CN108195544B - A kind of impulse type wind-tunnel tandem jet pipe - Google Patents
A kind of impulse type wind-tunnel tandem jet pipe Download PDFInfo
- Publication number
- CN108195544B CN108195544B CN201611122140.1A CN201611122140A CN108195544B CN 108195544 B CN108195544 B CN 108195544B CN 201611122140 A CN201611122140 A CN 201611122140A CN 108195544 B CN108195544 B CN 108195544B
- Authority
- CN
- China
- Prior art keywords
- jet pipe
- downstream
- upstream
- tunnel
- wind
- 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.)
- Active
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention relates to a kind of impulse type wind-tunnel tandem jet pipes, including upstream jet pipe, etc. straight linkage section and downstream jet pipe, upstream jet pipe and downstream jet pipe are the different solid block type face jet pipe of two Mach numbers, respectively there is a contraction venturi in the middle part of upstream jet pipe and downstream nozzle flow passage, the contraction throatpiston product of upstream jet pipe shunk throatpiston product and be less than downstream jet pipe, upstream jet pipe is set to become the geometry venturi of wind-tunnel tandem jet pipe, fairing is equipped with inside runner etc. straight linkage section, for integrating fluid, flow field quality is improved.The not complicated actuation control mechanism of jet pipe of the invention, has operability in practical implementation, and structure is simple, reliable, additionally it is possible to further shorten the starting time of jet pipe and improve test section flow field quality.
Description
Technical field
The invention belongs to impulse type wind tunnel test fields, in particular to a kind of impulse type wind-tunnel tandem jet pipe.
Background technique
Impulse type wind-tunnel is one kind of high Ma number ground-testing plant, and purpose seeks to the flight for reappearing aircraft as far as possible
Environment, and binding test technology obtain the aerodynamic parameter of dummy vehicle in such a case.Impulse type wind-tunnel is by shock tube
Grow up, according to the difference of the method for operation, there is reflection-type shock tunnel, gun wind tunnel, FREE-PISTON SHOCK TUNNEL, rood dimension
The uncommon multiple types such as tube wind tunnel and shock expansion tube wind tunnel.
Jet pipe is the core component of impulse type wind-tunnel, and effect is exactly to provide the air-flow met the requirements ginseng for test segment model
Number.Its flow field quality has important influence to the performance of equipment, therefore the purpose of pneumatic design is exactly according to certain theoretical base
Plinth obtains the wall surface molded line with converging diverging form for meeting design requirement.
Domestic and international impulse type wind tunnel test Ma base is originally all 6.0 or more at present: on the one hand being developed based on shock tube principle
Due to there is " big venturi effect " (being mismatched by driving caliber and nozzle throat size) in the impulse type wind-tunnel to get up, so that equipment
It is very difficult to apply in 5 or less Ma number；On the other hand although Ma number 5 may be implemented with the impulse type wind-tunnel of Ludwieg tube principle operation
It runs below, but requires drive section caliber size larger, it is difficult to accomplish that wide Ma number runs the unification of lower multi nozzle size.
Traditional super/hypersonic wind tunnel jet pipe is made of subsonic speed contraction section, venturi section and supersonic speed expansion segment.It receives
Contracting section generallys use three times or five fair curves；Venturi section is using Transonic Flow solution as initial value line；Supersonic speed expansion segment with
(in conjunction with boundary layer coupling technology) based on theory of characteristics, design method can be classified as two classes:
One kind is the Partial Feature line design method assumed based on current of spring, such as Foelsch method, Crown method.Total thinking
It is the supersonic speed current of spring become the sonic flow at throat using the multiple curve of leading portion at turning point.The shortcomings that this method be
Turning point wall surface curve can not be led, and show as having disturbance inside flow field, have larger impact to jet pipe overall performance.In order to improve
The fairness of jet pipe wall surface produces the Curve guide impeller method with continuous curvature, such as Kenney on the basis of above method
By one section of wall surface molded line previously given after turning point come the jet pipe molded line that smoothly transits.Although improved method is to a certain extent
Nozzle flow field quality is improved, but is all to use current of spring it is assumed that Profile Design before turning point is made to be theoretically unsound.
Another kind of is the complete method of characteristic curves, and can be further divided into the direct method of characteristic curves and Reverse features collimation method.Directly
The method of characteristic curves, close to expansion arc curve form (such as circular arc) after venturi, determines boundary characteristic according to Nozzle Design Ma number by specified
Line parameter and position.Reverse features collimation method passes through the distribution (such as axial direction Ma number or VELOCITY DISTRIBUTION) for the axial flow parameter given, knot
Interflow line tracer technique can be obtained without viscous boundary.In comparison, the complete method of characteristic curves eliminates current of spring area it is assumed that enhancing
The theoretical basis of Nozzle Design, it is thus possible to which obtained flow field quality is more preferable.
From the point of view of current data, as hypersonic aircraft develops the increase of demand, impulse type wind-tunnel is badly in need of to lower
The extension of Ma number section, if Ma number range is 3.5-8.0 after the transformation of U.S.'s CUBRC LENS II shock tunnel, but it is this based on biography
The modification scheme of system jet pipe is to sacrifice effective operation of apparatus time and flow field quality as cost.Therefore how to guarantee impulse type
Expand Ma number range of operation under the premise of performance of wind tunnel, realizes that the size under different Ma numbers is matched as research emphasis.
Summary of the invention
The present invention proposes a kind of impulse type wind-tunnel tandem jet pipe, to solve to be difficult in the prior art before guaranteeing equipment performance
Put the problem of realizing the matching of width Ma number range inside dimension.
In view of the above problem of the prior art, according to one aspect of the present disclosure, the present invention uses following technology
Scheme:
A kind of impulse type wind-tunnel tandem jet pipe, including upstream jet pipe, etc. straight linkage section and downstream jet pipe, wherein upstream spray
Pipe, etc. straight linkage section and downstream jet pipe constitute the wind-tunnel tandem jet pipe from left to right, upstream jet pipe, etc. straight linkage section and downstream
It is fixed between jet pipe by flange, the wind-tunnel tandem jet pipe is placed between the wind-tunnel tube body of wind tunnel test and experimental section, upstream
Jet pipe left end is fixedly connected with wind-tunnel tube body, and junction is equipped with diaphragm, and the right end of downstream jet pipe is fixedly connected with experimental section, upstream
Jet pipe and downstream jet pipe are the different solid block type face jet pipe of two Mach numbers, are respectively had in the middle part of upstream jet pipe and downstream nozzle flow passage
One contraction venturi, the contraction throatpiston product of upstream jet pipe shunk throatpiston product and be less than downstream jet pipe, makes upstream jet pipe
It as the geometry venturi of wind-tunnel tandem jet pipe, waits and is equipped with fairing inside the runner of straight linkage section, for integrating fluid, improve
Flow field quality.
It is characterized in that, the working media of the wind-tunnel tandem jet pipe is air, or other gaseous mediums than air.
It is characterized in that, the cross section of fluid channel shape of the wind-tunnel tandem jet pipe is rectangle, circle or annular.
It is characterized in that, the fairing in the straight linkage section such as described is damping screen or honeycomb.
It is characterized in that, the contraction throat area of downstream jet pipe should be greater than upstream nozzle throat area, while also should be less than
The limit that downstream jet pipe allows takes area, which takes the design Mach number of area and two jet pipes and going out for downstream jet pipe
Open area is related.
The utility model has the advantages that
Impulse type wind-tunnel tandem jet pipe of the invention is a kind of design scheme in fixed face, by changing upstream and downstream jet pipe
Design Ma number and the discharge area demand more different than can satisfy.Technical solution of the present invention is only needed to impulse type wind-tunnel
Jet pipe does local flow improvement, has operability in practical implementation.Tandem jet pipe of the invention not complicated actuation control
Mechanism processed realizes various sizes of matching by pneumatic principle, and structure is simple, reliable.By increasing rectification in waiting straight stable section
Device, additionally it is possible to further shorten the starting time of jet pipe and improve test section flow field quality.
Detailed description of the invention
Fig. 1 shows the structure connection diagram of impulse type wind-tunnel tandem jet pipe of the invention.
Fig. 2 shows the signals of the actual working state Fluid field architectural characteristic of impulse type wind-tunnel tandem jet pipe of the invention
Figure.
Fig. 3 shows the upstream and downstream jet pipe internal feature wire grid schematic diagram of impulse type wind-tunnel tandem jet pipe of the invention.
Fig. 4 shows Ma number cloud atlas in the tandem jet pipe plane of symmetry of the embodiment of the present invention.
Specific embodiment
The present invention is described in further detail below with reference to embodiment, embodiments of the present invention are not limited thereto.
As shown in Figure 1, impulse type wind-tunnel tandem jet pipe scheme provided by the invention, upstream jet pipe directly with impulse type wind-tunnel
Tube body connection, downstream jet pipe, which is used to generate, meets the flow conditions that test needs, and two sections of jet pipes all have the structure of converging diverging
Form.
The tandem jet pipe course of work of the invention is as follows:
Subsonic airflow enters contraction section in upstream nozzle entry and constantly accelerates, and reaches sound first at the nozzle throat of upstream
Speed, air-flow further speed up supersonic speed in expansion segment, until reaching upstream Nozzle Design Ma number, upstream jet pipe has started
At flow field is established；As supersonic flow continuation downstream moves, under the limitation that the limit takes area, reached at the venturi of downstream
To the velocity of sound, blocking is formed in entire internal flow channel, and in order to match flow, shock wave string structure is formed between upstream and downstream venturi,
And it gradually upstream promotes；Final shock wave string structure initial position tends towards stability, and downstream jet pipe start completion, Flow Field in Wind Tunnel is built
It is vertical.
As shown in Fig. 2, shock wave string structure can be stablized in upstream and downstream when tandem jet pipe according to the present invention is in running order
Some position between venturi.Its design method is most important to be sought to determine that the venturi limit of downstream jet pipe takes area, by
Flow formula in jet pipe can derive the relational expression of design Mach number and discharge area are as follows:
Wherein, A1For upstream nozzle exit area,For upstream nozzle throat area, M1For upstream Nozzle Design Ma number, A2
For downstream nozzle exit area,For downstream nozzle throat area, M2For downstream Nozzle Design Ma number, r is the specific heat ratio of gas.
Further, upstream and downstream nozzle inlet stagnation pressure has following relational expression under limiting condition:
Wherein, P10For upstream nozzle inlet stagnation pressure, P20For downstream nozzle inlet stagnation pressure.
Further, equal according to flow at upstream and downstream venturi, following relational expression can be obtained:
Further, above-mentioned relation formula can expand into following equivalent form under limiting condition:
Given upstream nozzle exit area A1With design Ma number M1: if downstream Nozzle Design Ma number is limited simultaneously as M2, then under
Swimming nozzle exit, there are greatest limit usable area A2,max；If limiting downstream nozzle exit area A simultaneously2, then downstream jet pipe goes out
There are minimums can use Ma number M for mouth2,min
Further, jet pipe supersonic speed expansion segment molded line is designed according to theory of characteristics, relational expression is as follows:
Δy±=λ±Δx±=tg (θ ± α) Δ x±
Wherein, x is abscissa or axial coordinate, and y is ordinate or radial coordinate, and θ is local airflow direction angle, and α is to work as
Ground Mach number angle, u is transversely or axial flow velocity, v are that flowing velocity, a are local velocity of sound, the table of δ=0 longitudinally or radially
Show that two-dimensional flow, δ=1 indicate axial symmetry flow.
As shown in figure 3, by venturi, transonic speed analytic solutions determine initial characteristics line, (usually adopt in conjunction with axial Mach Number Distribution
With Bezier curve or B-spline curves distribution form) jet pipe internal feature gauze is obtained, it is chased after on characteristic curve grid using streamline
Ultrasonic segment type line can be obtained in track technology.
Further, the displacement thickness in boundary layer, subsonic speed contraction section can be determined according to direct solution boundary-layer equation
Molded line generallys use three times or quintic curve form.
The present invention is further illustrated with a specific application example below:
Upstream nozzle exit diameter dimension 300mm, design Ma number are 4.5, and it is equal to limit upstream and downstream nozzle exit area.Root
It can determine that downstream jet pipe minimum can be 1.9 with Ma number according to above-mentioned implementation steps.Trip Nozzle Design Ma is removed in this application example
Number is 3.5, runs total temperature 750K, runs stagnation pressure 3.0bar.As shown in Figure 4, tandem jet pipe according to the present invention is in normal work
Make state, realizes the unification of jet pipe size under impulse type test chamber Ma number 3.5 and 4.5 two kind of operating condition, and flow field quality
Also it is guaranteed.
The present invention can be matched according to size and test section flow field demand, by the design Ma number of upstream and downstream jet pipe and
The cooperation of discharge area ratio meets practical application, and examples detailed above is in order to illustrate the present invention, not to protection scope of the present invention
It is construed as limiting.All embodiments identical with mentality of designing of the present invention and working principle are within the scope of the invention.
Claims (5)
1. a kind of impulse type wind-tunnel tandem jet pipe, including upstream jet pipe, etc. straight linkage section and downstream jet pipe, wherein upstream jet pipe,
Constitute the wind-tunnel tandem jet pipe from left to right etc. straight linkage section and downstream jet pipe, upstream jet pipe, etc. straight linkage section and downstream spray
It is fixed between pipe by flange, the wind-tunnel tandem jet pipe is placed between the wind-tunnel tube body of wind tunnel test and experimental section, upstream spray
Pipe left end is fixedly connected with wind-tunnel tube body, and junction is equipped with diaphragm, and the right end of downstream jet pipe is fixedly connected with experimental section, upstream spray
Pipe and downstream jet pipe are the different solid block type face jet pipe of two Mach numbers, respectively with one in the middle part of upstream jet pipe and downstream nozzle flow passage
A contraction venturi, upstream jet pipe shrink throatpiston product be less than downstream jet pipe contraction throatpiston product, make upstream jet pipe at
It for the geometry venturi of wind-tunnel tandem jet pipe, waits and is equipped with fairing inside the runner of straight linkage section, for integrating fluid, improve stream
Field quality.
2. a kind of impulse type wind-tunnel tandem jet pipe as described in claim 1, which is characterized in that the work of the wind-tunnel tandem jet pipe
It is air as medium, or other gaseous mediums than air.
3. a kind of impulse type wind-tunnel tandem jet pipe as described in claim 1, which is characterized in that the stream of the wind-tunnel tandem jet pipe
Road cross sectional shape is rectangle, circle or annular.
4. a kind of impulse type wind-tunnel tandem jet pipe as described in claim 1, which is characterized in that whole in the straight linkage section such as described
Flowing device is damping screen or honeycomb.
5. a kind of impulse type wind-tunnel tandem jet pipe as described in claim 1, which is characterized in that the contraction venturi face of downstream jet pipe
Product should be greater than upstream nozzle throat area, while the limit that also should be less than the permission of downstream jet pipe takes area, which takes face
It is long-pending related to the discharge area of the design Mach number of two jet pipes and downstream jet pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611122140.1A CN108195544B (en) | 2016-12-08 | 2016-12-08 | A kind of impulse type wind-tunnel tandem jet pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611122140.1A CN108195544B (en) | 2016-12-08 | 2016-12-08 | A kind of impulse type wind-tunnel tandem jet pipe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108195544A CN108195544A (en) | 2018-06-22 |
| CN108195544B true CN108195544B (en) | 2019-10-18 |
Family
ID=62572591
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611122140.1A Active CN108195544B (en) | 2016-12-08 | 2016-12-08 | A kind of impulse type wind-tunnel tandem jet pipe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108195544B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108240898A (en) * | 2016-12-23 | 2018-07-03 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of impulse type wind-tunnel tandem jet pipe |
| CN110207934B (en) * | 2019-05-28 | 2021-06-11 | 中国航天空气动力技术研究院 | Method for effectively prolonging flow time of large-size free piston high-enthalpy pulse wind tunnel |
| CN110907126A (en) * | 2019-12-05 | 2020-03-24 | 中国空气动力研究与发展中心超高速空气动力研究所 | Indirect measurement method for total temperature of wind tunnel stabilizing section |
| CN112413644B (en) * | 2020-12-04 | 2022-05-13 | 中国人民解放军国防科技大学 | Scramjet engine and double-throat combustion chamber thereof |
| CN112945507B (en) * | 2021-02-03 | 2023-05-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Hypersonic wind tunnel axisymmetric spray pipe |
| CN113720571B (en) * | 2021-06-02 | 2023-12-12 | 中国航天空气动力技术研究院 | Ludwieg tubular static wind tunnel and starting method thereof |
| CN113701987B (en) * | 2021-08-26 | 2022-07-29 | 中国科学院力学研究所 | High-pressure gas flow control device for wind tunnel test |
| CN114112286B (en) * | 2021-12-01 | 2023-02-28 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel axisymmetric profile spray pipe fitting throat section design method |
| CN115358101B (en) * | 2022-10-21 | 2022-12-20 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Jet pipe design method based on sound velocity solution and characteristic line reverse thrust |
| CN116256143B (en) * | 2023-05-15 | 2023-07-14 | 中国航空工业集团公司沈阳空气动力研究所 | Integrated structure of pipe wind tunnel spray pipe and test section and operation method |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2633677A1 (en) * | 1988-07-01 | 1990-01-05 | Sgn Soc Gen Tech Nouvelle | Aerodynamic shock generator |
| SU1561657A1 (en) * | 1988-02-03 | 1997-05-10 | Е.В. Зорин | Process of cooling of gas flow in cryogenic transonic wind tunnel and cryogenic transonic wind tunnel |
| CN102023078A (en) * | 2010-11-18 | 2011-04-20 | 中国人民解放军国防科学技术大学 | Supersonic plane mixing layer wind tunnel |
| CN102840960A (en) * | 2012-08-30 | 2012-12-26 | 华南理工大学 | Method for equalizing wind field of wind tunnel by using Rafah tube |
| CN103698100A (en) * | 2013-12-27 | 2014-04-02 | 中国人民解放军国防科学技术大学 | Ultrasonic wind tunnel and determining method thereof |
| CN103712768A (en) * | 2013-12-27 | 2014-04-09 | 中国人民解放军国防科学技术大学 | Supersonic-velocity wind tunnel |
| CN204405287U (en) * | 2015-01-28 | 2015-06-17 | 天津大学 | A kind of opening single flow icing tunnel of economical and efficient |
| RU163025U1 (en) * | 2015-12-14 | 2016-07-10 | МИНИСТЕРСТВО ОБОРОНЫ РОССИЙСКОЙ ФЕДЕРАЦИИ ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ КАЗЁННОЕ ВОЕННОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ПРОФЕССИОНАЛЬНОГО ОБРАЗОВАНИЯ Военная академия ракетных войск стратегического назначения имени Петра Великого | AERODYNAMIC TUBE |
-
2016
