公司 | Hinged tilting wing tip |
| CN111746783A (en) * | 2020-07-01 | 2020-10-09 | 西湖大学 | A flank structure and navigation ware for navigation ware |
| CN112193404A (en) * | 2020-10-13 | 2021-01-08 | 上海海事大学 | Z-shaped folding wing variable aircraft |
| WO2021109312A1 (en) * | 2019-12-04 | 2021-06-10 | 中国直升机设计研究所 | Morphing aircraft |
-
2009
- 2009-11-17 CN CN2009203149239U patent/CN201604793U/en not_active Expired - Fee Related
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102991668A (en) * | 2011-09-16 | 2013-03-27 | 赵文志 | Airplane |
| CN103786871B (en) * | 2012-10-30 | 2020-02-11 | 波音公司 | Hinged tilting wing tip |
| US9884681B2 (en) | 2013-01-10 | 2018-02-06 | SZ DJI Technology Co., Ltd. | Aerial vehicle with frame assemblies |
| CN104853988A (en) * | 2013-01-10 | 2015-08-19 | 深圳市大疆创新科技有限公司 | Transformable aerial vehicle |
| US10046844B2 (en) | 2013-01-10 | 2018-08-14 | SZ DJI Technology Co., Ltd. | Aerial vehicle with frame assemblies |
| CN103847954A (en) * | 2014-01-29 | 2014-06-11 | 江村 | Telescopic wing |
| CN103847954B (en) * | 2014-01-29 | 2015-10-07 | 江村 | Telescopic wing |
| CN104943850A (en) * | 2014-03-27 | 2015-09-30 | 杨文建 | Main wing retractable type fixed wing airplane |
| US10513329B2 (en) | 2014-06-26 | 2019-12-24 | SZ DJI Technology Co., Ltd. | Aerial vehicle and a signal line protection assembly thereof |
| US9896195B2 (en) | 2014-06-26 | 2018-02-20 | SZ DJI Technology Co., Ltd. | Aerial vehicle and a signal line protection assembly thereof |
| US11180246B2 (en) | 2014-06-26 | 2021-11-23 | SZ DJI Technology Co., Ltd. | Aerial vehicle and a signal line protection assembly thereof |
| US10227131B2 (en) | 2014-06-26 | 2019-03-12 | SZ DJI Technology Co., Ltd. | Aerial vehicle and a signal line protection assembly thereof |
| CN105398564A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Flexible aircraft control method based on wing structure transformation |
| CN107031819A (en) * | 2015-11-18 | 2017-08-11 | 空中客车德国运营有限责任公司 | Folding wing for aircraft and the aircraft with folding wing |
| CN105539807A (en) * | 2016-01-15 | 2016-05-04 | 杨汉波 | Deformable airplane with front-rear double propeller and front-rear double wing |
| CN105620721B (en) * | 2016-01-30 | 2018-02-23 | 江苏润侃瑞科技有限公司 | A kind of miniature self-service airfoil fold mechanism |
| CN105620721A (en) * | 2016-01-30 | 2016-06-01 | 邢永安 | Small wing face folding mechanism of unmanned aerial vehicle |
| CN107140218A (en) * | 2017-05-19 | 2017-09-08 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of unmanned air-refueling device and oiling method |
| WO2021109312A1 (en) * | 2019-12-04 | 2021-06-10 | 中国直升机设计研究所 | Morphing aircraft |
| CN111746783A (en) * | 2020-07-01 | 2020-10-09 | 西湖大学 | A flank structure and navigation ware for navigation ware |
| CN111746783B (en) * | 2020-07-01 | 2022-07-01 | 西湖大学 | A flank structure and navigation ware for navigation ware |
| CN112193404A (en) * | 2020-10-13 | 2021-01-08 | 上海海事大学 | Z-shaped folding wing variable aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: XI AN WIDE WORLD ZENITH AVIATION TECHNOLOGY CO., L Free format text: FORMER OWNER: XI AN FEIYA AVIATION TECHNOLOGY CO., LTD. Effective date: 20111010 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20111010 Address after: 710075 No. 1101 rose building, science and technology road, hi tech Zone, Shaanxi, Xi'an Patentee after: Xi'an Wide World Zenith Aviation Technology Co., Ltd. Address before: 710075 No. 1101 rose building, science and technology road, hi tech Zone, Shaanxi, Xi'an Patentee before: XiAn Feiya Aviation Technology Co., Ltd. |
|
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20101013 Termination date: 20131117 |