CN109367796A - A kind of Submerged Inlet boundary layer control device based on fluid oscillator - Google Patents
A kind of Submerged Inlet boundary layer control device based on fluid oscillator Download PDFInfo
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- CN109367796A CN109367796A CN201811083924.7A CN201811083924A CN109367796A CN 109367796 A CN109367796 A CN 109367796A CN 201811083924 A CN201811083924 A CN 201811083924A CN 109367796 A CN109367796 A CN 109367796A
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- oscillator
- out air
- air cleft
- goes out
- control device
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Revetment (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention provides a kind of Submerged Inlet boundary layer control device based on fluid oscillator, several oscillators are installed in aircraft body (1), is blown down by oscillator and aspirates boundary-layer low energy stream.Relatively previous single blowing or suction boundary-layer low energy stream, the present invention can significantly improve the total pressure recovery coefficient of Submerged Inlet, distortion index are effectively reduced, and have good engineering application value.
Description
Technical field
The invention belongs to flight vehicle aerodynamic design fields, are related to a kind of boundary layer control device, especially a kind of based on stream
The Submerged Inlet boundary layer control device of body oscillator.
Background technique
Submerged Inlet is that import and aircraft combine together, without the special air intake duct of any protrusion.
Submerged Inlet is not only due to the small frontal resistance that can be effectively reduced aircraft of front face area and radar scattering area, and
Its merging with body is conducive to installation, transport and multi-platform transmitting so that the size of body reduces.Therefore, flush type air inlet
Road is by more and more extensive concern and application.
But it is just only relied on since the import of Submerged Inlet is completely disposed in fuselage/bomb body boundary-layer low energy stream
The vortex air inlet that preceding lip is generated perpendicular to the barometric gradient and incline of direction of flow.Suck Submerged Inlet can
A large amount of low energy stream, leads to that air intake port total pressure recovery coefficient is lower, distortion is excessive.
Patent CN102249004 and patent CN101994570 proposes the blowing of the boundary-layer two sides based on vortex generator
For the solution that method and boundary layer are deflated to improve the performance of Submerged Inlet, patent ZL201318007259.5 proposes one
Boundary-layer rear notch of the kind based on vortex generator blows down method to improve the performance of Submerged Inlet.The present invention provides one
Boundary layer separations thinking of the kind based on fluidic oscillator, to improve the performance of Submerged Inlet.
Summary of the invention
The purpose of the present invention: lower biggish with discharge flow distortion for current Submerged Inlet total pressure recovery coefficient
Problem, the present invention provides a kind of a kind of boundary-layers based on fluidic oscillator for being different from vortex generator and boundary layer deflation
Thinking is controlled, to improve the performance of Submerged Inlet.
Technical solution of the present invention: a kind of Submerged Inlet boundary layer control device based on fluid oscillator is flying
Several oscillators are installed in row device body 1, is blown down by oscillator and aspirates boundary-layer low energy stream.
A kind of Submerged Inlet boundary layer control device based on fluid oscillator, the oscillator are mounted on
7 front of Fighter Inlet, symmetrical with 7 central compartment face of Fighter Inlet, distributing position, logarithm are independently adjustable.
A kind of Submerged Inlet boundary layer control device based on fluid oscillator, the oscillator include the
One oscillator goes out air cleft 2, the second oscillator goes out air cleft 3, high pressure chest 4, oscillator entrance 5, Oscillator feedback chamber 6, and described first
Oscillator goes out air cleft 2, the second oscillator goes out air cleft 3 and is located at 1 surface of aircraft body, and 4 high speed air-flow of high-pressure chamber passes through vibration
It swings device entrance 5 to move in Oscillator feedback chamber 6, air cleft 2 is gone out by the first oscillator or the second oscillator goes out air cleft 3 and flows out,
When the first oscillator go out air cleft 2 generate jet stream, the second oscillator go out air cleft 3 and meanwhile can occur flow backwards generate aspirates, with reduce into
Enter the boundary-layer low energy stream on 1 surface of aircraft body of Fighter Inlet 7.
