CN104908975B - 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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- CN104908975B CN104908975B CN201510219732.4A CN201510219732A CN104908975B CN 104908975 B CN104908975 B CN 104908975B CN 201510219732 A CN201510219732 A CN 201510219732A CN 104908975 B CN104908975 B CN 104908975B
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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 one
Change method for designing.
Background technology
Near Space Flying Vehicles research is one of focus of international at present competitively contention space technology, and scramjet engine
Research is again because its important strategic importance becomes the most important thing of Near Space Flying Vehicles development.With the U.S., Russia and German, method, Australia as representative
World powers all carrying forward vigorously respective scramjet engine research plan ([1] joseph, m.h, james
s.m.richard c.m.,the x-51a scramjet engine flight demonstration program[r],
15th aiaa international space 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 hypersonic systems and
technologies conference,2008).
It is anterior that hypersonic inlet is typically arranged in aircraft, with aircraft precursor moulding merge completely, Integral design,
X43 the and x51 aircraft developed in the recent period as the U.S..It's safe to say, hypersonic inlet has become as contact aircraft
Precursor and the important tie of propulsion system, therefore, realize the one that it is critical only that propulsion system and body of hypersonic flight
Change design, and the core of body/Propulsion Integrated is then the integration of aircraft precursor and air intake duct.Precursor is for flight
The effect of device is mainly and provides high lift-drag ratio and the pneumatic thermal protective performance of good leading edge；And the major function of air intake duct is pressure
Contracting hypersonic flowing, provide for combustion chamber that to promote effective source of the gas of burning to be down to flowed energy loss minimum simultaneously.Tradition
Method for designing be first to design aircraft precursor, according to design the aircraft precursor shape that completes design corresponding air intake duct with
Match, the shortcoming of this method for designing is, aircraft precursor is discrete design with air intake duct, then intercouples, and leads to design
Interfere between the precursor completing and air intake duct, the incident shock being produced by aircraft precursor is by the incident shock to air intake duct
Produce harmful effect, lead to air intake duct capture ability to reduce, spillage drag increases, and then reduce the ability to work of propulsion system.
Two parts are not only separately designed and trade off superposition again by integrated design, must take into full account in design process its with
Aircraft precursor aerodynamic characteristics, the coupling of three-dimensional profile, therefore, study efficient air intake duct precursor design method most important.
Content of the invention
Present invention aims to existing aircraft precursor and shortcoming present on air intake duct discrete design, provide
A kind of fixing geometry, design point come to flow shock wave patch mouth, low mach automatic overflow, aircraft precursor produce incident shock pair
Inlet characteristic does not produce impact, improves aircraft precursor and the internal waverider hypersonic inlet of propulsion system overall performance
Integrated design method.
The present invention comprises the following steps:
1) construct axial symmetry contract basic flow field, axial symmetry contract basic flow field for 360 ° of revolving body centres of gyration is
Axial symmetry contract basic flow field centre of gyration line, axial symmetry contract basic flow field includes axial symmetry contract basic flow field and flies
Inner wave rider type air inlet channel taking part in row device precursor portions, axial symmetry contract basic flow field, two parts are mutually different by compression angle
Article two, compression molded line is constituted；
2) use cfd technology to solve axial symmetry contract basic flow field, obtain axial symmetry contract basic flow field aircraft
Inner wave rider type air inlet channel taking portions incident shock wave, axial symmetry contract in precursor portions incident shock, axial symmetry contract basic flow field
Basic flow field reflected shock wave；
3) given aircraft precursor and internal waverider hypersonic inlet integrated apparatus export molded line, before aircraft
Body is separated into a little and in axial symmetry contract basic flow field with internal waverider hypersonic inlet integrated apparatus outlet molded line
Carry out reverse streamlined impeller in axial slices；
4) streamline between the intersection point of extraction streamline and reflected shock wave and streamline and the intersection point of incident shock, as aircraft
Precursor and the compression molded line of internal waverider hypersonic inlet integrated apparatus, the streamline after blocking is respectively arranged in axle pair
Internal waverider hypersonic inlet import molded line is obtained, aircraft precursor leading edge is caught in title contract basic flow field axial slices
Obtain molded line and air intake duct shoulder molded line；
5) geometric modeling completes aircraft precursor and the design of internal waverider hypersonic inlet integrated apparatus, interior rider
Compression-type face between formula hypersonic inlet import molded line and aircraft precursor leading edge capture molded line is aircraft precursor,
The compression-type face that aircraft precursor leading edge captures between molded line and air intake duct shoulder molded line is internal waverider hypersonic air inlet
Road, by air intake duct shoulder molded line, equivalent stretching obtains air intake duct distance piece backward, that is, complete aircraft precursor high with interior rider formula
Supersonic Inlet integrated design.
