CN104908975A - Aircraft fore-body and internal waverider-derived hypersonic inlet integrated design method - Google Patents
Aircraft fore-body and internal waverider-derived hypersonic inlet integrated design method Download PDFInfo
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- CN104908975A CN104908975A CN201510219732.4A CN201510219732A CN104908975A CN 104908975 A CN104908975 A CN 104908975A CN 201510219732 A CN201510219732 A CN 201510219732A CN 104908975 A CN104908975 A CN 104908975A
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Abstract
The invention discloses an aircraft fore-body and internal waverider-derived hypersonic inlet integrated design method and relates to an aircraft. The method is characterized in that the method is based on an axisymmetric internal contraction basic flow field; the axisymmetric internal contraction basic flow field only comprises an axisymmetric internal contraction rotary wall surface which is formed by connecting two sections of compression molded lines with different compression angles by the internal contraction basic flow field; after the shape of a separation section outlet is specified, basic flow field flow line tracing in different radial positions is performed on each circumferential plane of an inlet, so as to ensure that the internal contraction basic flow field meets designs of an aircraft fore-body and the hypersonic inlet, and an internal waverider-derived hypersonic inlet integrated device with the fore-body is obtained. The method overcomes the defect that inlet overflow of the traditional inlet is serious due to the action of the fore-body; incoming flow captured by the inlet in full flow is realized; the motor thrust is increased, the overflow resistance is reduced; the working range of the inlet is improved; and the low mach number performance of the inlet is improved.
Description
Technical field
The present invention relates to aircraft, especially relate to a kind of aircraft precursor and internal waverider hypersonic inlet integrated design method.
Background technology
Near Space Flying Vehicles research is current international competitively one of focus of fighting for space technology, and scramjet engine research becomes the most important thing of Near Space Flying Vehicles development because of its important strategic importance.The world powers being representative with the U.S., Russia and German, method, Australia is all carrying forward vigorously respective scramjet engine development effort ([1] Joseph, M.H, James S.M.RichardC.M., The X-51A Scramjet Engine Flight Demonstration Program [R], 15th AIAA InternationalSpace Planes and Hypersonic Systems and Technologies Conference, 2008; [2] Steven, H.W., Col, J.S., Dale S.R.et.al The DARPA/AF Falcon Program:The Hypersonic Technology Vehicle#2 (HCV-2) Flight Demonstration Phase [R], 15th AIAA International Space Planes and HypersonicSystems and Technologies Conference, 2008).
Hypersonic inlet is arranged in aircraft front portion usually, merges completely, Integral design with aircraft precursor moulding, as X43 and the X51 aircraft that the U.S. develops in the recent period.Can say for certain, hypersonic inlet has become the important tie of contact aircraft precursor and propulsion system, therefore, the key realizing hypersonic flight is that the integrated design of propulsion system and body, the core of body/Propulsion Integrated are then the integrations of aircraft precursor and inlet channel.Precursor is mainly for the effect of aircraft and provides high lift-drag ratio and good leading edge Aerodynamic Heating barrier propterty; And the radical function of inlet channel is the hypersonic incoming flow of compression, promote that flowed energy loss is down to minimum by effective source of the gas of burning simultaneously for combustion chamber provides.Traditional method of designing is for first to design aircraft precursor, the corresponding inlet channel of aircraft precursor profile design according to having designed matches with it, the shortcoming of this method of designing is, aircraft precursor and inlet channel are discrete design, intercouple again, cause mutually disturbing between the precursor that designed and inlet channel, the incident shock produced by aircraft precursor produces harmful effect by the incident shock of inlet channel, inlet channel capture ability is caused to reduce, spillage drag increases, and then reduces the working ability of propulsion system.Two parts not only design by integrated design respectively carries out compromise superposition again, must take into full account in design process its with aircraft precursor aerodynamic characteristics, the mating of three-dimensional profile, therefore, study efficient inlet channel precursor design method most important.
