CN105539863B - Hypersonic aircraft precursor, air intake duct and support plate integrated pneumatic layout method - Google Patents
Hypersonic aircraft precursor, air intake duct and support plate integrated pneumatic layout method Download PDFInfo
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- CN105539863B CN105539863B CN201610067619.3A CN201610067619A CN105539863B CN 105539863 B CN105539863 B CN 105539863B CN 201610067619 A CN201610067619 A CN 201610067619A CN 105539863 B CN105539863 B CN 105539863B
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- support plate
- flow field
- air intake
- intake duct
- precursor
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Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- 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
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
- B64D2033/026—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
Abstract
The invention discloses a kind of hypersonic aircraft precursor, air intake duct and support plate integrated pneumatic layout method, using the combination benchmark flow field of inner cone flow field+constant entropy flow field+truncation Busemann flow field triplicitys, using streamlined impeller technology, based on what air vehicle overall configuration gave size and downstream combustion chamber inlet size are captured from origin stream, from the outlet of downstream inlet road, with the streamline cluster construction precursor compressing surface, air intake duct compressing surface and the support plate lateral compression face that track out, by the smooth linking of precursor, air intake duct and support plate, realize that integrated pneumatic is laid out configuration.Present invention improves the three-D space structure of aircraft precursor air intake duct, the interference effect of support plate is solved by way of side is compressed, unfavorable factor is changed into favourable compensation, reasonably forebody and inlet support plate has been laid out from the angle of space three-dimensional, the flowing is set to remain equal entropy flux to greatest extent simultaneously, be conducive to reducing flow losses, improve aircraft overall performance.
Description
Technical field
The invention belongs to the integrated pneumatic topology field of hypersonic aircraft precursor, air intake duct and support plate, especially
It refers to a kind of Air-breathing hypersonic vehicle precursor for using multimode engine in parallel, air intake duct and support plate integration gas
Dynamic layout method.
Background technology
High speed near space vehicle is countries in the world for the one kind for making full use of space to greatly develop has important war
The slightly aircraft of meaning, including the world of new generation comes and goes vehicle, hypersonic cruise air vehicle, hypersonic long-range passenger plane
Deng；This kind of aircraft is generally using the various combinations propulsion circulatory system based on scramjet engine, such as rocket base, turbine base
The combination circulatory system.
Realize that one of key technology of near space hypersonic flight is aircraft precursor and propulsion system air intake duct
Integrated design, and in order to realize high thrust purpose, be generally arranged side by side multimode in parallel in aircraft precursor leading edge shock layer
Block air intake duct, among these by between aircraft precursor, air intake duct and module support plate integrated pneumatic layout be realize body with
The premise of Propulsion Integrated, the one in the layout process both on Structure of need, will also consider the association on each component function
Adjust：As the precommpression face of air intake duct while aircraft precursor is mainly to provide lift, air intake duct function is to flow as far as possible
Compress to flow for combustion chamber provides suitable air-flow on the premise of loss is low.Traditional way be the precursor that will be designed directly with
Two dimension or three-dimensional Inlet Port Matching, shock wave/boundary-layer that the passive support plate received between air intake duct module is produced are disturbed to whole
The interference in individual flow field, do not consider produce incident shock to capture flow, flow losses, resistance negative influence, and these because
Element will all largely effect on the overall performance of propulsion system.Therefore, aerodynamic arrangement is being carried out to aircraft precursor air intake duct support plate
Before, a suitable basic flow field is built, the combination configuration of efficient overall planning three is most important.
The content of the invention
Be directed to above-mentioned the deficiencies in the prior art, it is an object of the invention to provide a kind of hypersonic aircraft precursor,
Air intake duct and support plate integrated pneumatic layout method, to solve hypersonic aircraft precursor, air intake duct and branch in the prior art
The problem of the overall performance of the design influence propulsion system of plate, eliminates the unfavorable interference that support plate brings, the one for turning to advantage
Change air-flow compression, improve the overall performance of three.
