CN106043668A - Aerodynamic configuration of three-surface aircraft - Google Patents
Aerodynamic configuration of three-surface aircraft Download PDFInfo
- Publication number
- CN106043668A CN106043668A CN201610527472.1A CN201610527472A CN106043668A CN 106043668 A CN106043668 A CN 106043668A CN 201610527472 A CN201610527472 A CN 201610527472A CN 106043668 A CN106043668 A CN 106043668A
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- Prior art keywords
- wing
- aircraft
- canard
- horizontal tail
- aerodynamic
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/04—Noseplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Tires In General (AREA)
Abstract
The invention belongs to aircraft design in the technical field of aviation, relates to aerodynamic configuration of a three-surface aircraft, and solves the problem that the RCS of the three-surface aircraft with high aerodynamic performance is too large. The aerodynamic configuration comprises the aerodynamic configuration of an aircraft body, wings, canard wings, a horizontal tail and vertical tails and is characterized in that the wings, the canard wings and the horizontal tail form three surfaces for bearing aerodynamic force, the aircraft body has stealth performance, the full-flight-simulator double vertical tails incline outwardly, and double ventral fins incline outwardly. The aerodynamic configuration has the advantages that the aircraft using the aerodynamic configuration is high in lift-drag ratio, good in operability, good in stability and good in stealth performance.
Description
Technical field
The present invention relates to the aerodynamic arrangement of a kind of three-control aircraft, belong to the Flight Vehicle Design direction of technical field of aerospace.
Background technology
Three-control aircraft is formed the aircraft of aerodynamic force load-carrying surface by canard, wing and horizontal tail.Although three-control aircraft by
In increasing canard and the deficiency that slightly increases weight, but three-control aircraft in low latitude, extreme low-altitude time aeroperformance good, on high-altitude opportunity
Kinetic force is strong, therefore, by the extensive concern of domestic and international aeronautical chart.At present, Muscovite Su-30SM, Su-33 and Su-34 etc.
Three-control aircraft equips our troops in a large number, improves the fight capability of air unit.But, gas focused on by current three-control aircraft
Dynamic characteristic, ignores Stealth, causes the RCS (Radar Cross Section) of three-control aircraft bigger than normal, the existence of aircraft during operation
Power is relatively low.China is interested in three-control aircraft, and Air Branch is being researched and developed.
Summary of the invention
It is an object of the invention to provide the aerodynamic arrangement of a kind of three-control aircraft, it is outstanding that this aerodynamic arrangement makes aircraft possess
Aerodynamic characteristic, Stealth Fighter is good simultaneously.
For achieving the above object, the technical solution used in the present invention is:
A kind of aerodynamic arrangement of three-control aircraft, including the aerodynamic arrangement of fuselage, wing, canard, horizontal tail and vertical tail, its
In, the Three-wing-surface of wing (2), canard (1), horizontal tail (3) composition aerodynamic force load, Stealth fuselage, complete dynamic double fins flare,
Double abdomeinal fin flares.
As a further improvement on the present invention, described wing (2), canard (1), horizontal tail (3) composition aerodynamic force load
Three-wing-surface, wing (2) and fuselage blended wing-body, wing (2) is tapered airfoil, midsetwing, lower anti-, sweepback, and inverted diherdral is 2 °～4 °,
Its aspect ratio is 3～4, and wing (2) is with droope snoot (4) and flaperon (5), droope snoot (4) area and wing (2) area
Ratio be 7.5%～10.5%, flaperon (5) area and wing (2) area ratio are 9.5%～12.5%；Canard (1) is complete
Moment moves canard, upper anti-, sweepback, and its upper counterangle is 12 °～15 °, and its aspect ratio is 4～5, and the aerofoil profile of canard (1) is the lift wing
Type；Horizontal tail (3) is complete dynamic differential tailplane, lower anti-, sweepback, and its inverted diherdral is 2 °～5 °, and its aspect ratio is 3.5～4.5, horizontal tail
(3) aerofoil profile is lift aerofoil profile；The leading edge sweep of wing (2), canard (1) and horizontal tail (3) is equal, and its value is 42 °～45 °；
The trailing sweep of wing (2), canard (1) and horizontal tail (3) is equal, and its value is 27 °～30 °.
