CN206537485U - Blended wing-body aircraft - Google Patents
Blended wing-body aircraft Download PDFInfo
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- CN206537485U CN206537485U CN201720048984.XU CN201720048984U CN206537485U CN 206537485 U CN206537485 U CN 206537485U CN 201720048984 U CN201720048984 U CN 201720048984U CN 206537485 U CN206537485 U CN 206537485U
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Abstract
This application discloses the fuselage and wing of a kind of blended wing-body aircraft, including blended wing-body, wing includes the wing positioned at the fuselage left and right sides；Fuselage has central symmetry plane；Fuselage has the central cross section on the centrally located plane of symmetry, the center of gravity section perpendicular to central cross section apex；The top airfoil in center of gravity section is in the low convex streamlined in middle high, both sides, and the lower aerofoil in center of gravity section is in the high recessed streamlined in middle low, both sides, and height of the center of gravity section on central symmetry plane is H, and the width in center of gravity section is D, wherein 0.7≤H/D≤0.8.Blended wing-body aircraft provided herein, is laid out using new blended wing-body, i.e., the profile from fuselage to wing is seamlessly transitted, and greatly reduces interference drag, while adding internal body space, improves bearing capacity；Control the maximum gauge of fuselage and the width ratio of fuselage so that fuselage has high lift-drag ratio, improve the aeroperformance of aircraft.
Description
Technical field
The disclosure relates generally to aviation aircraft technical field, and in particular to a kind of unmanned plane, more particularly to a kind of wing body
Merge aircraft.
Background technology
In the 1960s, aircraft designers start to propose the concept of blended wing-body.The characteristic of airplane design is that do not have
There are obvious fuselage and wing connecting line.Fuselage can equally produce lift with all using Airfoil Design wing.Wing body melts
Close design and add body space, aircraft can obtain more preferable aeroperformance, reduce flight resistance, most third generation Supersonics
Fast fighter plane such as F-15, F-16, " phantom " 2000, meter Ge -29, Soviet Union -27 etc. are all laid out using blended wing-body, U.S.'s future wing body
Fusion concept aircraft X-48B is trial application of the blended wing-body layout in terms of passenger plane.
The layout of existing blended wing-body aircraft, causes load-carrying not big enough；And flight resistance is big, lift is small so that fly
Row radius is small, and cruising time is short.
Utility model content
In view of drawbacks described above of the prior art or deficiency, expect to provide the wing that a kind of aeroperformance is good, bearing capacity is strong
Body merges aircraft.
The application provides a kind of blended wing-body aircraft, includes the fuselage and wing of blended wing-body, and the wing includes being located at
The wing of the fuselage left and right sides；The fuselage has central symmetry plane；The fuselage, which has, is located at the central symmetry plane
On central cross section, the center of gravity section perpendicular to the central cross section apex；The top airfoil in the center of gravity section in it is middle high,
The low convex streamlined in both sides, the lower aerofoil in the center of gravity section is in the high recessed streamlined in middle low, both sides, and the center of gravity is cut
Height of the face on the central symmetry plane is H, and the width in the center of gravity section is D, wherein 0.7≤H/D≤0.8.
It is preferred that, 0.76≤H/D≤0.78.
It is preferred that, the upper limb face curvature in the center of gravity section is more than bottom wing face curvature.
It is preferred that, the structure in the center of gravity section is determined according to below equation：
Y=0.0003x3-0.0024x2+ 0.0742x+H,
Wherein x represents the vertical range away from the central cross section, 0≤x≤D/2；Y represents the center of gravity at corresponding x
The height in section.
It is preferred that, the upper limb face curvature of the central cross section is more than bottom wing face curvature.
It is preferred that, the wing includes multiple section aerofoil profiles for being slightly arranged side by side from wing root to the wing, the wing with
Wing root aerofoil profile, the wing slightly aerofoil profile and the external surface shape that multiple section aerofoil profiles are the bezier surface that chain of command is set up；
From the wing root aerofoil profile to the wing slightly aerofoil profile, the windup-degree of each aerofoil profile is gradually reduced, and each aerofoil profile
Chord length is gradually reduced.
