CN108533405A - Two-dimensional supersonic inlet with aerial drainage air cleft - Google Patents
Two-dimensional supersonic inlet with aerial drainage air cleft Download PDFInfo
- Publication number
- CN108533405A CN108533405A CN201810227304.XA CN201810227304A CN108533405A CN 108533405 A CN108533405 A CN 108533405A CN 201810227304 A CN201810227304 A CN 201810227304A CN 108533405 A CN108533405 A CN 108533405A
- Authority
- CN
- China
- Prior art keywords
- wall surface
- aerial drainage
- side wall
- drainage air
- air cleft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of two-dimensional supersonic inlet with aerial drainage air cleft, including outside wall surface, internal face, the precursor compressing surface extended forward from inner wall, symmetrically arranged two side walls face；The expansion segment for forming internal channel between the outside wall surface, internal face and two side walls face and extending back from internal channel, which is characterized in that described two side wall surfaces are symmetrically arranged with one or more aerial drainage air clefts, and the aerial drainage air cleft runs through side wall surface.The two dimensional inlet in side wall surface by opening up aerial drainage air cleft, utilize the pressure difference of Inlet, segment boundary layer low energy stream at side wall surface is even detached outside packet discharge air intake duct side wall surface, so that boundary layer of the air intake duct flow field at side wall surface is thinning, reduce influence of the side wall surface boundary layer to compressing surface flow field.The total pressure recovery coefficient and discharge coefficient for effectively increasing air intake duct, improve the performance of air intake duct.
Description
Technical field
The present invention relates to field of flight vehicle design, especially a kind of two-dimensional supersonic inlet with aerial drainage air cleft.
Background technology
Air intake duct provides the gas of low speed heavy pressure for engine chamber, and the kinetic energy of high-speed flow is converted to pressure potential
Energy.Three big components one of of the Supersonic Inlet as punching engine, the quality of performance directly affects the performance of engine
And normal range of operation.Judge the performance quality of Supersonic Inlet mainly to total pressure recovery coefficient, the performances such as discharge coefficient ginseng
Number is evaluated.
Air-flow is in the flow process of wall surface, and due to the effect of gas viscosity, there are the development in boundary layer on wall surface.It is super
There are problems that shock wave boundary layer interaction in the air-flow flowing of velocity of sound air intake duct.Shock wave is beaten in the wall surface for having boundary layer, shock wave
Apply a strong negative sequence harmonic to boundary layer, boundary layer is made to thicken, it could even be possible to leading to boundary layer separation, and detaches packet
Generation circulation area can be made to reduce, cause inlet total pres sure recovery coefficient, discharge coefficient decline.Some researches show that air intake ducts
Flow losses reduce 1 percentage point, the thrust of engine will increase by 1.5 percentage points.Therefore, it is dry to slow down shock-boundary
Disturbing problem becomes one of the research emphasis of supersonic speed/hypersonic flowing.
For two-dimensional supersonic inlet, most of research is concentrated mainly on shock wave and interferes the boundary layer of upper internal face
It influences, because shock wave is directly to beat on wall surface, and there are the reflections of shock wave, have obviously to the performance of air intake duct at upper internal face
It influences.And since two dimensional inlet side wall is parallel with direction of flow, not will produce shock wave generally, thus researcher to binary into
The influence research of the side wall of air flue is less, but the effect in real work engineering between side wall surface and air-flow also has boundary layer hair
Exhibition, while being influenced by negative sequence harmonic after compressing surface shock wave front, the Development of Boundary Layer of side wall surface also rapidly, directly affects
To the compressing surface flow field near side wall surface, lead to the decline of inlet total pres sure recovery coefficient and discharge coefficient.
Invention content
Goal of the invention：In order to overcome the Development of Boundary Layer of air intake duct side wall surface, reduce boundary layer interference, the present invention provides one
Two-dimensional supersonic inlet of the kind with aerial drainage air cleft, to improve the total pressure recovery coefficient and discharge coefficient of air intake duct.
Technical solution：A kind of two-dimensional supersonic inlet with aerial drainage air cleft, including outside wall surface, internal face, from inner wall
The precursor compressing surface that extends forward, symmetrically arranged two side walls face；Between the outside wall surface, internal face and two side walls face
The expansion segment for forming internal channel and extending back from internal channel, described two side wall surfaces are symmetrically arranged with one or more and let out
Gas is stitched, and the aerial drainage air cleft runs through side wall surface.