Advantages of the present invention is as follows:
Aircraft precursor and internal waverider hypersonic inlet integrated apparatus are a kind of fixing geometry air intake ducts.Flight
Device precursor can provide high lift coefficient for aircraft, and interior inner wave rider type air inlet channel taking ensure that air intake duct full flow captures, and increases
Reduce spillage drag while big motor power, be connected using two sections of different compression molded line of compression angle, the interior receipts of composition
Contracting basic flow field can meet the design requirement of aircraft precursor and interior rider air intake duct, realizes aircraft precursor and interior rider formula
The integrated design of hypersonic inlet.
Brief description
Fig. 1 is axial symmetry contract basic flow field schematic diagram.
Fig. 2 is axial symmetry contract basic flow field radial section figure.
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 side view.
Fig. 7 is aircraft precursor and internal waverider hypersonic inlet integrated apparatus upward view.
In figure is respectively labeled as: 1 represent hypersonic to flow, 2 expression axial symmetry contract basic flow field aircraft precursors
Partly, 3 represent that inner wave rider type air inlet channel taking part in axial symmetry contract basic flow field, 4 expression axial symmetry contract basic flow field fly
Row device precursor portions incident shock, 5 represent axial symmetry contract basic flow field in inner wave rider type air inlet channel taking portions incident shock wave, 6
Represent axial symmetry contract basic flow field reflected shock wave, the 7 expression axial symmetry contract basic flow field centres of gyration, 8 expression axles
The intersection point of the streamline in symmetrical contract basic flow field, 9 expression streamlines and reflected shock wave, 10 expression streamlines and incident shock
The intersection point of intersection point, 11 expression streamlines and air intake duct portions incident shock wave, 12 expression aircraft precursors are ultrasonic with interior rider formula height
Fast air intake duct integrated apparatus outlet molded line, 13 represent axial symmetry contract basic flow field axial slices, 14 represent in rider
Formula hypersonic inlet import molded line, 15 represent aircraft precursor leading edges capture molded line, 16 represent air intake duct shoulder molded line,
17 represent air intake duct distance piece, 18 expression aircraft precursors, 19 expression internal waverider hypersonic inlets.
Specific embodiment
Referring to Fig. 1～7, aircraft precursor and interior rider formula high supersonic velocity air intake duct integrated design method, it is a kind of empty
The mimetic design method of aerodynamics, first specifies its aerodynamic feature instead to release the design meeting this feature again.
Aircraft precursor is included with the key step of interior rider formula high supersonic velocity air intake duct integrated design method:
1st, construct axial symmetry contract basic flow field, axial symmetry contract basic flow field for 360 ° of revolving body centres of gyration is
Axial symmetry contract basic flow field centre of gyration line 7, axial symmetry contract basic flow field includes axial symmetry contract basic flow field
Inner wave rider type air inlet channel taking part 3 in aircraft precursor part 2, axial symmetry contract basic flow field, two parts are by the mutual not phase of compression angle
Two same compression molded line are constituted；
2nd, use cfd technology to solve axial symmetry contract basic flow field, obtain axial symmetry contract basic flow field aircraft
Inner wave rider type air inlet channel taking portions incident shock wave 5, the interior receipts of axial symmetry in precursor portions incident shock 4, axial symmetry contract basic flow field
Contracting basic flow field reflected shock wave 6；
3rd, given aircraft precursor and internal waverider hypersonic inlet integrated apparatus outlet molded line 12, by aircraft
Precursor and internal waverider hypersonic inlet integrated apparatus outlet molded line 12 be separated into a little and basic in axial symmetry contract
Carry out reverse streamlined impeller in flow field axial slices 13；
4th, the streamline between the intersection point 9 of extraction streamline and reflected shock wave and the intersection point 10 of streamline and incident shock, as winged
The compression molded line of row device precursor and internal waverider hypersonic inlet integrated apparatus, by the streamline after blocking be respectively arranged in
Obtain internal waverider hypersonic inlet import molded line 14 in axial symmetry contract basic flow field axial slices 13, before aircraft
Body leading edge capture molded line 15 and air intake duct shoulder molded line 16；
5th, geometric modeling completes aircraft precursor and the design of internal waverider hypersonic inlet integrated apparatus, interior rider
Compression-type face between formula hypersonic inlet import molded line 14 and aircraft precursor leading edge capture molded line 15 is aircraft
Precursor 18, it is high that the compression-type face that aircraft precursor leading edge captures between molded line 15 and air intake duct shoulder molded line 16 is interior rider formula
Supersonic Inlet 19, by air intake duct shoulder molded line 16, equivalent stretching obtains 17 air intake duct distance pieces backward；So far, complete to fly
Device precursor and internal waverider hypersonic inlet integrated design.