It is preferred that, from the wing root to the wing slightly provided with five section aerofoil profiles, respectively apart from the wing root aerofoil profile
0%th, 22%, 50%, 70%, 80% span distance.
It is preferred that, it is the wing root aerofoil profile, five section aerofoil profiles, described from direction of the wing root to the wing slightly
The torsion angle of the wing slightly aerofoil profile is followed successively by：0.5 °~1.5 °, 0.2 °~0.7 °, -0.2 °~0.2 °, -0.8 °~-0.5 °, -1.5 °
~-1.0 °, -2.2 °~-1.2 °, -3.5 °~-2.6 °.
It is preferred that, it is the wing root aerofoil profile, five section aerofoil profiles, described from direction of the wing root to the wing slightly
The torsion angle of the wing slightly aerofoil profile is followed successively by：1°、0.5°、0°、-0.65°、-1.35°、-2°、-3°.
It is preferred that, it is the wing root aerofoil profile, five section aerofoil profiles, described from direction of the wing root to the wing slightly
The chord length of the wing slightly aerofoil profile is followed successively by：P, 0.80P~0.85P, 0.72~0.76P, 0.58P~0.62P, 0.5P~0.55P,
0.46P~0.49P, 0.3P~0.35P.
It is preferred that, it is the wing root aerofoil profile, five section aerofoil profiles, described from direction of the wing root to the wing slightly
The chord length of the wing slightly aerofoil profile is followed successively by：P、0.83P、0.75P、0.6P、0.53P、0.48P、0.33P.
Blended wing-body aircraft provided herein, is laid out using new blended wing-body, i.e., outer from fuselage to wing
Shape is seamlessly transitted, and greatly reduces interference drag, while adding internal body space, improves bearing capacity；Control fuselage
Maximum gauge and fuselage width ratio so that fuselage has a high lift-drag ratio, improves the aeroperformance of aircraft.It is excellent in embodiment
Choosing limits the torsion angle of each aerofoil profile of wing, chord length, substantially improves the lift-drag ratio of complete machine, improves the cruising time of aircraft.
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：
The fuselage for the blended wing-body that Fig. 1 provides for the utility model embodiment and the front view of wing；
The structural representation for the fuselage that Fig. 2 provides for the utility model embodiment；
Fig. 3 is M-M faces sectional drawing in Fig. 2；
Fig. 4 is the width and the graph of a relation of thickness in the center of gravity section shown in Fig. 3；
The structural representation for the wing that Fig. 5 provides for the utility model embodiment；
Fig. 6 is Fig. 5 A-A end view drawings；
Fig. 7 is Fig. 5 B-B sectional drawings；
Fig. 8 is Fig. 5 C-C sectional drawings；
Fig. 9 is Fig. 5 D-D sectional drawings；
Figure 10 is Fig. 5 E-E sectional drawings；
Figure 11 is Fig. 5 F-F sectional drawings；
Figure 12 is Fig. 5 G-G end view drawings.
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.
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the application can phase
Mutually combination.Describe the application in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
Fig. 1 to Fig. 3 is refer to, the present embodiment provides a kind of blended wing-body aircraft, includes the fuselage 1 and machine of blended wing-body
The wing, wing includes the wing 2 positioned at the left and right sides of fuselage 1, and fuselage 1 has central symmetry plane, the length of the fuselage 1 of blended wing-body
For D；Fuselage 1 has central cross section 1-1, the center of gravity section 2-1 perpendicular to central cross section apex on the centrally located plane of symmetry,
M-M faces correspond to face where central cross section 1-1 in Fig. 2；Center of gravity section 2-1 top airfoil is in the low convex stream in middle high, both sides
Linear, center of gravity section 2-1 lower aerofoil is in the high recessed streamlined in middle low, both sides, the maximum of central cross section as shown in Figure 3
Highly it is H, that is, maximum gauges of the H for the fuselage of blended wing-body.It can be seen that height of the center of gravity section 2-1 on central symmetry plane
For H, the width in center of gravity section is D, wherein 0.7≤H/D≤0.8.
