CN114379765A - Unmanned aerial vehicle's front wing and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle's front wing and unmanned aerial vehicle Download PDFInfo
- Publication number
- CN114379765A CN114379765A CN202111653206.0A CN202111653206A CN114379765A CN 114379765 A CN114379765 A CN 114379765A CN 202111653206 A CN202111653206 A CN 202111653206A CN 114379765 A CN114379765 A CN 114379765A
- Authority
- CN
- China
- Prior art keywords
- front wing
- aerial vehicle
- unmanned aerial
- wing
- connecting piece
- 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.)
- Pending
Links
- 230000005484 gravity Effects 0.000 description 12
- 229910000831 Steel Inorganic materials 0.000 description 7
- 239000010959 steel Substances 0.000 description 7
- 238000009434 installation Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 239000002131 composite material Substances 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- 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
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The application relates to a front wing of an unmanned aerial vehicle and the unmanned aerial vehicle. The front wing of unmanned aerial vehicle includes: the two ends of the supporting rod are respectively provided with a mounting hole; the two front wing main bodies are respectively arranged at two sides of the supporting rod; the first connecting piece is arranged at the wing root of the front wing main body and penetrates into the mounting hole of the supporting rod. This application is adjusted the front and back position of unmanned aerial vehicle's aerodynamic focus through the front wing for unmanned aerial vehicle's focus and focus distance keep in reasonable scope, thereby make the aircraft can adapt to more operating condition.
Description
Technical Field
The application relates to the field of aviation equipment, especially relates to an unmanned aerial vehicle's front wing and unmanned aerial vehicle.
Background
A compound wing aircraft refers to an aircraft having both multiple rotors and fixed wings, for example, 4 lift propellers are used to realize vertical take-off and landing in the form of multiple rotors, and 1 thrust/drag propeller and wing are used to realize horizontal flight.
Composite wing aircraft also need to meet the design criteria for fixed wing aircraft pitching moment characteristics. Stability requirements require that the aircraft center of gravity be in front of the focal point and that the distance between the two be moderate. The large focal distance of the center of gravity can cause large low head moment, even exceed the balancing capability of an elevator, and the airplane is out of control; and too small a distance between the two would result in insufficient longitudinal stability and the aircraft would be susceptible to over-maneuvering. The trim requirement generally requires reasonable installation angles of wings and empennages and sufficient efficiency of pitching control surfaces, so that pitching moment balance can be realized in the whole flight envelope.
Due to the compact structure of the composite wing aircraft, when the configuration is changed, such as loading loads with different weights at the nose, increasing or decreasing the weight of a battery, and the like, the front and back positions of the gravity center of the aircraft are easy to change drastically, and the gravity center is difficult to adjust by adjusting the arrangement of equipment, so that only a new fuselage or a new empennage is redesigned to match the configuration change.
Disclosure of Invention
Based on the above problem, this application provides an unmanned aerial vehicle's front wing and unmanned aerial vehicle, adjusts unmanned aerial vehicle's pneumatic focus front and back position through the front wing for unmanned aerial vehicle's focus and focus distance keep at reasonable scope.
An embodiment of the present application provides a front wing of an unmanned aerial vehicle, including: the two ends of the supporting rod are respectively provided with a mounting hole; the two front wing main bodies are respectively arranged on two sides of the supporting rod; the first connecting piece is arranged at the wing root of the front wing main body and penetrates into the mounting hole of the supporting rod.
According to some embodiments of the application, unmanned aerial vehicle's front wing still include locking structure, locking structure is used for locking first connecting piece with the connection of bracing piece.
According to some embodiments of the present application, the front wing of the unmanned aerial vehicle further comprises a second connecting member, and the second connecting member is disposed at the wing root of the front wing main body.
According to some embodiments of the present application, a ratio of a tip chord length to a root chord length of the front wing body is 0.4 to 0.9.
