CN106628113A - Wing and fuselage integrated plane - Google Patents
Wing and fuselage integrated plane Download PDFInfo
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- CN106628113A CN106628113A CN201710032658.4A CN201710032658A CN106628113A CN 106628113 A CN106628113 A CN 106628113A CN 201710032658 A CN201710032658 A CN 201710032658A CN 106628113 A CN106628113 A CN 106628113A
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- wing
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- fuselage
- aerofoil profile
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Wind Motors (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a wing and fuselage integrated plane. The wing and fuselage integrated plane comprises a fuselage and wings which are integrated. The wings are located on the left side and the right side of the fuselage. The fuselage has a central symmetry surface, a central cross profile located above the central symmetry surface, and a gravity center cross profile perpendicular to the vertex of the central cross profile. The upper wing surface of the gravity center cross profile is in an upward convex streamline shape with the middle being high and the two sides being low. The lower wing surface of the gravity center cross profile is in a downward concave streamline shape with the middle being low and the two sides being high. The height of the gravity center cross profile on the central symmetry surface is H, the width of the gravity center cross profile is D, and H/D is larger than or equal to 0.7 but smaller than or equal to 0.8. The wing and fuselage integrated plane adopts a novel wing and fuselage integrated layout, namely, smooth transition from the outline of the fuselage to the outlines of the wings, the disturbance resistance is greatly reduced, the internal space of the fuselage is increased at the same time, and the loading capacity is improved. The maximum thickness and the width ratio of the fuselage are controlled, so that the fuselage has a high lift-drag ratio, and the pneumatic performance of the plane is improved.
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
Fusion aircraft.
Background technology
The sixties in 20th century, aircraft designers start the concept for proposing blended wing-body.The characteristic of airplane design is that do not have
There are obvious fuselage and wing connecting line.Fuselage all adopts Airfoil Design as wing, can equally produce lift.Wing body melts
Close design and increased 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. all adopt blended wing-body layout, 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 little so that fly
Row radius is little, and cruising time is short.
The content of the invention
In view of drawbacks described above of the prior art or deficiency, expect to provide that a kind of aeroperformance is good, the wing that bearing capacity is strong
Body merges aircraft.
The application provides a kind of blended wing-body aircraft, including 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 has positioned at the central symmetry plane
On central cross section, perpendicular to the center of gravity section of 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 in the high recessed streamlined in middle low, both sides, cut by the center of gravity
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.
Preferably, 0.76≤H/D≤0.78.
Preferably, the upper limb face curvature in the center of gravity section is more than bottom wing face curvature.
Preferably, the structure in the center of gravity section determines 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.
Preferably, the upper limb face curvature of the central cross section is more than bottom wing face curvature.
Preferably, the wing includes the multiple section aerofoil profiles being slightly arranged side by side from wing root to the wing, the wing have 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.
Preferably, from the wing root to the wing slightly be provided with five section aerofoil profiles, respectively apart from the wing root aerofoil profile
0%th, 22%, 50%, 70%, 80% span distance.
Preferably, the direction from the wing root to the wing slightly, it is the wing root aerofoil profile, five section aerofoil profiles, described
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 °.
Preferably, the direction from the wing root to the wing slightly, it is the wing root aerofoil profile, five section aerofoil profiles, described
The torsion angle of the wing slightly aerofoil profile is followed successively by：1°、0.5°、0°、-0.65°、-1.35°、-2°、-3°.
Preferably, the direction from the wing root to the wing slightly, it is the wing root aerofoil profile, five section aerofoil profiles, described
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.
Preferably, the direction from the wing root to the wing slightly, it is the wing root aerofoil profile, five section aerofoil profiles, described
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, it is using new blended wing-body layout, i.e., outer from fuselage to wing
Shape is seamlessly transitted, and greatly reduces interference drag, while increased internal body space, improves bearing capacity；Control fuselage
Maximum gauge and fuselage width ratio so that fuselage has high lift-drag ratio, improves the aeroperformance of aircraft.It is excellent in embodiment
Choosing limits torsion angle, the chord length of each aerofoil profile of wing, substantially improves the lift-drag ratio of whole machine, improves the cruising time of aircraft.