The technical scheme provided according to the embodiment of the present application, is laid out using new blended wing-body, when 0.7≤H/D≤0.8
When, the lift of fuselage can be more satisfactory, and H/D is when between 0.7~0.8, lift first increases and then decreases；H/D is preferably
0.7th, 0.71,0.72,0.73,0.74,0.75,0.76,0.77,0.78,0.79,0.8, H/D is between 0.76~0.78, fuselage
Lift there is maximum.For example Reynolds number is 500000, as H ＜ 0.7D, and fuselage profile thickness reduces, the pressure of lower surface
Subtractive is small, causes lift to reduce, the reduction of lift-drag ratio coefficient, is found by numerical simulation calculation, in the situation of Reynolds number 500000
Under, fuselage during H=0.65D, the fuselage lift reduction by 13.5% than H=0.75D, lift-drag ratio coefficient reduces 2.1, therefore L
Value should not be too small, it is too small if can influence the aeroperformance of fuselage；As H ＞ 0.8D, fuselage maximum gauge H is excessive, with
Transition is steeper between wing, easy turbulization, in the case of Reynolds number 500000, and the streamline of otherwise smooth is after fuselage
Edge becomes disorderly lines, and this is obvious turbulent area, and the generation of turbulent area can significantly reduce the lift of fuselage,
And pressure drag is added, in order to avoid Transitional And Turbulent Flow as far as possible, H height should not be greater than 0.8D.The maximum of fuselage is thick
0.7≤H/D≤0.8, preferably 0.76≤H/D≤0.78 are designed as between degree H and the length D of fuselage so that fuselage has promotion
Resistance ratio, lifts the aeroperformance of aircraft.
Further, the upper limb face curvature in center of gravity section is more than bottom wing face curvature, ensure that larger load volume
Fuselage 1 is caused to obtain lift simultaneously.
Further, the structure in center of gravity section is determined according to below equation：
Y=0.0003x3-0.0024x2+ 0.0742x+H,
Wherein x represents the vertical range away from central cross section, 0≤x≤D/2；Y represents the height in the center of gravity section at corresponding x
Degree.Reference picture 4, as x=0, y is maximum, the as maximum gauge H of fuselage；Work as x=D/2, y is minimum, as the wing root of wing
The thickness of (junction of fuselage and wing).
Further, the scheme that the present embodiment is provided is applied to shipping unmanned plane or the application in terms of passenger plane, example
If H is preferably 32.15dm, certain load space can be met in terms of height.
Further, the upper limb face curvature lower aerofoil curvature of central cross section, while ensure that larger load volume
So that fuselage 1 obtains lift.
Further, as shown in Fig. 5-Figure 12, the wing of the utility model blended wing-body aircraft, including from wing root 3 to the wing
The slightly 4 multiple section aerofoil profiles being arranged side by side, wing has using wing root aerofoil profile, the wing slightly aerofoil profile and multiple section aerofoil profiles as chain of command
The external surface shape of the bezier surface of foundation；The slightly aerofoil profile from wing root aerofoil profile to the wing, the windup-degree of each aerofoil profile is gradually reduced,
And the chord length of each aerofoil profile is gradually reduced.A-A faces are the end face at wing root in Fig. 1, corresponding to wing root aerofoil profile 3-1；G-G faces are the wing
The end face slightly located, corresponding to the wing slightly aerofoil profile 3-7.
The wing of blended wing-body aircraft provided by the utility model, forms the surface of wing by bezier surface, from
To the wing slightly, wing root aerofoil profile, the windup-degree of five section aerofoil profile, the wing slightly aerofoil profiles are gradually reduced wing root, and the chord length of each aerofoil profile
It is gradually reduced, namely passes through the restriction to each aerofoil profile torsion angle and chord length so that the wing has good aeroperformance, rises
Power is significantly improved, and reduces resistance, therefore can be improved aircraft payload using the wing and be lifted continuation of the journey energy
Power.