As a further improvement on the present invention, described Stealth fuselage is: the head (6) of band seamed edge, middle fuselage (7)
Inside having S curved intake port, inlet mouth is DSI type (10) (without boundary layer diverter supersonic inlet), the internal dress of rear body (8)
There are two fanjets, between two nozzles of afterbody, have drag reduction to bore (9).
As a further improvement on the present invention, described complete dynamic double fins flare is: vertical tail (11) is trapezoidal, and its aerofoil profile is
Symmetrical airfoil, vertical tail leading edge sweep is 47 °～52 °, and vertical tail trailing sweep is 22 °～30 °, vertical tail camber angle be 35 °～
40°。
As a further improvement on the present invention, described double abdomeinal fin flares are: abdomeinal fin (12) is trapezoidal, and its aerofoil profile is symmetrical
Aerofoil profile, abdomeinal fin camber angle is 35 °～40 °.
Compared with prior art, the having the beneficial effect that of advantages of the present invention and acquirement
First, lift-drag ratio is high.The air-flow flowing through canard produces whirlpool above wing, improves the lift of wing；Canard, machine
The wing, horizontal tail aircraft is flat fly trim time, positive lift force is all provided, lift does not lose, little due to the comparison of resistance of aircraft again, so
The lift-drag ratio of aircraft is high.
Second, navigability is good.The pitch control of aircraft is controlled by canard, horizontal tail, and yaw control is by entirely moving double fins control
System, rolling is controlled by canard, flaperon, horizontal tail, it can in addition contain deflection droope snoot and flaperon are for increasing the liter of aircraft
Power, so the navigability of aircraft is good.
3rd, good stability.The pneumatic focus of aircraft is after the center of gravity of aircraft, and the center of gravity of aircraft is produced by the lift of canard
Nose-up pitching moment, the center of gravity of aircraft produces by nose-down pitching moment that the center of gravity of aircraft is produced by the lift of wing, the positive lift force of horizontal tail
Nose-down pitching moment, three moments reach balance jointly, and damping in pitch is big, so the longitudinal stability of aircraft is good；Owing to aircraft is
Midsetwing, lower anti-, sweepback, so the lateral stability of aircraft is good；Owing to having double fins and double abdomeinal fin, so shipping-direction stability
Good.
4th, stealth is good.Owing to aircraft takes the head of band seamed edge, S curved intake port, DSI type inlet mouth, so
The forward direction RCS of aircraft reduces；Due to complete dynamic double fins flare, double abdomeinal fin flare, so the lateral RCS of aircraft reduces；Wing, duck
The leading edge sweep of the wing and horizontal tail is equal, and the trailing sweep of wing, canard and horizontal tail is equal, so the strong scattering source collection of aircraft
In in several narrow beams, the omnidirectional RCS number of peaks of aircraft reduces.
Accompanying drawing explanation
Fig. 1 is the axonometric chart of the present invention.
Fig. 2 is the front view of the present invention.
Fig. 3 is the rearview of the present invention.
Fig. 4 is the left view of the present invention.
Fig. 5 is the top view of the present invention.
Fig. 6 is the upward view of the present invention.
In the accompanying drawings, 1 is canard；2 is wing；3 is horizontal tail；4 is droope snoot；5 is flaperon；6 is head；During 7 are
Fuselage；8 is rear body；9 bore for drag reduction；10 is DSI type；11 is vertical tail；12 is abdomeinal fin.
Detailed description of the invention
Below in conjunction with accompanying drawing 1～6 and embodiment the present invention is further elaborated.
A kind of embodiment of the aerodynamic arrangement of three-control aircraft, pneumatic including fuselage, wing, canard, horizontal tail and vertical tail
Layout, it is characterised in that: the Three-wing-surface of wing (2), canard (1), horizontal tail (3) composition aerodynamic force load, Stealth fuselage, entirely
Dynamic double fins flare, double abdomeinal fin flares.The captain of three-control aircraft is 22m, a height of 4.5m of machine, and the span is 16.7m.