Advantageous effect：The present invention in the side wall surface of air intake duct by opening up aerial drainage air cleft, using the pressure difference of Inlet,
Segment boundary layer low energy stream at side wall surface is even detached outside packet discharge air intake duct side wall surface so that air intake duct flow field is in side wall
Boundary layer at face is thinning, reduces influence of the side wall surface boundary layer to compressing surface flow field.And it compares and existing cracks in other wall surfaces
Technology, opening up aerial drainage air cleft in side wall surface can effectively carry in the case where not sacrificing flow and flow improves
The high total pressure recovery coefficient of air intake duct, improves the performance of air intake duct.
Further, the side wall surface includes the leading edge seamed edge positioned at side wall surface forward position, the connection of leading edge seamed edge one end
The front end of the outside wall surface, the leading edge seamed edge other end are connected with the front end of the precursor compressing surface, and in order to make aerial drainage gas
Seaming the position set, the boundary layer of side wall surface preferably can be discharged, and the aerial drainage air cleft is from side wall surface and precursor compressing surface phase
It connects to be in side wall surface and extend.
The precursor compressing surface includes at least two compression wedge surfaces of arrangement of extending back successively, adjacent compression wedge surface
Junction forms turn-out track；Each turn-out track is correspondingly arranged an aerial drainage air cleft, the extending direction of each aerial drainage air cleft
Parallel or theoretical shock wave caused by being overlapped at turn-out track corresponding with the aerial drainage air cleft direction.
Description of the drawings
Fig. 1 is the cross-sectional view for the two-dimensional supersonic inlet that the present invention has aerial drainage air cleft；
Fig. 2 be the present invention confirmatory experiment one in any position of side wall surface open up the binary supersonic speed of aerial drainage air cleft into
The cross-sectional view of air flue；
Fig. 3 (a) is not open the prototype two-dimensional supersonic inlet of the aerial drainage air cleft Mach numbers section such as at side wall surface 1mm
Figure；
Fig. 3 (b) is that the two-dimensional supersonic inlet of the aerial drainage air cleft horses such as at side wall surface 1mm are opened up in confirmatory experiment one
Conspicuous several sectional views；
Fig. 3 (c) is not open the prototype two-dimensional supersonic inlet of the aerial drainage air cleft Mach numbers section such as at side wall surface 4mm
Figure；
Fig. 3 (d) is that the two-dimensional supersonic inlet of the aerial drainage air cleft horses such as at side wall surface 4mm are opened up in confirmatory experiment one
Conspicuous several sectional views；
Fig. 3 (e) is not open the prototype two-dimensional supersonic inlet of the aerial drainage air cleft Mach numbers section such as at side wall surface 6mm
Figure；
Fig. 3 (f) is that the two-dimensional supersonic inlet of the aerial drainage air cleft horses such as at side wall surface 6mm are opened up in confirmatory experiment one
Conspicuous several sectional views；
Fig. 3 (g) is not open the prototype two-dimensional supersonic inlet of the aerial drainage air cleft Mach numbers such as at side wall surface 11mm to cut
Face figure；
Fig. 3 (h) is that the two-dimensional supersonic inlet of aerial drainage air cleft is opened up in confirmatory experiment one at side wall surface 11mm etc.
Mach number sectional view；
Fig. 3 (i) is not open the prototype two-dimensional supersonic inlet of the aerial drainage air cleft Mach numbers such as at side wall surface 21mm to cut
Face figure；
Fig. 3 (j) is that the two-dimensional supersonic inlet of aerial drainage air cleft is opened up in confirmatory experiment one at side wall surface 21mm etc.
Mach number sectional view；
Fig. 3 (k) is not open the prototype two-dimensional supersonic inlet of the aerial drainage air cleft Mach numbers such as at side wall surface 36mm to cut
Face figure；
Fig. 3 (l) is that the two-dimensional supersonic inlet of aerial drainage air cleft is opened up in confirmatory experiment one at side wall surface 36mm etc.
