CN106275387A - A kind of band sawtooth swept-back wing that improves transonic speed is fallen off the wing of characteristic - Google Patents
A kind of band sawtooth swept-back wing that improves transonic speed is fallen off the wing of characteristic Download PDFInfo
- Publication number
- CN106275387A CN106275387A CN201610808422.0A CN201610808422A CN106275387A CN 106275387 A CN106275387 A CN 106275387A CN 201610808422 A CN201610808422 A CN 201610808422A CN 106275387 A CN106275387 A CN 106275387A
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- China
- Prior art keywords
- wing
- leading edge
- sawtooth
- transition
- obtuse
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/22—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
- B64C9/26—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by multiple flaps
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
nullA kind of band sawtooth swept-back wing that improves transonic speed is fallen off the wing of characteristic，Including Inside Leading Edge Flaps、Outboard Leading Edge Flap、Outer wing、Aileron and inner wing，The outside of inner wing and the fixing connection of outer wing，Outboard Leading Edge Flap is connected to outer nose of wing，Inside Leading Edge Flaps is connected to interior nose of wing，The trailing edge of outer wing connects aileron，For formula obtuse sawtooth transition of splaying between described Inside Leading Edge Flaps and Outboard Leading Edge Flap，This obtuse sawtooth transition link together with Outboard Leading Edge Flap Tong Bu deflection，A slit is had between Inside Leading Edge Flaps and described obtuse sawtooth transition，The leading edge of described obtuse sawtooth transition with come flow path direction in wingpiston in an acute angle，Splayed formula obtuse sawtooth transition by formation，Can weaken or eliminate the eddy current that sawtooth is deviate from top airfoil，Strength of vortex near sawtooth reduces，The flowing of top airfoil is more stable，Boundary region adverse pressure gradient more relaxes，Burble point is more posteriorly，Improve wing to fall off characteristic.
Description
Technical field
The present invention relates to a kind of band sawtooth swept-back wing that improves transonic speed fall off the wing of characteristic.
Background technology
In transonic speed maneuvering flight, extremely complex flow field around aircraft, can be generated.Swept-back wing with leading edge dog-tooth
Airplane is when transonic speed maneuvering flight, and shock wave can cause the eddy current of leading edge of a wing sawtooth to rupture, and then causes air-flow to separate.
If the shock wave formed on the wing of left and right is asymmetric, then cause separating flowing field the most asymmetric so that side wing absence of aura ground is suddenly
Stall, causes the unexpected rolling of aircraft, is commonly called as " wing drop " phenomenon, makes the lateral stability of aircraft and maneuverability be remarkably decreased, pole
The earth threatens flight safety.The engineering development stage prototype of this type of layout such as " Super Hornet " F/A-18E/F is at Mach number
0.7～0.95, highly 3000～12000 meters, under the transonic speed flying condition that the angle of attack is 6 °～12 °, this phenomenon the most once occurred, should
Problem was passed in succession through change droope snoot deflection program by Boeing later and had established newly on wingfold mechanism more than one
Hole door is tentatively solved.
Occur wing fall off phenomenon time flow field be extremely complex, mainly show themselves in that edge strip/wing joint,
The positions such as droope snoot, wingtip, head and vertical fin root are by the complicated wave system of multiple tracks Shock wave；At LEX vortex and droope snoot
Sawtooth whirlpool and the many places such as wing tip produce vortex；Vortex interacts on vortex breakdown and the impact separating generation with shock wave.
The whirlpool entering shock wave system under state of falling off is unstable and pulsation, the unsymmetry in flow field and non-stationarity ten
Clearly demarcated aobvious.
How on the premise of ensureing aircraft lifting resistance characteristic and stealth effect, weaken upper surface of the airfoil strength of vortex and
The air-flow that vortex breakdown causes under Shock wave interaction separates, thus the aircraft improving band routine sawtooth swept-wing layout is transonic speed dashed forward
So stalling characteristics, for improving the horizontal flight quality of this type of band sawtooth swept-wing layout aircraft and buffeting characteristic, will have weight
The engineer applied wanted is worth.
Summary of the invention
For disadvantage mentioned above, the present invention provides a kind of band sawtooth swept-back wing that improves transonic speed to fall off the wing of characteristic.