As the further improvement of the embodiment of the present invention, described wing (2), canard (1), horizontal tail (3) composition aerodynamic force
The Three-wing-surface of load is: wing (2) and fuselage blended wing-body, and wing (2) is tapered airfoil, midsetwing, lower anti-, sweepback, inverted diherdral
Being 2 °, its aspect ratio is 3, and the aerofoil profile of wing is NACA 64a204 aerofoil profile, and wing (2) is with droope snoot (4) and flaperon
(5), droope snoot (4) area and wing (2) area ratio are 7.5%, and flaperon (5) area with wing (2) area ratio is
9.5%；Canard (1) is that full moment moves canard, upper anti-, sweepback, and its upper counterangle is 12 °, and its aspect ratio is 4, the aerofoil profile of canard (1)
For NACA 64a202 aerofoil profile；Horizontal tail (3) is complete dynamic differential tailplane, lower anti-, sweepback, and its inverted diherdral is 2 °, and its aspect ratio is 3.5,
The aerofoil profile of horizontal tail (3) is NACA 64a202 aerofoil profile；The leading edge sweep of wing (2), canard (1) and horizontal tail (3) is equal, its value
It it is 42 °；The trailing sweep of wing (2), canard (1) and horizontal tail (3) is equal, and its value is 27 °.
As the further improvement of the embodiment of the present invention, described Stealth fuselage is: the head (6) of band seamed edge, in
Fuselage has S curved intake port in (7), and inlet mouth is DSI type (10) (without boundary layer diverter supersonic inlet), rear body
(8) internal equipped with two fanjets, there is drag reduction to bore (9) between two nozzles of afterbody.
As the further improvement of the embodiment of the present invention, described complete dynamic double fins flare is: vertical tail (11) is trapezoidal, its
Aerofoil profile is NACA 64a006 aerofoil profile, and vertical tail leading edge sweep is 47 °, and vertical tail trailing sweep is 22 °, and vertical tail camber angle is
35°。
As the further improvement of the embodiment of the present invention, described double abdomeinal fin flares are: abdomeinal fin (12) is trapezoidal, its aerofoil profile
For NACA64a006 aerofoil profile, abdomeinal fin camber angle is 35 °.
The above embodiment is only the preferred embodiments of the present invention, and and the feasible enforcement of non-invention exhaustive.Right
For one of ordinary skill in the art, on the premise of without departing substantially from the principle of the invention and spirit to its made any aobvious
And the change being clear to, within all should being contemplated as falling with the claims of the present invention.Therefore, the protection of the present invention
Scope should be as the criterion with described scope of the claims.
Claims (5)
1. an aerodynamic arrangement for three-control aircraft, including the aerodynamic arrangement of fuselage, wing, canard, horizontal tail and vertical tail, its feature
It is: the Three-wing-surface of wing (2), canard (1), horizontal tail (3) composition aerodynamic force load, Stealth fuselage, outside complete dynamic double fins
Incline, double abdomeinal fin flares.
The aerodynamic arrangement of a kind of three-control aircraft the most according to claim 1, it is characterised in that: wing (2) and the fuselage wing
Body merges, and the aerofoil profile of canard (1) is lift aerofoil profile, and the aerofoil profile of horizontal tail (3) is lift aerofoil profile；Wing (2), canard (1) and horizontal tail
(3) leading edge sweep is equal, and the trailing sweep of wing (2), canard (1) and horizontal tail (3) is equal.
The aerodynamic arrangement of a kind of three-control aircraft the most according to claim 1, it is characterised in that: Stealth fuselage is concrete
Using following structure, the head (6) of band seamed edge, the inlet mouth of middle fuselage (7) is DSI type (10), two tails of afterbody
Drag reduction is had to bore (9) between spout.
The aerodynamic arrangement of a kind of three-control aircraft the most according to claim 1, it is characterised in that: the flare of complete dynamic double fins
Angle is 35 °～40 °.