Further, from wing root 3 to the wing slightly 4 provided with five section aerofoil profiles, respectively apart from wing root aerofoil profile 0%, 22%,
50%th, 70%, 80% span distance.Each slice location is a section aerofoil profile in Fig. 5, from wing root 3 between the wing slightly 4
Five section aerofoil profiles are followed successively by the first section aerofoil profile 3-2, the second section aerofoil profile 3-3, the 3rd section aerofoil profile 3-4, the 4th section wing
Type 3-5, the 5th section aerofoil profile 3-6.In actual use, the aerofoil profile that aerofoil profile can be big using resistance coefficient is risen, such as from wing root to the wing
Five section aerofoil profiles between slightly can be GOE227, NACA5402, NACA7403, NACA7408, NACA6401, certainly, the wing
The selection of type is not limited solely to this five kinds, and the aerofoil profile of other models, five enumerated here can also be selected according to actual needs
Individual is only to illustrate.Certainly according to actual needs, the section aerofoil profile of other quantity can also be set.
Further, from wing root 3 to the direction of the wing slightly 4, wing root aerofoil profile, the torsion angle α of five section aerofoil profiles, the wings slightly aerofoil profile
It is followed successively by：0.5 °~1.5 °, 0.2 °~0.7 °, -0.2 °~0.2 °, -0.8 °~-0.5 °, -1.5 °~-1.0 °, -2.2 °~-
1.2 °, -3.5 °~-2.6 °.Torsion angle α mentioned here is aerofoil profile leading edge point and trailing edge point line and the angle of horizontal plane.It is logical
The setting of the torsion angle is crossed, lift can be preferably lifted, resistance is reduced.
Further, from wing root 3 to the direction of the wing slightly 4, wing root aerofoil profile, the torsion angle α of five section aerofoil profiles, the wings slightly aerofoil profile
It is followed successively by：1°、0.5°、0°、-0.65°、-1.35°、-2°、-3°.Torsion angle at each aerofoil profile is designed accordingly, can greatly be carried
The triumph of high wing, reduces resistance.
Further, from wing root 3 to the direction of the wing slightly 4, wing root aerofoil profile, the chord length of five section aerofoil profiles, the wings slightly aerofoil profile according to
It is secondary to be：P, 0.80P~0.85P, 0.72~0.76P, 0.58P~0.62P, 0.5P~0.55P, 0.46P~0.49P, 0.3P~
0.35P.That is, the chord length of wing root aerofoil profile is P, respectively apart from wing root aerofoil profile 0%, 22%, 50%, 70%, 80%, 100%
The chord length of aerofoil profile at span distance be respectively 0.80P~0.85P, 0.72~0.76P, 0.58P~0.62P, 0.5P~
0.55P, 0.46P~0.49P, 0.3P~0.35P.By setting chord length, lift can be preferably lifted, resistance is reduced.
Further, from wing root 3 to the direction of the wing slightly 4, wing root aerofoil profile, the chord length of five section aerofoil profiles, the wings slightly aerofoil profile according to
It is secondary to be：P、0.83P、0.75P、0.6P、0.53P、0.48P、0.33P.Chord length at each aerofoil profile is designed accordingly, can greatly be carried
The triumph of high wing, reduces resistance.
Influence of the present embodiment to the lift and resistance of complete machine is less than 5%, the height of blended wing-body fuselage given full play to
The characteristics of lift-drag ratio, complete machine lift-drag ratio is more than 14.0.
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 be equal
Feature be combined formed by other technical schemes.Such as features described above has with (but not limited to) disclosed herein
The technical characteristic for having similar functions carries out technical scheme formed by replacement mutually.
Claims (11)
1. a kind of blended wing-body aircraft, it is characterised in that fuselage and wing including blended wing-body, the wing includes being located at institute
State the wing of the fuselage left and right sides；The fuselage has central symmetry plane；The fuselage, which has, to be located on the central symmetry plane
Central cross section, the center of gravity section perpendicular to the central cross section apex；The top airfoil in the center of gravity section is in middle height, two
The low convex streamlined in side, the lower aerofoil in the center of gravity section is in the high recessed streamlined in middle low, both sides, the center of gravity section
Height on the central symmetry plane is H, and the width in the center of gravity section is D, wherein 0.7≤H/D≤0.8.
2. blended wing-body aircraft according to claim 1, it is characterised in that
0.76≤H/D≤0.78。
3. blended wing-body aircraft according to claim 1, it is characterised in that the upper limb face curvature in the center of gravity section is more than
Bottom wing face curvature.