Description of the drawings
By reading the detailed description made to non-limiting example made with reference to the following drawings, the application other
Feature, objects and advantages will become more apparent upon：
Fig. 1 is the front view of the fuselage of blended wing-body provided in an embodiment of the present invention and wing；
Fig. 2 is the structural representation of fuselage provided in an embodiment of the present invention；
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；
Fig. 5 is the structural representation of wing provided in an embodiment of the present invention；
Fig. 6 is the A-A end view drawings of Fig. 5；
Fig. 7 is the B-B sectional drawings of Fig. 5；
Fig. 8 is the C-C sectional drawings of Fig. 5；
Fig. 9 is the D-D sectional drawings of Fig. 5；
Figure 10 is the E-E sectional drawings of Fig. 5；
Figure 11 is the F-F sectional drawings of Fig. 5；
Figure 12 is the G-G end view drawings of Fig. 5.
Specific 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 related invention, rather than the restriction to the invention.It also should be noted that, in order to
It is easy to description, the part related to invention 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.Below with reference to the accompanying drawings and in conjunction with the embodiments describing the application in detail.
Fig. 1 to Fig. 3 is refer to, the present embodiment provides a kind of blended wing-body aircraft, including the fuselage 1 and machine of blended wing-body
The wing, wing includes being located at the wing 2 of 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 have the centrally located plane of symmetry on central cross section 1-1, perpendicular to the center of gravity section 2-1 of central cross section apex,
M-M faces correspond to central cross section 1-1 places face in Fig. 2；The top airfoil of center of gravity section 2-1 is in the low convex stream in middle high, both sides
It is linear, the lower aerofoil of center of gravity section 2-1 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.
According to the technical scheme that the embodiment of the present application is provided, using new blended wing-body layout, when 0.7≤H/D≤0.8
When, the lift of fuselage can be more satisfactory, and H/D between 0.7～0.8 when, 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, and as H ＜ 0.7D, fuselage profile thickness reduces, the pressure of lower surface
Subtractive is little, causes lift to reduce, and lift-drag ratio coefficient is reduced, and finds through numerical simulation calculation, in the situation of Reynolds number 500000
Under, fuselage during H=0.65D, the fuselage lift than H=0.75D reduces by 13.5%, and lift-drag ratio coefficient reduces 2.1, therefore L
Value should not be too little, it is too little if can affect the aeroperformance of fuselage；As H ＞ 0.8D, maximum gauge H is excessive for fuselage, with
Transition is steeper between wing, easy turbulization, and in the case of Reynolds number 500000, 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 increased, in order to the height for avoiding Transitional And Turbulent Flow, H as far as possible 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 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 determines 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.With reference to Fig. 4, as x=0, y is maximum, as the 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
As H is preferably 32.15dm, height aspect can meet certain load space.
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 blended wing-body aircraft of the present invention, including from wing root 3 to the wing slightly 4 simultaneously
Multiple section aerofoil profiles that row is arranged, wing has with wing root aerofoil profile, the wing slightly aerofoil profile and multiple section aerofoil profiles to be set up as chain of command
Bezier surface external surface shape；The slightly aerofoil profile from wing root aerofoil profile to the wing, the windup-degree of each aerofoil profile is gradually reduced, and respectively
The chord length of individual 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；Slightly locate for the wing in G-G faces
End face, corresponding to the wing slightly aerofoil profile 3-7.
The wing of blended wing-body aircraft provided by the present invention, forms the surface of wing, from wing root by bezier surface
To the wing slightly, wing root aerofoil profile, the windup-degree of five section aerofoil profile, the wing slightly aerofoil profiles are gradually reduced, and the chord length of each aerofoil profile is gradually
Reduce, namely by the restriction to each aerofoil profile torsion angle and chord length so that the wing has good aeroperformance, and lift is obtained
To significantly improving, and resistance is reduced, therefore aircraft payload can be improved using the wing and endurance is lifted.