Mach number sectional view；
Fig. 4 is the vertical view of Fig. 1 and shows that side wall surface aerial drainage air cleft in confirmatory experiment two cracks the schematic diagram in direction；
Fig. 5 is the equal Ma cloud atlas in confirmatory experiment mesarcs two-dimensional supersonic inlet of the present invention line A-A section along Fig. 1；
Fig. 6 is the line A-A along Fig. 1 that side wall surface opens up the two-dimensional supersonic inlet after aerial drainage air cleft in confirmatory experiment two
The equal Ma cloud atlas in section；
Fig. 7 is the discharge coefficient performance comparison that wall surface cracks and do not crack on the downside of off design point in confirmatory experiment two；
Fig. 8 is that the total pressure recovery coefficient that wall surface cracks and do not crack on the downside of off design point in confirmatory experiment two compares；
Fig. 9 is the close-up schematic view that side wall surface opens up aerial drainage air cleft in different location in confirmatory experiment three；
The situation of change of Flow coefficient of inlet when Figure 10 is aerial drainage air cleft change in location in confirmatory experiment three；
The situation of change of inlet total pres sure recovery coefficient when Figure 11 is aerial drainage air cleft change in location in confirmatory experiment three；
The situation of change of Flow coefficient of inlet when Figure 12 is aerial drainage air cleft change width in confirmatory experiment four；
The situation of change of inlet total pres sure recovery coefficient when Figure 13 is aerial drainage air cleft change width in confirmatory experiment four.
Specific implementation mode
In the following, being described in further details to the present invention in conjunction with attached drawing.
As shown in Figure 1, a kind of two-dimensional supersonic inlet with aerial drainage air cleft, including outside wall surface 1, internal face 2, in
Precursor compressing surface 3 that wall surface extends forward, symmetrically arranged two side walls face 4；The outside wall surface 1, internal face 2 and side wall surface 4
Between form internal channel 5 and the expansion segment 6 that extends back from internal channel.If the air intake duct concrete application is on board the aircraft
When, internal face 2 is the face that air intake duct is arranged close to aircraft fuselage outer surface.The side wall surface 4 includes before being located at side wall surface 4
The leading edge seamed edge 41 on edge, one end of the leading edge seamed edge 41 connect the front end of the seamed edge of the outside wall surface 1, and the other end can be with
Any point on the seamed edge of the precursor compressing surface 3 is connected.And in the present embodiment, preferably, the leading edge seamed edge 41
The other end is connected to the front end of the seamed edge of the precursor compressing surface 3.
In order to reduce influence of the two-dimensional supersonic inlet side wall surface boundary layer to compressing surface flow field, the total of air intake duct is improved
Press recovery coefficient and discharge coefficient.It allows also for and keeps the symmetrical of entire flow field, symmetrically set in described two side wall surfaces 4
One or more aerial drainage air clefts 7 are equipped with, the aerial drainage air cleft 7 runs through side wall surface 4.
Correspondingly, the pressure difference due to Inlet is different, the aerial drainage air cleft 7 can ensure that 4 structure of side wall surface is strong
Under the premise of degree, angle of in any direction, arbitrarily cracking and any width are arranged in any position of the side wall surface 4,
It can realize the purpose of discharge 4 boundary layer low energy stream of side wall surface.And it is further, aerial drainage air cleft 7 is arranged on 4 boundary of side wall surface
Layer develops most rapid region, that is, the region influenced by negative sequence harmonic after the shock wave front of precursor compressing surface 3, can make
The boundary layer for obtaining side wall surface 4 reaches preferably discharge effect.Therefore, preferably, the aerial drainage air cleft 7 is from the side wall surface 4
Extend in side wall surface 4 with the joint of precursor compressing surface 3.
Further, at least two compression wedge surfaces of the precursor compressing surface 3 including the arrangement that extends back successively are adjacent
Compression wedge surface junction formed turn-out track 31；Each turn-out track 31 is correspondingly arranged an aerial drainage air cleft 7, each aerial drainage air cleft
7 extending direction is parallel or is overlapped in the extending direction of the theoretical shock wave 32 generated at turn-out track corresponding with the aerial drainage air cleft 7 31.
For two-dimensional supersonic inlet, the direction that the front end of outside wall surface 1 is directed toward from turn-out track 31 and 4 intersection point of side wall surface is to manage
By the extending direction of shock wave 32.That is, in order to reach best promotion effect, each turn-out track 31, which corresponds to, generates theory together
Shock wave 32, and it is parallel with the extending direction of 31 corresponding aerial drainage air cleft 7 of turn-out track or be overlapped in the extension side of the theory shock wave 32
To.
