CN105539863A - Integrated aerodynamic layout method for hypersonic aircraft forebody, air inlet duct and supporting plate - Google Patents
Integrated aerodynamic layout method for hypersonic aircraft forebody, air inlet duct and supporting plate Download PDFInfo
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- CN105539863A CN105539863A CN201610067619.3A CN201610067619A CN105539863A CN 105539863 A CN105539863 A CN 105539863A CN 201610067619 A CN201610067619 A CN 201610067619A CN 105539863 A CN105539863 A CN 105539863A
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 6
- 239000002243 precursor Substances 0.000 claims description 53
- 230000035939 shock Effects 0.000 claims description 25
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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; ARRANGEMENT 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
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Abstract
The invention discloses an integrated aerodynamic layout method for a hypersonic aircraft forebody, an air inlet duct and a supporting plate. A combined standard flow field combining an inner core flow field, an isentropic flow field and a truncation Busemann flow field is adopted, a streamline tracer technology is used, based on a free incoming flow capture size and a downstream combustion chamber inlet size given by the overall configuration of an aircraft, a forebody compression face, an air inlet duct compression face and a supporting plate lateral compression face are constructed with traced streamline clusters starting from an outlet of the downstream air inlet duct, and the forebody, the air inlet duct and the supporting plate are smoothly connected to achieve integrated aerodynamic layout configuration. The three-dimensional space structure of the aircraft forebody and the air inlet duct is improved, the disturbing influence of the supporting plate is eliminated in a side face compression mode, adverse factors are converted into favorable compensation, the forebody, the air inlet duct and the supporting plate are reasonably laid out from the space three-dimension perspective, and flowing is kept to be isentropic flowing to the maximum extent, which is beneficial for reducing flowing loss and improving overall performance of the aircraft.
Description
Technical field
The invention belongs to the integrated pneumatic topology field of hypersonic aircraft precursor, inlet channel and support plate, especially for a kind of the Air-breathing hypersonic vehicle precursor, inlet channel and the support plate integrated pneumatic layout method that adopt multimode driving engine in parallel.
Background technology
High speed near space vehicle is countries in the world is make full use of a kind of aircraft with its own strategic significance greatly developed in space, comprises the world of new generation and comes and goes vehicle, hypersonic cruise air vehicle, hypersonic long-range passenger plane etc.; This kind of aircraft adopts the various combinations based on scramjet engine to advance circulating system usually, as rocket base, turbine base combination circulating system.
Realize the integrated design that one of gordian technique of near space hypersonic flight is aircraft precursor and propulsion system inlet channel, and in order to realize high thrust object, usually be arranged side by side multimode inlet channel in parallel in aircraft precursor leading edge shock layer, this is wherein by aircraft precursor, support plate integrated pneumatic layout between inlet channel and module is the prerequisite realizing body and Propulsion Integrated, one in layout process both on Structure of need, also the coordination on each component function to be considered: as the precompressed compression face of inlet channel while aircraft precursor mainly provides lift, inlet channel function compresses incoming flow under the prerequisite that flow losses are low as far as possible for combustion chamber to provide suitable air-flow.Traditional way be by the precursor that designs directly with two dimension or three-dimensional Inlet Port Matching, the passive shock wave accepting the support plate generation between the inlet channel module/interference of boundary-layer interference to whole flow field, do not consider that the incident shock produced is to the negative influence of catching flow, flow losses, resistance, and these factors all will affect the overall performance of propulsion system greatly.Therefore, before carrying out aerodynamic arrangement to aircraft precursor inlet channel support plate, build a suitable basic flow field, the combination configuration of efficient overall planning three is most important.
Summary of the invention
Be directed to above-mentioned the deficiencies in the prior art, the object of the present invention is to provide a kind of hypersonic aircraft precursor, inlet channel and support plate integrated pneumatic layout method, the problem of the overall performance of propulsion system is affected with the design solving hypersonic aircraft precursor, inlet channel and support plate in prior art, eliminate the unfavorable interference that support plate brings, the integrated air flow compression turned to advantage, improves the overall performance of three.
