CN110188447A - The three-dimensional side of completely pneumatic transition turns oval Design of Inlet method - Google Patents
The three-dimensional side of completely pneumatic transition turns oval Design of Inlet method Download PDFInfo
- Publication number
- CN110188447A CN110188447A CN201910442230.6A CN201910442230A CN110188447A CN 110188447 A CN110188447 A CN 110188447A CN 201910442230 A CN201910442230 A CN 201910442230A CN 110188447 A CN110188447 A CN 110188447A
- Authority
- CN
- China
- Prior art keywords
- dimensional side
- air intake
- intake duct
- oval
- turn
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
Abstract
The invention discloses the three-dimensional sides of complete pneumatic transition to turn oval Design of Inlet method, turn oval air intake duct including three-dimensional side, it includes that three-dimensional side turns oval air intake duct compressing surface, three-dimensional side turns oval inlet lip, three-dimensional side turns oval air intake duct shoulder molded line, three-dimensional side turns oval air intake duct distance piece that three-dimensional side, which turns oval air intake duct, and steps are as follows: 1) solving axial symmetry basic flow field using the method for characteristic curves according to design requirement；2) design three-dimensional side turns oval air intake duct initial outlet class rectangle section, and streamlined impeller is carried out in basic flow field；3) streamline magnification ratio is determined according to entrance, outlet two-dimension projection, carries out coordinate conversion using amplified streamline and generates three-dimensional side turn oval air intake duct compression-type face；4) ellipse air intake duct is turned to hypersonic three-dimensional side based on three-dimensional side turn oval air intake duct compression-type face and carries out geometrical construction, equal vertical pullings are stretched to obtain the oval air intake duct distance piece in three-dimensional side turn backward by the oval air intake duct shoulder molded line in three-dimensional side turn.
Description
Technical field
The present invention relates to the technical fields that three-dimensional side turns oval air intake duct, more particularly to the three of a kind of completely pneumatic transition
Dimension side turns oval Design of Inlet method.
Background technique
The development of near space vehicle is related to national security and peaceful use space, is that space is competitively fought in the current world
One of focus of technology.It is all ground carrying forward vigorously respective hypersonic flight with the U.S., Russia for the world powers of representative
System plan.And key technology of the scramjet engine as realization hypersonic aircraft, even more countries in the world fall over each other to pay close attention to
One of popular domain.Air intake duct is located at the forefront of hypersonic aircraft propulsion system, directly and hypersonic aircraft
Precursor is connected, and plays compression incoming flow, provides the effect of high energy air-flows as more as possible for downstream.It is mentioned by long-term development people
Go out a series of hypersonic inlet forms, specifically includes that dualistic formula air intake duct, axisymmetric air intake duct, side compression type air inlet
Road, and the problems such as design method with regard to them, flow characteristics, working characteristics, Study on Engineering Design, has carried out research.In addition, state
Outer researcher also proposed a series of hypersonic air inlet mentality of designing of three-dimensional contracts and scheme.Such as: U.S. Astrox is public
" Funnel " type air intake duct concept of the propositions such as the P.K.Ajay of department；The M.K.Smart etc. at U.S. spaceflight aerospace research center is mentioned
Out switch to oval outlet for rectangular inlet is smooth；The streamline of the propositions such as Johns Hopkins University, U.S. F.S.Billig chases after
The thinking etc. of track Busemann air intake duct.At home, prolong the scholars such as tomahawk especially and take the lead in outflow rider theoretical origin in air intake duct
In stream research, a kind of three-dimensional contract hypersonic inlet of rider formula in be referred to as is proposed.Numerical simulation and high enthalpy wind
Hole test confirms: under design point, which can capture incoming flow with full flow；In off design point, such air intake duct can be with
Pass through the automatic overflow of import, hence it is evident that improve low mach ability to work, thus there is preferable overall characteristic.