In the following, in order to verify the present invention, following confirmatory experiment is designed.In experiment, prototype two-dimensional supersonic inlet it is equal
Use design work state for Ma3.5, the four wave system Supersonic Inlet of binary that the angle of attack is 6 °.The precursor compressing surface of the air intake duct
3 are provided with three compression wedge surfaces of the arrangement that extends back successively, and three compression angles are respectively 8.7 °, 10.1 ° and 11.8 °, at this time
Theoretical shock wave just seals.Wherein, two turn-out tracks 31 are formed between three compression wedge surfaces.Second and third reason opinion shock wave 32
The forward position of the outside wall surface is directed toward from two turn-out tracks respectively.The prototype two-dimensional supersonic inlet is not before opening up aerial drainage air cleft
Performance parameter is referring to table 1：
1 side wall surface of table does not open performance parameter before aerial drainage air cleft
Confirmatory experiment one is any position in the two side walls face 4 of prototype two-dimensional supersonic inlet to any direction
Symmetrical two aerial drainage air clefts 7 for opening up any angle and width.Under design work state Ma3.5, opened in position as shown in Figure 2
If after aerial drainage air cleft 7, it is 1.289kg/s, total pressure recovery coefficient 0.683 to measure its discharge coefficient.With prototype binary supersonic speed
Air intake duct is compared, and discharge coefficient improves 1.67%；Total pressure recovery coefficient improves 2.68%.And it ought only open up one or open
If when more than two aerial drainage air clefts 7, although the effect different from promoted, the discharge coefficient measured and total pressure recovery coefficient
It is improved.
Further referring to Fig. 3 (a) to Fig. 3 (l), the prototype two-dimensional supersonic inlet of aerial drainage air cleft 7 is not opened respectively
The two-dimensional supersonic inlet that aerial drainage air cleft 7 is opened up with side wall surface 4, apart from side wall surface 4 be 1mm, 4mm, 6mm, 11mm,
The Mach numbers sectional view such as at six positions of 21mm, 36mm.Compare it is found that opening up the two-dimensional supersonic inlet of aerial drainage air cleft 7
Slightly weaken in the side wall surface boundary layer influence being subject at the positions side wall surface 1mm compared to prototype air intake duct.In distance
At side wall surface 6mm, open up the air intake duct of aerial drainage air cleft 7 is not influenced by side wall surface boundary layer completely, and prototype binary is super
Velocity of sound air intake duct is also influenced by more apparent at side wall surface 21mm, light being nevertheless suffered from side wall surface 36mm
Micro- influence.
So confirmatory experiment one is it can be proved that the present invention opens up aerial drainage gas in the side wall surface 4 of two-dimensional supersonic inlet
Seam 7, which can be realized, is expelled in boundary layer outside side wall surface 4 so that and the boundary layer in the air intake duct flow field at side wall surface 4 is thinning, from
And effectively improve the total pressure recovery coefficient and discharge coefficient of air intake duct.
In order to further verify each preferred embodiment of the present invention, in following confirmatory experiment, by aerial drainage air cleft 7 relative to
The angle of cracking of 4 thickness direction of side wall surface is fixed.Referring to Fig. 4, using the direction of air intake duct from front to back as coordinate system X-axis side
To, using 4 thickness of side wall surface from inside to outside direction as coordinate system Z-direction.The angle of cracking of aerial drainage air cleft 7 is in X-direction
30°。
Referring again to Fig. 1, two aerial drainage air clefts 7 that described two turn-out tracks 31 are correspondingly arranged are opened in side wall surface 4 respectively
Near the position of second and third reason opinion shock wave 32 and it is parallel to theoretical shock wave.Two aerial drainage air clefts 7 are not being opened up
Before, shape shown in Fig. 5 is presented in equal Ma cloud atlas of the prototype two-dimensional supersonic inlet along line A-A section.And in confirmatory experiment two, it opens
If after two aerial drainage air clefts 7, shape shown in Fig. 6 is presented in equal Ma cloud atlas of the two-dimensional supersonic inlet along line A-A section.Again
Together refering to Fig. 7 and Fig. 8, is compared with prototype two-dimensional supersonic inlet, open up the two-dimensional supersonic inlet of aerial drainage air cleft 7
Discharge coefficient and total pressure recovery coefficient are promoted by a relatively large margin.As shown in table 2：
Table 2 open up aerial drainage air cleft near side wall surface theory shock-wave spot after performance parameter
In design work state Ma3.5, discharge coefficient 1.296kg/s improves 2.21%, and total pressure recovery coefficient is
0.698, improve 4.96%.And effect when arbitrarily opening up aerial drainage air cleft 7 in contrast verification experiment one, near theoretical shock wave
And the position for being parallel to theoretical shock wave open up 7 performance of aerial drainage air cleft have be obviously improved.Equally, it further studies in non-design work
Make under state, when Ma3.2 and Ma3.7, the performance before not cracking that compares also is improved, and discharge coefficient is when Ma3.2
1.065kg/s improving 3%；Total pressure recovery coefficient is 0.727, improves 4.91%.Discharge coefficient is 1.379 when Ma3.7,
0.73% is improved, total pressure recovery coefficient 0.644 improves 2.22%.