According to some embodiments of the present application, the aspect ratio of the front wing body is 1.5 ~ 5.
According to some embodiments of the application, the leading and trailing edge contours of the front wing body are both straight or curved lines with sweep back.
According to some embodiments of the present application, the relative thickness of the front wing body is between 6% and 24%.
An embodiment of the present application provides an unmanned aerial vehicle, including: a body; the front wing of the drone as described above; wherein, the bracing piece sets up in on the fuselage.
According to some embodiments of this application, when unmanned aerial vehicle's front wing includes the second connecting piece, be provided with on the fuselage with the connecting hole that the second connecting piece corresponds.
The front wing is installed on the unmanned aerial vehicle, can generate strong head raising moment, and can balance head lowering moment caused by increased load of the nose, so that the aircraft can adapt to more working states; the front wings with different sizes can adjust the aerodynamic focus of the unmanned aerial vehicle, match with the change of the gravity center caused by different loads, and ensure the reasonable relative position between the aerodynamic focus and the gravity center; the front wing has simple installation form and can be quickly disassembled.
Drawings
In order to more clearly illustrate the technical solutions of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for a person skilled in the art to obtain other drawings based on these drawings without exceeding the protection scope of the present application.
Fig. 1 is a schematic view of a drone according to an embodiment of the present application;
FIG. 2 is a schematic view of a front wing of an embodiment of the present application;
FIG. 3 is a schematic view of a support pole according to an embodiment of the present disclosure;
FIG. 4 is a schematic view of a locking mechanism of an embodiment of the present application;
FIG. 5 is a schematic view of a front wing body of an embodiment of the present application;
FIG. 6 is a diagram illustrating the analysis and calculation of pitching moment after the front wing is added according to the embodiment of the present application;
fig. 7 is a graph showing an analysis calculation of lift force after the front wing is attached.
Detailed Description
The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, not all, of the embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
The compound wing unmanned aerial vehicle is compact in structure, and when the configuration changes, for example, the aircraft nose carries loads of different weights, increases and decreases battery weight, the sharp change in the front and back position of the aircraft center of gravity easily occurs, and it is difficult to adjust the center of gravity through adjusting device arrangement, resulting in the distance between the center of gravity and the focus of the unmanned aerial vehicle to exceed the allowable range. The application the focus be unmanned aerial vehicle's pneumatics focus.
As shown in fig. 1, the present embodiment provides a compound-wing drone, which includes a front wing 1, a fuselage 2, a fixed wing 3, a tail stay 4, and a tail 5. Wherein, the front wing 1, the fixed wing 3 and the tail wing brace rod 4 are all connected with the fuselage 2, and the tail wing 5 is connected with the tail wing brace rod 4. The propeller of the drone is not shown in fig. 1.
As shown in fig. 2, the front wing 1 of the drone includes a support bar 11, a front wing body 12, and a first connector 13.
As shown in fig. 3, the support rod 11 of the front wing 1 is disposed inside the fuselage 2, and the support rod 11 is fixedly connected to the fuselage 2. The support rod 11 is generally cylindrical, mounting holes 111 are respectively formed at two ends of the support rod 11, and the mounting holes 111 extend along the axis of the support rod 11. Alternatively, the mounting holes 111 at both ends of the support bar 11 may communicate.
The number of the front wing main bodies 12 is two, the two front wing main bodies 12 are respectively arranged on two sides of the supporting rod 11, and the front wing main bodies 12 are connected with the supporting rod 11, so that the two front wing main bodies 12 are respectively positioned on two sides of the fuselage 2. The front wing body 12 can generate a strong head-up moment when flying. The front wing body 12 is similar in structure to a conventional fixed wing and includes a skin and a reinforcing structure located inside the skin.
The first connecting member 13 is disposed at the wing root of the front wing body 12, and the first connecting member 13 penetrates the mounting hole 111 of the supporting rod 11, so that the front wing body 12 is connected with the supporting rod 11. In this embodiment, the first connecting member 13 is a cylindrical joint that fits into the mounting hole 111.