Although items research has been achieved for significantly being in progress, component capabilities in hypersonic inlet research field
Constantly promoted.However, necessarily consistent according to the air intake duct disengaging mouth-shaped that traditional streamlined impeller method generates.M.K.Smart
Also it is converted simply by type face and switchs to oval outlet for rectangular inlet is smooth, this can sacrifice the pneumatic property for rotating into air flue in three-dimensional
Energy.So far, scientific research personnel, which is not yet received, directly streamlined impeller generation class rectangle import pneumatically to transit to ellipse completely
Air flue design method is rotated into the three-dimensional of shape outlet.It can be seen that provide the three-dimensional side turn ellipse of completely pneumatic transition a kind of into
Air port performance is rotated into air flue design method three-dimensional hypersonic to raising to be of great significance with application range.
Summary of the invention
In order to solve the above-mentioned technical problems, the present invention provides a kind of three-dimensional sides of completely pneumatic transition to turn oval air intake duct
Design method.
The present invention adopts the following technical scheme: the three-dimensional side of completely pneumatic transition turns oval Design of Inlet method, including
Three-dimensional side turns oval air intake duct, and it includes that three-dimensional side turns oval air intake duct compressing surface, three-dimensional side that the three-dimensional side, which turns oval air intake duct,
Turn oval inlet lip, three-dimensional side turns oval air intake duct shoulder molded line, three-dimensional side turns oval air intake duct distance piece, the three-dimensional
The import that side turns oval air intake duct is class rectangle, and the outlet that three-dimensional side turns oval air intake duct is ellipse, and the three-dimensional side turns ellipse
Circle air intake duct compression-type face turns flat at the oval air intake duct shoulder molded line in three-dimensional side turn and enters the oval air intake duct isolation in three-dimensional side turn
Section, three-dimensional side turn oval inlet lip position and turn oval air intake duct incident shock reflection point position by three-dimensional side under design condition
Determining, three-dimensional side turns streamline on oval Design of Inlet cone section and exists with streamline on the oval air intake duct in three-dimensional side turn just cone of origin section
The ratio of projector distance in two-dimension projection is streamline magnification ratio in this cone section, is put according to streamline in this cone section
Large scale amplifies corresponding streamline in axial symmetry basic flow field by basic point of air intake duct leading edge point, with same procedure, calculates every
The magnification ratio of streamline in a cone section, and amplified streamline is arranged in corresponding cone section obtain three-dimensional side turn ellipse into
Air flue compression-type face, method and step are as follows:
1) axial symmetry basic flow field is solved using the method for characteristic curves according to design requirement；
2) design three-dimensional side turn ellipse air intake duct initial outlet class rectangle section, and in the step 1) basic flow field into
Row streamlined impeller；
3) streamline magnification ratio is determined according to entrance, outlet two-dimension projection, is sat using amplified streamline
Mark conversion generates three-dimensional side and turns oval air intake duct compression-type face；
4) turn oval air intake duct to hypersonic three-dimensional side based on three-dimensional side turn oval air intake duct compression-type face to carry out
Three-dimensional side is turned oval air intake duct shoulder molded line and vertical pullings is waited to stretch to obtain the oval air intake duct isolation in three-dimensional side turn backward by geometrical construction
Section.
Preferably, the axial symmetry contract basic flow field is 360 ° of revolving bodies, and the centre of gyration is axial symmetry contract base
This flow field centre of gyration line, axial symmetry contract basic flow field include that waves air intake duct portion is held in axial symmetry contract basic flow field
Point, axial symmetry contract basic flow field, which is solved, with the method for characteristic curves obtains the three-dimensional of rider formula in axial symmetry contract basic flow field
Side turns oval Fighter Inlet incident shock, axial symmetry contract basic flow field reflected shock wave.
Preferably, the class rectangle and the oval outlet of design are tangent, and gained streamline is constituted to stream on lateral position
Face obtains the three-dimensional side that inlet and outlet section is all class rectangle and turns oval air intake duct compression-type face.
Compared with prior art, the present invention has the advantage that: turning oval air inlet using the three-dimensional side that the design method generates
Road has combined the starting performance that air flue is rotated into inlet and outlet cross sectional shape and three-dimensional.Air intake duct can to rotate into air flue in three-dimensional
Guarantee that full flow captures incoming flow, reduces outflow resistance while increasing motor power；It again can be automatic in low mach
Overflow is adjusted, the work range of Mach numbers of air intake duct is widened.The three-dimensional side turn ellipse air intake duct of completely pneumatic transition ensure that into
Air flue will not sacrifice aeroperformance due to be changed into ellipse outlet by class rectangle import, thus in the feelings for not reducing lift resistance ratio
The design that three-dimensional side turns oval air intake duct is completed under condition with flying colors.
Detailed description of the invention
Fig. 1 is that the three-dimensional side of completely pneumatic transition turns oval Design of Inlet scheme basic flow field schematic diagram.
Fig. 2 is that the three-dimensional side of completely pneumatic transition turns oval Design of Inlet scheme entrance section and initial outlet section two
Tie up perspective view.
Fig. 3 is that the three-dimensional side of completely pneumatic transition turns oval Design of Inlet scheme general structure schematic diagram.
Fig. 4 is that the three-dimensional side of completely pneumatic transition turns oval Design of Inlet scheme half section structure diagram.
Fig. 5 is that the three-dimensional side of completely pneumatic transition turns oval Design of Inlet scheme left view schematic diagram.
Fig. 6 is that the three-dimensional side of completely pneumatic transition turns oval Design of Inlet scheme elevational schematic view.
Description of symbols: 1, three-dimensional side turns the oval air intake duct plane of reference 2, three-dimensional side turns oval air intake duct leading edge point institute
Turn oval inlet lip 6, three-dimensional side in position 3, the live part 4 of basic flow field streamline, reflected shock wave 5, three-dimensional side
Turn oval Fighter Inlet incident shock 7, basic flow field centre of gyration line 8, streamline and the intersection point 9 of reflected shock wave, three-dimensional side
Turn oval air intake duct initial classes rectangular outlet section 10, three-dimensional side turns oval air intake duct leading edge and captures molded line 11, streamlined impeller
Point set 13 that streamline 12 that method tracks out, basic streamline live part are separated into, that three-dimensional side turns oval Design of Inlet is oval
Outlet 14, three-dimensional side turn streamline 15 on oval Design of Inlet cone section, the oval air intake duct in three-dimensional side turn just cut by cone of origin
Streamline 16, three-dimensional side turn oval air intake duct compression-type face 17, the oval air intake duct distance piece 18 in three-dimensional side turn, three-dimensional side on face
Turn oval air intake duct distance piece outlet 19, three-dimensional side turns oval air intake duct shoulder molded line 20, hypersonic incoming flow.
Specific embodiment
The preferred embodiment of the present invention is described in detail with reference to the accompanying drawing, so that advantages and features of the invention energy
It is easier to be readily appreciated by one skilled in the art, so as to make a clearer definition of the protection scope of the present invention.
In the present embodiment, it is to be understood that term " centre ", "upper", "lower", " top ", " right side ", " left end ",
" top ", " back side ", " middle part ", etc. instructions orientation or positional relationship be based on the orientation or positional relationship shown in the drawings, only
It is of the invention for ease of description, rather than the device or element of indication or suggestion meaning must have a particular orientation, with spy
Fixed orientation construction and operation, therefore be not considered as limiting the invention.
The three-dimensional side of completely pneumatic transition turns oval Design of Inlet method, which is characterized in that turns ellipse including three-dimensional side
Air intake duct, the three-dimensional side turn oval air intake duct include three-dimensional side turn oval air intake duct compressing surface (16), three-dimensional side turn ellipse into
Air flue lip (5), three-dimensional side turn oval air intake duct shoulder molded line (19), three-dimensional side turns oval air intake duct distance piece (17), described
The import that three-dimensional side turns oval air intake duct is class rectangle, and the outlet that three-dimensional side turns oval air intake duct is ellipse, the three-dimensional side
Turn ellipse air intake duct compression-type face (16) and turns flat ellipse into a three-dimensional side turn at the oval air intake duct shoulder molded line (19) in three-dimensional side turn
Circle air intake duct distance piece (17), three-dimensional side turn oval inlet lip (5) position and turn oval air inlet by three-dimensional side under design condition
Road incident shock reflection point position determines that three-dimensional side turns streamline (14) and three-dimensional side on oval Design of Inlet cone section and turns ellipse
The ratio of projector distance of the streamline (15) in two-dimension projection is that streamline is put in this cone section on the first cone of origin section of air intake duct
Large scale amplifies in axial symmetry basic flow field according to streamline magnification ratio in this cone section by basic point of air intake duct leading edge point
Corresponding streamline calculates the magnification ratio of streamline in each cone section with same procedure, and amplified streamline is arranged in
Three-dimensional side is obtained in corresponding cone section and turns oval air intake duct compression-type face (16), and method and step is as follows:
1) axial symmetry basic flow field is solved using the method for characteristic curves according to design requirement；
2) design three-dimensional side turn ellipse air intake duct initial outlet class rectangle section, and in the step 1) basic flow field into
Row streamlined impeller；
3) streamline magnification ratio is determined according to entrance, outlet two-dimension projection, is sat using amplified streamline
Mark conversion generates three-dimensional side and turns oval air intake duct compression-type face (16)；
4) oval air intake duct is turned to hypersonic three-dimensional side based on the oval air intake duct compression-type face (16) in three-dimensional side turn
Geometrical construction is carried out, three-dimensional side is turned into oval air intake duct shoulder molded line (19), vertical pullings is waited to stretch to obtain the oval air inlet in three-dimensional side turn backward
Road distance piece (17).
Preferably, the axial symmetry contract basic flow field is 360 ° of revolving bodies, and the centre of gyration is axial symmetry contract base
This flow field centre of gyration line (7), axial symmetry contract basic flow field include holding waves air inlet in axial symmetry contract basic flow field
Road part solves axial symmetry contract basic flow field with the method for characteristic curves and obtains rider formula in axial symmetry contract basic flow field
Three-dimensional side turns oval Fighter Inlet incident shock (6), axial symmetry contract basic flow field reflected shock wave (4).
Preferably, the class rectangle and the oval outlet of design are tangent, and gained streamline is constituted to stream on lateral position
Face obtains the three-dimensional side that inlet and outlet section is all class rectangle and turns oval air intake duct compression-type face (16).
The three-dimensional side of this complete pneumatic transition turns oval Design of Inlet method and is keeping the oval air intake duct in three-dimensional side turn excellent
While point, realizes class rectangle entrance and pneumatically transit to oval outlet completely.Three-dimensional side turns oval Design of Inlet cone and cuts
Cone of origin section at the beginning of streamline (14) turns oval air intake duct relative to initial classes rectangular outlet section same position three-dimensional side on face is upper
Line (15) magnification ratio is simultaneously little.Therefore, the change of outlet shape turns the aerodynamic characteristic shadow of oval air intake duct to three-dimensional side
Sound can be ignored.Turn oval air inlet to complete three-dimensional side under conditions of not sacrificing three-dimensional side and turning oval air intake duct aerodynamic characteristic
The design in road.
Not limited to this, any change or replacement expected without creative work should all be covered in guarantor of the invention
Within the scope of shield.Therefore, protection scope of the present invention should be determined by the scope of protection defined in the claims.