For achieving the above object, hypersonic aircraft precursor of the present invention, inlet channel and support plate integrated pneumatic layout method, comprise step as follows:
1) the combination basic flow field in inner cone flow field+constant entropy flow field+brachymemma Busemann flow field is constructed, the inner cone flow field of this combination basic flow field and constant entropy flow field are used for designing aircraft precursor part, brachymemma Busemann flow Field Design inlet channel and strip portion, combine the integrated configuration ensureing aircraft precursor, inlet channel and support plate by the flow field in three kinds of flow fields simultaneously;
2) determine that in the process of combinations thereof basic flow field, integrated use is without the technology of viscosity flow field basic solution+compressible boundary layer coupling+computational fluid mechanics, comprise the location of aircraft precursor leading edge shock, the initial shock wave in low-angle brachymemma Busemann flow field, reflected shock wave key position;
3) given aircraft precursor incoming flow catches single module width and single module combustion chamber import molded line in height, multimode driving engine, and discrete single module combustion chamber import molded line utilizes combinations thereof basic flow field upstream incoming flow streamlined impeller; First brachymemma Busemann flow field is formed in reverse streamline tracing process, extract the wherein streamline air-flow compression profile as inlet channel and support plate integration configuration, the leading edge locus of both sides support plate reversely tracing depends on the width of driving engine single module, support plate leading edge angle and plot ratio; The inlet channel compressing surface of body side continues reverse streamlined impeller, form precursor isentropic compression face, finally be combined at suitable polar angle place with the inner cone flow field of most upstream, common formation aircraft precursor part, the length of precursor and width carry out adjusting and blocking according to air vehicle overall physical dimension and single module driving engine width.
Beneficial effect of the present invention:
Aircraft precursor of the present invention, inlet channel and support plate combine the thinking comp comprehensive layout of the basic flow field integral structure of three by a kind of, ensure that precursor lifting surface, inlet channel, support plate stream the equal entropy flux keeping low flow losses as far as possible; By inlet channel side plate and support plate integration, the layout of support plate fuel spout, Rocket ejector etc. can not be affected; To the association's reconciliation process on air-flow three dimensional space, what embody on 26S Proteasome Structure and Function is efficient.
Accompanying drawing explanation
Fig. 1 combines basic flow field schematic diagram in the present invention;
Fig. 2 is Busemann flow field schematic diagram;
Fig. 3 is the Busemann flow field schematic diagram of brachymemma;
Fig. 4 is inner cone flow field schematic diagram;
Fig. 5 is single module aircraft precursor, inlet channel and support plate integrated configuration 3-d modelling figure;
Fig. 6 is aircraft precursor, inlet channel and support plate integrated configuration assemble schematic diagram in overall aircraft;
Fig. 7 is integrated forebody and inlet plane of symmetry upward pressure distribution under Mach number 6 incoming flow;
Accompanying drawing illustrates: 1 is inner cone flow field in combination basic flow field, 2 is isentropic flow field in combination basic flow field, 3 is brachymemma Busemann flow field in combination basic flow field, 4 is aircraft precursor leading edge shock, 5 is the medium entropy Mach wave in constant entropy flow field, 6 is wall molded line in Busemann flow field, 7 is isentropic compression ripple in Busemann flow field, 8 is the cone shock that ends up in Busemann flow field, 9 is wall molded line in non-brachymemma Busemann flow field, 10 is wall molded line in brachymemma Busemann flow field, 11 is first isentropic compression ripple in Busemann flow field, 12 is first shock wave in brachymemma Busemann flow field, 13 is inner cone flow field wall molded line, 14 is inner cone flow field and constant entropy flow field boundary line, 15 is the isentropic compression section of aircraft precursor, 16 is isentropic compression section and downstream Busemann inlet channel boundary line, 17 is support plate leading edge, is also Busemann inlet channel side plate leading edge simultaneously, 18 for support plate be also simultaneously Busemann inlet channel side plate, 19 is Busemann inlet channel V-arrangement lip, 20 is side plate and downstream distance piece joint line, 21 is brachymemma Busemann inlet channel, 22 is distance piece outlet molded line, 23 for being aircraft precursor, 24 is brachymemma Busemann Fighter Inlet, 25 is the sidewall of support plate, 26 is support plate effective volume, 27 is body.
Detailed description of the invention
For the ease of the understanding of those skilled in the art, below in conjunction with embodiment and accompanying drawing, the present invention is further illustrated, and the content that embodiment is mentioned not is limitation of the invention.