A kind of Submerged Inlet boundary layer control device based on fluid oscillator, oscillator entrance 5, first
Oscillator goes out air cleft 2, the second oscillator goes out air cleft 3 and certain angle θ is presented with 7 central compartment face of Fighter Inlet；Oscillator
Entrance 5 and 1 cross section angle α of aircraft body；First oscillator goes out air cleft 2, the second oscillator go out air cleft 3 respectively with aircraft
Certain angle β 1, β 2 is presented in 1 cross section of body；Angle, θ, α, β 1, β 2 is independently adjustable, changes between 0 °~90 °.
Advantages of the present invention:
A kind of Submerged Inlet boundary layer control device based on fluid oscillator proposed by the present invention, passes through aircraft
Fluidic oscillator is arranged in internal body, and two of oscillator go out air cleft to the boundary-layer of body surface before entrance Fighter Inlet
Blow down while being aspirated.Relatively previous single blowing or suction boundary-layer low energy stream, the present invention can be significantly improved and be buried
The total pressure recovery coefficient for entering formula air intake duct, is effectively reduced distortion index, has good engineering application value.
Detailed description of the invention:
Fig. 1 is present invention layout top view；
Wherein: 1 aircraft body, 2 first oscillator goes out 3 second oscillator of air cleft and goes out 7 Fighter Inlet of air cleft；
Fig. 2 is present invention layout side view；
Wherein: 7 Fighter Inlet of aircraft body, 8 Submerged Inlet；
Fig. 3 is front view of the present invention；
Wherein: 4 high pressure chest, 5 oscillator entrance, 6 Oscillator feedback chamber.
Specific embodiment:
The invention discloses a kind of Submerged Inlet boundary layer control devices based on fluid oscillator.
As shown in FIG. 1 to 3, the boundary layer control device is mounted on 7 front of Fighter Inlet, with Fighter Inlet 7
Central compartment face is symmetrical, and distributing position, logarithm are independently adjustable.
A kind of Submerged Inlet boundary layer control device based on fluid oscillator, including the first oscillator go out air cleft 2,
Second oscillator goes out air cleft 3, high pressure chest 4, oscillator entrance 5, Oscillator feedback chamber 6.Wherein oscillator entrance 5, first vibrates
Device goes out air cleft 2, the second oscillator goes out air cleft 3 and 7 central compartment face of Fighter Inlet and is presented certain angle θ, oscillator entrance 5 with
1 cross section angle α of aircraft body, it is horizontal with aircraft body 1 respectively that the first oscillator goes out air cleft 2, the second oscillator goes out air cleft 3
Certain angle β 1, β 2 is presented in section.Angle, θ, α, β 1, β 2 is independently adjustable, changes between 0 °~90 °.
First oscillator goes out air cleft 2, the second oscillator goes out air cleft 3 and is located at 1 surface of aircraft body, high-pressure chamber 4
High speed air-flow is moved in Oscillator feedback chamber 6 by oscillator entrance 5, goes out air cleft 2 or the second vibration by the first oscillator
It swings device and goes out the outflow of air cleft 3.Jet stream is generated when the first oscillator goes out air cleft 2, the second oscillator, which goes out air cleft 3 while can occur to flow backwards, to be produced
Light soy sauce is inhaled, to reduce the boundary-layer low energy stream on 1 surface of aircraft body for entering Fighter Inlet 7.
Claims (4)
1. a kind of Submerged Inlet boundary layer control device based on fluid oscillator, which is characterized in that in aircraft body
(1) several oscillators are installed in, is blown down by oscillator and aspirates boundary-layer low energy stream.
2. a kind of Submerged Inlet boundary layer control device based on fluid oscillator according to claim 1, special
Sign is that the oscillator is mounted in front of Fighter Inlet (7), symmetrical with Fighter Inlet (7) central compartment face, point
Cloth position, logarithm are independently adjustable.
3. a kind of Submerged Inlet boundary layer control device based on fluid oscillator according to claim 2, special
Sign is that the oscillator includes that the first oscillator goes out air cleft (2), the second oscillator goes out air cleft (3), high pressure chest (4), oscillator
Entrance (5), Oscillator feedback chamber (6), first oscillator goes out air cleft (2), the second oscillator goes out air cleft (3) and is located at aircraft
Body (1) surface, high-pressure chamber (4) high speed air-flow movement in Oscillator feedback chamber (6) by oscillator entrance (5), leads to
It crosses that the first oscillator goes out air cleft (2) or the second oscillator goes out air cleft (3) outflow, generates jet stream when the first oscillator goes out air cleft (2),
Second oscillator, which goes out air cleft (3) while can occur to flow backwards, generates suction, to reduce the aircraft body for entering Fighter Inlet (7)
(1) the boundary-layer low energy stream on surface.
