CN205370766U - Compromise and bore swell intake duct of leading with close rider - Google Patents
Compromise and bore swell intake duct of leading with close rider Download PDFInfo
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- CN205370766U CN205370766U CN201620170139.5U CN201620170139U CN205370766U CN 205370766 U CN205370766 U CN 205370766U CN 201620170139 U CN201620170139 U CN 201620170139U CN 205370766 U CN205370766 U CN 205370766U
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Abstract
The utility model provides a compromise and bore swell intake duct of leading with close rider, relates to supersonic intake duct. A compromise and bore swell intake duct of leading with close rider that can realize bulging the intake duct pressure distribution and steadilyd decrease to both sides by the centre, strengthens blowdown boundary layer effect is provided. Be equipped with the multishock, this multishock interlude is the circular arc, and both ends are curve, both tangent transition. Intake duct swell lower surface molded lines corresponds the swell curved surface by the surperficial decision of supersonic airframe, interlude circular arc, and the interlude circular arc splices into three -dimensional swell curved surface with the swell curved surface, and the intake duct dustcoat smoothly is connected in the edge with the three -dimensional curved surface of swell that close curve generated, forms whole intake duct. Change the single shortcoming of swell intake duct shape, reduced the overflow resistance simultaneously. Protruding, the mild characteristic in both sides in the middle of having can blowdown boundary layer vortexs. Middle bulge's round conic section uses the awl to lead rider theoretical design, and mild part in both sides and changeover portion are with close rider theoretical design.
Description
Technical field
This utility model relates to Supersonic Inlet, especially relates to a kind of cone of taking into account and leads and the bump inlet of close rider.
Background technology
Supersonic Inlet relies primarily on pressure rise across shock envelope, and the flow-disturbing produced near body boundary-layer usually can produce induction shock wave, causes very big flow losses.Traditional Supersonic Inlet generally uses boundary layer suction every road to stop flow-disturbing to enter air intake duct, to improve inlet total pres sure recovery coefficient.In order to realize air intake duct pumping function, generally require subsidiary earial drainage system, bypath system etc., not only increase aircraft weight, and reduce Stealth Fighter, it is impossible to meet the requirement of advanced fighter.Therefore bulge (Bump) air intake duct is more and more used in recent years.
Bump inlet is a kind of Novel ultrasonic speed Design of Inlet concept.The method arranges the projection bulge compression curved surface as high speed incoming flow at inlet mouth, not only instead of the boundary layer suction between conventional gas introduction road and fuselage every road, also eliminates some control system and complex mechanisms.The use of bump inlet alleviates aircraft weight, indirectly increases the thrust-weight ratio of aircraft, simultaneously because fuselage is close in precursor bulge, is conducive to body-air intake duct integrated design.
American lockheed LMT started to explore bump inlet from nineteen ninety.1996, Luo Ma company reequiped a frame F-16 and has carried out bump inlet proving flight, and finally employs the bump inlet of both sides air inlet on X-35/F-35.Calendar year 2001, China's Chengdu Flight Design institute proceeds by the research of bump inlet, and this technology is applied to " brave dragon " 04 frame.After remodeling in 2004 destroy-10B also changed the outfit below head bump inlet (Tang Xin .DSI air intake duct high wind tunnel testing technology and characteristic research [D]. Nanjing Aero-Space University, 2007.).
Traditional bump inlet leads rider Design Theory generally according to cone.Rely on the conical flow feature of rider bulge, construct the pressure distribution successively decreased to both sides by centre, thus realizing blowing down the effect of boundary region.Ultimate principle is that a virtual circular cone is equivalent to a compression curved surface, produced cone shock be attached to curved edges (poplar should triumphant .Bump Design of Inlet and experimental study [J]. aerodynamic journal, 2007,03 (3): 336-338.).Owing to conical flow itself has transverse and longitudinal barometric gradient, flow field is constantly expanded along axis, thus the flow-disturbing that major part fuselage boundary-layer produces can be got rid of outside air inlet road junction by cone shock.But cone is led the generated bulge of rider theory and is only capable of producing cone shock, causes that bump inlet shape is excessively single, therefore this utility model combines closely cone and leads rider theory, designs and a kind of uses cone to lead and the bump inlet of close rider theory simultaneously.
Summary of the invention
The purpose of this utility model is in that offer can realize bump inlet pressure distribution and be successively decreased to both sides by centre, and a kind of cone of taking into account strengthening blowing down boundary layer effect is led and the bump inlet of close rider.
This utility model is provided with multishock, and this multishock interlude is circular arc, and two ends are curve, both tangent transition；Air intake duct bulge lower surface molded line is determined by supersonic aircraft body surface, interlude circular arc correspondence bulge curved surface, interlude circular arc becomes three-dimensional bulge curved surface with bulge surface joining, the bulge three-dimension curved surface that air intake duct outer housing and osculating curve generate is smoothly connected in edge, forms whole air intake duct.
Compared with tradition bump inlet, this utility model has the advantage that
This utility model changes the shortcoming that bump inlet shape is single, reduces spillage drag simultaneously.Air intake duct bulge of the present utility model has the feature that intermediate projections, both sides are mild, just constitutes the pressure distribution successively decreased by centre to both sides, it is possible to blow down boundary region flow-disturbing.The conical section of intermediate raised portion uses cone to lead the close rider Design Theory of rider Design Theory, both sides flat part and changeover portion.
