CN111017190A - Large-scale civil passenger plane of integration overall arrangement - Google Patents
Large-scale civil passenger plane of integration overall arrangement Download PDFInfo
- Publication number
- CN111017190A CN111017190A CN201911346695.8A CN201911346695A CN111017190A CN 111017190 A CN111017190 A CN 111017190A CN 201911346695 A CN201911346695 A CN 201911346695A CN 111017190 A CN111017190 A CN 111017190A
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- wing
- layout
- central body
- fused
- passenger plane
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- 230000010354 integration Effects 0.000 title description 2
- 230000004927 fusion Effects 0.000 abstract description 18
- 230000008595 infiltration Effects 0.000 abstract description 3
- 238000001764 infiltration Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type
- B64D27/12—Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type
- B64D27/14—Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, fuselages
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a large civil passenger plane with a fusion body layout, which adopts a wing body fusion and V-shaped double-vertical-tail layout, is assembled with four turbofan engines, two of which are hung below wings, two of which are carried at the rear part of the fusion body and between the V-shaped double-vertical-tail, on the premise of the same internal volume of the body, the infiltration area of the wing body fusion layout is reduced by 1/3 compared with the conventional layout, therefore, the frictional resistance can be greatly reduced, in addition, the aspect ratio of the wing body fusion layout is larger, the corresponding induced resistance is also lower, according to estimation, the cruising lift-drag ratio of the wing body fusion passenger plane at least exceeds 23, the aerodynamic efficiency is far higher than that of the passenger plane with the conventional layout, two engines are arranged at the rear upper part of the passenger plane, the noise of the engines cannot be reflected to the ground by the wings like the passenger plane with the conventional layout, and the V-shaped empennage and the rear fuselage also play a good shielding role, and the noise level is far lower than that of the layout of four-wing-crane engines.
Description
Technical Field
The invention belongs to the field of aircraft design, and particularly relates to a large civil passenger plane with a fusion layout.
Background
The large civil passenger aircraft which is put into use at present adopts a conventional layout, the boeing-777 of the long-range wide-body passenger aircraft, two engines of a wing-hung aircraft, the cruising lift-drag ratio of the two engines is less than 20, the takeoff noise is 87.1 decibels, and the landing noise is 101.6 decibels; the current most advanced remote wide-body passenger plane boeing-787 has a cruising lift-drag ratio of less than 21, a takeoff noise of 86 dB and a landing noise of 99 dB. The cruising lift-drag ratio of the most advanced large civil passenger aircraft at present has a larger difference with a wing-body fusion layout aircraft, the noise level also has a larger difference with the noise level (42 decibels less than Boeing-777) of the N +2 generation civil aircraft used in 2020, which is proposed by NASA, and in addition, the adoption of double-shot Boeing-777 and Boeing-787 passenger aircraft also needs to meet ETOPS, thereby increasing the maintenance and operation cost of an airline company.
Disclosure of Invention
The purpose of the invention is as follows: the large civil passenger plane with the integrated layout can improve the pneumatic efficiency and the environmental protection performance and reduce the operation cost of an airline company.
The technical scheme of the invention is as follows:
a large civil airliner with a fusion body layout comprises a central body, outer wings, wing-hung engine nacelles, a V-shaped empennage, a front three-point landing gear, leading edge slats, trailing edge ailerons, trailing edge flaps, a control surface, a backpack engine hanger, a wing-hung engine hanger and a backpack engine nacelle, wherein the outer wings are arranged on two sides of the central body, the V-shaped empennage is arranged above the tail part of the central body, the backpack engine nacelle is arranged in the middle of the V-shaped empennage through the backpack engine hanger, the wing-hung engine nacelle is arranged below the outer wings, the spreading position is arranged at the joint of the outer wings and the central body, the top end of the engine hanger is directly connected with the lower surface of the outer wings, the upper surface of the wing-hung engine nacelle is connected with the bottom end of the engine hanger, the leading edge slats are arranged on the outer wings, the trailing edge ailerons and the trailing edge flaps are arranged on the trailing, and the trailing edge flap is close to the central body, the control surface is arranged at the trailing edge of the V-shaped empennage, and the front three-point landing gear is arranged at the lower part of the central body.
The central body is flat, and the sweepback angle of the front edge is 50-60 degrees.
The two piggyback nacelle air inlets are located above the central body contour.