Degree is improved for inlet characteristic relative to the position of theoretical shock wave 32 in order to further verify aerial drainage air cleft 7
It influences, design verification experiment three.As shown in figure 9, the width of fixed aerial drainage air cleft 7 is that 4mm is constant, respectively in x1, x2, x3, x4
And aerial drainage air cleft 7 is opened up at x5 five.Wherein, x1~x3 is located at 32 front of theoretical shock wave, and the distance of x1 is farthest, and x2 and x3 are gradual
It is close, and theoretical shock wave 32 is just overlapped in the aerial drainage air cleft 7 that the positions x4 are opened up, x5 is located at theoretical shock wave rear.
As shown in Figure 10, Figure 11, it is found that when aerial drainage air cleft 7 moves closer to theoretical shock wave 32, total pressure recovery coefficient
It was substantially improved before this with discharge coefficient, and then started to present to decline again when the theoretical shock wave 32 of x4 and aerial drainage air cleft 7 are overlapped to become
Gesture.The effect that the positions x2 and x3 are promoted is the most apparent, that is to say, that the aerial drainage gas opened up at the side slightly to the front of theoretical shock wave 32
Seam 7, it is the most apparent to the improvement of two-dimensional supersonic inlet.This is because being influenced by boundary layer, the physical location ratio of shock wave
Theoretical position is slightly by preceding.
Continue to verify influence of 7 width of aerial drainage air cleft to inlet characteristic improvement degree, design verification experiment four.It takes respectively
Six crack width d=0mm, 1mm, 2mm, 3mm, 4mm, 5mm, wherein crack width d=0mm when do not crack as.
Under above-mentioned six width that crack, two-dimensional supersonic inlet discharge coefficient and total pressure recovery coefficient such as Figure 12, figure
Shown in 13.It can be found that discharge coefficient and total pressure recovery coefficient have more apparent promotion after cracking, specifically, with aerial drainage gas
The increase of 7 width is stitched, discharge coefficient was obviously improved before this, and after more than 3mm, discharge coefficient starts on a declining curve.For
Total pressure recovery coefficient is equally obviously improved before this with the increase of 7 width of aerial drainage air cleft, after more than 3mm, although still having
Small elevation, but promote effect and gradually weaken.Aerial drainage air cleft 7 can be obtained from figure in 2~5mm, to the discharge coefficient of promotion
Promotion with total pressure recovery coefficient has good effect.
The above is only a preferred embodiment of the present invention, it should be pointed out that in the premise for the design for not departing from the present invention
Under, several deductions or replacement can also be made, these, which are deduced or substitute, is regarded as protection scope of the present invention.
Claims (6)
1. a kind of two-dimensional supersonic inlet with aerial drainage air cleft, including outside wall surface, internal face, extend forward from inner wall
Precursor compressing surface, symmetrically arranged two side walls face；Between the outside wall surface, internal face and two side walls face formed internal channel with
And the expansion segment to extend back from internal channel, which is characterized in that described two side wall surfaces are symmetrically arranged with one or more and let out
Gas is stitched, and the aerial drainage air cleft runs through side wall surface.