The front wing 1 of the present embodiment is simple in structure and can be quickly disassembled and assembled. After the front wing 1 of the unmanned aerial vehicle is installed, the front wing 1 can generate a strong head raising moment, and a head lowering moment caused by the increase of the load of a nose can be balanced, so that the unmanned aerial vehicle can adapt to more working states. The front wing main body 12 with various sizes can be designed according to the needs, and the front wing main body 12 with the proper size can be replaced according to different load weights, so that the requirements of stability and balancing of different load weights are met.
As shown in fig. 4, according to an optional technical solution of the present application, the front wing 1 of the drone further includes a locking structure, and the locking structure is used for locking the connection between the first connecting piece 13 and the support rod 11.
In this embodiment, the locking structure is a spring locking structure. A blind hole 131 is arranged on the first connecting piece 13, a steel ball 132 is slidably arranged in the blind hole 131, and a spring 133 is arranged between the steel ball 132 and the bottom surface of the blind hole 131. The diameter of the opening of blind bore 131 is slightly less than the diameter of steel ball 132 so that steel ball 132 can only partially extend out of blind bore 131. The urging force of the spring 133 causes the steel ball 132 to move away from the bottom surface of the blind hole 131.
The side wall of the support bar 11 is provided with a positioning hole 112, and the positioning hole 112 is communicated with the mounting hole 111. The first connecting piece 13 is inserted into the mounting hole 111, and the steel ball 132 is clamped into the positioning hole 112, so that the first connecting piece 13 is connected and locked with the support rod 11. When the first connecting piece 13 needs to be separated from the supporting rod 11, the steel ball 132 is pressed to withdraw the first connecting piece 13 from the mounting hole 111.
According to an optional technical scheme of this application, unmanned aerial vehicle's front wing 1 still includes second connecting piece 14, and second connecting piece 14 sets up in the wing root of front wing main part 12. In this embodiment, the second connecting member 14 is located on the rear side of the first connecting member 13. In this embodiment, the second connecting member 14 is a cylindrical joint, and the body 2 is provided with a connecting hole corresponding to the second connecting member 14. The stability of the connection of the front wing 1 and the body 2 can be improved by inserting the second connecting member 14 into the connecting hole.
As shown in fig. 5, in the present embodiment, the ratio of the tip chord length C1 to the root chord length C0 of the front wing main body 12 is 0.4 to 0.9 as C1/C0. The aspect ratio of the front wing main body 12 is 1.5-5. The leading edge contour line 121 and the trailing edge contour line 122 of the front wing main body 12 are both straight lines or arcs with backswept. The airfoil profile of the front wing body 12 should be a cambered airfoil profile. The relative thickness of the front wing body 12 is between 6% and 24%. The parameter range can better improve the aerodynamic efficiency and the structural load carrying capacity of the front wing 1.
The design method of the front wing 1 of the present embodiment includes:
1. and (3) performing aerodynamic calculation on the unmanned plane without the front wing by adopting a CFD (computational fluid dynamics) method to obtain the aerodynamic focus position of the unmanned plane.
2. And (4) carrying out gravity center calculation on the unmanned aerial vehicle, and calculating the required pneumatic focus movement amount and the pitching moment zero value adjustment amount according to the pitching operation and stability requirements in the flight envelope of the unmanned aerial vehicle.
3. Designing an initial front wing shape and installation angle scheme, and after integrating with the unmanned aerial vehicle shape, performing CFD analysis according to the method in the step 1 to obtain the focal position.
4. And (3) repeating the step (2) after considering the weight of the front wing, finishing the iteration if the pitching control and the stability of the airplane are met, otherwise, adjusting the appearance and the installation angle scheme of the front wing again, and iterating the steps (1) and (2) until the pitching control and the stability requirements of the unmanned aerial vehicle are met.