Summary of the invention
The object of the invention is to the shortcoming for existing aircraft precursor and inlet channel discrete design exist, a kind of fixing geometry, design point incoming flow shock wave subsides mouth are provided, low mach automatic overflow, the incident shock that aircraft precursor produces does not have an impact to inlet characteristic, improves aircraft precursor and the internal waverider hypersonic inlet integrated design method of propulsion system overall performance.
The present invention includes following steps:
1) contracted basic flow field in tectonic axis symmetry, in rotational symmetry, contracted basic flow field is 360 ° of gyro-rotor center of gyrations is contracted basic flow field center of gyration line in rotational symmetry, in rotational symmetry, contracted basic flow field to comprise in rotational symmetry in contracted basic flow field aircraft precursor part, rotational symmetry inner wave rider type air inlet channel taking part in contracted basic flow field, and two parts are made up of mutually different two the compression molded line of compression angle;
2) use CFD technology to solve contracted basic flow field in rotational symmetry, to obtain in rotational symmetry in contracted basic flow field aircraft precursor portions incident shock wave, rotational symmetry in contracted basic flow field contracted basic flow field reflected shock wave in inner wave rider type air inlet channel taking portions incident shock wave, rotational symmetry;
3) given aircraft precursor and internal waverider hypersonic inlet integrated apparatus export molded line, aircraft precursor and internal waverider hypersonic inlet integrated apparatus are exported molded line and is separated into a little and carries out reverse streamlined impeller in contracted basic flow field axial slices in rotational symmetry;
4) streamline and the intersection point of reflected shock wave and the streamline between streamline and the intersection point of incident shock is extracted, as the compression molded line of aircraft precursor and internal waverider hypersonic inlet integrated apparatus, the streamline after blocking is arranged in rotational symmetry respectively and in contracted basic flow field axial slices, obtains internal waverider hypersonic inlet import molded line, aircraft precursor leading edge catches molded line and inlet channel shoulder molded line;
5) geometric modeling completes aircraft precursor and internal waverider hypersonic inlet integrated apparatus designs, the compression profile that internal waverider hypersonic inlet import molded line and aircraft precursor leading edge are caught between molded line is aircraft precursor, the compression profile that aircraft precursor leading edge is caught between molded line and inlet channel shoulder molded line is internal waverider hypersonic inlet, by the inlet channel shoulder molded line equivalent acquisition inlet channel distance piece that stretches backward, namely complete aircraft precursor and internal waverider hypersonic inlet integrated design.
Advantage of the present invention is as follows:
Aircraft precursor and internal waverider hypersonic inlet integrated apparatus are a kind of fixing geometry inlet channels.Aircraft precursor can provide high lift coefficient for aircraft, interior inner wave rider type air inlet channel taking can ensure that inlet channel full flow is caught, spillage drag is reduced while increasing engine thrust, the compression molded line adopting two sections of compression angles different is connected, the interior contracted basic flow field formed can meet the designing requirement of aircraft precursor and interior rider inlet channel, realizes the integrated design of aircraft precursor and internal waverider hypersonic inlet.
Accompanying drawing explanation
Fig. 1 is contracted basic flow field schematic diagram in rotational symmetry.
Fig. 2 is contracted basic flow field radial section figure in rotational symmetry.
Fig. 3 is aircraft precursor and internal waverider hypersonic inlet integrated design method schematic diagram.
Fig. 4 is aircraft precursor and internal waverider hypersonic inlet integrated apparatus line drawing.
Fig. 5 is aircraft precursor and internal waverider hypersonic inlet integrated apparatus three dimensional sectional view.
Fig. 6 is aircraft precursor and internal waverider hypersonic inlet integrated apparatus lateral plan.
Fig. 7 is aircraft precursor and internal waverider hypersonic inlet integrated apparatus upward view.