It is an object of the invention to be achieved through the following technical solutions:
A kind of band sawtooth swept-back wing that improves transonic speed is fallen off the wing of characteristic, before Inside Leading Edge Flaps, outside
Edge wing flap, outer wing, aileron and inner wing, the outside of inner wing and outer wing are fixing to be connected, and Outboard Leading Edge Flap is connected to outer nose of wing, interior
Side droope snoot is connected to interior nose of wing, and the trailing edge of outer wing connects aileron, described Inside Leading Edge Flaps and the outside leading edge flap
For formula obtuse sawtooth transition of splaying between the wing, this obtuse sawtooth transition link together with Outboard Leading Edge Flap Tong Bu deflection, interior
A slit, the leading edge of described obtuse sawtooth transition and the side of stream is had between side droope snoot and described obtuse sawtooth transition
To in an acute angle in wingpiston.
The present invention also has a following technical characteristic: the leading edge of described obtuse sawtooth transition with carry out flow path direction at wingpiston
Interior angular range is 15 °～75 °.
Beneficial effects of the present invention and advantage be: is splayed formula obtuse sawtooth transition by formation, can weaken or eliminate saw
The eddy current that tooth is deviate from top airfoil, the strength of vortex near sawtooth reduces, and the flowing of top airfoil is more stable, boundary region adverse pressure gradient
More relaxing, burble point more posteriorly, can reduce eddy current and rupture caused separation area scope under Shock wave interaction, improve
Wing is fallen off characteristic；Alleviate owing to air-flow separates the wing unsteady flo w load caused, improve wing and transonic speed buffet
Characteristic, the present invention designs simply, constructs the advantages such as reasonable, with low cost, flexible practicality, has preferable application prospect.
Accompanying drawing explanation
Fig. 1 is the overall structure top view of the present invention.
Fig. 2 is the partial schematic diagram of the present invention.
Fig. 3 is the A-A profile of Fig. 2.
Fig. 4 is the structural representation of embodiments of the invention 2.
Detailed description of the invention
The invention will be further described in citing below in conjunction with the accompanying drawings:
Embodiment 1
As Figure 1-3: a kind of band sawtooth swept-back wing that improves transonic speed is fallen off the wing of characteristic, including inner side leading edge
Wing flap 1, Outboard Leading Edge Flap 4, outer wing 5, aileron 6 and inner wing 7, the outside of inner wing 7 and the fixing connection of outer wing 5, the outside leading edge flap
The wing 4 is connected to outer wing 5 leading edge, and Inside Leading Edge Flaps 1 is connected to inner wing 7 leading edge, and the trailing edge of outer wing 5 connects aileron 6, described
For formula obtuse sawtooth transition 3 of splaying between Inside Leading Edge Flaps 1 and Outboard Leading Edge Flap 4, before this obtuse sawtooth transition 3 and outside
Edge wing flap links together and synchronizes deflection, has a slit, institute between Inside Leading Edge Flaps 1 and described obtuse sawtooth transition 3
The leading edge of the obtuse sawtooth transition 3 stated is 15 °～75 ° with carrying out flow path direction angular range in wingpiston.The present embodiment exists
During transonic speed is motor-driven, the deflection angle of Inside Leading Edge Flaps 1, Outboard Leading Edge Flap 4 and aileron 6 according to state of flight by flying
Row control program determines.
Embodiment 2
As shown in Figure 4: a kind of band sawtooth swept-back wing that improves transonic speed is fallen off the wing of characteristic, including the inner side leading edge flap
The wing 1, Outboard Leading Edge Flap 4, outer wing 5, aileron 6 and inner wing 7, the outside of inner wing 7 and the fixing connection of outer wing 5, Outboard Leading Edge Flap 4
Being connected to outer wing 5 leading edge, Inside Leading Edge Flaps 1 is connected to inner wing 7 leading edge, and the trailing edge of outer wing 5 connects aileron 6, and described is interior
For formula obtuse sawtooth transition 3 of splaying between side droope snoot 1 and Outboard Leading Edge Flap 4, this obtuse sawtooth transition 3 and outside leading edge
Wing flap links together and synchronizes deflection, has a slit, this reality between Inside Leading Edge Flaps 1 and described obtuse sawtooth transition 3
The wing aspect ratio executing example is 2.0, Inside Leading Edge Flaps 1 leading edge sweep 30 °, Outboard Leading Edge Flap 4 leading edge sweep 35 °,
Inside Leading Edge Flaps 1 and inclined 10 ° of Outboard Leading Edge Flap 4 times, inclined 5 ° of aileron 6 times, the leading edge of obtuse sawtooth transition 3 with carry out flow path direction
Angle in wingpiston is 30 °, can improve this wing Transonic Wing under flight speed 0.85Ma and fall off spy
Property and buffet characteristic.