As shown in fig. 6 and 7, comparing the unmanned aerial vehicle with the front wing and the unmanned aerial vehicle without the front wing, the pitching moment of the unmanned aerial vehicle is significantly affected after the front wing is added, and the maximum lift coefficient of the unmanned aerial vehicle is increased by 3%.
According to the method, the front wing is mounted on the unmanned aerial vehicle, so that a strong head raising moment can be generated, and a head lowering moment caused by the increase of the load of the nose can be balanced, so that the aircraft can adapt to more working states; the front wings with different sizes can adjust the aerodynamic focus of the unmanned aerial vehicle, match with the change of the gravity center caused by different loads, and ensure the reasonable relative position between the aerodynamic focus and the gravity center; the front wing has simple installation form and can be quickly disassembled.
The embodiments of the present application are described in detail above. The principle and the implementation of the present application are explained herein by applying specific examples, and the above description of the embodiments is only used to help understand the technical solutions and the core ideas of the present application. Therefore, the person skilled in the art should, according to the idea of the present application, change or modify the embodiments and applications of the present application based on the scope of protection of the present application. In view of the above, the description should not be taken as limiting the application.
Claims (9)
1. A front wing of a drone, comprising:
the two ends of the supporting rod are respectively provided with a mounting hole;
the two front wing main bodies are respectively arranged on two sides of the supporting rod;
the first connecting piece is arranged at the wing root of the front wing main body and penetrates into the mounting hole of the supporting rod.
2. The front wing of a drone of claim 1, further comprising a locking structure for locking the connection of the first connector to the support bar.
3. The front wing of an unmanned aerial vehicle of claim 1, further comprising a second connecting piece, the second connecting piece is arranged at the wing root of the front wing main body, and the second connecting piece is used for being connected with a fuselage.
4. The front wing of the unmanned aerial vehicle of claim 1, wherein the ratio of the tip chord length to the root chord length of the front wing body is 0.4-0.9.
5. The front wing of the unmanned aerial vehicle of claim 1, wherein the aspect ratio of the front wing main body is 1.5-5.
6. The front wing of a drone of claim 1, wherein the leading and trailing edge contours of the front wing body are both straight or curved lines with sweepback.
7. The front wing of a drone of claim 1, wherein the relative thickness of the front wing body is between 6% and 24%.
8. An unmanned aerial vehicle, comprising:
a body;
a front wing of the drone of any one of claims 1 to 7;
wherein, the bracing piece sets up in on the fuselage.
9. The unmanned aerial vehicle of claim 8, wherein when the front wing of the unmanned aerial vehicle comprises the second connecting piece, a connecting hole corresponding to the second connecting piece is arranged on the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111653206.0A CN114379765A (en) | 2021-12-30 | 2021-12-30 | Unmanned aerial vehicle's front wing and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111653206.0A CN114379765A (en) | 2021-12-30 | 2021-12-30 | Unmanned aerial vehicle's front wing and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114379765A true CN114379765A (en) | 2022-04-22 |
Family
ID=81199996
