CN110143282A - A kind of aircraft using high aspect ratio twin fuselage Flying-wing - Google Patents
A kind of aircraft using high aspect ratio twin fuselage Flying-wing Download PDFInfo
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- CN110143282A CN110143282A CN201910525982.9A CN201910525982A CN110143282A CN 110143282 A CN110143282 A CN 110143282A CN 201910525982 A CN201910525982 A CN 201910525982A CN 110143282 A CN110143282 A CN 110143282A
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- wing
- aspect ratio
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- fuselage
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- 230000004927 fusion Effects 0.000 claims abstract description 4
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 7
- 238000010276 construction Methods 0.000 description 4
- 230000007423 decrease Effects 0.000 description 4
- 238000010586 diagram Methods 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
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
-
- B64D27/40—
Abstract
The invention discloses a kind of aircraft using high aspect ratio twin fuselage Flying-wing, including two symmetrically arranged fuselages, two fuselages are connected as to the entirety of a blended wing-body by the straight wing, the outside of each fuselage respectively connects the outside wing an of blended wing-body.The present invention carries out twin fuselage fusion layout by the straight wing, and the straight wing and twin fuselage form an entirety, improve high aspect ratio Vehicle Structure Strength, keep high aspect ratio Flight Vehicle Structure weight lighter；Full machine aspect ratio can be improved, so that flight vehicle aerodynamic is more efficient, flight resistance is smaller, and energy consumption is lower；The area ratio of full machine lift can be provided, i.e., the area that full machine surface provides lift is bigger, and the region for generating resistance is smaller, and flight lift resistance ratio is higher, and the flight time is longer.
Description
Technical field
The present invention relates to aerodynamic scopes, and in particular to is flown to a kind of using high aspect ratio twin fuselage Flying-wing
Row device.
Background technique
Aircraft is that core force and major economy strength, scientific and technological strength and basic industries of modern national defense etc. are comprehensive
Close the symbol of strength.In the complication system engineering of Flight Vehicle Design, it is the most important thing, directly that aerodynamic arrangement's design, which is commander of an advance unit or vanguard,
The arrangement and design for being related to all subsystems are connect, while being also the key factor that can each system play its potential.For big
For aspect ratio aircraft, aerodynamic arrangement's scheme relatively common at present has normal arrangement, delta wing configuration, Flying-wing and the wing
Body fusion layout.To giving full play to shape layout pneumatic efficiency and structure efficiency, these layouts, which still have, centainly to be promoted
Potentiality, such as Helios are high to wing area, aspect ratio, lift resistance ratio and Structural strength calls.In low-speed condition,
The pneumatic efficiency of aircraft is mainly determined by full machine aspect ratio, higher using normal arrangement housing construction intensity, but pneumatic efficiency
It is lower；It is high using delta wing configuration housing construction intensity, but pneumatic efficiency is low；Housing construction is laid out using all-wing aircraft and blended wing-body
Intensity is higher, but is limited to structural strength and weight limitation, and aspect ratio is smaller, and low velocity pneumatic efficiency is lower.
Summary of the invention
The present invention proposes a kind of aircraft of high aspect ratio twin fuselage Flying-wing on the basis of existing technology, and realization mentions
High aircraft cylinder block strength, the purpose for improving aircraft aspect ratio, improving aircraft low velocity pneumatic efficiency.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of aircraft using high aspect ratio twin fuselage Flying-wing, including two symmetrically arranged fuselages, pass through the straight wing
Two fuselages are connected as to the entirety of a blended wing-body, the outside of each fuselage respectively connects the outside machine an of blended wing-body
The wing.
In the above-mentioned technical solutions, the straight wing angle of sweep between described two fuselages is 0 °.
In the above-mentioned technical solutions, the length of the straight wing accounts for the 5%~15% of entire aircraft length.
In the above-mentioned technical solutions, the spacing between two fuselage axis accounts for the 10%~30% of entire aircraft length.
In the above-mentioned technical solutions, the outside wing setting is 10 °~30 °.
In the above-mentioned technical solutions, the outside wing slightly root ratio is 0.2~0.8.
In the above-mentioned technical solutions, the chord length of the straight wing is 1~2 times of outside airfoil root chord length.