- 2016-12-08 CN CN201611122140.1A patent/CN108195544B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1561657A1 (en) * | 1988-02-03 | 1997-05-10 | Е.В. Зорин | Process of cooling of gas flow in cryogenic transonic wind tunnel and cryogenic transonic wind tunnel |
| FR2633677A1 (en) * | 1988-07-01 | 1990-01-05 | Sgn Soc Gen Tech Nouvelle | Aerodynamic shock generator |
| CN102023078A (en) * | 2010-11-18 | 2011-04-20 | 中国人民解放军国防科学技术大学 | Supersonic plane mixing layer wind tunnel |
| CN102840960A (en) * | 2012-08-30 | 2012-12-26 | 华南理工大学 | Method for equalizing wind field of wind tunnel by using Rafah tube |
| CN103698100A (en) * | 2013-12-27 | 2014-04-02 | 中国人民解放军国防科学技术大学 | Ultrasonic wind tunnel and determining method thereof |
| CN103712768A (en) * | 2013-12-27 | 2014-04-09 | 中国人民解放军国防科学技术大学 | Supersonic-velocity wind tunnel |
| CN204405287U (en) * | 2015-01-28 | 2015-06-17 | 天津大学 | A kind of opening single flow icing tunnel of economical and efficient |
| RU163025U1 (en) * | 2015-12-14 | 2016-07-10 | МИНИСТЕРСТВО ОБОРОНЫ РОССИЙСКОЙ ФЕДЕРАЦИИ ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ КАЗЁННОЕ ВОЕННОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ПРОФЕССИОНАЛЬНОГО ОБРАЗОВАНИЯ Военная академия ракетных войск стратегического назначения имени Петра Великого | AERODYNAMIC TUBE |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108195544A (en) | 2018-06-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108195544B (en) | A kind of impulse type wind-tunnel tandem jet pipe | |
| CN108168832B (en) | A kind of throat structure improving tube wind tunnel test Reynolds number | |
| CN105667811B (en) | The design method of hypersonic aircraft precursor and the multistage coupling integrated configuration of air intake duct | |
| CN108846224B (en) | Supersonic flow channel design method and device | |
| CN112035952B (en) | Design method of ejector nozzle experimental device for simulating outflow of aircraft | |
| CN102434315A (en) | Bypass type double-throat passive vectoring sprayer nozzle | |
| CN208310917U (en) | A kind of switching segment structure solving S bending nozzle and fanjet matching problem | |
| CN108999725B (en) | Jet nozzle with double-bell-shaped jet sleeve | |
| CN108182319B (en) | Supersonic velocity integrated spray pipe design method | |
| CN102998084A (en) | Hypersonic velocity spray pipe structure | |
| CN111339681A (en) | Nozzle outlet parameter matching method for simulating engine gas medium jet flow aerodynamic interference effect by adopting air medium | |
| CN104772239B (en) | Supersonic speed chrysanthemum type nozzle and the gas blowing type vacuum pump for being equipped with the nozzle | |
| CN107741313A (en) | A kind of low wide Mach number wind-tunnel laminar flow double venturi of disturbance | |
| CN207923408U (en) | A kind of wide Mach number wind-tunnel laminar flow double venturi of low disturbance | |
| CN104807610A (en) | Sprayer nozzle used for tail jet flow interference test | |
| CN108240898A (en) | A kind of impulse type wind-tunnel tandem jet pipe | |
| CN107120210A (en) | A kind of supersonic nozzle | |
| CN103926050B (en) | Hypersonic quiet jet pipe and determine method | |
| CN110633522A (en) | Supersonic thrust nozzle reverse design method based on maximum thrust theory | |
| CN201983920U (en) | Segmentation jet tube for supersonic wind tunnel | |
| CN105464838B (en) | Method and apparatus for being deflected by dynamicthrust guiding and plume | |
| CN110671231B (en) | Throat offset type pneumatic thrust vectoring nozzle with front spoiler | |
| CN106837601A (en) | Venturi offset fluidic vectoring nozzle with lateral expansion | |
| CN105059531A (en) | Osculating cone waverider with curve head and controllable sweepback angle | |
| CN111559492A (en) | High-efficiency shock wave resistance reduction system of hypersonic aircraft |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Gao Liangjie Inventor after: Qian Zhansen Inventor after: Wang Lu Inventor before: Gao Liangjie Inventor before: Qian Zhansen Inventor before: Wang Lu |