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111653206.0A Pending CN114379765A (en) | 2021-12-30 | 2021-12-30 | Unmanned aerial vehicle's front wing and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114379765A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1416342A (en) * | 1972-02-04 | 1975-12-03 | Senhenn L A | Fixed-wing dual-purpose aeroplanes |
| CN106892089A (en) * | 2015-12-18 | 2017-06-27 | 波音公司 | For adapting to the empennage of different sizes and shapes and the airframe structure of canard |
| CN207157486U (en) * | 2017-08-05 | 2018-03-30 | 北京海利天梦科技有限公司 | Unmanned plane wing rapid dismounting apparatus |
| CN109572984A (en) * | 2018-11-02 | 2019-04-05 | 海空天科技股份有限公司 | A kind of fast assembly and disassembly mechanism of unmanned plane |
| CN109720564A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | Fixed-wing unmanned plane and its control method with VTOL function |
| CN109850121A (en) * | 2017-11-28 | 2019-06-07 | 天津天航智远科技有限公司 | A kind of small drone wing and fuselage fast assembling disassembling structure |
| CN211766284U (en) * | 2019-08-19 | 2020-10-27 | 西北工业大学 | Foldable VTOL reconnaissance monitoring unmanned aerial vehicle |
-
2021
- 2021-12-30 CN CN202111653206.0A patent/CN114379765A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1416342A (en) * | 1972-02-04 | 1975-12-03 | Senhenn L A | Fixed-wing dual-purpose aeroplanes |
| CN106892089A (en) * | 2015-12-18 | 2017-06-27 | 波音公司 | For adapting to the empennage of different sizes and shapes and the airframe structure of canard |
| CN207157486U (en) * | 2017-08-05 | 2018-03-30 | 北京海利天梦科技有限公司 | Unmanned plane wing rapid dismounting apparatus |
| CN109850121A (en) * | 2017-11-28 | 2019-06-07 | 天津天航智远科技有限公司 | A kind of small drone wing and fuselage fast assembling disassembling structure |
| CN109572984A (en) * | 2018-11-02 | 2019-04-05 | 海空天科技股份有限公司 | A kind of fast assembly and disassembly mechanism of unmanned plane |
| CN109720564A (en) * | 2019-02-13 | 2019-05-07 | 深圳创壹通航科技有限公司 | Fixed-wing unmanned plane and its control method with VTOL function |
| CN211766284U (en) * | 2019-08-19 | 2020-10-27 | 西北工业大学 | Foldable VTOL reconnaissance monitoring unmanned aerial vehicle |
Non-Patent Citations (2)
| Title |
|---|
| 刘虎: "《飞机总体设计》", vol. 1, 31 August 2019, 北京航空航天大学出版社, pages: 60 - 61 * |
| 吴文海: "《飞行综合控制系统》", vol. 1, 31 March 2019, 西安交通大学出版社, pages: 205 - 206 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102282070B (en) | Horizontal stabilising surface of an aircraft | |
| US7455264B2 (en) | Reconfiguration control system for an aircraft wing | |
| US4390150A (en) | Tandem wing airplane | |
| US10625847B2 (en) | Split winglet | |
| EP3034396A1 (en) | Lifting surfaces | |
| US20150183518A1 (en) | Aircraft configuration | |
| US4641796A (en) | Airfoil | |
| JP2013212834A (en) | Performance-enhancing winglet system and method therefor | |
| US10518865B2 (en) | Aircraft horizontal stabilizer design | |
| US9555874B2 (en) | Fixed wing of an aircraft | |
| US8109473B2 (en) | Slotted high lift aerofoils | |
| EP2757039A1 (en) | Fuselage and method for reducing drag | |
| US10196129B2 (en) | Aerofoil and wings for air vehicles | |
| EP3279082A1 (en) | Aircraft having supporting fuselage | |
| CN111003210B (en) | Unmanned aerial vehicle of removable wing verification machine in | |
| CN103538717A (en) | Aircraft lifting surface with variable sweep distribution along the span | |
| CN114379765A (en) | Unmanned aerial vehicle's front wing and unmanned aerial vehicle | |
| CN110550203A (en) | Supersonic aircraft | |
| US10611460B2 (en) | Aircraft vertical stabilizer design | |
| US8474747B2 (en) | Pivoting stabilising surface for aircraft | |
| Kentfield | Case for aircraft with outboard horizontal stabilizers | |
| CN110940481A (en) | Dynamic derivative test model of high-speed wind tunnel of flying wing layout aircraft | |
| CN210503149U (en) | Screw power trim tailless unmanned aerial vehicle | |
| CN219215392U (en) | Unmanned plane | |
| KR102669208B1 (en) | VTOL M-wing configuration |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |