CN103797229A - Method for adjusting a supersonic air inlet - Google Patents
Method for adjusting a supersonic air inlet Download PDFInfo
- Publication number
- CN103797229A CN103797229A CN201280032672.XA CN201280032672A CN103797229A CN 103797229 A CN103797229 A CN 103797229A CN 201280032672 A CN201280032672 A CN 201280032672A CN 103797229 A CN103797229 A CN 103797229A
- Authority
- CN
- China
- Prior art keywords
- regulating panel
- panel
- rear portion
- anterior
- regulating
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 24
- 230000035939 shock Effects 0.000 claims abstract description 20
- 230000001105 regulatory effect Effects 0.000 claims description 115
- 230000008859 change Effects 0.000 claims description 11
- 238000007493 shaping process Methods 0.000 claims description 7
- 238000006073 displacement reaction Methods 0.000 claims description 2
- 230000015572 biosynthetic process Effects 0.000 abstract 2
- 230000007246 mechanism Effects 0.000 description 7
- 230000000694 effects Effects 0.000 description 6
- 238000007664 blowing Methods 0.000 description 5
- 238000005304 joining Methods 0.000 description 3
- 238000000926 separation method Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 238000007373 indentation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 238000003892 spreading Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/80—Application in supersonic vehicles excluding hypersonic vehicles or ram, scram or rocket propulsion
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to aviation technology and, more specifically, to air inlets for supersonic aircraft propulsion systems. The preferred field of use of the invention is in turbojet aircraft with a maximum Mach number of 3. The invention is intended to achieve the technical result of making it possible to adjust the apex angle of the stages of one of the swept wedges and the minimum area of the flow passage of the air inlet (throat) without the formation of unwanted longitudinal grooves in the air inlet channel and the jamming of movable elements. The method for adjusting a supersonic air inlet consists in altering the area of the throat and positioning the shock waves. The area of the throat is altered and the shock waves are positioned by the simultaneous rotation of a front adjustable panel (11), the axis of rotation (9) of which coincides with the line of intersection of the first and second stages of one of the swept wedges (7, 22), which is not perpendicular to the oncoming flow, and a rear adjustable panel (12), the axis of rotation (10) of which is situated in the region of the trailing edge of the rear adjustable panel (12) and is oriented in order to intersect the axis of rotation of the front adjustable panel, wherein, as the front and rear adjustable panels rotate, the lateral edges thereof are displaced relative to the profiled lateral surfaces of the channel without the formation of grooves therebetween.
Description
Technical field
The present invention relates to aeronautical engineering, and relate more specifically to the intake duct for supersonic aircraft propulsion system.It is 3.0 bypass type turbojet engine aircraft that the present invention can preferably be applicable to Mach Number Never To Be Exceeded.The production of the aircraft (AC) that radar perceptibility is low means that the shape of its all elements all contributes to reduce the Radar Cross Section of aircraft (RCS).This is equally applicable to the shape of the entrance of the intake duct of motor.In order to obtain Expected Results, all edges of intake duct all should have the portion of scanning and be parallel to some aircraft elements (edge, the empennage etc. of wing).The realization that spreads all over this intake duct that operating range all has high inherent characteristic is infeasible in the situation that it not being adjusted.
Background technique
Conventionally, intake duct deceleration surfaces (for example, wedge-like portion or conic section) is adjustable.Under supersonic speed, change the area that the drift angle of deceleration surfaces has caused changing the mobile deceleration intensity in intake duct and changed its critical section.Meanwhile, the effect of this adjustment provides the high-performance of the flying speed scope of the aircraft that spreading all over of intake duct be provided with this intake duct.
Exist a kind of for adjusting the known method of supersonic speed two dimension intake duct, the deceleration surfaces of this intake duct shows as multistage non-(the Remeev N.H. of wedge-like portion that scans, aerodynamics (the Aerodynamics of Supersonic Aircraft Air Intakes.) TsAGI of supersonic aircraft intake duct, Zhukovsky publishes, 2002,178 pages).In known solution, intake duct is by adjusting around the panel of corresponding axle rotation.Panel adjoining land is arranged in pipeline.Front panel comprises the multiple levels except the first order of deceleration wedge-like portion.The axis of front panel overlaps with the first order of wedge-like portion and the intersection of the second level.Front panel is a part for pipeline and has complicated shape.The axis of front panel extends above its trailing edge.In the level of deceleration wedge-like portion and edge, do not exist the portion of scanning to make it possible to use the parallel rotating axis perpendicular to impact air-flow of panel.Inferior position for the method for adjusting two-dimentional intake duct with regard to having the intake duct that scans edge is that, by the infeasibility of it being adjusted perpendicular to the axis of flow direction, this is because all elements of inlet mouth were all scanned.
Immediate prior art of the present invention is a kind of for adjusting the method for supersonic inlet, and the method relates to the position (RU2343297C1) of the area and the shock wave that change critical section.Known solution depends on utilizes the Three-dimensional Flow of V-arrangement wedge-like portion (, as from anterior finding, each other in two of the obtuse angle orientation adjacent wedge-like portions of scanning) to slow down.Intake duct is constructed such that all edges of entrance were all scanned.Adjust intake duct by utilizing around two counter plates of corresponding axis rotation.Front panel in every counter plate is all parts of deceleration surfaces.Front panel is a part for pipeline.In the time that every counter plate is adjusted, transverse slot appears between their adjacent face, and longitudinal slot appear at they not only and the joining portion of sidewall on, but also the joining portion that is being engaged with each other on landscape surface between.The method has following inferior position:
-not providing necessary critical section area under subsonic flight speed and low supersonic flight speed for adjusting the method for intake duct, this is because movably panel is to move by a small margin.Otherwise, there will be the unacceptable aforementioned longitudinal slot of size.This means and do not spread all over speed operation scope by intake duct bypass type turbojet engine running and this intake duct are provided not is multimodal.
The method that – realizes for adjusting intake duct is complicated technically.
Summary of the invention
Treat that the technique effect being obtained by the present invention comprises, guarantee in its pipeline, do not forming the longitudinal slot not meeting the requirements and in the situation that not blocking displaceable element, change drift angle and a minimum inlet passageway area (critical section) that scans the level of deceleration wedge-like portion.This adjustment then can provide the steady running of the motor in all offline mode of the aircraft of Mach number up to M=3.0, wherein, engine charge total pressure recovery factor has the level being not less than for the conventional levels of adjustable two-dimentional intake duct, and total flow irregularity (overall flow heterogeneity) is lower than the maximum permissible value (aerodynamics of supersonic aircraft, stability and navigability (Aerodynamics, Stability and Maneuverability of Supersonic Aircraft), G.S.Byushgens. editor, Nauka.Fizmatlit publishes, 1998).Due to inlet mouth as being seen parallelogram shape and the marginate portion of scanning from front portion, caused reducing the radar perceptibility of the object that this intake duct is installed.In the time that intake duct edge is parallel to some elements (leading edge or trailing edge, the empennage etc. of wing) of object, reduce effect by obtaining maximum radar perceptibility.
Described technique effect obtains for the method for adjusting supersonic inlet a kind of, the method comprises the position of the area and the shock wave that change critical section, wherein, the described change of the area of critical section and the position of shock wave is by make anterior capable of regulating panel and rear portion capable of regulating panel rotate to realize simultaneously, the spin axis of this front portion capable of regulating panel overlaps with an intersection, this intersection is one and scans the first order of wedge-like portion and the intersection of the second level, this intersection is also not orthogonal to impact air-flow, the spin axis of this rear portion capable of regulating panel be arranged in rear portion capable of regulating panel trailing edge region and be oriented to the spin axis of anterior capable of regulating panel and there is intersection point, wherein, in the time of anterior capable of regulating panel and the rotation of rear portion capable of regulating panel, the transverse edge of anterior capable of regulating panel and the transverse edge of rear portion capable of regulating panel are with respect to the lateral surfaces displacement of the shaping of pipeline and not at the transverse edge of anterior capable of regulating panel, between the lateral surfaces of the transverse edge of rear portion capable of regulating panel and the shaping of pipeline, form gap.
In addition, in the time of anterior capable of regulating panel and the rotation of rear portion capable of regulating panel, transverse slot in planimetric map between anterior capable of regulating panel and rear portion capable of regulating panel does not change its orientation and its position overlaps with a straight line, this straight line is through the intersection point of the spin axis of anterior capable of regulating panel and the spin axis of rear portion capable of regulating panel, wherein, this gap has the shape close to rectangle for arbitrary possible position of capable of regulating panel.
In addition, in the time of the rotation of anterior capable of regulating panel and rear portion capable of regulating panel, the panel of covering is around the spin axis rotation of this covering and be oriented to the spin axis that makes this covering have common intersection point between the spin axis of himself and rear portion capable of regulating panel.
In addition, in the time of the rotation of anterior capable of regulating panel and rear portion capable of regulating panel, with anterior capable of regulating panel and rear portion capable of regulating panel kinology be connected and close the pivoted door that is arranged in the transverse slot in the nonadjustable deceleration wedge-like portion that is arranged in critical section region and change its position.
Accompanying drawing explanation
By accompanying drawing, present invention is described, and wherein, Fig. 1 shows the worm's eye view of adjustable supersonic inlet; Fig. 2 is the side view of adjustable supersonic inlet; Fig. 3 is the plan view of adjustable supersonic inlet; Fig. 4 is the section A-A in Fig. 1; Fig. 5 shows the schematic diagram of the mobile deceleration in the aloft adjustable supersonic inlet of rated power; Fig. 6 is supersonic inlet and for adjusting the plan view of panel of this supersonic inlet; Fig. 7 is supersonic inlet and for adjusting the side view of panel of this supersonic inlet; Fig. 8 is the section B-B in Fig. 6.
Embodiment
Adjustable supersonic inlet comprises following elements:
The edge of 1-deceleration wedge-like portion 7;
The edge of the deceleration wedge-like portion 22 that 2-is fixing;
3, the edge of 4-shell;
The pipeline of 5-intake duct;
6-cylindrical portion;
7-comprises the deceleration wedge-like portion of anterior capable of regulating panel 11;
The region of the possible position of 8-inhalation type safety door;
The spin axis of the anterior capable of regulating panel 11 of 9-;
The spin axis of 10-rear portion capable of regulating panel 12;
The anterior capable of regulating panel (be shown in dotted line minimum critical sectional position) of 11-in maximum critical section position;
The rear portion capable of regulating panel (be shown in dotted line minimum critical sectional position) of 12-in maximum critical section position;
The anterior capable of regulating panel 11 of 13-in minimum critical sectional position;
The rear portion capable of regulating panel 12 of 14-in minimum critical sectional position;
15-is for blowing down the transverse slot between anterior capable of regulating panel and rear portion capable of regulating panel in (bleed) boundary layer;
Deflection curve between the first order and the second level of deceleration wedge-like portion of 16-in comprising anterior capable of regulating panel;
Deflection curve between the first order and the second level of 17-in fixing deceleration wedge-like portion 22;
Deflection curve between the second level and the third level of deceleration wedge-like portion of 18-in comprising anterior capable of regulating panel;
The cut-off portion of the dihedral angle that 19-is formed by shell;
The chamfered section of the entrance in the joining portion between deceleration wedge-like portion and the shell of 20-in comprising anterior capable of regulating panel;
The cut-off portion of the dihedral angle that 21-is formed by the deceleration wedge-like portion 22 of fixing and shell;
The deceleration wedge-like portion that 22-is fixing;
The door that 23-adjusts being arranged in the additional lateral gap in the critical section region in fixing deceleration wedge-like portion 22;
24-supersonic diffuser (deceleration system);
25-subsonic diffuser;
26-is from the oblique shock wave of the first order that scans wedge-like portion;
27-is from the oblique shock wave of the second level that scans wedge-like portion;
28-is from the oblique shock wave of the third level that scans wedge-like portion;
The normal shock wave that 29-is final;
30-by-pass area, this by-pass area is positioned at the downstream of oblique shock wave and normal shock wave, for increasing the gas flow rate range by intake duct, provides the stable operation of intake duct at this by-pass area place;
31-comprises the first order of the wedge-like portion of anterior capable of regulating panel 11;
32,33, the spin axis of 34-covering (curtain) 45;
The intersection point of the axis of the spin axis of 35-covering 43 and rear portion capable of regulating panel 12;
The intersection point of the spin axis of the anterior capable of regulating panel 11 of 36-and the spin axis of rear portion capable of regulating panel 12;
37 – arrange the line on the transverse slot institute edge between capable of regulating panel 11 and capable of regulating panel 12;
The attachment location of the actuator of 38-rear portion capable of regulating panel 12;
Tap hole in 39-rear portion capable of regulating panel 12;
The spin axis of 40-door 23;
The tight seal part of 41-above rear portion capable of regulating panel 12;
The control mechanism of the horizontal pivoted door 23 of 42-;
The actuating rod of the anterior capable of regulating panel 11 of 43-;
The profile of 44-pipeline;
45-covering;
The compartment of the control mechanism of 46-rear portion capable of regulating panel 12;
The cross side of the shaping of 47-pipeline 5.