To reach above-mentioned purpose, hypersonic aircraft precursor of the invention, air intake duct and support plate integrated pneumatic layout
Method, including step is as follows：
1）The combination basic flow field in construction inner cone flow field+constant entropy flow field+truncation Busemann flow fields, the combination basic flow field
Inner cone flow field and constant entropy flow field be used for design aircraft precursor part, truncate Busemann flow Field Designs air intake duct and branch plate portion
Point, while combining to ensure aircraft precursor, air intake duct and the integrated configuration of support plate by three kinds of flow fields in flow field；
2）Integrated use is without viscosity flow elementary solution+compressible boundary layer coupling during determining combinations thereof basic flow field
The technology of+Fluid Mechanics Computation, including aircraft precursor leading edge shock, low-angle truncate Busemann flow fields starting shock wave, anti-
Penetrate the positioning of shock wave key position；
3）Given aircraft precursor is to flow capture height, single module width and single module combustion chamber are entered in multimode engine
Shape of the mouth as one speaks line, discrete single module combustion chamber import molded line upstream flows streamlined impeller using combinations thereof basic flow field；Reverse
Truncation Busemann flow fields are initially formed during streamlined impeller, wherein streamline is extracted as air intake duct and support plate integration configuration
Air-flow compression-type face, the leading edge locus of both sides support plate reversely tracing depend on width, the support plate toe angle of engine single module
Degree and plot ratio；The air intake duct compressing surface of body side continues reverse streamlined impeller, forms precursor isentropic Compression face, finally with most
The inner cone flow field of upstream combines at suitable polar angle, is collectively forming aircraft precursor part, and the length and width of precursor is according to winged
Row device overall geometry size and single module engine width are adjusted and block.
Beneficial effects of the present invention：
Aircraft precursor of the invention, air intake duct and support plate are by a kind of thinking comp comprehensive layout three for combining basic flow field
The integral structure of person, ensures that precursor lifting surface, air intake duct, support plate stream the equal entropy flux for keeping low flow losses as far as possible；
By air intake duct side plate and support plate integration, the arrangement of support plate fuel spout, Rocket ejector etc. is not interfered with；To air-flow three
Association's reconciliation process on dimension space, embody structurally and functionally is efficient.
Brief description of the drawings
Fig. 1 is combination basic flow field schematic diagram in the present invention；
Fig. 2 is Busemann flow fields schematic diagram；
Fig. 3 is the Busemann flow fields schematic diagram for truncating；
Fig. 4 is inner cone flow field schematic diagram；
Fig. 5 is single module aircraft precursor, air intake duct and support plate integrated configuration 3-d modelling figure；
Fig. 6 is aircraft precursor, air intake duct and support plate the integrated configuration assembling schematic diagram in overall aircraft；
Fig. 7 flows down pressure distribution on the integrated forebody and inlet plane of symmetry for Mach number 6；
Brief description of the drawings：1 is inner cone flow field in combination basic flow field, 2 in combination basic flow field isentropic stream, 3 be combination
Truncated in basic flow field Busemann flow fields, 4 be aircraft precursor leading edge shock, 5 be the medium entropy Mach wave in constant entropy flow field, 6 be
Wall molded line in Busemann flow fields, 7 be isentropic Compression ripple in Busemann flow fields, 8 be the taper that ends up in Busemann flow fields
Shock wave, 9 are not to truncate wall molded line in Busemann flow fields, 10 to truncate wall molded line in Busemann flow fields, 11 being
First isentropic Compression ripple, 12 are that first shock wave, 13 are inner cone flow field in truncating Busemann flow fields in Busemann flow fields
Wall molded line, 14 be inner cone flow field and constant entropy flow field boundary line, 15 for aircraft precursor isentropic Compression section, 16 be isentropic Compression
Section is support plate leading edge with downstream Busemann air intake ducts boundary line, 17, while being also Busemann air intake duct side plates leading edge, 18 being
Support plate be also simultaneously Busemann air intake ducts side plate, 19 be Busemann air intake duct V-arrangements lip, 20 be side plate and downstream distance piece
Joint line, 21 are to truncate Busemann air intake ducts, 22 be distance piece outlet molded line, 23 to be aircraft precursor, 24 to truncate
Busemann Fighter Inlets, 25 for support plate side wall, 26 be support plate dischargeable capacity, 27 be body.
Specific embodiment
For the ease of the understanding of those skilled in the art, the present invention is made further with reference to embodiment and accompanying drawing
It is bright, the content that implementation method is referred to not limitation of the invention.