The aerodynamic arrangement of a kind of three-control aircraft the most according to claim 1, it is characterised in that: the camber angle of double abdomeinal fins is
35 °～40 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610527472.1A CN106043668B (en) | 2016-07-06 | 2016-07-06 | A kind of aerodynamic arrangement of three-control aircraft |
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|---|---|---|---|
| CN201610527472.1A CN106043668B (en) | 2016-07-06 | 2016-07-06 | A kind of aerodynamic arrangement of three-control aircraft |
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| Publication Number | Publication Date |
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| CN106043668A true CN106043668A (en) | 2016-10-26 |
| CN106043668B CN106043668B (en) | 2019-07-19 |
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Cited By (9)
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|---|---|---|---|---|
| CN107031812A (en) * | 2017-03-30 | 2017-08-11 | 北京临近空间飞行器系统工程研究所 | It is a kind of to meet aerodynamic arrangement's design method that hypersonic big angle of attack horizontal stroke is laterally controlled |
| CN107284641A (en) * | 2017-07-03 | 2017-10-24 | 武汉华伍航空科技有限公司 | A kind of baby plane aerodynamic configuration suitable for supersonic flight |
| CN108583849A (en) * | 2018-05-25 | 2018-09-28 | 中国航天空气动力技术研究院 | A kind of mute UAV aerodynamic layout of supersonic speed |
| CN109489491A (en) * | 2018-11-26 | 2019-03-19 | 北京金朋达航空科技有限公司 | The control method of stealthy high maneuver target drone and stealthy high maneuver target drone |
| CN109720535A (en) * | 2017-10-30 | 2019-05-07 | 成都飞机工业（集团）有限责任公司 | A kind of blended wing-body aircraft |
| CN110077589A (en) * | 2019-06-11 | 2019-08-02 | 四川垚磊科技有限公司 | UAV aerodynamic layout |
| CN110203372A (en) * | 2019-06-28 | 2019-09-06 | 南京航空航天大学 | A kind of variant invisbile plane and its changing method and application |
| CN110395389A (en) * | 2019-06-28 | 2019-11-01 | 中国航天空气动力技术研究院 | A kind of aerodynamic arrangement improving the horizontal side-coupled characteristic of hypersonic aircraft |
| 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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| CN107031812A (en) * | 2017-03-30 | 2017-08-11 | 北京临近空间飞行器系统工程研究所 | It is a kind of to meet aerodynamic arrangement's design method that hypersonic big angle of attack horizontal stroke is laterally controlled |
| CN107031812B (en) * | 2017-03-30 | 2019-08-09 | 北京临近空间飞行器系统工程研究所 | A kind of aerodynamic arrangement's design method for meeting hypersonic big angle of attack cross and laterally controlling |
| CN107284641A (en) * | 2017-07-03 | 2017-10-24 | 武汉华伍航空科技有限公司 | A kind of baby plane aerodynamic configuration suitable for supersonic flight |
| CN107284641B (en) * | 2017-07-03 | 2023-09-08 | 安徽国援智能科技有限公司 | Pneumatic appearance of small-size aircraft suitable for supersonic flight |
| CN109720535A (en) * | 2017-10-30 | 2019-05-07 | 成都飞机工业（集团）有限责任公司 | A kind of blended wing-body aircraft |
| CN108583849A (en) * | 2018-05-25 | 2018-09-28 | 中国航天空气动力技术研究院 | A kind of mute UAV aerodynamic layout of supersonic speed |
| CN109489491A (en) * | 2018-11-26 | 2019-03-19 | 北京金朋达航空科技有限公司 | The control method of stealthy high maneuver target drone and stealthy high maneuver target drone |
| CN110077589A (en) * | 2019-06-11 | 2019-08-02 | 四川垚磊科技有限公司 | UAV aerodynamic layout |
| CN110203372A (en) * | 2019-06-28 | 2019-09-06 | 南京航空航天大学 | A kind of variant invisbile plane and its changing method and application |
| CN110395389A (en) * | 2019-06-28 | 2019-11-01 | 中国航天空气动力技术研究院 | A kind of aerodynamic arrangement improving the horizontal side-coupled characteristic of hypersonic aircraft |
| 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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