CN112319813A - Sweepforward duck type flying wing pneumatic layout unmanned aerial vehicle - Google Patents
Sweepforward duck type flying wing pneumatic layout unmanned aerial vehicle Download PDFInfo
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- CN112319813A CN112319813A CN202011383595.5A CN202011383595A CN112319813A CN 112319813 A CN112319813 A CN 112319813A CN 202011383595 A CN202011383595 A CN 202011383595A CN 112319813 A CN112319813 A CN 112319813A
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- 241000272525 Anas platyrhynchos Species 0.000 title claims description 14
- 241000272517 Anseriformes Species 0.000 claims abstract description 23
- UJCHIZDEQZMODR-BYPYZUCNSA-N (2r)-2-acetamido-3-sulfanylpropanamide Chemical compound CC(=O)N[C@@H](CS)C(N)=O UJCHIZDEQZMODR-BYPYZUCNSA-N 0.000 claims description 3
- 241001669680 Dormitator maculatus Species 0.000 claims description 3
- 230000007547 defect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 238000007654 immersion Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/12—Canard-type aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a sweepforward canard type flying wing pneumatic layout unmanned aerial vehicle, which comprises a fuselage, and a main wing, an edge wing, a full-motion canard wing and a full-motion vertical tail wing which are connected with the fuselage, wherein the full-motion canard wing and the full-motion vertical tail wing are arranged at the front end of the fuselage, the main wing and the edge wing are arranged at the rear end of the fuselage, the main wing and the fuselage are of an integrated structure, the flying wing pneumatic layout, the canard type pneumatic layout and the sweepforward wing pneumatic layout are integrated, the flight performance of a fixed wing aircraft is better improved, the contradiction between the sweepforward wing pneumatic divergence and the structural quality is solved, and the maximum lift coefficient C of the flying wing layout is solvedlmaxThe problem of undersize and poor pitching maneuverability solves the problem of complex duck-type layout structureThe maneuvering performance, the loading capacity, the low-speed performance and the like of the unmanned aerial vehicle are all greatly improved, and compared with the lift force of a conventional aerodynamic layout fixed-wing unmanned aerial vehicle, the effective load of the unmanned aerial vehicle is improved by 20%, the take-off and landing distance is shortened by 35%, the maximum flight speed is improved by 5%, and the minimum flight speed is reduced by 30%.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a forward-swept duck type flying wing aerodynamic layout unmanned aerial vehicle.
Background
The conventional fixed-wing aircraft, tailless aircraft, three-wing-surface aircraft and the like have the defects of poor low-speed performance, poor take-off and landing performance and insufficient maneuvering performance, and the like.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a forward-swept canard flying wing aerodynamic layout unmanned aerial vehicle, which aims to overcome the defects of poor low-speed performance, poor take-off and landing performance and poor maneuvering performance of a fixed wing unmanned aerial vehicle in the related technology.
The utility model provides a sweepforward duck formula all-wing aircraft aerodynamic configuration unmanned aerial vehicle, includes fuselage and the main wing of being connected with the fuselage, strake wing, move duck wing entirely and move perpendicular fin entirely and locate the front end of fuselage, main wing and strake wing locate the fuselage rear end, the main wing is the all-wing configuration, is connected with the fuselage as integrated into one piece.
Preferably, the length of the fuselage is 650-750 mm.
Preferably, the wingspan of the main wing is 1500-2。
Preferably, the airfoil profile of the main wing is C72, RAF32DOM, NACA6412 or NACA 0012.
Preferably, the main wing has an average aerodynamic chord length of 279.85mm, an aspect ratio of 6.01, a leading edge sweep angle of-27.5 °, and spanwise relative thickness arrangements of 22%, 17%, 14%, 10%.
Preferably, the wingspan of the full-motion duck wing is 440-540mm, and the wing area is 660-860cm2。
Preferably, the sweep angle of the full-motion duck wing is 4.42 degrees, and the dihedral angle is 7 degrees.