In the above-mentioned technical solutions, the outside wing tip is provided with wing tip vertical fin.
In conclusion by adopting the above-described technical solution, the beneficial effects of the present invention are:
The present invention carries out twin-fuselage configuration by the straight wing, and the straight wing and twin fuselage form an entirety, improves high aspect ratio and flies
Row device structural strength keeps high aspect ratio Flight Vehicle Structure weight lighter；
The present invention carries out twin-fuselage configuration by the straight wing, can improve full machine aspect ratio, so that flight vehicle aerodynamic is more efficient, flies
Row resistance is smaller, and energy consumption is lower；
The present invention can provide the area ratio of full machine lift by twin fuselage Flying-wing, i.e., full machine surface provides the face of lift
Product is bigger, and the region for generating resistance is smaller, and flight lift resistance ratio is higher, and the flight time is longer.
Detailed description of the invention
Examples of the present invention will be described by way of reference to the accompanying drawings, in which:
Fig. 1 high aspect ratio twin fuselage Flying-wing schematic diagram；
Fig. 2 is a kind of implementation diagram of the invention；
Wherein: 1 is the straight wing, and 2 be inside blended wing-body section, and 3 be fuselage, and 4 be outside wing (swept-back wing), and 5 be ala lateralis body
Section is merged, 6 be wing tip vertical fin.
Specific embodiment
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
Any feature disclosed in this specification (including any accessory claim, abstract and attached drawing), except non-specifically chatting
It states, can be replaced by other alternative features that are equivalent or have similar purpose.That is, unless specifically stated, each feature is only
It is an example in a series of equivalent or similar characteristics.
Embodiment one
The present embodiment use two symmetrically arranged fuselages 3, from the point of view of plane projection, as shown in Fig. 1, two fuselages 3 at
It is symmetrical, using arranged in parallel in same level.The straight wing 1 is for connecting two fuselages 3, the both ends of the straight wing 1
It is connected on a fuselage 3 by an inside blended wing-body section 2, is melted in the outside of each fuselage 3 by ala lateralis body respectively
It closes section 5 and connects an outside wing 4.
Compared to existing single-fuselage arrangement, the fuselage arrangement of this implementation, because twin fuselage and the straight wing are used, so that two
The inner space of a fuselage increases, therefore integral arrangement is more convenient, and the overall structure efficiency that the two is formed is compared to existing
Single-fuselage arrangement it is higher.
For the present embodiment in order to realize straight wing convenient processing and manufacture, wing load-carrying construction is simple so that wing not by
Complicated surface constraint, is conducive to dock with fuselage, the angle of sweep of the straight wing is set as 0 °.
In the present embodiment, in order to reduce the aerial resistance of the straight wing, increase lifting area, between the straight wing and fuselage
Carry out blended wing-body.
In the case where entire aircraft length is certain, if the ratio that the straight wing accounts for total length is too small, can make straight
The wing and inside blended wing-body section lifting area reduce, and the lifting area of outside wing is significantly increased, and lead to the knot of outside wing
Structure is increasingly complex；And the ratio that the straight wing accounts for total length is excessive, and straight wing structure intensity requirement can be made to increase, corresponding outside
Wing area substantially reduces, so that the pneumatic efficiency of outside wing be made to be not in full use, lift resistance ratio reduces.Therefore the straight wing
The 0.05~0.15 of length Zhan Quanji length in the present embodiment, the axis spacing Zhan Quanji length of two fuselages 0.1~
0.3。
If the straight wing, inside blended wing-body section and two fuselages form an entirety, overall structure can increase flight
The main force support structure intensity of device, can reduce the empty weight of whole aircraft, to increase the payload of full machine.Therefore originally
In embodiment, the connection between all parts is all made of fuselage fusion section and is attached.
The size of outside wing setting influences significantly full machine performance, if angle of sweep is too small, full machine pitch channel behaviour
The vertical arm of force is too short, and full machine stability decline causes safety to reduce to increase flight control difficulty；If angle of sweep is excessive,
Pitch channel stability is substantially increased, and the trim resistance of full machine is caused to increase, lift resistance ratio decline.Therefore in the present embodiment after, plunder
The angle of sweep of the wing 5 is 10 °~30 °.