Claims (3)
1. the three-dimensional side of completely pneumatic transition turns oval Design of Inlet method, which is characterized in that including three-dimensional side turn ellipse into
Air flue, it includes that three-dimensional side turns oval air intake duct compressing surface (16), three-dimensional side turns oval air inlet that the three-dimensional side, which turns oval air intake duct,
Road lip (5), three-dimensional side turn oval air intake duct shoulder molded line (19), three-dimensional side turns oval air intake duct distance piece (17), and described three
The import that dimension side turns oval air intake duct is class rectangle, and the outlet that three-dimensional side turns oval air intake duct is ellipse, and the three-dimensional side turns
Oval air intake duct compression-type face (16) turns to turn to put down into three-dimensional side at oval air intake duct shoulder molded line (19) to turn ellipse in three-dimensional side
Air intake duct distance piece (17), three-dimensional side turn oval inlet lip (5) position and turn oval air intake duct by three-dimensional side under design condition
Incident shock reflection point position determines, three-dimensional side turn on oval Design of Inlet cone section streamline (14) and three-dimensional side turn ellipse into
The ratio of projector distance of the streamline (15) in two-dimension projection is streamline amplification in this cone section on the first cone of origin section of air flue
Ratio, according to streamline magnification ratio in this cone section, it is right in axial symmetry basic flow field to amplify using air intake duct leading edge point as basic point
The streamline answered calculates the magnification ratio of streamline in each cone section with same procedure, and amplified streamline is arranged in pair
It should bore in section and obtain the oval air intake duct compression-type face (16) in three-dimensional side turn, method and step is as follows:
1) axial symmetry basic flow field is solved using the method for characteristic curves according to design requirement；
2) design three-dimensional side turns oval air intake duct initial outlet class rectangle section, and is flowed in the step 1) basic flow field
Line tracking；
3) streamline magnification ratio is determined according to entrance, outlet two-dimension projection, carries out coordinate using amplified streamline and turns
It changes and generates the oval air intake duct compression-type face (16) in three-dimensional side turn；
4) turn oval air intake duct to hypersonic three-dimensional side based on the oval air intake duct compression-type face (16) in three-dimensional side turn to carry out
Geometrical construction, by three-dimensional side turn oval air intake duct shoulder molded line (19) backward equal vertical pullings stretch to obtain three-dimensional side turn ellipse air intake duct every
From section (17).
2. the three-dimensional side of completely pneumatic transition according to claim 1 turns oval Design of Inlet method, which is characterized in that
The axial symmetry contract basic flow field is 360 ° of revolving bodies, and the centre of gyration is axial symmetry contract basic flow field centre of gyration line
(7), axial symmetry contract basic flow field includes that waves air intake duct part is held in axial symmetry contract basic flow field, with characteristic curve
Method solves axial symmetry contract basic flow field and obtains the oval air inlet in three-dimensional side turn of rider formula in axial symmetry contract basic flow field
Road import incident shock (6), axial symmetry contract basic flow field reflected shock wave (4).
3. the three-dimensional side of completely pneumatic transition according to claim 1 turns oval Design of Inlet method, which is characterized in that
The class rectangle and the oval outlet of design are tangent, and gained streamline is constituted to stream interface on lateral position and obtains inlet and outlet section
All turn oval air intake duct compression-type face (16) for the three-dimensional side of class rectangle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910442230.6A CN110188447A (en) | 2019-05-24 | 2019-05-24 | The three-dimensional side of completely pneumatic transition turns oval Design of Inlet method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910442230.6A CN110188447A (en) | 2019-05-24 | 2019-05-24 | The three-dimensional side of completely pneumatic transition turns oval Design of Inlet method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110188447A true CN110188447A (en) | 2019-08-30 |
Family
ID=67717805
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910442230.6A Pending CN110188447A (en) | 2019-05-24 | 2019-05-24 | The three-dimensional side of completely pneumatic transition turns oval Design of Inlet method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110188447A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN112324572A (en) * | 2020-11-02 | 2021-02-05 | 厦门大学 | Reverse design method of full three-dimensional inward-turning air inlet channel based on bending shock wave theory |