2. the two-dimensional supersonic inlet according to claim 1 with aerial drainage air cleft, which is characterized in that the side wall surface
Include the leading edge seamed edge positioned at side wall surface forward position, leading edge seamed edge one end connects the front end of the outside wall surface, leading edge seamed edge
The other end is connected with the front end of the precursor compressing surface, and the aerial drainage air cleft is from side wall surface and precursor compressing surface joint in side
Extend on wall surface.
3. the two-dimensional supersonic inlet according to claim 2 with aerial drainage air cleft, which is characterized in that the precursor pressure
Contracting face includes at least two compression wedge surfaces of arrangement of extending back successively, and the junction of adjacent compression wedge surface forms turn-out track；Often
A turn-out track is correspondingly arranged an aerial drainage air cleft.
4. the two-dimensional supersonic inlet according to claim 3 with aerial drainage air cleft, which is characterized in that described each to let out
The extending direction of gas seam is parallel or is overlapped in the extending direction that turn-out track corresponding with the aerial drainage air cleft is formed by theoretical shock wave.
5. the two-dimensional supersonic inlet according to claim 4 with aerial drainage air cleft, which is characterized in that described each to let out
Gas seam is located at the theoretical shock wave front parallel with the aerial drainage air cleft.
6. according to any two-dimensional supersonic inlet with aerial drainage air cleft of Claims 1 to 5, which is characterized in that institute
The width for stating aerial drainage air cleft is 2~5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810227304.XA CN108533405B (en) | 2018-03-19 | 2018-03-19 | Two-dimensional supersonic inlet with aerial drainage air cleft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810227304.XA CN108533405B (en) | 2018-03-19 | 2018-03-19 | Two-dimensional supersonic inlet with aerial drainage air cleft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108533405A true CN108533405A (en) | 2018-09-14 |
| CN108533405B CN108533405B (en) | 2019-06-14 |
Family
ID=63484136
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810227304.XA Expired - Fee Related CN108533405B (en) | 2018-03-19 | 2018-03-19 | Two-dimensional supersonic inlet with aerial drainage air cleft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108533405B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110043367A (en) * | 2019-04-22 | 2019-07-23 | 南京航空航天大学 | A kind of super/hypersonic inlet of side plate openings |
| CN110594022A (en) * | 2019-09-18 | 2019-12-20 | 南京航空航天大学 | Supersonic two-dimensional air inlet channel with overflow gap on side plate |
| CN113247276A (en) * | 2021-06-30 | 2021-08-13 | 中国人民解放军国防科技大学 | Two-stage pneumatic separation type hypersonic air inlet duct fairing |
| CN113247278A (en) * | 2021-06-30 | 2021-08-13 | 中国人民解放军国防科技大学 | Hypersonic air inlet duct fairing scheme with control surface |
| CN113247279A (en) * | 2021-06-30 | 2021-08-13 | 中国人民解放军国防科技大学 | Scheme for realizing separation of hypersonic air inlet duct fairing by utilizing gap flow |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07189737A (en) * | 1993-12-27 | 1995-07-28 | Natl Aerospace Lab | Intake air bleeding device for supersonic plane |
| JPH07189736A (en) * | 1993-12-27 | 1995-07-28 | Natl Aerospace Lab | Intake side wall for supersonic plane |
| JPH0914053A (en) * | 1995-06-28 | 1997-01-14 | Ishikawajima Harima Heavy Ind Co Ltd | Air bleeding device for intake for supersonic aircraft |
| CN102953825A (en) * | 2012-11-22 | 2013-03-06 | 南京航空航天大学 | Pneumatic supersonic velocity/hypersonic velocity adjustable air inlet passage for self-circulation of forebody |
| CN103950543A (en) * | 2014-04-18 | 2014-07-30 | 南京航空航天大学 | Aircraft supersonic air inlet channel with variable deflation system |
-
2018
- 2018-03-19 CN CN201810227304.XA patent/CN108533405B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07189737A (en) * | 1993-12-27 | 1995-07-28 | Natl Aerospace Lab | Intake air bleeding device for supersonic plane |
| JPH07189736A (en) * | 1993-12-27 | 1995-07-28 | Natl Aerospace Lab | Intake side wall for supersonic plane |
