CN203962165U - Based on close cone, lead the bump inlet of rider theory - Google Patents
Based on close cone, lead the bump inlet of rider theory Download PDFInfo
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- CN203962165U CN203962165U CN201420357200.8U CN201420357200U CN203962165U CN 203962165 U CN203962165 U CN 203962165U CN 201420357200 U CN201420357200 U CN 201420357200U CN 203962165 U CN203962165 U CN 203962165U
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- bulge
- intake duct
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- close cone
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Abstract
The bump inlet of leading rider theory based on close cone, relates to supersonic vehicle.Be provided with bulge and the intake duct lip cover of based on close cone, leading rider theory; The described bulge of leading rider theory based on close cone is provided with bulge compression profile, edge compression molded line in face of bulge compression-type; Described intake duct lip is covered with inlet lip, intake duct side overflow mouth, wherein inlet lip is class ellipse arc, the Three-Dimensional Shock Wave curve producing with the bump inlet of leading rider theory based on close cone fits, between lip and bulge compression profile, have intake duct side overflow mouth, the shape of intake duct side overflow mouth is determined according to intake duct reflected shock wave.The bulge of leading rider theory based on close cone covers in bulge compression profile edge with intake duct lip and is connected.The utility model is that supersonic vehicle bump inlet is introduced new variable, and the shape of bulge is controlled, thereby obtains out meeting the bump inlet of different flight state.
Description
Technical field
The utility model relates to supersonic vehicle, especially relates to a kind of bump inlet of leading rider theory based on close cone.
Background technique
For a long time, supersonic flight is that the mankind constantly pursue and the dream surmounting all the time, is also the study hotspot in aerospace field forward position.Air-breathing Propulsion is the foundation stone that supersonic flight is achieved.The engine compartment scramjet engine of Air-breathing Propulsion first-selection.And scramjet engine is most important, and determine that the constituent element whether motor works is exactly Supersonic Inlet.The Main Function of intake duct is to compress incoming flow and improve the blending that incoming-flow pressure is fuel and incoming flow to provide condition, thereby promotes the burning of fuel, for supersonic vehicle provides enough thrust.Research shows, hydrocarbon fuel aircraft to Mach number 5 to 7 one-levels, the every raising 1% of compression efficiency of intake duct, will for propulsion system bring 3% to 5% specific impulse gain (You Yancheng. three-dimensional internal waverider hypersonic inlet design method is studied with flow performance. Nanjing Aero-Space University's thesis for the doctorate. 2008,1-23) therefore, the height of inlet characteristic is directly connected to the overall performance of motor, intake duct is carried out to deep research work, explore novel design concept and have great significance for supersonic flight.
The nineties in 20th century, U.S. Lip river. horse company starts to seek the new method of alternative conventional ultrasound speed Design of Inlet, proposes a kind ofly can effectively arrange the Supersonic Inlet Design method of moving boundary layer, is bump inlet.At the beginning of the nineties, USAF has comprehensively compared after all kinds of Supersonic Inlets, has affirmed the comprehensive advantage of bump inlet, thinks that this intake duct has the high feature of the good vital capacity of Stealth Fighter.Therefore, US military adopt bump inlet as the intake method of F-35 (Eric Hesh JSF. Diverter-less Supersonic Inlet[R]. Lockheed Martine Aeronautics Company. Washington D C.2000).
Traditional bump inlet is led rider Theoretical Design based on cone, feature due to conical flow itself, can in the compression profile of bump inlet, construct stronger pressure gradient, thereby most of fuselage boundary layer is blown out outside air inlet road junction, boundary layer is low speed low energy air-flow, if enter firing chamber, will have a negative impact to burning, therefore, bump inlet does not need to take boundary layer to improve inlet characteristic every road, blowing/technology such as suction.Also because bump inlet has been cancelled boundary layer every devices such as road, earial drainage systems, make aircraft there is very big advantage at aspects such as performance, mobility, stealthy, structure and quality.(Yang Yingkai. brave imperial aircraft Bump Design of Inlet. Nanjing Aero-Space University's journal. the 39th the 4th phase of volume in 2007: 450-45).
Traditional bump inlet, though have very large advantage, due to cone, leading the theoretical intrinsic narrow limitation of rider is that profile of shock wave is defined as conical shock wave, cause bulge air inlet to bulge design be tending towards monotony.By analyzing the demand of supersonic inlet, the utility model proposes a kind of bump inlet of leading rider theory based on close cone is that bump inlet is introduced new variable, the shape of bulge is controlled, thereby obtained out meeting the bump inlet of different flight state.
Summary of the invention
The purpose of this utility model aims to provide a kind of bump inlet of leading rider theory based on close cone.