Respectively be labeled as in figure: 1 represents hypersonic incoming flow, 2 represent contracted basic flow field aircraft precursor part in rotational symmetry, inner wave rider type air inlet channel taking part in contracted basic flow field in 3 expression rotational symmetry, 4 represent contracted basic flow field aircraft precursor portions incident shock wave in rotational symmetry, inner wave rider type air inlet channel taking portions incident shock wave in contracted basic flow field in 5 expression rotational symmetry, 6 represent contracted basic flow field reflected shock wave in rotational symmetry, 7 represent contracted basic flow field center of gyration in rotational symmetry, 8 represent the streamline in rotational symmetry in contracted basic flow field, the intersection point of 9 expression streamlines and reflected shock wave, the intersection point of 10 expression streamlines and incident shock, the intersection point of 11 expression streamlines and inlet channel portions incident shock wave, 12 represent that aircraft precursor and internal waverider hypersonic inlet integrated apparatus export molded line, 13 represent contracted basic flow field axial slices in rotational symmetry, 14 represent internal waverider hypersonic inlet import molded line, 15 represent that aircraft precursor leading edge catches molded line, 16 represent inlet channel shoulder molded line, 17 represent inlet channel distance piece, 18 represent aircraft precursor, 19 represent internal waverider hypersonic inlet.
Detailed description of the invention
See Fig. 1 ~ 7, aircraft precursor and interior rider formula high supersonic velocity inlet channel integrated design method are a kind of aerodynamic mimetic design methods, namely first specify its aerodynamic feature instead to release the design plan meeting this feature again.
The key step of aircraft precursor and interior rider formula high supersonic velocity inlet channel integrated design method comprises:
1, contracted basic flow field in tectonic axis symmetry, in rotational symmetry, contracted basic flow field is 360 ° of gyro-rotor center of gyrations is contracted basic flow field center of gyration line 7 in rotational symmetry, in rotational symmetry, contracted basic flow field to comprise in rotational symmetry in contracted basic flow field aircraft precursor part 2, rotational symmetry inner wave rider type air inlet channel taking part 3 in contracted basic flow field, and two parts are made up of mutually different two the compression molded line of compression angle;
2, use CFD technology to solve contracted basic flow field in rotational symmetry, to obtain in rotational symmetry in contracted basic flow field aircraft precursor portions incident shock wave 4, rotational symmetry in contracted basic flow field contracted basic flow field reflected shock wave 6 in inner wave rider type air inlet channel taking portions incident shock wave 5, rotational symmetry;
3, given aircraft precursor and internal waverider hypersonic inlet integrated apparatus export molded line 12, aircraft precursor and internal waverider hypersonic inlet integrated apparatus are exported molded line 12 and is separated into a little and carries out reverse streamlined impeller in contracted basic flow field axial slices 13 in rotational symmetry;
4, the streamline between the intersection point 9 of streamline and reflected shock wave and the intersection point 10 of streamline and incident shock is extracted, as the compression molded line of aircraft precursor and internal waverider hypersonic inlet integrated apparatus, the streamline after blocking is arranged in rotational symmetry respectively and in contracted basic flow field axial slices 13, obtains internal waverider hypersonic inlet import molded line 14, aircraft precursor leading edge catches molded line 15 and inlet channel shoulder molded line 16;
5, geometric modeling completes aircraft precursor and internal waverider hypersonic inlet integrated apparatus designs, the compression profile that internal waverider hypersonic inlet import molded line 14 and aircraft precursor leading edge are caught between molded line 15 is aircraft precursor 18, the compression profile that aircraft precursor leading edge is caught between molded line 15 and inlet channel shoulder molded line 16 is internal waverider hypersonic inlet 19, by inlet channel shoulder molded line 16 equivalent stretching acquisition 17 inlet channel distance piece backward; So far, aircraft precursor and internal waverider hypersonic inlet integrated design is completed.