As from anterior finding, inlet mouth is the height of corresponding side and the length of this corresponding side and has parallelogram or its particular condition---the rectangle of arbitrary ratio.Inlet mouth can have except the cut-off portion 19 and 21 or chamfered section 18 by scanning the angle the angle that wedge-like portion forms.The edge of inlet mouth is arranged in flow direction and acutangulates directed plane.Thus, all edges of this entrance were all scanned.
Wedge- like portion 7 and 22 is the same with scanning, and shell forms dihedral angle.Specific features is, shell is oriented to and makes it that flowing velocity is further slowed down, and shell is not arranged in from scanning on the streamline in downstream of shock wave of wedge-like portion.The undercut corner of shell can be adjustable.Can groove be set at the edge of inlet mouth in the region that is arranged in the dihedral angle being formed by shell, and shell itself can have the hole of any shaping.
Above-mentioned as follows for adjusting the method for intake duct.Make to comprise that an anterior capable of regulating panel 11 of multiple grades except the first order that scans wedge-like portion 7 rotates around axis 9, this axis 9 is positioned at the first order of wedge-like portion 7 and the intersection of the second level.The rear portion capable of regulating panel 12 of coupling is a part for subsonic diffuser 25 and rotates around sterically defined axis 10.If the axis 9 of anterior capable of regulating panel is specially appointed, the position of the axis 10 of the trailing edge top that can extend to this rear portion capable of regulating panel of rear portion capable of regulating panel is just determined to be so, makes the axis 10 of rear portion capable of regulating panel and the axis 9 of anterior capable of regulating panel 11 crossing.
In the process that intake duct is adjusted, can between anterior capable of regulating panel 11 and rear portion capable of regulating panel 12, form transverse slot 15, for blowing down boundary layer.In the system of selection of the setting axis of capable of regulating panel, the transverse slot between them has the shape close to rectangle.
Anterior capable of regulating panel 11 is connected to rear portion capable of regulating panel 12 by bar 43.
In the time that intake duct is adjusted, anterior capable of regulating panel 11 and rear portion capable of regulating panel 12 change their position when rotated simultaneously according to specific rule.The rotation of panel 11 and 12 changed intake duct critical section area, scan the drift angle of movably level and the size in horizontal blowing gap 15 between panel 11 and 12 of wedge-like portion 7, and the transverse edge of panel 11 and 12 lateral surfaces with respect to the shaping of pipeline 47 in the situation that not forming gap is shifted.
Can be disposed in the fixing wedge-like portion 22 of scanning that is positioned at critical section region by the door 23 additional lateral gaps for boundary layer blowing-off that close.This mechanism that can carry out synchronization control by counter plate 11,12 controls.For example, can apply kinology mechanism 42, this kinology mechanism 42 is by bar and control crank by axis 9 associated of pivoted door and anterior capable of regulating panel 11.
Above-mentioned transverse slot in wedge-like portion and perforation contribute to improve the inlet characteristic under supersonic speed.
Rear portion capable of regulating panel 12 has tap hole 39, equates (level) so that be positioned at chamber and the ducted pressure of the top of rear portion capable of regulating panel 12.The covering 45 that the chamber that is positioned at the top of capable of regulating panel 11,12 is the form of folding divider is divided into two half-unit, and this covering 45 is for opening entering into by perforation, horizontal blowing gap 15 between capable of regulating panel and tap hole 39 air separation that space above panel has different pressures.This covering 45 comprises two hinged flat panel---top panel and bottom panel.Top panel is hinged to the structure of rear portion capable of regulating panel control mechanism compartment 46, and bottom panel is hinged to rear portion capable of regulating panel.For the kinology performance of covering 45 is provided, spin axis 32,33,34 space orientations of this covering 45, make them have an intersection point on the spin axis 10 that is positioned at rear portion capable of regulating panel 12.