The invention has the beneficial effects that:
the invention fuses the aerodynamic layout of the flying wings, the canard aerodynamic layout and the forward swept wing aerodynamic layout, so that the flight performance of the fixed wing aircraft is better improved, the contradiction between the forward swept wing aerodynamic divergence and the structural quality is solved, and the maximum lift coefficient C of the layout of the flying wings is solvedlmaxThe problem of undersize and poor pitching maneuverability is solved, the problem of complex duck-type layout structure is solved, the maneuvering performance, the loading capacity, the low-speed performance and the like of the unmanned aerial vehicle are greatly improved, the effective load of the unmanned aerial vehicle is improved by 20% compared with the lifting force of a conventional aerodynamic layout fixed wing unmanned aerial vehicle, the take-off and landing distance is shortened by 35%, the maximum flying speed is improved by 5%, and the minimum flying speed is reduced by 30%.
Drawings
In order to more clearly illustrate the detailed description of the invention or the technical solutions in the prior art, the drawings that are needed in the detailed description of the invention or the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
Fig. 1 is a schematic structural diagram of a forward-swept canard flying wing aerodynamic layout unmanned aerial vehicle provided by an embodiment of the invention;
fig. 2 is a top view of the forward-swept canard flying wing aerodynamic layout drone shown in fig. 1;
fig. 3 is a front view of the forward-swept canard flying wing aerodynamic layout drone shown in fig. 1.
In the attached drawing, 1-main wing, 2-edge wing, 3-full-motion canard wing, 4-full-motion vertical tail wing and 5-fuselage.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.
It is to be noted that, unless otherwise specified, technical or scientific terms used herein shall have the ordinary meaning as understood by those skilled in the art to which the invention pertains.
The utility model provides a sweepforward duck formula all-wing aircraft pneumatics overall arrangement unmanned aerial vehicle, as shown in fig. 1 to 3, including fuselage 5 and the main wing 1, the strake wing 2 of being connected with fuselage 5, move duck wing 3 and move perpendicular fin 4 entirely and locate the front end of fuselage 5, main wing 1 and strake wing 2 locate 5 rear ends of fuselage, main wing 1 is the winged configuration, is connected as integrated into one piece with fuselage 5.
In the present embodiment, the length of the body 5 is 650-750mm, preferably 650 mm; the wingspan of the main wing 1 is 1500-2Preferably 3745cm2(ii) a The airfoil profile of the main airfoil 1 can be optimized airfoil profiles such as C72, RAF32DOM, NACA6412 or NACA 0012; the average aerodynamic chord length of the main wing 1 is 279.85mm, the aspect ratio is 6.01, the sweepback angle of the front edge is-27.5 degrees, and the spanwise relative thickness is 22%, 17%, 14% and 10%; the wingspan of the full-moving canard 3 is 440-540mm, preferably 440mm, and the wingarea is 660-860cm2Preferably 660cm2(ii) a The sweepback angle of the full-motion duck wing 3 is 4.42 degrees, and the dihedral angle is 7 degrees.
The minimum flying speed of the forward-swept canard flying wing aerodynamic layout unmanned plane provided by the embodiment is preferably 6m/s, the cruising speed is preferably 15m/s, the maximum takeoff weight of the unmanned plane is preferably 6kg, the effective load is preferably 4.5kg, the transition radius is preferably 10km, and the minimum turning radius is preferably 0.75 m.
