CN204399478U - A kind of tandem wing formula unmanned plane - Google Patents
A kind of tandem wing formula unmanned plane Download PDFInfo
- Publication number
- CN204399478U CN204399478U CN201420752558.0U CN201420752558U CN204399478U CN 204399478 U CN204399478 U CN 204399478U CN 201420752558 U CN201420752558 U CN 201420752558U CN 204399478 U CN204399478 U CN 204399478U
- Authority
- CN
- China
- Prior art keywords
- wing
- main wing
- front wing
- unmanned plane
- fuselage
- 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
Landscapes
- Toys (AREA)
Abstract
The utility model relates to a kind of tandem wing formula unmanned plane, comprise fuselage, front wing, front wing elevating rudder, main wing, main wing elevating rudder, vertical tail, screw propeller and driving engine, front wing is fixed with in the longitudinal bilateral symmetry of forebody, a front wing elevating rudder is all hinged with at the front wing rear portion of both sides, main wing is fixed with in the longitudinal bilateral symmetry of fuselage afterbody, laterally a vertical tail is fixed with in the middle part of body upper between the main wing of these both sides, back body transverse uniaxial is provided with screw propeller, this screw propeller is rotated by the engine drive being arranged on rear portion in fuselage, main wing and front wing adopt the inline configuration of parallel interval.The utility model adopts the aerodynamic arrangement of the wing formula of tandem, and structure simple layout is reasonable, and load capacity is strong, and can realize short field take-off, landing.
Description
Technical field
The utility model belongs to unmanned plane field, especially a kind of tandem wing formula unmanned plane.
Background technology
In recent years, along with the maturation gradually of robot airplane technology, and the progress of supporting control convenience had possessed the feasibility of technical multiple application.At present, the structure of unmanned plane itself is generally stationary structure, and agent structure is fixed, and the lift that wing produces is not enough, makes the load capacity of unmanned plane limited.
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, structure is simple, degree of stability is high, load capacity is strong tandem wing formula unmanned plane.
The utility model solves its technical matters and takes following technical scheme to realize:
A kind of tandem wing formula unmanned plane, comprise fuselage, front wing, front wing elevating rudder, main wing, aileron, vertical tail, screw propeller and driving engine, front wing is fixed with in the longitudinal bilateral symmetry of forebody, a front wing elevating rudder is all hinged with at the front wing rear portion of both sides, main wing is fixed with in the longitudinal bilateral symmetry of fuselage afterbody, laterally a vertical tail is fixed with in the middle part of body upper between the main wing of these both sides, back body transverse uniaxial is provided with screw propeller, this screw propeller is rotated by the engine drive being arranged on rear portion in fuselage, it is characterized in that: main wing and front wing adopt the inline configuration of parallel interval.
And the stage casing, front wing rear portion of described both sides is all hinged with a front wing elevating rudder.
And the main wing rear portion of described both sides is all hinged with a main wing elevating rudder.
Advantage of the present utility model and good effect are:
1, this unmanned plane is simple for structure, rationally distributed, and aerodynamic arrangement adopts the wing formula of tandem, flies more stable.
2, this unmanned plane structure effectively increases the lifting area of wing, thus strengthens Aircraft Load, strengthens the working ability of unmanned plane, can carry out work by a greater variety of equipment of load.
3, this unmanned plane front wing adopts elevating rudder form, can realize short-rangely taking off, landing, thus more can adapt to less to take off, place of landing, complete corresponding aviation operation.
4, the utility model adopts the aerodynamic arrangement of the wing formula of tandem, and structure simple layout is reasonable, and load capacity is strong, and can realize short field take-off, landing.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model;
Fig. 2 is the upward view of Fig. 1;
Fig. 3 is the left view of Fig. 2.
Detailed description of the invention
Below in conjunction with accompanying drawing, also by specific embodiment, the utility model is described in further detail, and following examples are descriptive, are not determinate, can not limit protection domain of the present utility model with this.
A kind of tandem wing formula unmanned plane, comprise fuselage 6, front wing 1, main wing 3, main wing elevating rudder 4, vertical tail 5, screw propeller 7, driving engine 8, nose-gear 10 and rear alighting gear 9, be described with direction shown in accompanying drawing 1, left is front fuselage, and right is back body; It is the cylindrical structural of the circular arc termination of horizontally set in fuselage main body, front wing 1 is fixed with in the longitudinal bilateral symmetry of forebody, a front wing elevating rudder 2 is all hinged with at the front wing rear portion of both sides, be fixed with main wing 3 in the longitudinal bilateral symmetry of fuselage afterbody, the main wing rear portion of these both sides is all hinged with a main wing elevating rudder 4; Laterally a vertical tail 5 is fixed with in the middle part of body upper between the main wing of these both sides;
Back body transverse uniaxial is provided with screw propeller 7, and this screw propeller is driven by the driving engine 6 being arranged on rear portion in fuselage and rotates; Forebody lower end is provided with a nose-gear 10, and fuselage afterbody lower end is provided with rear alighting gear 9.
Innovative point of the present utility model is:
Main wing and front wing adopt the inline configuration of parallel interval, and the lifting area of front wing makes main wing lifting area increase, thus increases overall lifting area;
All be hinged with a front wing elevating rudder 2 in the stage casing, front wing rear portion of both sides, enhancing elevating control power, shortening is taken off, the landing time.