Hypersonic aircraft precursor of the invention, air intake duct and support plate integrated pneumatic layout method, including step is such as
Under：
（1）In basis flowing in high-speed aerodynamics field, in accordance with the axle of Taylor-Maccoll governing equations
Symmetric pyramid flowing has four kinds of solutions, and involved combination basic flow field relate to two kinds of solutions therein in the present invention：1）It is parallel equal
Even Supersonic Flow finally pools one independent ending cone shock 8 by symmetric pyramid isentropic Compression ripple 7, after shock wave
Flowing for uniform flow and parallel to flowing, this flow field is Busemann flow fields（Reference picture 2）, due to basic Busemann
The length of air intake duct wall molded line 6 designed by flow field is generally very big, so using truncation Busemann flow fields in actual design（Ginseng
According to Fig. 3）, the wall molded line 9 before air intake duct is truncated shorten to truncate wall molded line 10, Busemann flow fields in Busemann flow fields
In first isentropic Compression ripple 11 be also changed into truncating first shock wave 12 in Busemann flow fields；2）Concurrent flow by flying together
Device precursor leading edge shock 4 is converged to axis, i.e. inner cone flow field（Internal Conical Flow A, ICFA）（Reference picture 4）,
Its wall molded line is inner cone flow field wall molded line 13.As shown in fig. 1, in the aircraft precursor part based on inner cone flow Field Design
And rely on to truncate and build a fillet surface between the integrated air intake duct strip portion that obtains of Busemann flow Field Designs, at this
Air-flow is compressed by continuous constant entropy Mach wave 5 on curved surface, the stream of this continuous compression gas of dependence constant entropy Mach wave 5
Field is referred to as constant entropy flow field 2, with reference to these three flow fields, constructs " inner cone flow field 1（ICFA）+ constant entropy flow field 2+ truncates Busemann streams
Field 3 " combination basic flow field, the configuration that the combination basic flow field is designed is corresponded to by inner cone flow field 1 respectively（ICFA）And isentropic stream
The aircraft precursor parts of the design of field 2, the air intake duct and strip portion that are designed by truncation Busemann flow fields 3.
（2）Hypersonic aircraft scale effect is considered, it is determined that integrated use is without viscosity flow during combination basic flow field
Field elementary solution+compressible boundary layer coupling+Fluid Mechanics Computation（CFD）Technology, wherein passing through quadravalence without viscosity flow elementary solution
Runge-Kutta method solves Taylor-Maccoll equations and obtains；Compressible boundary layer coupling includes：First with streamlined impeller method
Aircraft precursor, air intake duct, the reference model face of support plate are obtained, then using the compressible boundary-layer equation of finite difference method,
The boundary-layer displacement thickness that will be tried to achieve is superimposed on reference model face, obtains final physical face；Finally solved with CFD technologies
Whole combination basic flow field, positions to key position, including aircraft precursor leading edge shock 4, truncation Busemann flow fields
In end up in first shock wave 12, Busemann flow fields the positioning of the key positions such as cone shock 8.
（3）Given aircraft precursor flows capture height, single module width in multimode engine（Reference picture 5) and single mode
Block distance piece exports molded line 22, between side plate and distance piece joint line 20 and distance piece outlet molded line 22 using uiform section product every
From section, streamlined impeller upstream then is flowed using combinations thereof basic flow field, be initially formed in reverse streamline tracing process
Busemann flow fields 3 are truncated, wherein streamline is extracted as air intake duct and the truncation Busemann air intake ducts of support plate integration configuration
21, while the self-starting according to air intake duct requires to form V-arrangement lip 19, the support plate leading edge 17 of both sides support plate reversely tracing is depended on
The width of engine single module, the leading edge angle of support plate 18 and plot ratio；In the side of body 27, from isentropic Compression section and downstream
Continue reverse streamlined impeller at Busemann air intake ducts boundary line 16, precursor isentropic Compression section 15 is formed, finally with most upstream
Inner cone flow field wall molded line 13 is combined at inner cone flow field and constant entropy flow field boundary line 14, with reference to principle be to select to close at 14
Suitable polar angle, is collectively forming aircraft precursor 23, and the length and width of aircraft precursor 23 is according to air vehicle overall physical dimension
It is adjusted and blocks with single module engine width, is finally completed hypersonic aircraft forebody and inlet support plate integration cloth
Office（Reference picture 6）, wherein truncating side wall 25, support plate dischargeable capacity 26, the and of body 27 of Busemann Fighter Inlets 24, support plate
Above-mentioned aircraft precursor 23 collectively forms aircraft precursor, air intake duct and the branch board member of integral structure.
In the case of given free stream Mach number 6, according to the integrated forebody and inlet branch board member designed by method above
As shown in figure 5, the pressure distribution on its plane of symmetry is as shown in Figure 7, it is seen that along journey flow field except the weaker precursor leading edge shock of intensity
Outside reflected shock wave in Busemann flow fields, based on constant entropy flow field, reached subtracts air-flow on the premise of flow losses are low
The purpose of speed supercharging.
Hypersonic aircraft precursor, air intake duct and support plate aerodynamic arrangement structure designed by the present invention, using combination base
This flow field " inner cone flow field+constant entropy flow field+truncation Busemann flow fields ", using streamlined impeller technology, based on air vehicle overall structure
What type gave captures size and downstream combustion chamber inlet size from origin stream, from the outlet of downstream inlet road, with what is tracked out
Streamline cluster construction precursor compressing surface, air intake duct compressing surface and support plate lateral compression face, by the smooth rank of precursor, air intake duct and support plate
Connect, realize that integrated pneumatic is laid out configuration.The combination basic flow field has the isentropic Compression flow field of very big share, with weaker
Shock wave compression intensity and pitot loss, can largely reduce the thrust requirements of aircraft.Simultaneously present invention improves biography
In system aerodynamic arrangement between air intake duct module support plate stream field unfavorable interference, convert the three of integrated support plate inlet structure
Dimension air current composition, is conducive to shortening whole forebody and inlet length under conditions of flow losses are reduced.
