CN110143282B - Aircraft adopting high aspect ratio double-fuselage flying wing layout - Google Patents
Aircraft adopting high aspect ratio double-fuselage flying wing layout Download PDFInfo
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- CN110143282B CN110143282B CN201910525982.9A CN201910525982A CN110143282B CN 110143282 B CN110143282 B CN 110143282B CN 201910525982 A CN201910525982 A CN 201910525982A CN 110143282 B CN110143282 B CN 110143282B
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- 230000004927 fusion Effects 0.000 claims abstract description 17
- 230000009977 dual effect Effects 0.000 claims 1
- 238000000926 separation method Methods 0.000 claims 1
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 6
- 230000007423 decrease Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
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- 210000001503 joint Anatomy 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
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- B64D27/40—
Abstract
The invention discloses an aircraft adopting a large-aspect-ratio double-fuselage flying wing layout, which comprises two symmetrically arranged fuselages, wherein the two fuselages are connected into a wing body fusion whole through flat wings, and the outer side of each fuselages is respectively connected with an outer wing with the wing body fusion. According to the invention, double-fuselage fusion layout is carried out through the straight wings, the straight wings and the double fuselages form a whole, so that the structural strength of the high-aspect-ratio aircraft is improved, and the structural weight of the high-aspect-ratio aircraft is lighter; the full-aircraft aspect ratio can be improved, so that the aerodynamic efficiency of the aircraft is higher, the flight resistance is smaller, and the energy consumption is lower; the area ratio of the lift force of the whole aircraft can be provided, namely the area of the lift force provided by the surface of the whole aircraft is larger, the area generating resistance is smaller, the flying lift-drag ratio is higher, and the flying time is longer.
Description
Technical Field
The invention relates to the field of aerodynamics, in particular to an aircraft adopting a large aspect ratio double-fuselage flying wing layout.
Background
The aircraft is a middle-hardness force of modern national defense, and is also a symbolism of comprehensive strength such as national economy strength, scientific strength, basic industry and the like. In complex system engineering of aircraft design, pneumatic layout design is a leading officer, is of great importance, directly relates to the arrangement and design of all subsystems, and is also a key factor for each system to be able to play its potential. For high aspect ratio aircraft, the current more common aerodynamic layout schemes are conventional, delta, flying wing, and wing body fusion layouts. To fully exploit the aerodynamic and structural efficiency of the profile layout, these layouts still have some potential for improvement, such as high requirements for wing area, aspect ratio, lift-drag ratio and structural strength of solar aircraft. In a low-speed flight state, the aerodynamic efficiency of the aircraft is mainly determined by the aspect ratio of the whole aircraft, and the structural strength of the aircraft body is higher by adopting the conventional layout, but the aerodynamic efficiency is lower; the triangular wing layout machine body has high structural strength, but low pneumatic efficiency; the integrated layout of the flying wing and the wing body has higher structural strength, but is limited by structural strength and weight, has smaller aspect ratio and lower low-speed aerodynamic efficiency.
Disclosure of Invention
The invention provides an aircraft with a large aspect ratio double-fuselage flying wing layout on the basis of the prior art, and aims of improving the strength of an aircraft body, the aspect ratio of the aircraft and the low-speed aerodynamic efficiency of the aircraft are fulfilled.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
an aircraft adopting a large-aspect-ratio double-fuselage flying wing layout comprises two symmetrically arranged fuselages, wherein the two fuselages are connected into a wing body fusion whole through flat wings, and the outer side of each fuselages is respectively connected with an outer wing of the wing body fusion.
In the technical scheme, the sweepback angle of the straight wing between the two fuselages is 0 degrees.
In the technical scheme, the length of the straight wing accounts for 5% -15% of the extension length of the whole aircraft.
In the technical scheme, the distance between the two fuselage axes accounts for 10% -30% of the whole aircraft.
In the technical scheme, the sweepback angle of the outer wing is 10-30 degrees.
In the technical scheme, the outer side wing tip root ratio is 0.2-0.8.
In the technical scheme, the chord length of the straight wing is 1-2 times of the chord length of the root of the outer wing.
In the above technical scheme, the outer wing wingtip is provided with a wingtip vertical tail.
In summary, due to the adoption of the technical scheme, the beneficial effects of the invention are as follows:
according to the invention, the double-fuselage layout is carried out through the straight wings, the straight wings and the double-fuselage form a whole, so that the structural strength of the high-aspect-ratio aircraft is improved, and the structural weight of the high-aspect-ratio aircraft is lighter;
according to the invention, the double-fuselage layout is performed through the straight wings, so that the whole-fuselage aspect ratio can be improved, the aerodynamic efficiency of the aircraft is higher, the flight resistance is smaller, and the energy consumption is lower;
the invention can provide the area proportion of the lift force of the whole aircraft, namely the area of the lift force provided by the surface of the whole aircraft is larger, the area for generating resistance is smaller, the flying lift-drag ratio is higher and the flying time is longer through the layout of the double-aircraft body flying wings.