Nose-gear is provided with elastic buffer structure, avoids hard landing; Shown in accompanying drawing 3, the agent structure of rear alighting gear is a semi arch support, and the cambered surface top of this semi arch support is packed in fuselage lower end, and the two ends of semi arch support are symmetrically installed with roller.
Although disclose embodiment of the present utility model and accompanying drawing for the purpose of illustration, but it will be appreciated by those skilled in the art that: in the spirit and scope not departing from the utility model and claims, various replacement, change and amendment are all possible, therefore, scope of the present utility model is not limited to the content disclosed in embodiment and accompanying drawing.
Claims (3)
1. a tandem wing formula unmanned plane, comprise fuselage, front wing, front wing elevating rudder, main wing, main wing elevating rudder, vertical tail, screw propeller and driving engine, front wing is fixed with in the longitudinal bilateral symmetry of forebody, main wing is fixed with in the longitudinal bilateral symmetry of fuselage afterbody, laterally a vertical tail is fixed with in the middle part of body upper between the main wing of these both sides, back body transverse uniaxial is provided with screw propeller, this screw propeller is rotated by the engine drive being arranged on rear portion in fuselage, forebody lower end is provided with a nose-gear, fuselage afterbody lower end is provided with rear alighting gear, it is characterized in that: main wing and front wing adopt the inline configuration of parallel interval.
2. tandem wing formula unmanned plane according to claim 1, is characterized in that: the stage casing, front wing rear portion of described both sides is all hinged with a front wing elevating rudder.
3. tandem wing formula unmanned plane according to claim 1, is characterized in that: the main wing rear portion of described both sides is all hinged with a main wing elevating rudder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420752558.0U CN204399478U (en) | 2014-12-04 | 2014-12-04 | A kind of tandem wing formula unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420752558.0U CN204399478U (en) | 2014-12-04 | 2014-12-04 | A kind of tandem wing formula unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204399478U true CN204399478U (en) | 2015-06-17 |
Family
ID=53423358
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420752558.0U Expired - Fee Related CN204399478U (en) | 2014-12-04 | 2014-12-04 | A kind of tandem wing formula unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204399478U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828933A (en) * | 2017-02-10 | 2017-06-13 | 北京航空航天大学 | A kind of HAE tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference |
| CN106828872A (en) * | 2017-02-10 | 2017-06-13 | 北京航空航天大学 | The HAE tandem rotor aircraft aerodynamic arrangement of empennage is supported using rear wing high |
| CN110104160A (en) * | 2019-04-24 | 2019-08-09 | 北京航空航天大学 | Double-vane aircraft is folded away from coupling in one kind |
-
2014
- 2014-12-04 CN CN201420752558.0U patent/CN204399478U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828933A (en) * | 2017-02-10 | 2017-06-13 | 北京航空航天大学 | A kind of HAE tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference |
| CN106828872A (en) * | 2017-02-10 | 2017-06-13 | 北京航空航天大学 | The HAE tandem rotor aircraft aerodynamic arrangement of empennage is supported using rear wing high |
| CN106828933B (en) * | 2017-02-10 | 2019-06-18 | 北京航空航天大学 | A kind of high altitude long time tandem rotor aircraft aerodynamic arrangement using upper inverted diherdral difference |
| CN106828872B (en) * | 2017-02-10 | 2019-10-29 | 北京航空航天大学 | Using the high rear wing high altitude long time tandem rotor aircraft aerodynamic arrangement of support empennage |
| CN110104160A (en) * | 2019-04-24 | 2019-08-09 | 北京航空航天大学 | Double-vane aircraft is folded away from coupling in one kind |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204433041U (en) | Vehicle rudder drive mechanism | |
| CN204399478U (en) | A kind of tandem wing formula unmanned plane | |
| CN108473191A (en) | Aircraft | |
| CN204250356U (en) | New fan wing aircraft | |
| CN207860452U (en) | It is a kind of can VTOL connection wing unmanned plane | |
| CN204197290U (en) | A kind of novel tiltrotor aircraft | |
| CN208149591U (en) | It is a kind of to realize the motor-driven wing of promotion rolling by can be changed winglet | |
| CN205022854U (en) | Deformable compound aircraft | |
| CN103482057B (en) | The telescopic wing of aircraft | |
| CN205044954U (en) | Coaxial two thick liquid hybrid gyroplane | |
| CN204802084U (en) | Many rotors plant protection unmanned aerial vehicle | |
| CN204433031U (en) | Portable fast assembling-disassembling unmanned plane | |
| CN203767062U (en) | High-speed fan wing aircraft | |
| CN206502025U (en) | A kind of fixed-wing unmanned plane for adapting to a variety of environment that take off | |
| CN203780794U (en) | Lightweight wing tip structure for protecting wing | |
| CN202666408U (en) | Six-arm model aerial propeller | |
| CN215043672U (en) | Aircraft with four ducts in tilting layout | |
| CN206502016U (en) | A kind of all-wing aircraft unmanned plane of vertical lift | |
| CN204310057U (en) | A kind of fixed-wing unmanned plane | |
| CN203486132U (en) | Telescopic aircraft wing | |
| CN202379089U (en) | Novel unmanned aerial vehicle | |
| CN203698646U (en) | Flying wing imitating rapidly ascending unmanned plane | |
| CN103640695A (en) | Novel vertical lift fixed wing aircraft | |
| CN203528806U (en) | Fixed wing type unmanned aerial vehicle | |
| CN206679262U (en) | VTOL Fixed Wing AirVehicle |
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: 20150617 Termination date: 20171204 |