Hypersonic aircraft precursor of the present invention, inlet channel and support plate integrated pneumatic layout method, comprise step as follows:
(1) in the basis flowing in high-speed aerodynamics field, rotational symmetry conical flow in accordance with Taylor-Maccoll governing equation has four kinds of solutions, combination basic flow field involved in the present invention relate to two kinds of solutions wherein: 1) parallel uniform Supersonic Flow finally pools by symmetric pyramid isentropic compression ripple 7 cone shock 8 that independently ends up together, flowing after shock wave is equal uniform flow and is parallel to incoming flow, this flow field and Busemann flow field (with reference to Fig. 2), inlet channel wall molded line 6 length designed by basic Busemann flow field is usually very large, so adopt brachymemma Busemann flow field (with reference to Fig. 3) in actual design, wall molded line 9 before inlet channel brachymemma shortens to wall molded line 10 in brachymemma Busemann flow field, in Busemann flow field, first isentropic compression ripple 11 also becomes first shock wave 12 in brachymemma Busemann flow field, 2) parallel flow is converged to axis by one aircraft precursor leading edge shock 4, i.e. inner cone flow field (InternalConicalFlowA, ICFA) (with reference to Fig. 4), its wall molded line is inner cone flow field wall molded line 13.As shown in fig. 1, a fillet surface is built between the integrated inlet channel strip portion that aircraft precursor part and the support brachymemma Busemann flow Field Design based on inner cone flow Field Design obtains, this curved surface rely on continuous print constant entropy Mach wave 5 pairs of air-flows compress, the flow field of the continuous pressure gas of this dependence constant entropy Mach wave 5 is called constant entropy flow field 2, in conjunction with these three kinds of flow fields, structure " inner cone flow field 1(ICFA)+2+ brachymemma Busemann flow field, constant entropy flow field 3 " combination basic flow field, the configuration designed of this combination basic flow field is corresponding to inner cone flow field 1(ICFA respectively) and the aircraft precursor part that designs of constant entropy flow field 2, the inlet channel designed by brachymemma Busemann flow field 3 and strip portion.
(2) hypersonic aircraft scale effect is considered, determine that in the process of combination basic flow field, integrated use is without the technology of viscosity flow field basic solution+compressible boundary layer coupling+computational fluid mechanics (CFD), wherein solve Taylor-Maccoll equation without viscosity flow field basic solution by fourth-order Runge-Kutta method and obtain; Compressible boundary layer coupling comprises: first utilize streamlined impeller method to obtain the benchmark profile of aircraft precursor, inlet channel, support plate, then the compressible boundary-layer equation of finite difference method is utilized, the boundary-layer displacement thickness of trying to achieve is superimposed in benchmark profile, obtains final physics profile; Finally use CFD technology to solve whole combination basic flow field, key position is positioned, comprises in aircraft precursor leading edge shock 4, brachymemma Busemann flow field the location of the key positions such as cone shock 8 that end up in first shock wave 12, Busemann flow field.
(3) given aircraft precursor incoming flow catches height, single module width (with reference to Fig. 5) and single module distance piece outlet molded line 22 in multimode driving engine, exporting between molded line 22 at side plate and distance piece joint line 20 and distance piece adopts uniform cross section to amass distance piece, then combinations thereof basic flow field upstream incoming flow streamlined impeller is utilized, first brachymemma Busemann flow field 3 is formed in reverse streamline tracing process, extract the wherein streamline brachymemma Busemann inlet channel 21 as inlet channel and support plate integration configuration, require to form V-arrangement lip 19 according to the self-starting of inlet channel simultaneously, the support plate leading edge 17 of both sides support plate reversely tracing depends on the width of driving engine single module, the leading edge angle of support plate 18 and plot ratio, in body 27 side, reverse streamlined impeller is continued from isentropic compression section and downstream Busemann inlet channel boundary line 16, form precursor isentropic compression section 15, finally be combined with boundary line 14 place, constant entropy flow field in inner cone flow field with the inner cone flow field wall molded line 13 of most upstream, in conjunction with principle be select suitable polar angle at 14 places, common formation aircraft precursor 23, the length of aircraft precursor 23 and width carry out adjusting and blocking according to air vehicle overall physical dimension and single module driving engine width, finally complete hypersonic aircraft forebody and inlet support plate integrated configuration (with reference to Fig. 6), wherein brachymemma Busemann Fighter Inlet 24, the sidewall 25 of support plate, support plate effective volume 26, the aircraft precursor of body 27 and above-mentioned aircraft precursor 23 being integrally formed structure jointly, inlet channel and a plate member.
In given free stream Mach number 6 situation, plate member is propped up as shown in Figure 5 according to the integrated forebody and inlet above designed by method, distribution of pressure on its plane of symmetry as shown in Figure 7, visible along journey flow field except reflected shock wave in the more weak precursor leading edge shock of intensity and Busemann flow field, based on constant entropy flow field, reach the object making flow slowing down supercharging under the prerequisite that flow losses are low.
Hypersonic aircraft precursor designed by the present invention, inlet channel and support plate aerodynamic arrangement structure, adopt combination basic flow field " inner cone flow field+constant entropy flow field+brachymemma Busemann flow field ", utilize streamlined impeller technology, size and fired downstream room inlet size is caught based on the free incoming flow that air vehicle overall configuration is given, from the outlet of downstream inlet road, with the streamline tracked out bunch structure precursor compressing surface, inlet channel compressing surface and support plate lateral compression face, precursor, inlet channel and support plate smoothness is connected, realizes integrated pneumatic layout configuration.This combination basic flow field has the isentropic compression flow field of very great share, has more weak shock wave compression intensity and pitot loss, can reduce the thrust requirements of aircraft to a great extent.Present invention improves the unfavorable interference of support plate stream field between inlet channel module in traditional, pneumatic layout simultaneously, be converted into the three-dimensional air current composition of integrated support plate inlet structure, be conducive to shortening whole forebody and inlet length under the condition reducing flow losses.