4. blended wing-body aircraft according to claim 3, it is characterised in that the structure in the center of gravity section is according to following public affairs
Formula is determined：
Y=0.0003x3-0.0024x2+ 0.0742x+H,
Wherein x represents the vertical range away from the central cross section, 0≤x≤D/2；Y represents the center of gravity section at corresponding x
Height.
5. blended wing-body aircraft according to claim 1, it is characterised in that the upper limb face curvature of the central cross section is more than
Bottom wing face curvature.
6. the blended wing-body aircraft according to claim any one of 1-5, it is characterised in that the wing include from wing root to
Multiple section aerofoil profiles that the wing is slightly arranged side by side, the wing have using wing root aerofoil profile, the wing slightly aerofoil profile and multiple section aerofoil profiles as
The external surface shape for the bezier surface that chain of command is set up；
From the wing root aerofoil profile to the wing slightly aerofoil profile, the windup-degree of each aerofoil profile is gradually reduced, and the chord length of each aerofoil profile
It is gradually reduced.
7. blended wing-body aircraft according to claim 6, it is characterised in that from the wing root to the wing slightly be provided with
Five section aerofoil profiles, respectively apart from the span distance of the wing root aerofoil profile 0%, 22%, 50%, 70%, 80%.
8. blended wing-body aircraft according to claim 7, it is characterised in that from direction of the wing root to the wing slightly,
The wing root aerofoil profile, five the section aerofoil profiles, the torsion angles of the wing slightly aerofoil profile are followed successively by：0.5 °~1.5 °, 0.2 °~
0.7 °, -0.2 °~0.2 °, -0.8 °~-0.5 °, -1.5 °~-1.0 °, -2.2 °~-1.2 °, -3.5 °~-2.6 °.
9. blended wing-body aircraft according to claim 8, it is characterised in that from direction of the wing root to the wing slightly,
The wing root aerofoil profile, five the section aerofoil profiles, the torsion angles of the wing slightly aerofoil profile are followed successively by：1°、0.5°、0°、-0.65°、-
1.35°、-2°、-3°。
10. blended wing-body aircraft according to claim 7, it is characterised in that from direction of the wing root to the wing slightly,
The wing root aerofoil profile, five the section aerofoil profiles, the chord lengths of the wing slightly aerofoil profile are followed successively by：P, 0.80P~0.85P, 0.72~
0.76P, 0.58P~0.62P, 0.5P~0.55P, 0.46P~0.49P, 0.3P~0.35P.
11. blended wing-body aircraft according to claim 10, it is characterised in that from side of the wing root to the wing slightly
To the wing root aerofoil profile, five the section aerofoil profiles, the chord lengths of the wing slightly aerofoil profile are followed successively by：P、0.83P、0.75P、0.6P、
0.53P、0.48P、0.33P。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720048984.XU CN206537485U (en) | 2017-01-16 | 2017-01-16 | Blended wing-body aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720048984.XU CN206537485U (en) | 2017-01-16 | 2017-01-16 | Blended wing-body aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN206537485U true CN206537485U (en) | 2017-10-03 |
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ID=59938939
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| CN201720048984.XU Active CN206537485U (en) | 2017-01-16 | 2017-01-16 | Blended wing-body aircraft |
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| Country | Link |
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| CN (1) | CN206537485U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628113A (en) * | 2017-01-16 | 2017-05-10 | 顺丰科技有限公司 | Wing and fuselage integrated plane |
-
2017
- 2017-01-16 CN CN201720048984.XU patent/CN206537485U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628113A (en) * | 2017-01-16 | 2017-05-10 | 顺丰科技有限公司 | Wing and fuselage integrated plane |
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Effective date of registration: 20210722 Address after: 518063 5th floor, block B, building 1, software industry base, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province Patentee after: Fengyi Technology (Shenzhen) Co.,Ltd. Address before: 518061 Intersection of Xuefu Road (south) and Baishi Road (east) in Nanshan District, Shenzhen City, Guangdong Province, 6-13 floors, Block B, Shenzhen Software Industry Base Patentee before: SF TECHNOLOGY Co.,Ltd. |