4. a kind of Submerged Inlet boundary layer control device based on fluid oscillator according to claim 3, special
Sign is, oscillator entrance (5), the first oscillator go out air cleft (2), the second oscillator go out air cleft (3) with Fighter Inlet (7)
Certain angle θ is presented in central compartment face；Oscillator entrance (5) and aircraft body (1) cross section angle α；First oscillator goes out
Air cleft (2), the second oscillator go out air cleft (3) and certain angle β 1, β 2 are presented with aircraft body (1) cross section respectively；Angle, θ,
α, β 1, β 2 is independently adjustable, changes between 0 °~90 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811083924.7A CN109367796B (en) | 2018-09-17 | 2018-09-17 | Embedded air inlet boundary layer control device based on fluid oscillator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811083924.7A CN109367796B (en) | 2018-09-17 | 2018-09-17 | Embedded air inlet boundary layer control device based on fluid oscillator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109367796A true CN109367796A (en) | 2019-02-22 |
| CN109367796B CN109367796B (en) | 2022-03-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811083924.7A Active CN109367796B (en) | 2018-09-17 | 2018-09-17 | Embedded air inlet boundary layer control device based on fluid oscillator |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020134891A1 (en) * | 2001-02-09 | 2002-09-26 | Guillot Stephen A. | Ejector pump flow control |
| CN1950255A (en) * | 2004-05-13 | 2007-04-18 | 空中客车德国有限公司 | Boundary layer suction arrangement |
| US20100229952A1 (en) * | 2005-10-06 | 2010-09-16 | Supersonic Aerospace International, Llc | Dual bimorph synthetic pulsator |
| CN101956996A (en) * | 2009-07-08 | 2011-01-26 | 通用电气公司 | The adjustable fluid flow system |
| CN102009744A (en) * | 2010-07-01 | 2011-04-13 | 北京航空航天大学 | Blow/suction control method of flow separation on control surface of airplane |
| CN102249004A (en) * | 2011-05-23 | 2011-11-23 | 南京航空航天大学 | Aircraft using submerged intake |
| CN103616155A (en) * | 2013-11-29 | 2014-03-05 | 中国人民解放军国防科学技术大学 | Flow control device of supersonic flow field |
| CN106809377A (en) * | 2015-12-01 | 2017-06-09 | 波音公司 | A kind of aerodynamic simplified fluidic oscillator for controlling aircraft |
-
2018
- 2018-09-17 CN CN201811083924.7A patent/CN109367796B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020134891A1 (en) * | 2001-02-09 | 2002-09-26 | Guillot Stephen A. | Ejector pump flow control |
| CN1950255A (en) * | 2004-05-13 | 2007-04-18 | 空中客车德国有限公司 | Boundary layer suction arrangement |
| US20100229952A1 (en) * | 2005-10-06 | 2010-09-16 | Supersonic Aerospace International, Llc | Dual bimorph synthetic pulsator |
| CN101956996A (en) * | 2009-07-08 | 2011-01-26 | 通用电气公司 | The adjustable fluid flow system |
| CN102009744A (en) * | 2010-07-01 | 2011-04-13 | 北京航空航天大学 | Blow/suction control method of flow separation on control surface of airplane |
| CN102249004A (en) * | 2011-05-23 | 2011-11-23 | 南京航空航天大学 | Aircraft using submerged intake |
| CN103616155A (en) * | 2013-11-29 | 2014-03-05 | 中国人民解放军国防科学技术大学 | Flow control device of supersonic flow field |
| CN106809377A (en) * | 2015-12-01 | 2017-06-09 | 波音公司 | A kind of aerodynamic simplified fluidic oscillator for controlling aircraft |
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| Publication number | Publication date |
|---|---|
| CN109367796B (en) | 2022-03-15 |
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