The working principle of the embodiment is as follows: when the airflow blows from the right front, the airflow firstly passes through the full-motion canard wing 3 and the full-motion vertical tail wing 4 and then flows through the strake wing 2 and the main wing 1. In the process, the full-motion vertical tail wing 4 plays a role in stabilizing the course of the unmanned aerial vehicle, meanwhile, the incoming airflow is rectified, the incoming airflow does not flow in a spreading direction when flowing through the main wing 1 and the strake wing 2, the full-motion canard wing 3 has the function of improving the controllable range of the whole machine during pitching operation, meanwhile, the wing tip of the full-motion canard wing 3 where the airflow flows through is used for generating a shedding vortex, the pressure difference of the upper surface of the main wing 1 can be reduced, the energy of the boundary layer of the upper surface of the main wing 1 can be increased, the lift force of the whole machine can be improved, and the load problem can be improved. Meanwhile, the other part of the airflow flowing through the edge strip wing 2 can also generate a shedding vortex, and the shedding vortex is converged with the wing tip vortex and the shedding vortex generated by the canard wing on the inner side of the main wing 1, and simultaneously acts on the main wing 1, so that the boundary layer energy of the inner side part of the main wing 1 is increased, and the effects of delaying the separation degree of the inner side gas and increasing the stalling incidence angle of the aircraft are achieved. The main wing 1 is designed to be in a flying wing configuration, the resistance of the whole aircraft is effectively reduced by utilizing a wing body fusion technology, and meanwhile, the quality of the aircraft is reduced to some extent by the integrated design of the aircraft body 5 and the main wing 1 while the strength is ensured, so that the problem of contradiction between the aerodynamic divergence and the structural quality of forward swept wings is solved.
The embodiment fuses the aerodynamic layout of flying wing, the canard aerodynamic layout and the forward-swept wing aerodynamic layout, so that the flight performance of the fixed-wing aircraft is better improved. The main wing 1 adopts a flying wing structure, so that the structural quality can be reduced, the effective lift area is increased, and the immersion area is reduced. The full-motion canard wing 3 is added in front of the main wing 1, so that the pitching control range of the unmanned aerial vehicle is widened, the maximum lift coefficient of the flying wing is improved, the contradiction between the aerodynamic divergence and the structural quality of the forward swept wing is solved, and the maximum lift coefficient C of the flying wing layout is solvedlmaxThe problem of undersize and poor pitching maneuverability solves the problem of complex duck-type layout structure, and has the advantages of maneuverability, loading capacity, low-speed performance and the likeThe great improvement is that compared with the lift force of a conventional aerodynamic layout fixed wing unmanned aerial vehicle, the effective load of the unmanned aerial vehicle is improved by 20%, the take-off and landing distance is shortened by 35%, the maximum flying speed is improved by 5%, and the minimum flying speed is reduced by 30%.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.
Claims (7)
1. The utility model provides a sweepforward duck formula all-wing aircraft aerodynamic layout unmanned aerial vehicle which characterized in that: including fuselage (5) and main wing (1), strake wing (2) be connected with fuselage (5), move duck wing (3) and move vertical tail wing (4) entirely and locate the front end of fuselage (5), fuselage (5) rear end is located to main wing (1) and strake wing (2), main wing (1) is the all-wing aircraft configuration, is connected as integrated into one piece with fuselage (5).
2. The forward-swept canard flying wing aerodynamic layout drone of claim 1, wherein: the length of the machine body (5) is 650-750 mm.
3. The forward-swept canard flying wing aerodynamic layout drone of claim 2, wherein: the wingspan of the main wing (1) is 1500-2。
4. The forward-swept duck-type flying wing pneumatic layout unmanned aerial vehicle of claim 3, wherein: the wing profile of the main wing (1) is C72, RAF32DOM, NACA6412 or NACA 0012.
5. The forward-swept canard flying wing aerodynamic layout drone of claim 4, wherein: the average pneumatic chord length of the main wing (1) is 279.85mm, the aspect ratio is 6.01, the leading edge sweepback angle is-27.5 degrees, and the spanwise relative thickness arrangement is 22%, 17%, 14% and 10%.
