CN206344988U - A kind of unmanned plane - Google Patents
A kind of unmanned plane Download PDFInfo
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- CN206344988U CN206344988U CN201621159387.6U CN201621159387U CN206344988U CN 206344988 U CN206344988 U CN 206344988U CN 201621159387 U CN201621159387 U CN 201621159387U CN 206344988 U CN206344988 U CN 206344988U
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Abstract
The application provides a kind of unmanned plane, wing including central body and with central machine body phase even, central body has a central symmetry plane, and central body has central cross section on the centrally located plane of symmetry, the tip section of centrally located plane of symmetry both sides and the first section being arranged in order from the either side of central symmetry plane to tip section, the second section, the 3rd section and the 4th section；Central body has the external surface shape for the bezier surface set up using central cross section, tip section and first to fourth section as chain of command.The technical scheme provided according to the embodiment of the present application, the 3-d modelling that bezier surface obtains body external surface shape is set up by rationally setting chain of command, and by chain of command；By the computational fluid dynamics simulation to unmanned plane, the distribution situation in the external flow field of analysis machine, so that the fuselage after being optimized, not only possesses enough space containers, and it is smaller by resistance in flight, and produces compared with lift, and aeroperformance is good.
Description
Technical field
The application is related to technical field of aircraft design, and in particular to a kind of unmanned plane.
Background technology
With the fast development of unmanned plane industry, unmanned plane species is more and more, but the aerodynamic arrangement of most of unmanned plane
All it is Conventional pneumatic layout.The unmanned plane of Conventional pneumatic layout does not often consider the aeroperformance of fuselage, cause fuselage resistance compared with
Greatly, pneumatic efficiency is low.Relative to the unmanned plane of normal arrangement, the fuselage of blended wing-body layout unmanned plane is lifting body, with more
Small resistance, can produce bigger lift, possess higher pneumatic efficiency.Under the same conditions, the unmanned plane of this layout has
Higher lifting capacity, longer endurance and voyage.But in traditional blended wing-body layout, the pneumatic efficiency of body need more
Further improve.
Utility model content
In view of drawbacks described above of the prior art or deficiency, expect to provide the nothing that a kind of pneumatic efficiency is high, fuselage resistance is small
It is man-machine.
The application provides a kind of unmanned plane, including central body and the wing with central machine body phase even, and central body has
There is central symmetry plane, central body central cross section, the tip of centrally located plane of symmetry both sides on the centrally located plane of symmetry to cut
Face and the first section being arranged in order from the either side of central symmetry plane to tip section, the second section, the 3rd section and
Four sections；Central body has the Bezier set up using central cross section, tip section and first to fourth section as chain of command
The external surface shape of curved surface.
The technical scheme provided according to the embodiment of the present application, by rationally setting 6 chains of command, and passes through this 6 controls
The 3-d modelling that bezier surface obtains body external surface shape is set up in face, improves the pneumatic efficiency of unmanned plane, reduction fuselage resistance
Power.The application passes through the computational fluid dynamics simulation to unmanned plane, the distribution situation of labor body Flow Field outside, so as to machine
Body contour is modified, the fuselage after being optimized.The unmanned aerial vehicle body finally given not only possesses enough space goods
Case, and it is smaller by resistance in flight, and produce compared with lift, unmanned plane is possessed bigger lifting capacity.
Brief description of the drawings
By reading the detailed description made to non-limiting example made with reference to the following drawings, the application's is other
Feature, objects and advantages will become more apparent upon：
Fig. 1 is the unmanned plane dimensional structure diagram of the embodiment of the present application；
Fig. 2 is the central body overlooking the structure diagram of the unmanned plane of the embodiment of the present application；
Fig. 3 is A-A faces sectional drawing in Fig. 2；
Fig. 4 is B-B faces sectional drawing in Fig. 2；
Fig. 5 is C-C faces sectional drawing in Fig. 2；
Fig. 6 is D-D faces sectional drawing in Fig. 2；
Fig. 7 is E-E faces sectional drawing in Fig. 2；
Fig. 8 is F-F faces sectional drawing in Fig. 2；
The central cross section pressure cloud atlas of the unmanned plane of the application more preferably embodiment when Fig. 9 is air speed 25m/s；
The unmanned plane central cross section upper and lower surface pressure of the application more preferably embodiment is along tangential when Figure 10 is air speed 25m/s
Distribution map.