Aircraft precursor and interior rider formula high supersonic velocity air intake duct integrated design method, this example gives free stream Mach number ma
=6.5, incident shock angle beta=12 °, integrated apparatus as shown in Figure 4 can be designed.Described device by aircraft precursor 18, interior take advantage of
Waves hypersonic inlet 19 is formed with air intake duct distance piece 17.This device shock wave under design condition pastes cause for gossip completely and now manages
It is more than 100% by capture flow.
Aircraft precursor designed by the present invention and internal waverider hypersonic inlet integrated apparatus, including aircraft
, for three-dimensional to contract, distance piece is to wait directly for precursor, air intake duct contraction section and distance piece, aircraft precursor and air intake duct contraction section
Passage.Hypersonic form initial shock wave at aircraft precursor to flow, and it is incident to form three-dimension curved surface at inlet mouth
Shock wave, air intake duct three-dimensional inlet face is completely enclosed by this shock wave.
The present invention is based on axial symmetry contract basic flow field.Described axial symmetry contract basic flow field only includes axle
Symmetrical contract revolution wall, this contract revolution wall is by this contract basic flow field by the different compression-type of two sections of compression angles
Line connects composition, carries out the basic flow of different radial positions after specified distance piece outlet shapes in each circumferential plane of air intake duct
Field streamlined impeller, thus ensure that this contract 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 conventional gas introduction road is led because of precursor effect
Cause the serious shortcoming of spillover, realize air intake duct full flow and capture to flow, increase and while motor power, reduce overflow
Resistance；Increase the working range of air intake duct, improve the low mach performance of air intake duct.
Claims (1)
1. aircraft precursor and internal waverider hypersonic inlet integrated design method are it is characterised in that include following walking
Rapid:
1) construct axial symmetry contract basic flow field, axial symmetry contract basic flow field is 360 ° of revolving bodies, the centre of gyration is axle
Symmetrical contract basic flow field centre of gyration line, axial symmetry contract basic flow field includes the flight of axial symmetry contract basic flow field
Inner wave rider type air inlet channel taking part in device precursor portions, axial symmetry contract basic flow field, two parts are by compression angle mutually different two
Bar compression molded line is constituted；
2) use cfd technology to solve axial symmetry contract basic flow field, obtain axial symmetry contract basic flow field aircraft precursor
In portions incident shock wave, axial symmetry contract basic flow field, inner wave rider type air inlet channel taking portions incident shock wave, axial symmetry contract are basic
Flow field reflected shock wave；
3) given aircraft precursor and internal waverider hypersonic inlet integrated apparatus export molded line, by aircraft precursor with
Internal waverider hypersonic inlet integrated apparatus outlet molded line is separated into a little and in axial symmetry contract basic flow field axial direction
Carry out reverse streamlined impeller in tangent plane；
4) extract the intersection point of streamline and reflected shock wave, and its part and the intersection point of incident shock between, as aircraft precursor
With the compression molded line of internal waverider hypersonic inlet integrated apparatus, the streamline after blocking is respectively arranged in axial symmetry
Internal waverider hypersonic inlet import molded line, aircraft precursor leading edge trap-type is obtained in contracted basic flow field axial slices
Line and air intake duct shoulder molded line；
5) geometric modeling completes aircraft precursor and the design of internal waverider hypersonic inlet integrated apparatus, and interior rider formula is high
Compression-type face between Supersonic Inlet import molded line and aircraft precursor leading edge capture molded line is aircraft precursor, flight
The compression-type face that device precursor leading edge captures between molded line and air intake duct shoulder molded line is internal waverider hypersonic inlet, will
Equivalent stretching obtains air intake duct distance piece to air intake duct shoulder molded line backward, that is, complete aircraft precursor and internal waverider hypersonic
Air intake duct integrated design.
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN106250597B (en) * | 2016-07-26 | 2019-03-22 | 厦门大学 | It is a kind of it is complete flow direction suction three-dimensional in rotate into air flue design method |
| 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 |
| 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 |
| CN109927917B (en) * | 2019-04-22 | 2020-10-16 | 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 |
| 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 |
| CN110566348B (en) * | 2019-09-03 | 2021-05-25 | 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 |
| 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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