Embody rule approach of the present invention is a lot, and the above is only the preferred embodiment of the present invention, should be understood that; for those skilled in the art; under the premise without departing from the principles of the invention, can also make some improvement, these improvement also should be considered as protection scope of the present invention.
Claims (3)
1. hypersonic aircraft precursor, inlet channel and a support plate integrated pneumatic layout method, is characterized in that, comprise step as follows:
1) the combination basic flow field in inner cone flow field+constant entropy flow field+brachymemma Busemann flow field is constructed, the inner cone flow field of this combination basic flow field and constant entropy flow field are used for designing aircraft precursor part, brachymemma Busemann flow Field Design inlet channel and strip portion, combine the integrated configuration ensureing aircraft precursor, inlet channel and support plate by the flow field in three kinds of flow fields simultaneously;
2) determine that in the process of combinations thereof basic flow field, integrated use is without the technology of viscosity flow field basic solution+compressible boundary layer coupling+computational fluid mechanics, comprise the location of aircraft precursor leading edge shock, the initial shock wave in low-angle brachymemma Busemann flow field, reflected shock wave key position;
3) given aircraft precursor incoming flow catches single module width and single module combustion chamber import molded line in height, multimode driving engine, and discrete single module combustion chamber import molded line utilizes combinations thereof basic flow field upstream incoming flow streamlined impeller; First brachymemma Busemann flow field is formed in reverse streamline tracing process, extract the wherein streamline air-flow compression profile as inlet channel and support plate integration configuration, the leading edge locus of both sides support plate reversely tracing depends on the width of driving engine single module, support plate leading edge angle and plot ratio; The inlet channel compressing surface of body side continues reverse streamlined impeller, form precursor isentropic compression face, finally be combined at suitable polar angle place with the inner cone flow field of most upstream, common formation aircraft precursor part, the length of precursor and width carry out adjusting and blocking according to air vehicle overall physical dimension and single module driving engine width.
2. hypersonic aircraft precursor according to claim 1, inlet channel and support plate integrated pneumatic layout method, it is characterized in that, described Busemann flow field is specially: parallel uniform Supersonic Flow finally pools by symmetric pyramid isentropic compression ripple the cone shock that independently ends up together, and the flowing after shock wave is equal uniform flow and is parallel to incoming flow.
3. hypersonic aircraft precursor according to claim 1, inlet channel and support plate integrated pneumatic layout method, is characterized in that, described inner cone flow field is that parallel flow is converged to axis by one aircraft precursor leading edge shock.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111339672A (en) * | 2020-03-02 | 2020-06-26 | 上海索辰信息科技有限公司 | Method for analyzing aerodynamic thermal simulation of shock wave at front edge of air inlet channel |
| CN113236424A (en) * | 2021-06-22 | 2021-08-10 | 西安航天动力研究所 | Double-lower-side rear supersonic air inlet |
| CN113250821A (en) * | 2021-06-30 | 2021-08-13 | 中国人民解放军国防科技大学 | Hypersonic air inlet layout for annular combustion chamber |
| CN114379812A (en) * | 2021-12-28 | 2022-04-22 | 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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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111339672A (en) * | 2020-03-02 | 2020-06-26 | 上海索辰信息科技有限公司 | Method for analyzing aerodynamic thermal simulation of shock wave at front edge of air inlet channel |
| 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 |
| CN113236424A (en) * | 2021-06-22 | 2021-08-10 | 西安航天动力研究所 | Double-lower-side rear supersonic air inlet |
| CN113250821A (en) * | 2021-06-30 | 2021-08-13 | 中国人民解放军国防科技大学 | Hypersonic air inlet layout for annular combustion chamber |
| CN114379812A (en) * | 2021-12-28 | 2022-04-22 | 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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Inventor after: Wang Chengpeng Inventor after: Cheng Chuan Inventor after: Xue Longsheng Inventor after: Yan Lingfeng Inventor after: Tian Xuang Inventor after: Ni Shiyang Inventor after: Cheng Keming Inventor before: Wang Chengpeng Inventor before: Xue Longsheng Inventor before: Cheng Chuan Inventor before: Yan Lingfeng Inventor before: Tian Xuang Inventor before: Ni Shiyang Inventor before: Cheng Keming |
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