6. The forward-swept canard flying wing aerodynamic layout drone of claim 2, wherein: the wingspan of the full-motion duck wing (3) is 440-540mm, and the wingarea is 660-860cm2。
7. The forward-swept canard flying wing aerodynamic layout drone of claim 6, wherein: the sweepback angle of the full-motion duck wing (3) is 4.42 degrees, and the dihedral angle is 7 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011383595.5A CN112319813A (en) | 2020-12-01 | 2020-12-01 | Sweepforward duck type flying wing pneumatic layout unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011383595.5A CN112319813A (en) | 2020-12-01 | 2020-12-01 | Sweepforward duck type flying wing pneumatic layout unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN112319813A true CN112319813A (en) | 2021-02-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011383595.5A Pending CN112319813A (en) | 2020-12-01 | 2020-12-01 | Sweepforward duck type flying wing pneumatic layout unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119503178A (en) * | 2023-08-25 | 2025-02-25 | 峰飞航空科技(昆山)有限公司 | A drone |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110127384A1 (en) * | 2008-12-01 | 2011-06-02 | Sergey Nikolaevich Afanasyev | Flying vehicle |
| CN102267557A (en) * | 2011-04-27 | 2011-12-07 | 中国航天空气动力技术研究院 | Canard forward-sweep telescoping wing aerodynamic configuration with variable span wing area |
| CN108974361A (en) * | 2017-06-01 | 2018-12-11 | 北京猎鹰无人机科技有限公司 | Canard and the hybrid layout unmanned plane of all-wing aircraft |
| CN108995803A (en) * | 2018-06-08 | 2018-12-14 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of folding Waverider aerodynamic arrangement of supersonic airliner |
| CN110979682A (en) * | 2019-12-30 | 2020-04-10 | 西北工业大学 | A variable area canard forward-swept wing variant aircraft |
| CN210793660U (en) * | 2018-12-25 | 2020-06-19 | 连云港瑞云智能科技有限公司 | Single rotor tail seat type vertical take-off and landing unmanned aerial vehicle |
| CN211107954U (en) * | 2019-06-28 | 2020-07-28 | 南京航空航天大学 | Variant stealth aircraft |
-
2020
- 2020-12-01 CN CN202011383595.5A patent/CN112319813A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110127384A1 (en) * | 2008-12-01 | 2011-06-02 | Sergey Nikolaevich Afanasyev | Flying vehicle |
| CN102267557A (en) * | 2011-04-27 | 2011-12-07 | 中国航天空气动力技术研究院 | Canard forward-sweep telescoping wing aerodynamic configuration with variable span wing area |
| CN108974361A (en) * | 2017-06-01 | 2018-12-11 | 北京猎鹰无人机科技有限公司 | Canard and the hybrid layout unmanned plane of all-wing aircraft |
| CN108995803A (en) * | 2018-06-08 | 2018-12-14 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of folding Waverider aerodynamic arrangement of supersonic airliner |
| CN210793660U (en) * | 2018-12-25 | 2020-06-19 | 连云港瑞云智能科技有限公司 | Single rotor tail seat type vertical take-off and landing unmanned aerial vehicle |
| CN211107954U (en) * | 2019-06-28 | 2020-07-28 | 南京航空航天大学 | Variant stealth aircraft |
| CN110979682A (en) * | 2019-12-30 | 2020-04-10 | 西北工业大学 | A variable area canard forward-swept wing variant aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119503178A (en) * | 2023-08-25 | 2025-02-25 | 峰飞航空科技(昆山)有限公司 | A drone |
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Effective date of registration: 20220627 Address after: 519000 No. 4409, 4th floor, No. 4 plant, No. 32 Nanwan North Road, Nanping, Xiangzhou District, Zhuhai City, Guangdong Province Applicant after: Zhuhai Zhongke Huachuang Technology Co.,Ltd. Address before: Zhuhai College, Beijing University of technology, No.6 Jinfeng Road, Xiangzhou District, Zhuhai City, Guangdong Province Applicant before: Li Yonglin |
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Application publication date: 20210205 |