Drawings
The invention will now be described by way of example and with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of a high aspect ratio double fuselage flying wing layout;
FIG. 2 is a schematic representation of one implementation of the present invention;
wherein: 1 is a straight wing, 2 is an inboard wing body fusion segment, 3 is a fuselage, 4 is an outboard wing (swept wing), 5 is an outboard wing body fusion segment, and 6 is a wingtip tail.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
Any feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise. That is, each feature is one example only of a generic series of equivalent or similar features, unless expressly stated otherwise.
Example 1
In this embodiment, two symmetrically arranged bodies 3 are adopted, and from the perspective of plane projection, as shown in fig. 1, the two bodies 3 are symmetrically distributed and are arranged in parallel with each other on the same horizontal plane. The straight wing 1 is used for connecting two airframes 3, two ends of the straight wing 1 are respectively connected to one airframe 3 through an inner wing body fusion section 2, and an outer wing 4 is connected to the outer side of each airframe 3 through an outer wing body fusion section 5.
Compared with the existing single-body layout, the fuselage layout of the implementation has the advantages that due to the adoption of the double fuselages and the straight wings, the inner space of the two fuselages is increased, so that the overall structure layout is more convenient, and the overall structure efficiency of the two fuselages is higher than that of the existing single-body layout.
For the embodiment, in order to realize convenient processing and manufacturing of the straight wing, the wing bearing structure is simple, so that the wing is not constrained by a complex surface, the wing is beneficial to being in butt joint with a fuselage, and the sweepback angle of the straight wing is set to be 0 degrees.
In this embodiment, in order to reduce the drag of a straight wing in the air, the lift area is increased, and wing body fusion is performed between Ping Zhiyi and the fuselage.
Under the condition that the whole aircraft has a certain length, if the proportion of the straight wing to the total length is too small, the lift force area of the fusion section of the straight wing and the inner wing body is reduced, the lift force area of the outer wing is greatly increased, and the structure of the outer wing is more complex; the proportion of the straight wing to the total length is too large, so that the structural strength requirement of the straight wing is increased, the corresponding area of the outer wing is greatly reduced, the aerodynamic efficiency of the outer wing is not fully exerted, and the lift-drag ratio is reduced. Therefore, the length of the straight wing in the embodiment is 0.05-0.15 of the whole machine extension, and the axial distance between the two machine bodies is 0.1-0.3 of the whole machine extension.
If the straight wing, the inboard wing body fusion section and the two fuselages form a whole, the overall structure can increase the main load bearing structural strength of the aircraft, and can reduce the weight of the aircraft of the overall aircraft, thereby increasing the payload of the whole aircraft. In this embodiment, the connection between the individual components is therefore made using a fuselage fusion.
The size of the sweepback angle of the outer wing has obvious influence on the performance of the whole aircraft, if the sweepback angle is too small, the operating arm of the pitching channel of the whole aircraft is too short, and the stability of the whole aircraft is reduced, so that the flight control difficulty is increased, and the safety is reduced; if the sweep angle is too large, the pitch channel stability increases substantially, resulting in an increase in trim resistance and a decrease in lift-drag ratio for the whole machine. Thus, in this embodiment, the sweep angle of the sweep wing 5 is 10 ° to 30 °.
If the slightly root ratio of the sweepback wing is too small, the extension is too large under the condition that the area of the outer wing is certain, so that the outer wing structure is complex; and if the root ratio is too large, the length of the wing is too small under the condition that the area of the outer wing is fixed, the induced resistance is increased, and the lift-drag ratio is reduced. Therefore, in the embodiment, the tip-root ratio of the sweepback wing is 0.2-0.8.
If the ratio of the chord length of the straight wing to the root chord length of the outboard wing is too small, the structural strength of the straight wing may decrease, resulting in a complex structure and increased weight between the straight wing and the fuselage; if the ratio is too high, the lift-drag ratio of the whole of the straight wing, the inboard wing body fusion segment and the two fuselages decreases. In this embodiment, therefore, the chord length of the straight wing is 1 to 2 times the root chord length of the swept-back wing.
Example two
As shown in fig. 2, on the basis of the first embodiment, a wingtip tail 6 is added to the wingtip of the outboard wing 4, which aims to increase heading stability.
For how the engine is laid out on the two embodiments described above, two different arrangements, internal and external, may be employed as follows:
the engine is built in: and two engines are respectively arranged in the two machine bodies, and the engines are utilized to realize back-pushing propulsion.
The engine is arranged externally:
first, the engine is suspended outside the two bodies, and the engine can be arranged above the bodies or below the bodies, so that the engine is utilized to realize push-back propulsion.
Second, the engine is suspended in the center of the straight wing, either above or below the straight wing, and no engine is provided on the fuselage.