In figure：1st, central body；2nd, wing；3rd, central cross section；4th, tip section；5th, the first section；6th, the second section；7、
3rd section；8th, the 4th section.
Embodiment
The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining relevant utility model, rather than the restriction to the utility model.Further need exist for explanation
, for the ease of description, the part related to utility model is illustrate only in accompanying drawing.
Describe the application in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Fig. 1, a kind of unmanned plane of the present embodiment offer, including central body 1 and the wing being connected with central body 1 are provided
2, central body 1 has central symmetry plane.
Please further refer to Fig. 2, central body 1 has central cross section 3 on the centrally located plane of symmetry, centrally located symmetrical
The first section 5 for being arranged in order between the tip section 4 and centrally located section 3 and tip section 4 of face both sides, second section
Face 6, the 3rd section 7 and the 4th section 8；A-A faces correspond to the place face of central cross section 3, B-B faces, C-C faces, D-D faces, E- in Fig. 2
E faces, F-F faces correspond respectively to central symmetry plane diagram on the right side of the first section 5, the second section 6, the 3rd section 7, the 4th section
8th, the place face of tip section 4.Central body 1 has using central cross section 3, the section of tip section 4 and first to fourth as control
The external surface shape for the bezier surface that face is set up.
Body external surface shape is obtained by rationally setting 6 chains of command, and bezier surface being set up by 6 chains of command
3-d modelling；Because bezier surface curvature is gradually transition, the surface pressing change of the body so designed is more delayed
With, slow down air-flow separation generation, have preferable aeroperformance and relatively low fuselage resistance.The control of this 4, first to fourth section
Face processed ensure that the change of taper aerofoil profile will not be affected greatly to central body, so design is applied to different demands
Shipping unmanned plane.
It is preferred that, it is laid out using blended wing-body, central body 1 is identical in connection cross sectional shape with wing 2, and keeps
Continual curvature, according to different demands, concrete shape can make corresponding change.
It is preferred that, the wing relative thickness of central body root is 25%~27%, i.e., central body root is maximum thick
Degree and the ratio of chord length are expressed as 25%~27% with percentage, it is ensured that while having larger freight house volume in body, also make
Obtaining fuselage has more preferable aeroperformance.
It is preferred that, the bottom wing face curvature of the central root aerofoil profile of body 1 is less than top airfoil, ensure that larger freight house volume
While central body is obtained lift.
It is preferred that, the centrally located body 1 of freight house is anterior.
It is preferred that, distance is equal between adjacent chain of command.
It is preferred that, the chord length of central cross section 3 be L, in the present embodiment such as L=1257mm, its leading edge apex coordinate for (0,
0,0)；The chord length of tip section 4 is 0.313L~0.383L, and the span distance with central cross section 3 is 0.36L~0.44L；Tip is cut
The leading edge apex coordinate of face 4 is (0.241L~0.295L, 0.313L~0.383L, -0.051L~-0.063L).First section 5,
Second section 6, the 3rd section 7, the chord length of the 4th section 8 be respectively 0.751L~0.917L, 0.487L~0.587L, 0.386L~
0.472L, 0.340L~0.416L, leading edge apex coordinate be respectively (0.387L~0.047L, 0.072L~0.088L ,-
0.011L~-0.013L), (0.148L~0.180L, 0.144L~0.176L, -0.035L~-0.043L), (0.203L~
0.248L, 0.216L~0.264L, -0.049L~-0.059L), (0.228L~0.278L, 0.288L~0.352L, -
0.052L~-0.064L).By rationally set 6 chain of command chord lengths, leading edge vertex position and between central cross section 3 away from
From etc. parameter, improve unmanned plane aeroperformance, relatively low fuselage resistance.