Concrete application approach of the present invention is a lot, and the above is only the preferred embodiment of the present invention, it is noted that for
For those skilled in the art, under the premise without departing from the principles of the invention, some improvement can also be made, this
A little improvement also should be regarded as protection scope of the present invention.
Claims (2)
1. a kind of hypersonic aircraft precursor, air intake duct and support plate integrated pneumatic layout method, it is characterised in that including step
It is rapid as follows：
1) the combination basic flow field in construction inner cone flow field+constant entropy flow field+truncation Busemann flow fields, the combination basic flow field it is interior
Coning tower tray and constant entropy flow field are used for designing aircraft precursor part, truncate Busemann flow Field Designs air intake duct and strip portion,
Combine to ensure aircraft precursor, air intake duct and the integrated configuration of support plate by three kinds of flow fields in flow field simultaneously；
2) integrated use is without viscosity flow elementary solution+compressible boundary layer coupling+meter during determining combinations thereof basic flow field
The technology of fluid operator mechanics, including aircraft precursor leading edge shock, low-angle truncate Busemann flow fields starting shock wave, reflection and swash
The positioning of ripple key position；
3) given aircraft precursor is to flow capture height, the shape of the mouth as one speaks is entered in single module width and single module combustion chamber in multimode engine
Line, discrete single module combustion chamber import molded line upstream flows streamlined impeller using combinations thereof basic flow field；In reverse streamline
Truncation Busemann flow fields are initially formed in tracing process, wherein streamline is extracted as air intake duct and the gas of support plate integration configuration
Stream compression-type face, the leading edge locus of both sides support plate reversely tracing depend on the width of engine single module, support plate leading edge angle and
Plot ratio；The air intake duct compressing surface of body side continues reverse streamlined impeller, forms precursor isentropic Compression face, finally and most upstream
Inner cone flow field combined at suitable polar angle, be collectively forming aircraft precursor part, the length and width of precursor is according to aircraft
Overall geometry size and single module engine width are adjusted and block.
2. hypersonic aircraft precursor according to claim 1, air intake duct and support plate integrated pneumatic layout method, its
It is characterised by, described inner cone flow field is converged for concurrent flow passes through one aircraft precursor leading edge shock to axis.
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| CN201610067619.3A CN105539863B (en) | 2016-01-29 | 2016-01-29 | Hypersonic aircraft precursor, air intake duct and support plate integrated pneumatic layout method |
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| CN105539863B true CN105539863B (en) | 2017-06-13 |
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| CN111339672B (en) * | 2020-03-02 | 2021-06-08 | 上海索辰信息科技股份有限公司 | Method for analyzing aerodynamic thermal simulation of shock wave at front edge of air inlet channel |
| CN113236424B (en) * | 2021-06-22 | 2022-07-05 | 西安航天动力研究所 | Double-lower-side rear supersonic air inlet |
| CN113250821B (en) * | 2021-06-30 | 2022-06-07 | 中国人民解放军国防科技大学 | Hypersonic air inlet layout for annular combustion chamber |
| CN114379812B (en) * | 2021-12-28 | 2023-04-28 | 南京航空航天大学 | High-speed precursor/compression surface pneumatic design method with controllable spanwise pressure distribution |
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| US5337975A (en) * | 1992-02-28 | 1994-08-16 | Rockwell International Corporation | Breathing system for hypersonic aircraft |
| US7866599B2 (en) * | 2006-02-14 | 2011-01-11 | Lockheed-Martin Corporation | Integrated inward turning inlets and nozzles for hypersonic air vehicles |
| CN101392685B (en) * | 2008-10-29 | 2010-06-09 | 南京航空航天大学 | Internal waverider hypersonic inlet and design method based on random shock form |
| CN103662087B (en) * | 2013-12-11 | 2015-07-15 | 厦门大学 | Hypersonic aerocraft and air inlet internal and external waverider integrated design method |
| CN104895676A (en) * | 2015-04-14 | 2015-09-09 | 中国科学院力学研究所 | High supersonic speed variable cross section air intake duct and design method thereof |
| CN105151306B (en) * | 2015-09-29 | 2017-02-22 | 厦门大学 | Method of integrally designing forebody and air intake duct of cone configuration hypersonic flight vehicle |
| CN105151307B (en) * | 2015-10-08 | 2017-02-01 | 北京航空航天大学 | Method for cutting Mach surface of hypersonic aircraft with forebody/air inlet pipeline in integrated design |
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