Further, five section aerofoil profiles are slightly provided with 4 from wing root 3 to the wing, 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 to the wing slightly between 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 actually used, aerofoil profile can be adopted and rise the big aerofoil profile of resistance coefficient, 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, can also according to actual needs from the aerofoil profile of other models, five for enumerating here
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, the torsion angle α of wing root aerofoil profile, 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, the torsion angle α of wing root aerofoil profile, 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, the chord length of wing root aerofoil profile, 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 the 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, reduce resistance.
Further, from wing root 3 to the direction of the wing slightly 4, the chord length of wing root aerofoil profile, 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.
Impact of the present embodiment to the lift of whole machine and resistance be less than 5%, the height of blended wing-body fuselage for giving full play to
The characteristics of lift-drag ratio, whole 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 invention scope involved in the application, however it is not limited to the technology of the particular combination of above-mentioned technical characteristic
Scheme, while also should cover in the case of without departing from the inventive concept, is carried out by above-mentioned technical characteristic or its equivalent feature
Other technical schemes for being combined and being formed.Such as features described above has similar work(with (but not limited to) disclosed herein
The technical scheme that the technical characteristic of energy is replaced mutually and formed.
Claims (11)
1. a kind of blended wing-body aircraft, it is characterised in that including the fuselage and wing of 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 has on the central symmetry plane
Central cross section, perpendicular to the center of gravity section of the central cross section apex；The top airfoil in the center of gravity section in it is middle high, 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 determines：
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 any one of claim 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 be with wing root aerofoil profile, the wing slightly aerofoil profile and multiple section aerofoil profiles
The external surface shape of 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 aircrafts 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 (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710032658.4A CN106628113A (en) | 2017-01-16 | 2017-01-16 | Wing and fuselage integrated plane |
| PCT/CN2017/072079 WO2018129768A1 (en) | 2017-01-16 | 2017-01-22 | Fused wing and body aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710032658.4A CN106628113A (en) | 2017-01-16 | 2017-01-16 | Wing and fuselage integrated plane |
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| Publication Number | Publication Date |
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| CN106628113A true CN106628113A (en) | 2017-05-10 |
Family
ID=58840769
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710032658.4A Pending CN106628113A (en) | 2017-01-16 | 2017-01-16 | Wing and fuselage integrated plane |
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| CN (1) | CN106628113A (en) |
| WO (1) | WO2018129768A1 (en) |
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| CN110318931A (en) * | 2019-05-24 | 2019-10-11 | 中国航天空气动力技术研究院 | A kind of flying wing structure for underwater power generation |
| CN111563295A (en) * | 2020-04-24 | 2020-08-21 | 西北工业大学 | Parameterization method applicable to appearance design of wing body fusion underwater glider |
| CN111581722A (en) * | 2020-04-30 | 2020-08-25 | 中国直升机设计研究所 | Wing body fused transportation helicopter short wing shape design method |
| CN112478127A (en) * | 2020-12-04 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Flying wing unmanned aerial vehicle with geometry twists reverse structure |
| CN114313253A (en) * | 2022-03-03 | 2022-04-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Aerodynamic layout and design method of high lift-drag ratio air-breathing hypersonic aircraft |
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| CN110318931B (en) * | 2019-05-24 | 2020-09-18 | 中国航天空气动力技术研究院 | Flying wing structure for underwater power generation |
| CN111563295A (en) * | 2020-04-24 | 2020-08-21 | 西北工业大学 | Parameterization method applicable to appearance design of wing body fusion underwater glider |
| CN111581722A (en) * | 2020-04-30 | 2020-08-25 | 中国直升机设计研究所 | Wing body fused transportation helicopter short wing shape design method |
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| CN112478127A (en) * | 2020-12-04 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Flying wing unmanned aerial vehicle with geometry twists reverse structure |
| CN114313253A (en) * | 2022-03-03 | 2022-04-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Aerodynamic layout and design method of high lift-drag ratio air-breathing hypersonic aircraft |
| CN114852299A (en) * | 2022-04-30 | 2022-08-05 | 西北工业大学 | Wing body fusion underwater glider with forward swept wing layout |
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