Aircraft precursor and interior rider formula high supersonic velocity inlet channel integrated design method, this routine given free stream Mach number Ma=6.5, β=12 °, incident shock angle, can design integrated apparatus as shown in Figure 4.Described device is made up of with inlet channel distance piece 17 aircraft precursor 18, internal waverider hypersonic inlet 19.This device shock wave under design condition pastes a mouthful realization theory completely and catches flow and be greater than 100%.
Aircraft precursor designed by the present invention and internal waverider hypersonic inlet integrated apparatus, comprise aircraft precursor, inlet channel contraction section and distance piece, and aircraft precursor and inlet channel contraction section are three-dimensional inwardly to shrink, and distance piece such as is at the straight channel.Hypersonic incoming flow forms initial shock wave in aircraft precursor place, and forms three-dimension curved surface incident shock in inlet mouth place, and this shock wave is by completely closed for three-dimensional for inlet channel inlet face.
The present invention is in rotational symmetry based on contracted basic flow field.In described rotational symmetry, contracted basic flow field only comprises in rotational symmetry shrinking back and turns wall, this is interior shrinks back and turns wall and connected to form by the compression molded line that two sections of compression angles are different by this interior contracted basic flow field, carry out the basic flow field streamlined impeller of different radial position in each circumferential plane of inlet channel after specifying distance piece outlet shapes, thus ensure that this interior contracted basic flow field meets the design of aircraft precursor and hypersonic inlet simultaneously, obtain band precursor internal waverider hypersonic inlet integrated apparatus.Instant invention overcomes the shortcoming that conventional gas introduction road causes spillover serious because of precursor effect, realize inlet channel full flow and catch incoming flow, while increasing engine thrust, reduce spillage drag; Increase the operating range of inlet channel, improve the low mach performance of inlet channel.
Claims (1)
1. aircraft precursor and internal waverider hypersonic inlet integrated design method, is characterized in that comprising the following steps:
1) contracted basic flow field in tectonic axis symmetry, in rotational symmetry, contracted basic flow field is 360 ° of gyro-rotor center of gyrations is contracted basic flow field center of gyration line in rotational symmetry, in rotational symmetry, contracted basic flow field to comprise in rotational symmetry in contracted basic flow field aircraft precursor part, rotational symmetry inner wave rider type air inlet channel taking part in contracted basic flow field, and two parts are made up of mutually different two the compression molded line of compression angle;
2) use CFD technology to solve contracted basic flow field in rotational symmetry, to obtain in rotational symmetry in contracted basic flow field aircraft precursor portions incident shock wave, rotational symmetry in contracted basic flow field contracted basic flow field reflected shock wave in inner wave rider type air inlet channel taking portions incident shock wave, rotational symmetry;
3) given aircraft precursor and internal waverider hypersonic inlet integrated apparatus export molded line, aircraft precursor and internal waverider hypersonic inlet integrated apparatus are exported molded line and is separated into a little and carries out reverse streamlined impeller in contracted basic flow field axial slices in rotational symmetry;
4) streamline and the intersection point of reflected shock wave and the streamline between streamline and the intersection point of incident shock is extracted, as the compression molded line of aircraft precursor and internal waverider hypersonic inlet integrated apparatus, the streamline after blocking is arranged in rotational symmetry respectively and in contracted basic flow field axial slices, obtains internal waverider hypersonic inlet import molded line, aircraft precursor leading edge catches molded line and inlet channel shoulder molded line;
5) geometric modeling completes aircraft precursor and internal waverider hypersonic inlet integrated apparatus designs, the compression profile that internal waverider hypersonic inlet import molded line and aircraft precursor leading edge are caught between molded line is aircraft precursor, the compression profile that aircraft precursor leading edge is caught between molded line and inlet channel shoulder molded line is internal waverider hypersonic inlet, by the inlet channel shoulder molded line equivalent acquisition inlet channel distance piece that stretches backward, namely complete aircraft precursor and internal waverider hypersonic inlet integrated design.