The utility model is provided with bulge and the intake duct lip cover of leading rider theory based on close cone; The described bulge of leading rider theory based on close cone is provided with bulge compression profile, edge compression molded line in face of bulge compression-type; Described intake duct lip is covered with inlet lip, intake duct side overflow mouth, wherein intake duct bulge compression profile contains two larger bulges, middle part is slightly sagging, inlet lip is class ellipse arc, the Three-Dimensional Shock Wave curve producing with the bump inlet of leading rider theory based on close cone fits, and between lip and bulge compression profile, has intake duct side overflow mouth, and the shape of intake duct side overflow mouth is determined according to intake duct reflected shock wave.The bulge of leading rider theory based on close cone covers in bulge compression profile edge with intake duct lip and is connected.
Advantage of the present utility model: when keeping existing bump inlet advantage, for bump inlet has added a new variables, changed the bulge shape of traditional bump inlet, thereby increased the diversity of bump inlet.Inlet lip shape described in the utility model, can make incident shock major part all in the reflection of lip cover place, thereby avoid lip cover place to produce a large amount of overflows, improves the traffic capture coefficient of intake duct.
Accompanying drawing explanation
Fig. 1 leads the bump inlet front view of rider theory based on close cone.
Fig. 2 leads the bump inlet complete section right elevation of rider theory based on close cone.
Fig. 3 leads the bump inlet bulge compression profile line drawing of rider theory based on close cone.
In figure, 1 represents to lead based on close cone the Three-Dimensional Shock Wave curve that the bump inlet of rider theory produces, 2 represent bulge leading edge upper surface molded line, 3 represent bump inlet bulge leading edge compression molded line, 4 represent to lead based on close cone the bulge compression profile of rider theory, 5 represent inlet lip, 6 represent supersonic speed incoming flow, 7 represent the local compression of bulge molded line, 8 represent the local lower surface molded line of bulge, 9 represent bump inlet lip cover, 10 represent the bump inlet incident shock of leading rider theory based on close cone, 11 represent intake duct side overflow mouth, 12 intake duct reflected shock waves.
Embodiment
The utility model embodiment comprises bulge and the bump inlet lip cover 9 of leading rider theory based on close cone; The described bulge of leading rider theory based on close cone comprises the bulge compression profile 4 of leading rider theory based on close cone, bump inlet bulge leading edge compression molded line 3; Described intake duct lip cover 9 comprises inlet lip 5, intake duct side overflow mouth 11, wherein inlet lip 5 is class ellipse arc, the Three-Dimensional Shock Wave curve 1 producing with the bump inlet of leading rider theory based on close cone fits, at inlet lip 5 and lead based on close cone between the bulge compression profile 4 of rider theory and have intake duct side overflow mouth 11, the shape of intake duct side overflow mouth 11 is determined according to intake duct reflected shock wave 12.The bulge compression profile 4 of leading rider theory based on close cone is connected in the edge that leads the bulge compression profile 4 of rider theory based on close cone with intake duct lip cover 9.
Claims (1)
1. based on close cone, lead the bump inlet of rider theory, be provided with bulge and the intake duct lip cover of based on close cone, leading rider theory; The described bulge of leading rider theory based on close cone is provided with bulge compression profile, edge compression molded line in face of bulge compression-type; Described intake duct lip is covered with inlet lip, intake duct side overflow mouth, wherein inlet lip is class ellipse arc, the Three-Dimensional Shock Wave curve producing with the bump inlet of leading rider theory based on close cone fits, between lip and bulge compression profile, there is intake duct side overflow mouth, the shape of intake duct side overflow mouth is definite according to intake duct reflected shock wave, and the bulge of leading rider theory based on close cone covers in bulge compression profile edge with intake duct lip and is connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420357200.8U CN203962165U (en) | 2014-07-01 | 2014-07-01 | Based on close cone, lead the bump inlet of rider theory |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420357200.8U CN203962165U (en) | 2014-07-01 | 2014-07-01 | Based on close cone, lead the bump inlet of rider theory |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203962165U true CN203962165U (en) | 2014-11-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420357200.8U Expired - Fee Related CN203962165U (en) | 2014-07-01 | 2014-07-01 | Based on close cone, lead the bump inlet of rider theory |
Country Status (1)
| Country | Link |
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| CN (1) | CN203962165U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105649779A (en) * | 2016-01-29 | 2016-06-08 | 厦门大学 | Design method for bump with controllable transverse pressure gradient |
| CN105697150A (en) * | 2016-03-07 | 2016-06-22 | 厦门大学 | Bump air inlet design method integrating cone-derived and osculating waveriders |
| 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 |
-
2014
- 2014-07-01 CN CN201420357200.8U patent/CN203962165U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105649779A (en) * | 2016-01-29 | 2016-06-08 | 厦门大学 | Design method for bump with controllable transverse pressure gradient |
| CN105697150A (en) * | 2016-03-07 | 2016-06-22 | 厦门大学 | Bump air inlet design method integrating cone-derived and osculating waveriders |
| 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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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141126 Termination date: 20170701 |