Accompanying drawing explanation
Fig. 1 leads the bulge 3D solid schematic diagram theoretical with close rider based on cone；
Fig. 2 leads the bulge three-dimensional profile schematic diagram theoretical with close rider based on cone；
Fig. 3 leads the bump inlet principle schematic theoretical with close rider based on cone；
Fig. 4 leads the bulge profile theoretical with close rider based on cone to catch schematic diagram；
Fig. 5 is bump inlet import wave system schematic diagram.
nullFigure is respectively labeled as: 1 represents Supersonic Gas flow path direction，2 represent bulge leading edge point，3 represent bulge longitudinal cross-section，4 represent bulge design section upper surface molded line，5 represent bulge design section lower surface molded line，6 represent bulge three-dimensional profile，7 represent based on the shock wave curve that the close section of the bulge that close rider is theoretical generates，8 represent the radius of curvature leading the cone shock curve that the theoretical bulge conical section of rider generates based on cone，9 represent the cone shock curve leading the theoretical bulge conical section generation of rider based on cone，10 symmetrical center line representing bulge design section，11 represent the center of curvature leading the cone shock curve that the theoretical bulge conical section of rider generates based on cone，The 12 cone shock curves obtained based on Conical Shock Wave theory，13 centers of curvature representing the shock wave curve generated based on the close section of the bulge that close rider is theoretical，14 radius of curvature representing the shock wave curve generated based on the close section of the bulge that close rider is theoretical，15 represent discrete point curvature radius and bulge lower surface molded line intersection point，16 discrete points representing given Three-Dimensional Shock Wave curve，17 represent summit, cone shock flow field，18 represent the circular cone entity corresponding based on boring the bulge conical section leading rider theory，19 represent the taper flow field corresponding based on boring the bulge conical section leading rider theory，20 represent bulge design section，21 represent inlet lip.
Detailed description of the invention
This utility model will be further described by following example in conjunction with accompanying drawing.
Referring to Fig. 1～5, choosing supersonic speed fighter plane bump inlet is object of study, according to the back-stepping design thought that rider is theoretical, provides Three-Dimensional Shock Wave system and Supersonic Stream 1, and given multishock interlude is circular arc 9, and both sides are curve 7.According to given multishock, use cone to lead rider theory and solve circular arc 9, obtain taper flow field 12 and the center of circle 11 thereof.Theoretical by close rider, first curve 7 is separated into many discrete points 16, then uses each discrete point of circular cone flow field calculation to obtain the center of curvature of correspondence；Known bulge design section 20, projection obtains its lower surface molded line 5.Can obtaining in conjunction with Fig. 3, the corresponding radius of curvature 8 of circular arc 9, the corresponding radius of curvature 14 of curve 7 are respectively with the intersection point 15 of lower surface molded line 5.Use cone to lead to carry out streamlined impeller with close rider theory and can obtain bulge three-dimension curved surface 6.Bump inlet lip 21 is positioned at multishock and is close to multishock 19.
This utility model leads each advantage theoretical with close rider in conjunction with cone, and according to the mimetic design thought that rider is theoretical, given Three-Dimensional Shock Wave system, wherein this multishock interlude is circular arc, and two ends are the osculating curve of center of curvature change.The center of circle of circular arc is continuous with the center of curvature of osculating curve, and both secondary phases cut through and cross, and radius of curvature is incremented by along center to both sides.Lead rider Design Theory based on cone and go out bulge curved surface corresponding to interlude circular arc, use close rider Design Theory to go out bulge curved surface corresponding to the osculating curve of two ends.Namely both splicings obtain bulge three-dimension curved surface, and multishock produced by bulge three-dimension curved surface and inlet lip are close to, and then design air intake duct outer housing.Bulge intermediate projections of the present utility model, two ends are mild, just define the barometric gradient successively decreased by centre to both sides, strengthen blowing down the effect of boundary region.
Claims (1)
1. one kind take into account cone lead and the bump inlet of close rider, it is characterised in that being provided with multishock, this multishock interlude is circular arc, and two ends are curve, both tangent transition；Air intake duct bulge lower surface molded line is determined by supersonic aircraft body surface, interlude circular arc correspondence bulge curved surface, interlude circular arc becomes three-dimensional bulge curved surface with bulge surface joining, the bulge three-dimension curved surface that air intake duct outer housing and osculating curve generate is smoothly connected in edge, forms whole air intake duct.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620170139.5U CN205370766U (en) | 2016-03-07 | 2016-03-07 | Compromise and bore swell intake duct of leading with close rider |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620170139.5U CN205370766U (en) | 2016-03-07 | 2016-03-07 | Compromise and bore swell intake duct of leading with close rider |
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| Publication Number | Publication Date |
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| CN205370766U true CN205370766U (en) | 2016-07-06 |
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| CN201620170139.5U Active CN205370766U (en) | 2016-03-07 | 2016-03-07 | Compromise and bore swell intake duct of leading with close rider |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109969374A (en) * | 2019-04-09 | 2019-07-05 | 中国空气动力研究与发展中心计算空气动力研究所 | Biao Mo aerodynamic arrangement and design method for hypersonic boundary layer transition research |
| CN112340014A (en) * | 2020-11-06 | 2021-02-09 | 南京航空航天大学 | Inner-outer flow decoupling double-waverider high-speed air suction type aircraft and generation method thereof |
-
2016
- 2016-03-07 CN CN201620170139.5U patent/CN205370766U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109969374A (en) * | 2019-04-09 | 2019-07-05 | 中国空气动力研究与发展中心计算空气动力研究所 | Biao Mo aerodynamic arrangement and design method for hypersonic boundary layer transition research |
| CN112340014A (en) * | 2020-11-06 | 2021-02-09 | 南京航空航天大学 | Inner-outer flow decoupling double-waverider high-speed air suction type aircraft and generation method thereof |
| CN112340014B (en) * | 2020-11-06 | 2022-05-13 | 南京航空航天大学 | Inner-outer flow decoupling double-waverider high-speed air suction type aircraft and generation method thereof |
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