The engine can adopt a jet engine, and can also adopt a conventional piston or turboshaft engine to drive a propeller to propel.
The invention is not limited to the specific embodiments described above. The invention extends to any novel one, or any novel combination, of the features disclosed in this specification, as well as to any novel one, or any novel combination, of the steps of the method or process disclosed.
Or any new combination, as well as any new method or process steps or any new combination disclosed.
Claims (8)
1. An aircraft adopting a large-aspect-ratio double-fuselage flying wing layout is characterized by comprising two symmetrically arranged fuselages, wherein the two fuselages are connected into a wing body fusion whole through flat wings, and the outer side of each fuselages is respectively connected with an outer wing fused with the wing body.
2. An aircraft employing a high aspect ratio double fuselage fly wing layout according to claim 1, wherein the straight wing sweep angle between the two fuselages is 0 °.
3. An aircraft employing a high aspect ratio double fuselage flying wing configuration according to claim 1 or 2, wherein the length of the straight wing is from 5% to 15% of the overall aircraft span.
4. An aircraft employing a high aspect ratio double fuselage flying wing configuration according to claim 1 or 2, wherein the separation between the two fuselage axes is between 10% and 30% of the overall aircraft length.
5. An aircraft employing a high aspect ratio double fuselage fly wing configuration according to claim 1, wherein the outboard wing sweep angle is from 10 ° to 30 °.
6. An aircraft employing a high aspect ratio dual fuselage fly wing layout according to claim 5, wherein the outboard wing tip root ratio is from 0.2 to 0.8.
7. An aircraft employing a high aspect ratio double fuselage flying wing configuration according to claim 1, wherein the chord length of the straight wing is 1-2 times the chord length of the outboard wing root.
8. An aircraft employing a high aspect ratio double fuselage flying wing configuration according to claim 1, wherein the distal end of the outboard wing body fusion end is provided with a wingtip tail.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910525982.9A CN110143282B (en) | 2019-06-18 | 2019-06-18 | Aircraft adopting high aspect ratio double-fuselage flying wing layout |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910525982.9A CN110143282B (en) | 2019-06-18 | 2019-06-18 | Aircraft adopting high aspect ratio double-fuselage flying wing layout |
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| Publication Number | Publication Date |
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| CN110143282A CN110143282A (en) | 2019-08-20 |
| CN110143282B true CN110143282B (en) | 2023-07-04 |
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| CN201910525982.9A Active CN110143282B (en) | 2019-06-18 | 2019-06-18 | Aircraft adopting high aspect ratio double-fuselage flying wing layout |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111532426A (en) * | 2020-04-22 | 2020-08-14 | 中国空气动力研究与发展中心 | Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout |
| CN111792027A (en) * | 2020-07-03 | 2020-10-20 | 中国空气动力研究与发展中心 | Aircraft with double-fuselage tandem wing vertical take-off and landing layout |
| CN112265631B (en) * | 2020-10-16 | 2022-07-12 | 中国空气动力研究与发展中心 | Box-type folding wing unmanned aerial vehicle layout capable of realizing modular assembly with variable aspect ratio |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2224641A (en) * | 1938-04-07 | 1940-12-10 | Burnelli Aircraft Corp | All-wing airplane |
| CN107187599A (en) * | 2017-05-11 | 2017-09-22 | 北京航空航天大学 | A kind of HAE aerodynamic configuration of aircraft of use two-shipper height rear wing Three-wing-surface |
| CN207450215U (en) * | 2017-09-20 | 2018-06-05 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of change sweepforward twin-fuselage configuration aircraft |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6666406B2 (en) * | 2000-06-29 | 2003-12-23 | The Boeing Company | Blended wing and multiple-body airplane configuration |
| CN103144769B (en) * | 2013-03-05 | 2015-04-15 | 西北工业大学 | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct |
| CN107972869B (en) * | 2017-11-29 | 2020-10-30 | 北京航空航天大学 | Variable-configuration double-body cross-water-air-medium unmanned aerial vehicle |
| CN108569399B (en) * | 2018-04-10 | 2022-07-26 | 西北工业大学 | Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power |
-
2019
- 2019-06-18 CN CN201910525982.9A patent/CN110143282B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2224641A (en) * | 1938-04-07 | 1940-12-10 | Burnelli Aircraft Corp | All-wing airplane |
| CN107187599A (en) * | 2017-05-11 | 2017-09-22 | 北京航空航天大学 | A kind of HAE aerodynamic configuration of aircraft of use two-shipper height rear wing Three-wing-surface |
| CN207450215U (en) * | 2017-09-20 | 2018-06-05 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of change sweepforward twin-fuselage configuration aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 大展弦比无人机高速风洞测力试验技术研究;樊建超;陈德华;彭云;吴文华;;实验流体力学(第03期);第62-65页 * |
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