It is preferred that, the concrete shape of central cross section 3 is as shown in Figure 3；Using the leading edge summit of central cross section 3 as origin, with center
The direction that rear end is pointed on the leading edge summit of section 3 is X-axis, using the direction perpendicular to the sensing tip of central cross section 3 section 4 as Y-axis, with
The direction of the plane constituted perpendicular to X-axis and Y-axis is Z axis, in units of the chord length L of central cross section 3, constitutes the side of central cross section 3
The coordinate (X, Y, Z) of each data point of edge is as shown in table 1：
Each data point coordinate value at the composition central cross section of table 1 edge
It is preferred that, the concrete shape in the first section 5 is as shown in Figure 4；Constitute the coordinate of each data point at the edge of the first section 5
(X, Y, Z) is as shown in table 2：
Table 2 constitutes each data point coordinate value of the first section edges
It is preferred that, the concrete shape in the second section 6 is as shown in Figure 5；Constitute the coordinate of each data point at the edge of the second section 6
(X, Y, Z) is as shown in table 3：
Table 3 constitutes each data point coordinate value of the second section edges
It is preferred that, the concrete shape in the 3rd section 7 is as shown in Figure 6；Constitute the coordinate of each data point at the edge of the 3rd section 7
(X, Y, Z) is as shown in the table：
Table 4 constitutes each data point coordinate value of the 3rd section edges
It is preferred that, the concrete shape in the 4th section 8 is as shown in Figure 7；Constitute the coordinate of each data point at the edge of the 4th section 8
(X, Y, Z) is as shown in the table：
Table 5 constitutes each data point coordinate value of the 4th section edges
It is preferred that, the concrete shape in tip section 4 is as shown in Figure 8；Constitute the coordinate of each data point at the edge of tip section 4
(X, Y, Z) is as shown in the table：
Table 6 constitutes each data point coordinate value of tip section edges
Above-mentioned all preferred technical characteristics are combined with basic scheme, a more preferably embodiment is obtained；Please be further
With reference to Fig. 9 and Figure 10, this is more preferably above and below embodiment central cross section pressure cloud atlas and central cross section when respectively illustrating air speed 25m/s
Surface pressing is along tangential distribution map.
It can be seen that central body produces upward lift from Fig. 9 and Figure 10.Calculated, can obtained by fluid mechanical emulation
It is 131N to go out this body to produce lift.The unmanned plane aeroperformance that the application is provided is good, and bearing capacity is strong.
Above description is only the preferred embodiment of the application and the explanation to institute's application technology principle.People in the art
Member should be appreciated that utility model scope involved in the application, however it is not limited to the particular combination of above-mentioned technical characteristic
Technical scheme, while should also cover in the case where not departing from utility model design, by above-mentioned technical characteristic or its equivalent feature
Other technical schemes formed by being combined.Such as features described above has class with (but not limited to) disclosed herein
The technical scheme like formed by the technical characteristic of function carries out replacement mutually.
Claims (15)
1. a kind of unmanned plane, including：Central body and the wing with central machine body phase even, the central body have central symmetry
Face, it is characterised in that
The central body has the central cross section being located on the central symmetry plane, the end positioned at the central symmetry plane both sides
Tip section and the first section being arranged in order from the either side of the central symmetry plane to tip section, the second section, the 3rd
Section and the 4th section；
The central body has the shellfish set up using the central cross section, tip section and first to fourth section as chain of command
The external surface shape of Sai Er curved surfaces.
2. unmanned plane according to claim 1, it is characterised in that the central body is cut with the wing in connection
Face shape is identical, and keeps continual curvature.
3. unmanned plane according to claim 1, it is characterised in that the relative thickness of the aerofoil profile of central body root is 25%
~27%.
4. unmanned plane according to claim 1, it is characterised in that the bottom wing face curvature of central body root aerofoil profile is less than upper
Aerofoil.