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Cited By (9)
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| CN105151306A (en) * | 2015-09-29 | 2015-12-16 | 厦门大学 | Method of integrally designing forebody and air intake duct of cone configuration hypersonic flight vehicle |
| CN106250597A (en) * | 2016-07-26 | 2016-12-21 | 厦门大学 | Air flue design method is rotated in a kind of three-dimensional flowing to suction completely |
| CN106401796A (en) * | 2016-12-06 | 2017-02-15 | 中国科学技术大学 | Shockwave tube |
| CN107514311A (en) * | 2017-10-24 | 2017-12-26 | 西南科技大学 | Based on rotatable air intake duct/waverider forebody derived integrated design method in precursor shock wave |
| CN107867387A (en) * | 2017-10-16 | 2018-04-03 | 中国航天空气动力技术研究院 | Outflow Waverider aircraft layout in a kind of |
| CN109927917A (en) * | 2019-04-22 | 2019-06-25 | 中国人民解放军国防科技大学 | Integrated design method for internal rotation type wave-rider forebody air inlet channel of supersonic aircraft |
| CN110304267A (en) * | 2019-07-19 | 2019-10-08 | 中国人民解放军国防科技大学 | Hypersonic aircraft design method and system |
| CN110566348A (en) * | 2019-09-03 | 2019-12-13 | 中国航空工业集团公司西安飞机设计研究所 | Center line design method for air inlet channel of nacelle |
| CN113800001A (en) * | 2021-09-30 | 2021-12-17 | 西安航天动力研究所 | Design method of internal shrinkage hypersonic inlet channel integrated with forebody |
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Cited By (14)
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| CN105151306A (en) * | 2015-09-29 | 2015-12-16 | 厦门大学 | Method of integrally designing forebody and air intake duct of cone configuration hypersonic flight vehicle |
| CN106250597A (en) * | 2016-07-26 | 2016-12-21 | 厦门大学 | Air flue design method is rotated in a kind of three-dimensional flowing to suction completely |
| CN106401796A (en) * | 2016-12-06 | 2017-02-15 | 中国科学技术大学 | Shockwave tube |
| CN106401796B (en) * | 2016-12-06 | 2017-11-07 | 中国科学技术大学 | A kind of shock tube |
| CN107867387B (en) * | 2017-10-16 | 2019-06-18 | 中国航天空气动力技术研究院 | Outflow Waverider aircraft layout in a kind of |
| CN107867387A (en) * | 2017-10-16 | 2018-04-03 | 中国航天空气动力技术研究院 | Outflow Waverider aircraft layout in a kind of |
| CN107514311B (en) * | 2017-10-24 | 2019-04-30 | 西南科技大学 | Based on air intake duct/waverider forebody derived integrated design method rotatable in precursor shock wave |
| CN107514311A (en) * | 2017-10-24 | 2017-12-26 | 西南科技大学 | Based on rotatable air intake duct/waverider forebody derived integrated design method in precursor shock wave |
| CN109927917A (en) * | 2019-04-22 | 2019-06-25 | 中国人民解放军国防科技大学 | Integrated design method for internal rotation type wave-rider forebody air inlet channel of supersonic aircraft |
| CN110304267A (en) * | 2019-07-19 | 2019-10-08 | 中国人民解放军国防科技大学 | Hypersonic aircraft design method and system |
| CN110304267B (en) * | 2019-07-19 | 2020-08-11 | 中国人民解放军国防科技大学 | Hypersonic aircraft design method and system |
| CN110566348A (en) * | 2019-09-03 | 2019-12-13 | 中国航空工业集团公司西安飞机设计研究所 | Center line design method for air inlet channel of nacelle |
| CN113800001A (en) * | 2021-09-30 | 2021-12-17 | 西安航天动力研究所 | Design method of internal shrinkage hypersonic inlet channel integrated with forebody |
| CN113800001B (en) * | 2021-09-30 | 2024-02-27 | 西安航天动力研究所 | Design method of inner-shrinkage hypersonic air inlet channel integrated with precursor |
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