If the slightly root of swept-back wing is than too small, in the case that wing area is certain on the outside, it is excessive to will lead to length, thus
So that outside wing structure is complicated；And slightly root is than excessive, in the case that wing area is certain on the outside, it is too small to will lead to length,
Induced drag increases, lift resistance ratio decline.Therefore in the present embodiment, the taper ratio of swept-back wing is 0.2~0.8.
If the chord length of the straight wing and the ratio of the root chord length of outside wing are too small, the structural strength of the straight wing can under
Drop, leads between the straight wing and fuselage that structure is complicated and weight increases；If ratio is excessive, the straight wing, inside blended wing-body section
The whole lift resistance ratio decline formed with two fuselages.Therefore in the present embodiment, the chord length of the straight wing is the root string of swept-back wing
Long 1~2 times.
Embodiment two
As shown in Fig. 2, on the basis of example 1, the wing tip of wing 4 increases wing tip vertical fin 6 on the outside, and the purpose is to increase
Add shipping-direction stability.
For how being laid out in two kinds of above-mentioned embodiments for engine, can using it is following built-in and external two kinds not
Same arrangement:
It is engine embedded: an engine being respectively set in two fuselages, realizes that back-pushed promotes using engine.
Engine is external:
The first, external on two fuselages hangs engine, can be set in body upper, also can be set under fuselage
Side realizes that back-pushed promotes using engine.
Second, engine is suspended on the center of the straight wing, can be in the top of the straight wing, can also be in the straight wing
Lower section, and engine is no longer set on fuselage.
Above-mentioned engine can use jet engine, can also be driven using conventional piston or turboshaft engine
Propeller is promoted.
The invention is not limited to specific embodiments above-mentioned.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Or any new combination, and disclose any new method or process the step of or any new combination.
Claims (8)
1. a kind of aircraft using high aspect ratio twin fuselage Flying-wing, it is characterised in that including two symmetrically arranged machines
Two fuselages, the entirety of a blended wing-body is connected as by the straight wing by body, and the outside of each fuselage respectively connects a wing
The outside wing of body fusion.
2. a kind of aircraft using high aspect ratio twin fuselage Flying-wing according to claim 1, it is characterised in that institute
Stating the straight wing angle of sweep between two fuselages is 0 °.
3. a kind of aircraft using high aspect ratio twin fuselage Flying-wing according to claim 1 or 2, it is characterised in that
The length of the straight wing accounts for the 5%~15% of entire aircraft length.
4. a kind of aircraft using high aspect ratio twin fuselage Flying-wing according to claim 1 or 2, it is characterised in that
Spacing between two fuselage axis accounts for the 10%~30% of entire aircraft length.
5. a kind of aircraft using high aspect ratio twin fuselage Flying-wing according to claim 1, it is characterised in that institute
Stating outside wing setting is 10 °~30 °.
6. a kind of aircraft using high aspect ratio twin fuselage Flying-wing according to claim 5, it is characterised in that institute
Stating outside wing slightly root ratio is 0.2~0.8.
7. a kind of aircraft using high aspect ratio twin fuselage Flying-wing according to claim 1, it is characterised in that flat
The chord length of the straight wing is 1~2 times of outside airfoil root chord length.
8. a kind of aircraft using high aspect ratio twin fuselage Flying-wing according to claim 1, it is characterised in that institute
The end for stating outside blended wing-body end is provided with wing tip vertical fin.
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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110143282A true CN110143282A (en) | 2019-08-20 |
| CN110143282B CN110143282B (en) | 2023-07-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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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Cited By (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 |
| CN112265631A (en) * | 2020-10-16 | 2021-01-26 | 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 |
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| US2224641A (en) * | 1938-04-07 | 1940-12-10 | Burnelli Aircraft Corp | All-wing airplane |
| US20020003190A1 (en) * | 2000-06-29 | 2002-01-10 | Sankrithi Mithra M.K.V. | Blended wing and multiple-body airplane configuration |
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Cited By (4)
| 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 |
| CN112265631A (en) * | 2020-10-16 | 2021-01-26 | 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110143282B (en) | 2023-07-04 |
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