Claims (2)
1. improve band sawtooth swept-back wing transonic speed to fall off the wing of characteristic, before Inside Leading Edge Flaps (1), outside
Edge wing flap (4), outer wing (5), aileron (6) and inner wing (7), the outside of inner wing (7) and outer wing (5) are fixing to be connected, the outside leading edge flap
The wing (4) is connected to outer wing (5) leading edge, and Inside Leading Edge Flaps (1) is connected to inner wing (7) leading edge, and the trailing edge of outer wing (5) connects pair
The wing (6), it is characterised in that: for formula obtuse sawtooth mistake of splaying between described Inside Leading Edge Flaps (1) and Outboard Leading Edge Flap (4)
Crossing (3), this obtuse sawtooth transition (3) links together with Outboard Leading Edge Flap Tong Bu deflection, Inside Leading Edge Flaps (1) and described
Obtuse sawtooth transition (3) between have a slit, the leading edge of described obtuse sawtooth transition (3) is put down at wing with carrying out flow path direction
In face in an acute angle.
A kind of band sawtooth swept-back wing that improves the most according to claim 1 is transonic speed fallen off the wing of characteristic, its feature
It is: the leading edge of described obtuse sawtooth transition (3) is 15 °～75 ° with carrying out flow path direction angular range in wingpiston.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610808422.0A CN106275387A (en) | 2016-09-07 | 2016-09-07 | A kind of band sawtooth swept-back wing that improves transonic speed is fallen off the wing of characteristic |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610808422.0A CN106275387A (en) | 2016-09-07 | 2016-09-07 | A kind of band sawtooth swept-back wing that improves transonic speed is fallen off the wing of characteristic |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106275387A true CN106275387A (en) | 2017-01-04 |
Family
ID=57711232
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610808422.0A Pending CN106275387A (en) | 2016-09-07 | 2016-09-07 | A kind of band sawtooth swept-back wing that improves transonic speed is fallen off the wing of characteristic |
Country Status (1)
| Country | Link |
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| CN (1) | CN106275387A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444612A (en) * | 2017-08-15 | 2017-12-08 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of change leading edge of a wing device of λ wings Flying-wing unmanned vehicle |
| CN111216877A (en) * | 2018-11-26 | 2020-06-02 | 空中客车营运有限公司 | Aircraft control mechanism, aircraft wing and aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6513754B1 (en) * | 2001-09-26 | 2003-02-04 | The United States Of America As Represented By The Secretary Of The Navy | Transonic flow shockwave position stabilizer |
| CN103057691A (en) * | 2011-09-06 | 2013-04-24 | 空中客车西班牙运营有限责任公司 | Aircraft tail surface with leading edge section of undulated shape |
| CN103592099A (en) * | 2013-11-28 | 2014-02-19 | 中国航空工业集团公司沈阳空气动力研究所 | Measuring equipment for wind tunnel free-rolling vibration test and measuring method thereof |
| CN105644770A (en) * | 2015-12-30 | 2016-06-08 | 哈尔滨工业大学 | Sharkskin-imitating resistance-reducing wing |
| CN205998114U (en) * | 2016-09-07 | 2017-03-08 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of improvement is transonic speed fallen off with sawtooth swept-back wing the wing of characteristic |
-
2016
- 2016-09-07 CN CN201610808422.0A patent/CN106275387A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6513754B1 (en) * | 2001-09-26 | 2003-02-04 | The United States Of America As Represented By The Secretary Of The Navy | Transonic flow shockwave position stabilizer |
| CN103057691A (en) * | 2011-09-06 | 2013-04-24 | 空中客车西班牙运营有限责任公司 | Aircraft tail surface with leading edge section of undulated shape |
| CN103592099A (en) * | 2013-11-28 | 2014-02-19 | 中国航空工业集团公司沈阳空气动力研究所 | Measuring equipment for wind tunnel free-rolling vibration test and measuring method thereof |
| CN105644770A (en) * | 2015-12-30 | 2016-06-08 | 哈尔滨工业大学 | Sharkskin-imitating resistance-reducing wing |
| CN205998114U (en) * | 2016-09-07 | 2017-03-08 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of improvement is transonic speed fallen off with sawtooth swept-back wing the wing of characteristic |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107444612A (en) * | 2017-08-15 | 2017-12-08 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of change leading edge of a wing device of λ wings Flying-wing unmanned vehicle |
| CN111216877A (en) * | 2018-11-26 | 2020-06-02 | 空中客车营运有限公司 | Aircraft control mechanism, aircraft wing and aircraft |
| CN111216877B (en) * | 2018-11-26 | 2024-06-07 | 空中客车营运有限公司 | Aircraft control mechanism, aircraft wing and aircraft |
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Application publication date: 20170104 |