The root chord of the leading-edge slat is 15-20% equivalent to the chord length of the slat.
The chord of the front edge slot wing tip is 20-30% equivalent to the chord length of the ground machine.
The planar shape of the outer wing is a swept-back trapezoid, and the swept-back angle of the leading edge is 30-35 degrees.
The planar shape of the V-shaped empennage is a swept-back trapezoid.
The tail capacity of the V-shaped tail wing is 0.3-0.4, the relative thickness of the wing profile is 9-11%, and the internal inclination angle is 50-60 degrees.
The invention has the advantages that:
the invention relates to a large civil passenger plane with a fused layout, which adopts a wing body fusion and V-shaped double-vertical-tail layout, four turbofan engines are assembled, two turbofan engines are hung below wings, two wings are carried at the back of the fused body, and V-shaped double-vertical-tail layout, on the premise that the internal volumes of the airplane bodies are the same, the infiltration area of the wing body fusion layout is reduced by 1/3 compared with the conventional layout, so that the friction resistance can be greatly reduced. In addition, the aspect ratio of the wing body fusion layout is large, the corresponding induced resistance is low, the cruising lift-drag ratio of the wing body fusion passenger plane is estimated to be at least more than 23, the aerodynamic efficiency is far higher than that of the passenger plane with the conventional layout, the two engines are arranged at the rear upper part of the plane body, the noise of the engines cannot be reflected to the ground by the wings like the passenger plane with the conventional layout, the V-shaped empennage and the rear plane body also play a good shielding role, and the noise level is far lower than that of the layout of four wing-hung engines. In addition, four engines are adopted, ETOPS does not need to be met, and the operation expense of an airline company is reduced.
Description of the drawings:
FIG. 1 is a schematic diagram of the present invention.
The specific implementation mode is as follows:
the present invention is described in further detail below with reference to the attached drawings.
A fused layout large civil airliner, comprising: the aircraft comprises a central body 1, an outer wing 2, four engine nacelles 3, a V-shaped tail wing 4, a front three-point landing gear 5, a leading edge slat 6, a trailing edge aileron 7, a trailing edge flap 8, a control surface 9 and engine pylons 10 and 11.
The front three-point undercarriage 5 is retracted forwards and backwards, and retracted forwards when being mainly lifted.
The central body 1 is flat, and the sweepback angle of the front edge is 50-60 °
The two wing-hung engine nacelles 3 are arranged below the outer wing 2, the spreading positions are located at the joint of the outer wing and the central body, the top end of the engine hanger 11 is directly connected with the lower surface of the outer wing 2, and the upper surface of the wing-hung engine nacelle 3 is connected with the bottom end of the engine hanger 11.
The two backpack type engine nacelles 3 are arranged between the V-shaped tail wings 4 at the rear part of the central body 1, the lower surface of the backpack type engine nacelle 3 is directly connected with the top end of the engine hanging rack 10, and the bottom end of the engine hanging rack 10 is connected with the upper surface at the rear part of the central body 1.
The planar shape of the outer wing 2 is a swept-back trapezoid, the swept-back angle of the leading edge is 30-35 degrees, the leading edge is provided with leading-edge slats 6, the root chord of each slat is 15-20% of the chord length of the ground machine, the tip chord is 20-30% of the chord length of the ground machine, the trailing edge is provided with a flap 8 and an aileron 7, the flap is close to the inside, and the aileron is close to the outside.
The rear edge of the V-shaped tail wing 4 is provided with an operation control surface 9, the tail capacity is 0.3-0.4, the plane shape is a sweepback trapezoid, the relative thickness of the wing type is 9-11%, and the internal inclination angle is 50-60 degrees.
The wing body fusion and V-shaped double-vertical-tail layout is adopted, four turbofan engines are assembled, two turbofan engines are hung below the wings, and two turbofan engines are carried on the back of the fusion body and between the V-shaped double-vertical-tail.