| CN113032894A (en) * | 2021-02-24 | 2021-06-25 | 东方空间技术(山东)有限公司 | Double-cone fairing-shaped wire optimization design method based on Von Karman wire |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775158A (en) * | 2016-03-07 | 2016-07-20 | 厦门大学 | Integration design method for hypersonic slender body air vehicle and three-dimensional inward rotation air inlet channel |
| 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 |
| CN106837550A (en) * | 2017-02-06 | 2017-06-13 | 厦门大学 | The method for designing of hypersonic triple channel air intake duct |
| CN207297170U (en) * | 2017-02-06 | 2018-05-01 | 厦门大学 | Hypersonic triple channel air intake duct |
-
2019
- 2019-05-24 CN CN201910442230.6A patent/CN110188447A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775158A (en) * | 2016-03-07 | 2016-07-20 | 厦门大学 | Integration design method for hypersonic slender body air vehicle and three-dimensional inward rotation air inlet channel |
| 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 |
| CN106837550A (en) * | 2017-02-06 | 2017-06-13 | 厦门大学 | The method for designing of hypersonic triple channel air intake duct |
| CN207297170U (en) * | 2017-02-06 | 2018-05-01 | 厦门大学 | Hypersonic triple channel air intake duct |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN112324572A (en) * | 2020-11-02 | 2021-02-05 | 厦门大学 | Reverse design method of full three-dimensional inward-turning air inlet channel based on bending shock wave theory |
| CN112324572B (en) * | 2020-11-02 | 2021-11-19 | 厦门大学 | Reverse design method of full three-dimensional inward-turning air inlet channel based on bending shock wave theory |
| CN113032894A (en) * | 2021-02-24 | 2021-06-25 | 东方空间技术(山东)有限公司 | Double-cone fairing-shaped wire optimization design method based on Von Karman wire |
| CN113032894B (en) * | 2021-02-24 | 2023-01-03 | 东方空间技术(山东)有限公司 | Double-cone fairing shape line optimization design method based on Feng Ka door-shaped line |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105151306B (en) | Method of integrally designing forebody and air intake duct of cone configuration hypersonic flight vehicle | |
| CN105775158B (en) | Hypersonic slender bodies aircraft in three-dimensional with rotating into air passage integrated design method | |
| CN110188447A (en) | The three-dimensional side of completely pneumatic transition turns oval Design of Inlet method | |
| CN106250597A (en) | Air flue design method is rotated in a kind of three-dimensional flowing to suction completely | |
| CN106837550B (en) | The design method of hypersonic triple channel air intake duct | |
| CN104632411B (en) | Binary is used to become the interior rider type turbine base assembly power air intake duct of geometric ways | |
| CN105667812B (en) | Hypersonic aircraft precursor, air intake duct and wing rider integrated design method | |
| CN105947230B (en) | A kind of Waverider and the method for designing of air intake duct integration configuration | |
| CN104908975B (en) | Aircraft fore-body and internal waverider-derived hypersonic inlet integrated design method | |
| CN106005475A (en) | Design method for hypersonic speed inner and outer flow integrated full wave rider flight vehicle | |
| CN109670269B (en) | Design method of multi-channel parallel three-power combined engine | |
| CN102705081A (en) | Binary hypersonic variable geometrical inlet channel, design method and work mode | |
| CN107089341B (en) | With aircraft integrated hypersonic inlet external compression face design method | |
| CN108590860B (en) | The assembly power variable geometry inlet and its design method of single-degree-of-freedom control | |
| CN103963996B (en) | The waverider forebody derived that transverse-pressure gradient is controlled and inlet channel integrated design method | |
| CN109455309A (en) | Rider air intake duct integrated design method in sweepforward based on circular cone precursor shock wave | |
| CN107013334A (en) | A kind of double combustion chamber's Scramjet Inlet and air intake control method | |
| CN202628279U (en) | Binary hypersonic speed-variable geometric air inlet channel | |
| CN110304267A (en) | Hypersonic aircraft design method and system | |
| CN106894917A (en) | Double outlet S bending nozzles and its control method of a kind of low-infrared radiation signal | |
| CN108038295A (en) | Hypersonic inlet channel and isolation section integrated design method | |
| CN110210096A (en) | The variable cross-section three-dimensional contract Design of Inlet method of the bent cone bomb body of matching | |
| CN209080155U (en) | Rider air intake duct integrated apparatus in sweepforward based on circular cone precursor shock wave | |
| CN104443402A (en) | Embedded type air inlet passage structure of aircraft | |
| CN109733634B (en) | Design method of three-dimensional inward-turning four-channel hypersonic combined air inlet channel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190830 |
|
| RJ01 | Rejection of invention patent application after publication |