The method of adjusting for the intake duct that scans edge to having is achieved as follows.
Under subsonic flight speed, the capable of regulating panel 11 and 12 of intake duct is in maximum critical section position (in figure by the retracted position shown in solid line), thereby critical section region is provided, in this critical section region, in pipeline, does not have ultrasonic flow velocity.
Under supersonic flight speed, aircraft propelling system efficiency is relevant with the efficiency of the mobile deceleration in intake duct.Supersonic Flow in intake duct is slowed down in shock wave 26,27,28, when these shock waves 26,27,28 appear at air-flow and flow around the wedge-like portion of scanning of deceleration system.Along with supersonic flight speed increases, capable of regulating panel 11 and 12 is from synchronously deflection of the position corresponding with subsonic flight.The synchronous deflection of panel 11,12 is provided via bar 43 by the mechanical linkage between anterior capable of regulating panel 11 and rear portion capable of regulating panel 12.Thus, the rotation of passing through this mechanism of rear portion capable of regulating panel 12 drives this front portion capable of regulating panel 11 simultaneously.The rotation of the drift angle of the level towards increase wedge-like portion of anterior capable of regulating panel 11 has increased from the mobile deceleration intensity in the shock wave of these grades.In this simultaneously, the rotation of front panel 12 has reduced critical section area.Increase and the dwindling in the performance of intake duct of critical section area of the deceleration intensity that flows have good effect.
Realize at the normal shock wave 29 that is arranged in inlet mouth place up to subsonic mobile deceleration.This subsonic flow finally in subsonic diffuser 25, is slowed down and launched machine consumes.
The stable operation of intake duct in all regime of flight and under all engine power states guaranteed by the utilizability of the gas bypassing 30 in oblique shock wave 28 and by the boundary layer blowing-off system of the form that is perforation in the level of wedge-like portion of deceleration system and transverse slot between anterior capable of regulating panel and rear portion capable of regulating panel.
In addition, to realize be possible the critical section region in the boundary layer blowing-off deceleration wedge-like portion 22 that (to have fix level) by being arranged in fixing and the additional lateral gap adjusted by door 23.
In the time that the position of capable of regulating panel 11 and 12 is different from retracted position, additional lateral gap is opened conventionally in supersonic mode.In the time that capable of regulating panel 11 and 12 is in retracted position, described additional lateral gap is closed by door 23.
In the time that panel is extended, covering 45 starts to open, this covering 45 by enter into by tap hole 39 the air in the chamber above rear portion capable of regulating panel 12 and by perforation and the horizontal blowing gap 15 between capable of regulating panel 11 and 12 enter into be arranged in anterior capable of regulating panel 11 above the air separation in chamber open.
The intrinsic air dynamic behaviour of height of having guaranteed intake duct for the method for adjusting required for protection, the configuration of this intake duct contributes to scan as the level of all edges of being seen parallelogram shape and entrance from front portion and deceleration wedge-like portion the radar perceptibility that has reduced this intake duct by entrance simultaneously.Allow to guide with respect to radar illumination their structure for the directed selection of element that forms this entrance, so that from the radar signal deflection of this structure reflection and removed corner reflector.
Claims (4)
1. for adjusting a method for supersonic inlet, described method comprises the position of the area and the shock wave that change critical section,
It is characterized in that, for the described change of the area of described critical section and the position of described shock wave by make anterior capable of regulating panel and rear portion capable of regulating panel rotate to realize simultaneously, the spin axis of described anterior capable of regulating panel overlaps with an intersection, described intersection is to scan the first order of in wedge-like portion and the intersection of the second level, described intersection is also not orthogonal to impact air-flow, and the spin axis of described rear portion capable of regulating panel be arranged in described rear portion capable of regulating panel trailing edge region and be oriented with the described spin axis of described anterior capable of regulating panel and there is intersection point,
Wherein, in the time of the rotation of described anterior capable of regulating panel and described rear portion capable of regulating panel, the transverse edge of the transverse edge of described anterior capable of regulating panel and described rear portion capable of regulating panel is all with respect to the lateral surfaces displacement of the shaping of pipeline and do not form gap between the lateral surfaces of the transverse edge of described anterior capable of regulating panel, the transverse edge of described rear portion capable of regulating panel and the shaping of pipeline.