On the premise that the internal volumes of the bodies are the same, the infiltration area of the wing body fusion layout is reduced by 1/3 compared with that of the conventional layout, so that the friction resistance can be greatly reduced. In addition, the wing body fusion layout has a large aspect ratio and low corresponding induced resistance, and the cruising lift-drag ratio of the wing body fusion passenger plane is estimated to exceed 23 at least, so that the aerodynamic efficiency is far higher than that of the passenger plane with the conventional layout. The two engines are arranged at the rear upper part of the engine body, the noise of the engines cannot be reflected to the ground by the wings like a passenger plane in the conventional layout, the V-shaped empennage and the rear fuselage also play a good role in shielding, and the noise level is far lower than that of the four-wing-mounted engine layout. In addition, four engines are adopted, ETOPS does not need to be met, and the operation expense of an airline company is reduced.
Claims (8)
1. A large civil passenger plane with a fused body layout is characterized in that: comprises a central body (1), an outer wing (2), a wing-hung engine nacelle (3), a V-shaped tail wing (4), a front three-point landing gear (5), a leading edge slat (6), a trailing edge aileron (7), a trailing edge flap (8), a control surface (9), a backpack engine hanger (10), a wing-hung engine hanger (11) and a backpack engine nacelle (12), wherein the outer wing (2) is arranged at two sides of the central body, the V-shaped tail wing (4) is arranged above the tail part of the central body (1), the backpack engine nacelle (12) is arranged in the middle of the V-shaped tail wing (4) through the backpack engine hanger (10), the wing-hung engine nacelle (3) is arranged below the outer wing (2), the unfolding position is arranged at the joint of the outer wing (2) and the central body (1), the top end of the engine hanger (11) is directly connected with the lower surface of the outer wing (2), the upper surface of the wing-mounted engine nacelle (3) is connected with the bottom end of an engine hanger (11), leading edge slats (6) are arranged on the leading edge of the outer wing (2), trailing edge ailerons (7) and trailing edge flaps (8) are arranged on the trailing edge of the outer wing (2) in parallel, the trailing edge flaps (8) are close to the central body (1), the control surface (9) is arranged on the trailing edge of the V-shaped empennage (4), and the front three-point undercarriage (5) is arranged on the lower portion of the central body (1).
2. A fused layout large civil airliner as defined in claim 1 wherein: the central body (1) is flat, and the sweepback angle of the front edge is 50-60 degrees.
3. A fused layout large civil airliner as defined in claim 1 wherein: the air inlets of the two backpack type engine nacelles (10) are positioned above the outline of the central body (1).
4. A fused layout large civil airliner as defined in claim 1 wherein: the chord of the leading edge slat (6) is 15-20% equivalent to the chord length of the machine.
5. A fused layout large civil airliner as defined in claim 1 wherein: the chord of the leading-edge slat (6) is 20-30% equivalent to the chord length of the machine.
6. A fused layout large civil airliner as defined in claim 1 wherein: the planar shape of the outer wing (2) is a swept-back trapezoid, and the swept-back angle of the leading edge is 30-35 degrees.
7. A fused layout large civil airliner as defined in claim 1 wherein: the planar shape of the V-shaped empennage (4) is a swept-back trapezoid.
8. A fused layout large civil airliner as defined in claim 1 wherein: the tail capacity of the V-shaped tail wing (4) is 0.3-0.4, the relative thickness of the wing profile is 9-11%, and the internal inclination angle is 50-60 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911346695.8A CN111017190A (en) | 2019-12-24 | 2019-12-24 | Large-scale civil passenger plane of integration overall arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911346695.8A CN111017190A (en) | 2019-12-24 | 2019-12-24 | Large-scale civil passenger plane of integration overall arrangement |
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| Publication Number | Publication Date |
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| CN111017190A true CN111017190A (en) | 2020-04-17 |
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| CN201911346695.8A Pending CN111017190A (en) | 2019-12-24 | 2019-12-24 | Large-scale civil passenger plane of integration overall arrangement |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112660381A (en) * | 2020-12-24 | 2021-04-16 | 中国航空工业集团公司西安飞机设计研究所 | Laminar flow control technology-based wing body fusion layout passenger plane layout method |
| CN117755478A (en) * | 2024-02-22 | 2024-03-26 | 中国航空工业集团公司西安飞机设计研究所 | Pneumatic layout structure of airplane and operation method thereof |
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| US20120032033A1 (en) * | 2010-08-03 | 2012-02-09 | Jason Everett Cole | Wing piercing airplane |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117755478A (en) * | 2024-02-22 | 2024-03-26 | 中国航空工业集团公司西安飞机设计研究所 | Pneumatic layout structure of airplane and operation method thereof |
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Application publication date: 20200417 |