5. unmanned plane according to claim 1, it is characterised in that the centrally located front part of a body of freight house.
6. unmanned plane according to claim 1, it is characterised in that distance is equal between the adjacent chain of command.
7. unmanned plane according to claim 6, it is characterised in that the central cross section chord length is L, its leading edge apex coordinate
For (0,0,0)；Tip section chord length is 0.313L~0.383L, and the span distance with central cross section is 0.36L~0.44L；Institute
Tip section leading edge apex coordinate is stated for (0.241L~0.295L, 0.313L~0.383L, -0.051L~-0.063L).
8. unmanned plane according to claim 7, it is characterised in that first section, the second section, the 3rd section,
Four section chord lengths are respectively 0.751L~0.917L, 0.487L~0.587L, 0.386L~0.472L, 0.340L~0.416L.
9. unmanned plane according to claim 8, it is characterised in that first section, the second section, the 3rd section,
Four section leading edge apex coordinates be respectively (0.387L~0.047L, 0.072L~0.088L, -0.011L~-0.013L),
(0.148L~0.180L, 0.144L~0.176L, -0.035L~-0.043L), (0.203L~0.248L, 0.216L~
0.264L, -0.049L~-0.059L), (0.228L~0.278L, 0.288L~0.352L, -0.052L~-0.064L).
10. unmanned plane according to claim 9, it is characterised in that using the central cross section leading edge summit as origin, with institute
State central cross section leading edge summit and point to the direction of rear end for X-axis, to point to the tip section perpendicular to the central cross section
Direction is Y-axis, using the direction of plane that is constituted perpendicular to the X-axis and Y-axis as Z axis, using the central cross section chord length L for singly
Position, the coordinate (X, Y, Z) for constituting each data point at the central cross section edge is as shown in the table：
11. unmanned plane according to claim 10, it is characterised in that each data point of composition first section edges
Coordinate (X, Y, Z) is as shown in the table：
12. unmanned plane according to claim 11, it is characterised in that each data point of composition second section edges
Coordinate (X, Y, Z) is as shown in the table：
13. unmanned plane according to claim 12, it is characterised in that each data point of composition the 3rd section edges
Coordinate (X, Y, Z) is as shown in the table：
14. unmanned plane according to claim 13, it is characterised in that each data point of composition the 4th section edges
Coordinate (X, Y, Z) is as shown in the table：
15. unmanned plane according to claim 14, it is characterised in that each data point of the composition tip section edges
Coordinate (X, Y, Z) is as shown in the table：
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621159387.6U CN206344988U (en) | 2016-11-01 | 2016-11-01 | A kind of unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621159387.6U CN206344988U (en) | 2016-11-01 | 2016-11-01 | A kind of unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206344988U true CN206344988U (en) | 2017-07-21 |
Family
ID=59316566
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621159387.6U Withdrawn - After Issue CN206344988U (en) | 2016-11-01 | 2016-11-01 | A kind of unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206344988U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106564584A (en) * | 2016-11-01 | 2017-04-19 | 顺丰科技有限公司 | Unmanned aerial vehicle |
| CN112849387A (en) * | 2021-01-22 | 2021-05-28 | 西北工业大学 | Flying wing reverse-bending wing section considering power installation platform |
-
2016
- 2016-11-01 CN CN201621159387.6U patent/CN206344988U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106564584A (en) * | 2016-11-01 | 2017-04-19 | 顺丰科技有限公司 | Unmanned aerial vehicle |
| CN106564584B (en) * | 2016-11-01 | 2019-07-23 | 顺丰科技有限公司 | A kind of unmanned plane |
| CN112849387A (en) * | 2021-01-22 | 2021-05-28 | 西北工业大学 | Flying wing reverse-bending wing section considering power installation platform |
| CN112849387B (en) * | 2021-01-22 | 2022-11-08 | 西北工业大学 | Flying wing reverse-bending wing section considering power installation platform |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170721 Effective date of abandoning: 20190723 |