2. method according to claim 1, it is characterized in that, in the time of described anterior capable of regulating panel and the rotation of described rear portion capable of regulating panel, transverse slot in planimetric map between described anterior capable of regulating panel and described rear portion capable of regulating panel does not change its orientation, and the position of described transverse slot overlaps with a straight line, described straight line crosses the described intersection point of the described spin axis of described anterior capable of regulating panel and the described spin axis of described rear portion capable of regulating panel, wherein, described gap has the shape close to rectangle for arbitrary possible position of described capable of regulating panel.
3. method according to claim 1, it is characterized in that, in the time of the rotation of described anterior capable of regulating panel and described rear portion capable of regulating panel, the panel of covering is around the spin axis rotation of described covering and be oriented to the described spin axis that makes described covering have common intersection point between the described spin axis of himself and described rear portion capable of regulating panel.
4. method according to claim 1, wherein, in the time of the rotation of described anterior capable of regulating panel and described rear portion capable of regulating panel, with described anterior capable of regulating panel and described rear portion capable of regulating panel kinology be connected and the pivoted door that closes the described transverse slot in the nonadjustable deceleration wedge-like portion that is arranged in described critical section region changes its position.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2011116972 | 2011-04-29 | ||
| RU2011116972/06A RU2460892C1 (en) | 2011-04-29 | 2011-04-29 | Method of adjusting supersonic air intake |
| PCT/RU2012/000342 WO2012148319A1 (en) | 2011-04-29 | 2012-04-28 | Method for adjusting a supersonic air inlet |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103797229A true CN103797229A (en) | 2014-05-14 |
| CN103797229B CN103797229B (en) | 2016-10-26 |
Family
ID=46938991
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201280032672.XA Expired - Fee Related CN103797229B (en) | 2011-04-29 | 2012-04-28 | For the method adjusting supersonic inlet |
Country Status (3)
| Country | Link |
|---|---|
| CN (1) | CN103797229B (en) |
| RU (1) | RU2460892C1 (en) |
| WO (1) | WO2012148319A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107023395A (en) * | 2017-06-07 | 2017-08-08 | 中国空气动力研究与发展中心计算空气动力研究所 | The supersonic aircraft air intake duct and adjusting method of a kind of adjustable throat area |
| WO2021001674A3 (en) * | 2019-07-01 | 2021-09-30 | Zhang Chuanrui | Aerodynamic techniques and methods for quieter supersonic flight |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103939217B (en) * | 2014-04-18 | 2016-03-02 | 南京航空航天大学 | Rectangular cross-section hypersonic change geometry intake duct and design method and working method |
| RU2672825C2 (en) * | 2017-04-17 | 2018-11-19 | Федеральное государственное бюджетное учреждение науки Институт теоретической и прикладной механики им. С.А. Христиановича Сибирского отделения Российской академии наук (ИТПМ СО РАН) | Supersonic air intake (options) |
| CN112504612A (en) * | 2020-12-29 | 2021-03-16 | 北京航天益森风洞工程技术有限公司 | Two-throat real-time adjustable super-expanding section |
| CN113153530A (en) * | 2021-05-28 | 2021-07-23 | 西北工业大学 | Hypersonic variable structure air inlet mechanism and wide-area combined power aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3250071A (en) * | 1962-05-16 | 1966-05-10 | Bristol Siddeley Engines Ltd | Ramjet engine |
| GB1190812A (en) * | 1967-04-18 | 1970-05-06 | British Aircraft Corp Ltd | Improvements relating to Aircraft Air Intakes |
| US5881758A (en) * | 1996-03-28 | 1999-03-16 | The Boeing Company | Internal compression supersonic engine inlet |
| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
| CN101029597A (en) * | 2007-03-22 | 2007-09-05 | 南京航空航天大学 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3589379A (en) * | 1969-02-17 | 1971-06-29 | Mc Donnell Douglas Corp | Inlet duct |
| DE4008956A1 (en) * | 1990-03-20 | 1991-09-26 | Messerschmitt Boelkow Blohm | INLET SYSTEM FOR SUPERVISOR OR HYPERSONIC AIRCRAFT |
| DE19651491C2 (en) * | 1996-12-11 | 1999-04-01 | Daimler Benz Aerospace Ag | Air intake for engines |
| RU2171211C2 (en) * | 1997-12-29 | 2001-07-27 | Медведев Владимир Тимофеевич | Self-adjustable air intake |
| RU2343297C1 (en) * | 2007-04-24 | 2009-01-10 | Институт теоретической и прикладной механики им. С.А. Христиановича СО РАН (ИТПМ СО РАН) | Supersonic intake |
-
2011
- 2011-04-29 RU RU2011116972/06A patent/RU2460892C1/en active
-
2012
- 2012-04-28 WO PCT/RU2012/000342 patent/WO2012148319A1/en active Application Filing
- 2012-04-28 CN CN201280032672.XA patent/CN103797229B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3250071A (en) * | 1962-05-16 | 1966-05-10 | Bristol Siddeley Engines Ltd | Ramjet engine |
| GB1190812A (en) * | 1967-04-18 | 1970-05-06 | British Aircraft Corp Ltd | Improvements relating to Aircraft Air Intakes |
| US5881758A (en) * | 1996-03-28 | 1999-03-16 | The Boeing Company | Internal compression supersonic engine inlet |
| CN1384794A (en) * | 1999-08-25 | 2002-12-11 | 波音公司 | Supersonic external-compression diffuser and method for designing same |
| CN101029597A (en) * | 2007-03-22 | 2007-09-05 | 南京航空航天大学 | Fixed geometrical supersonic-speed and high supersonic-speed adjusting air inlet |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107023395A (en) * | 2017-06-07 | 2017-08-08 | 中国空气动力研究与发展中心计算空气动力研究所 | The supersonic aircraft air intake duct and adjusting method of a kind of adjustable throat area |
| CN107023395B (en) * | 2017-06-07 | 2019-02-26 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of the supersonic aircraft air intake duct and adjusting method of adjustable throat area |
| WO2021001674A3 (en) * | 2019-07-01 | 2021-09-30 | Zhang Chuanrui | Aerodynamic techniques and methods for quieter supersonic flight |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2012148319A1 (en) | 2012-11-01 |
| RU2460892C1 (en) | 2012-09-10 |
| CN103797229B (en) | 2016-10-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103748337B (en) | Adjustable supersonic inlet | |
| CN103797229A (en) | Method for adjusting a supersonic air inlet | |
| EP0253028B1 (en) | Vortex generators for inlets | |
| CN107554802B (en) | Air inlet channel suitable for small jet unmanned aerial vehicle with flying wing layout | |
| US5598990A (en) | Supersonic vortex generator | |
| US9587585B1 (en) | Augmented propulsion system with boundary layer suction and wake blowing | |
| CA2898624C (en) | Propulsion system using large scale vortex generators for flow redistribution and supersonic aircraft equipped with the propulsion system | |
| EP3016859B1 (en) | Propulsion system for an aerial vehicle | |
| CN106628163B (en) | A kind of supersonic speed unmanned fighter that big drag braking and VTOL can be achieved | |
| US20090313968A1 (en) | Hypersonic Inlet Systems and Methods | |
| CA2703748A1 (en) | Low shock strength inlet | |
| CN101200220A (en) | Systems and methods for passively directing aircraft engine nozzle flows | |
| CN109878704A (en) | It is a kind of based on circulation control principle without rudder face aircraft | |
| CN106014684A (en) | Combined flow control method and structure for improving SERN for TBCC | |
| EP2871131B1 (en) | Variable geometry helicopter engine inlet | |
| RU2670664C9 (en) | Asymmetrical air-scoop for three flow engine of faster-than-sound aircraft | |
| AU2019292004B2 (en) | Flight vehicle engine inlet with internal diverter, and method of configuring | |
| US3291420A (en) | Wing structure and duct means for aircraft | |
| RU2371352C1 (en) | Variable-thrust vector aircraft | |
| CN109850128A (en) | Multistage air blowing circular rector high lift device and aircraft | |
| US20070176052A1 (en) | Air inlet for a turbofan engine | |
| US20110240804A1 (en) | Integrated aircraft | |
| EP0052360B1 (en) | Air aspiration device of aircraft-mounted gas-turbine engine | |
| RU176021U1 (en) | Variable geometry air intake for multi-mode combined turbo-exhaust power plant | |
| CN113464280B (en) | Controllable air inlet channel based on leakage gap switch and method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161026 |