| JPH0914053A (en) * | 1995-06-28 | 1997-01-14 | Ishikawajima Harima Heavy Ind Co Ltd | Air bleeding device for intake for supersonic aircraft |
| CN102953825A (en) * | 2012-11-22 | 2013-03-06 | 南京航空航天大学 | Pneumatic supersonic velocity/hypersonic velocity adjustable air inlet passage for self-circulation of forebody |
| CN103950543A (en) * | 2014-04-18 | 2014-07-30 | 南京航空航天大学 | Aircraft supersonic air inlet channel with variable deflation system |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110043367A (en) * | 2019-04-22 | 2019-07-23 | 南京航空航天大学 | A kind of super/hypersonic inlet of side plate openings |
| CN110594022A (en) * | 2019-09-18 | 2019-12-20 | 南京航空航天大学 | Supersonic two-dimensional air inlet channel with overflow gap on side plate |
| CN113247276A (en) * | 2021-06-30 | 2021-08-13 | 中国人民解放军国防科技大学 | Two-stage pneumatic separation type hypersonic air inlet duct fairing |
| CN113247278A (en) * | 2021-06-30 | 2021-08-13 | 中国人民解放军国防科技大学 | Hypersonic air inlet duct fairing scheme with control surface |
| CN113247279A (en) * | 2021-06-30 | 2021-08-13 | 中国人民解放军国防科技大学 | Scheme for realizing separation of hypersonic air inlet duct fairing by utilizing gap flow |
| CN113247279B (en) * | 2021-06-30 | 2022-06-07 | 中国人民解放军国防科技大学 | Scheme for realizing separation of hypersonic air inlet duct fairing by utilizing gap flow |
| CN113247276B (en) * | 2021-06-30 | 2022-06-07 | 中国人民解放军国防科技大学 | Two-stage pneumatic separation type hypersonic air inlet duct fairing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108533405B (en) | 2019-06-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108533405B (en) | Two-dimensional supersonic inlet with aerial drainage air cleft | |
| CN107089340B (en) | With the integrated lower chin formula supersonic speed of precursor or hypersonic inlet and design method | |
| CN107191272B (en) | A kind of internal channel method for designing profile of rectangle hypersonic inlet | |
| CA2379091C (en) | Supersonic external-compression diffuser and method for designing same | |
| CN106021831B (en) | Adaptive connection reverse backflow slot Design of Inlet method | |
| CN104481700B (en) | Assembly power axisymmetric becomes geometry intake duct, motor and intake duct controlling method | |
| CN106335642B (en) | A kind of noise suppression device for weapon bay based on environmental gas jet flow | |
| RU2011121662A (en) | AIRCRAFT WITH ENGINES PARTially INTEGRATED IN THE FUSELAGE | |
| CN107089341B (en) | With aircraft integrated hypersonic inlet external compression face design method | |
| CN108301926B (en) | Hypersonic convex-to-circular inner contraction air inlet channel and design method thereof | |
| JP6885673B2 (en) | Supersonic cullet intake system front edge slats for improved intake performance in off-design flight conditions | |
| CN107023395A (en) | The supersonic aircraft air intake duct and adjusting method of a kind of adjustable throat area | |
| CN108412618B (en) | Hypersonic/supersonic axisymmetric inlet lip and design method thereof | |
| CN111767613A (en) | Design method of fixed-geometry high-speed air inlet channel inlet section with offset compression surface | |
| CN109367795A (en) | Fuselage bilateral air inlet high-speed aircraft aerodynamic arrangement | |
| CN105523189B (en) | One kind slides the adjustable CARET air intake ducts of variant | |
| CN102817716B (en) | Binary mixed pressure intake duct applied to supersonic solid ramjet | |
| CN108412617B (en) | A kind of air intake duct and widen the design method that air intake duct excess determines free stream Mach number range | |
| CN107341323B (en) | A kind of design method for the continuously adjustable air intake duct that rigid/flexible combines | |
| CN101392686A (en) | Internal waverider hypersonic inlet and design method for giving attention to internal and external flow performance | |
| CN113148192B (en) | Binary adjustable air inlet channel and aircraft forebody integrated assembly and design method | |
| CN109595076B (en) | Air inlet channel protective cover | |
| CN103029830B (en) | A kind of two Waverider is to spelling air suction type hypersonic vehicle precursor and method of designing thereof | |
| CN109899178A (en) | Hypersonic air inlet channel with pre-compression device | |
| CN108502204B (en) | Hypersonic speed combined wedge waverider design method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190614 Termination date: 20210319 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |