CN103797229B - For the method adjusting supersonic inlet - Google Patents
For the method adjusting supersonic inlet Download PDFInfo
- Publication number
- CN103797229B CN103797229B CN201280032672.XA CN201280032672A CN103797229B CN 103797229 B CN103797229 B CN 103797229B CN 201280032672 A CN201280032672 A CN 201280032672A CN 103797229 B CN103797229 B CN 103797229B
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- China
- Prior art keywords
- adjustable panel
- panel
- rear portion
- anterior
- adjustable
- Prior art date
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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
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- 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
Abstract
The present invention relates to aeronautical technology, and more particularly relate to the air intake duct of supersonic plane propulsion system.The preferred use field of the present invention is in the turbojet that Mach Number Never To Be Exceeded is 3.The invention is intended to obtain the technical result of the minimum area (critical cross-section) that the drift angle of a level scanning wedge-like portion and the flow channel of air intake duct in the case of or not forming undesirable longitudinal slot in air intake duct pipeline and in the case of not blocking displaceable element, can be adjusted.Area and the position of shock wave of critical cross-section is included changing for adjusting the method for supersonic inlet.nullThe setting of the change of critical cross-section area and the position of shock wave realizes by rotating while anterior adjustable panel (11) and rear portion adjustable panel (12)，The rotation axis (9) of this front portion adjustable panel (11) with scan wedge-like portion (7、22) first order of in overlaps with the intersection of the second level，This intersection is not perpendicular to impact air-flow，In the region of the trailing edge that the rotation axis (10) at this rear portion adjustable panel (12) is positioned at rear portion adjustable panel (12) and be oriented in case with the jante et perpendiculaire of anterior adjustable panel，Wherein，When anterior adjustable panel and rear portion adjustable panel rotate，The anterior transverse edge of adjustable panel and the transverse edge of rear portion adjustable panel shift relative to the lateral surfaces of the shaping of pipeline and not at the transverse edge of anterior adjustable panel、Gap is formed between the lateral surfaces of the transverse edge of rear portion adjustable panel and the shaping of pipeline.
Description
Technical field
The present invention relates to aeronautical engineering, and more particularly relate to supersonic plane propulsion system
Air intake duct.The present invention preferably is applicable to the by-pass type turbojet that Mach Number Never To Be Exceeded is 3.0
Engine aircraft.The production of the aircraft (AC) that radar perceptibility is low means its all elements
Shape each contributes to reduce the Radar Cross Section (RCS) of aircraft.This is equally applicable to start
The shape of the entrance of the air intake duct of machine.In order to obtain Expected Results, all edges of air intake duct are all answered
When there is the portion of scanning and being parallel to some aircraft component (edge of wing, empennage etc.).Throughout
Opereating specification be respectively provided with this air intake duct of high inherent character realize it be not adjusted
In the case of be infeasible.
Background technology
Generally, air intake duct deceleration surfaces (such as, wedge-like portion or conic section) is adjustable.?
Under supersonic speed, change flowing deceleration intensity that the drift angle of deceleration surfaces causes changing in air intake duct also
And change the area of its critical cross-section.Meanwhile, the effect of this adjustment provide air intake duct throughout
The high-performance of the flight speed scope of the aircraft of this air intake duct is installed.
There is a kind of known method for adjusting supersonic speed two dimension air intake duct, the deceleration of this air intake duct
Surface exhibits is multistage non-to scan wedge-like portion (Remeev N.H., the sky of supersonic plane air intake duct
Aerodynamics (Aerodynamics of Supersonic Aircraft Air Intakes.) TsAGI,
Zhukovsky publishes, 2002, page 178).In known solution, air intake duct passes through
The panel rotated around corresponding axle is adjusted.Panel is succeedingly arranged in the duct.Forward face
Plate includes the multiple levels in addition to the first order in deceleration wedge-like portion.The axis of front panel and wedge-like
The first order in portion and the intersection of the second level overlap.Front panel is a part for pipeline and has multiple
Miscellaneous shape.Extending above of the axis of front panel edge behind.The level in deceleration wedge-like portion and limit
Edge does not exist the portion of scanning and makes it possible for the parallel rotary axes being perpendicular to impact air-flow of panel
Line.For adjusting the method inferior position for there is the air intake duct scanning edge of two dimension air intake duct
It is, by being perpendicular to the infeasibility that it is adjusted by the axis of flow direction, this is because enter
All elements of air flue entrance are the most swept.
The immediate prior art of the present invention is a kind of method for adjusting supersonic inlet,
The method relates to area and the position (RU2343297C1) of shock wave changing critical cross-section.?
The solution known depends on and utilizes V-arrangement wedge-like portion (i.e., Seen from the front, each other in obtuse angle
Two of orientation are adjacent scans wedge-like portion) Three-dimensional Flow slow down.Air intake duct is constructed such that
All edges of entrance are the most swept.Two counter plates rotated around corresponding axis by utilization
Adjust air intake duct.Front panel in every counter plate is all a part for deceleration surfaces.Rear
Plate is a part for pipeline.When being adjusted every counter plate, transverse slot occurs in theirs
Between adjacent face, and longitudinal slot occur in they be both positioned at on the junction surface of sidewall,
Again between the horizontal face on the junction surface being engaged with each other.The method has a following inferior position:
-do not provide for the method adjusting air intake duct and to fly in subsonic flight speed and low supersonic speed
Necessary critical cross-section area under line speed, this is because movably panel is to move by a small margin
Dynamic.Otherwise, it may appear that the unacceptable aforementioned longitudinal slot of size.This means that air intake duct is not
Turbofan engine operating and this air intake duct is provided not throughout speed operating range
It is multimodal.
The method for adjusting air intake duct that realizes is complicated technically.
Summary of the invention
Treat that the technique effect obtained by the present invention includes, it is ensured that or not do not formed in its pipeline departing from
In the case of the longitudinal slot required and in the case of not blocking displaceable element, change one and sweep
Plunder the drift angle of the level in deceleration wedge-like portion and minimum inlet passageway area (critical cross-section).This tune
Electromotor in all offline mode of the whole aircraft that Mach number then can be provided to be up to M=3.0
Steady running, wherein, engine charge gross pressure recovery factor has and is not less than for adjustable
The level of the conventional levels of two dimension air intake duct, and total flow irregularity (overall flow
Heterogeneity) less than maximum permissible value (aerodynamic of supersonic plane, stability and
Navigability (Aerodynamics, Stability and Maneuverability of Supersonic
Aircraft), G.S.Byushgens. edits, and Nauka.Fizmatlit publishes, and 1998).Due to
The parallelogram shape Seen from the front of inlet mouth and all edges scan portion, lead
Cause to reduce the radar perceptibility of the object being provided with this air intake duct.When air intake duct sides aligned parallel is in thing
During some elements (leading edge of wing or trailing edge, the empennage etc.) of body, maximum radar sense will be obtained
Degree of knowing reducing effect.
Described technique effect obtains in a kind of method for adjust supersonic inlet, the method
Including area and the position of shock wave of change critical cross-section, wherein, the area of critical cross-section and punching
Hit the described change of position of ripple by making anterior adjustable panel and rear portion adjustable panel simultaneously
Rotating and realize, the rotation axis of this front portion adjustable panel and an intersection overlap, and this intersection is one
The individual first order scanning wedge-like portion and the intersection of the second level, this intersection is not perpendicular to impact air-flow,
In the region of the trailing edge that the rotation axis of this rear portion adjustable panel is positioned at rear portion adjustable panel also
And it is oriented to, with the rotation axis of anterior adjustable panel, there is intersection point, wherein, when front portion is adjustable
When whole panel and rear portion adjustable panel rotate, transverse edge and the rear portion of anterior adjustable panel can
The transverse edge adjusting panel can not in front portion relative to the lateral surfaces displacement of the shaping of pipeline
Adjust transverse edge and the shaping of pipeline horizontal of the transverse edge of panel, rear portion adjustable panel
Gap is formed between surface.
It addition, when anterior adjustable panel and rear portion adjustable panel rotate, locate in plan view
Transverse slot between anterior adjustable panel and rear portion adjustable panel does not change its orientation
And its position overlaps with a straight line, this pass straight through the rotation axis of anterior adjustable panel with after
The intersection point of the rotation axis of portion's adjustable panel, wherein, this gap has for adjustable panel
Arbitrary possible position close to rectangular shape.
It addition, when anterior adjustable panel and rear portion adjustable panel rotate, the panel of covering
Rotation axis around this covering rotates and is oriented such that the rotation axis of this covering
Between himself and the rotation axis of rear portion adjustable panel, there is common intersection point.
It addition, when anterior adjustable panel and rear portion adjustable panel rotate, with anterior adjustable
Panel and rear portion adjustable panel movement ground connect and close and be disposed in critical cross-section
The pivoted door of the transverse slot in nonadjustable deceleration wedge-like portion in region changes its position.
Accompanying drawing explanation
By accompanying drawing, present invention is described, and wherein, Fig. 1 shows that adjustable supersonic speed is entered
The upward view of air flue；Fig. 2 is the side view of adjustable supersonic inlet；Fig. 3 is adjustable
The front view of supersonic inlet；Fig. 4 is the section A-A in Fig. 1；Fig. 5 shows at volume
Determine the schematic diagram that the flowing in the aloft adjustable supersonic inlet of power is slowed down；Fig. 6 is
Supersonic inlet and for adjusting the top view of panel of this supersonic inlet；Fig. 7 is Supersonic
Speed air intake duct and for adjusting the side view of panel of this supersonic inlet；Fig. 8 is in Fig. 6
Section B-B.
Detailed description of the invention
Adjustable supersonic inlet includes following elements:
The edge in 1-deceleration wedge-like portion 7；
The edge in the deceleration wedge-like portion 22 that 2-is fixing；
3, the edge of 4-shell；
The pipeline of 5-air intake duct；
6-cylindrical portion；
7-includes the deceleration wedge-like portion of anterior adjustable panel 11；
The region of the possible position of 8-suction-type safety door；
The rotation axis of 9-front portion adjustable panel 11；
The rotation axis of 10-rear portion adjustable panel 12；
Anterior adjustable panel that 11-is in maximum critical cross-section position (minimum shown in phantom
Critical cross-section position)；
Rear portion adjustable panel that 12-is in maximum critical cross-section position (minimum shown in phantom
Critical cross-section position)；
The anterior adjustable panel 11 that 13-is in minimum critical sectional position；
The rear portion adjustable panel 12 that 14-is in minimum critical sectional position；
What 15-was used for blowing down (bleed) boundary region is in anterior adjustable panel and rear portion adjustable
Transverse slot between panel；
16-be in the deceleration wedge-like portion including anterior adjustable panel the first order and the second level it
Between sweep；
17-is in the sweep between the first order and the second level in fixing deceleration wedge-like portion 22；
18-be in the deceleration wedge-like portion including anterior adjustable panel the second level and the third level it
Between sweep；
The cut-off portion of the dihedral angle that 19-is formed by shell；
20-is in connecing between deceleration wedge-like portion and the shell including anterior adjustable panel
The chamfered section of the entrance in conjunction portion；
The cut-off portion of the dihedral angle that 21-is formed with shell by the deceleration wedge-like portion 22 fixed；
The deceleration wedge-like portion that 22-is fixing；
23-is pointed to the additional lateral in the critical cross-section region in the deceleration wedge-like portion 22 fixed
The door that gap is adjusted；
24-supersonic diffuser (deceleration system)；
25-subsonic diffuser；
26-is from the oblique shock wave of the first order scanning wedge-like portion；
27-is from the oblique shock wave of the second level scanning wedge-like portion；
28-is from the oblique shock wave of the third level scanning 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, uses
In increasing the gas flow rate range by air intake duct, at this by-pass area, provide the steady of air intake duct
Fixed operation；
31-includes the first order in the wedge-like portion of anterior adjustable panel 11；
32,33, the rotation axis of 34-covering (curtain) 45；
The intersection point of the axis of the rotation axis of 35-covering 43 and rear portion adjustable panel 12；
The rotation axis of 36-front portion adjustable panel 11 and the rotary shaft of rear portion adjustable panel 12
The intersection point of line；
37 arrangements are in along the transverse slot between adjustable panel 11 and adjustable panel 12
Line；
The attachment location of the actuator of 38-rear portion adjustable panel 12；
Tap in 39-rear portion adjustable panel 12；
The rotation axis of 40-door 23；
41-tight seal above rear portion adjustable panel 12；
The controlling organization of the horizontal pivoted door of 42-23；
The actuator lever of 43-front portion adjustable panel 11；
The profile of 44-pipeline；
45-covering；
The compartment of the controlling organization of 46-rear portion adjustable panel 12；
The cross side of the shaping of 47-pipeline 5.
Supersonic diffuser 24, critical cross-section portion, subsonic diffuser 25, respectively around axis 9
Air inlet can be referred to as with the 10 anterior adjustable panels 11 pivoted and rear portion adjustable panel 12
The primary element in road.
Seen from the front, inlet mouth is that the length of height side corresponding to this of corresponding side has
The parallelogram of arbitrary ratio or its particular condition rectangle.Inlet mouth can have except
By the cut-off portion 19 at the angle scanned outside the angle that wedge-like portion is formed and 21 or chamfered section 18.Air intake duct
The edge of entrance is positioned in the plane acutangulating orientation with flow direction.Thus, this entrance is all
Edge is the most swept.
Supersonic diffuser 24 is a kind of flowing deceleration system, and this flowing deceleration system is by forming two
A pair of angle, face scans wedge-like portion 7 and 22 and shell (edges of 3,4 shells) composition.
Scan wedge-like portion 7 and 22 and there is at least one level, and the quantity of the level in wedge-like portion is permissible
It is different.As a kind of example, Fig. 1,2,3 and 4 show and scan in wedge-like portion at one
There are three levels and scan at second there is in wedge-like portion the air intake duct of two levels.Scan wedge-like portion
The bending section 16,17 and 18 of corresponding stage in the corresponding stage being positioned at the wedge-like portion forming dihedral angle
Position on the intersection on surface intersects each other.Sweep angle in each level scanned in wedge-like portion can
To be different from the sweep angle at the edge in corresponding wedge-like portion, and it is also between them.When slowing down
System be designed to produce from every pair of corresponding wedge-like portion level have given intensity single tiltedly
Shock wave, i.e. utilize aerodynamic design principle (Shchepanovsky V.A., Gutov B.I.
Aerodynamic design (the Gas-dynamic Designing of Super-of supersonic inlet
Sonic Air Intakes.) Nauka, Novosibirsk, 1993) time, it is intended that scan wedge-like portion
The drift angle of level.
As scanning wedge-like portion 7 and 22, shell forms dihedral angle.Specific features is, shell
Be oriented such that it makes flowing velocity slow down further, i.e. shell is not arranged in from scanning wedge
On the streamline in the downstream of the shock wave in shape portion.The undercut corner of shell can be adjustable.Can be in place
The edge of the inlet mouth in the region of the dihedral angle formed by shell arranges groove, and
Shell itself can have the hole of arbitrarily shaping.
Subsonic diffuser 23 can have suction-type safety door 8, and this suction-type safety door 8 provides
Outer gas stream around air intake duct flowing enters into the path in this subsonic diffuser 25.This suction
Enter formula safety door 8 to contribute to strengthening the air inlet under low speed (be under high attack angle taking off and flying)
Road performance.
The above-mentioned method for adjusting air intake duct is as follows.Make to include one scan wedge-like portion 7 except
The anterior adjustable panel 11 of multiple grades outside the first order rotates around axis 9, this axis 9
It is positioned at the first order in wedge-like portion 7 and the intersection of the second level.The rear portion adjustable panel 12 of coupling
It is a part for subsonic diffuser 25 and rotates around sterically defined axis 10.If it is front
The axis 9 of portion's adjustable panel is specially appointed, then can extending of rear portion adjustable panel
The position of the axis 10 above the trailing edge of this rear portion adjustable panel is just determined to be so that after
The axis 10 of portion's adjustable panel intersects with the axis 9 of anterior adjustable panel 11.
During air intake duct is adjusted, can with rear portion at anterior adjustable panel 11
Adjust and between panel 12, form transverse slot 15, be used for blowing down boundary region.At adjustable panel
Setting in the system of selection of axis, the transverse slot between them has the shape close to rectangle
Shape.
Anterior adjustable panel 11 is connected to rear portion adjustable panel 12 by bar 43.
When air intake duct is adjusted, anterior adjustable panel 11 and rear portion adjustable panel 12
Change their position when rotated according to specific rule simultaneously.The rotation of panel 11 and 12 changes
Air intake duct critical cross-section area, scan the drift angle of the moveable level in wedge-like portion 7 and be in
The size laterally blowing down gap 15 between panel 11 and 12, and the horizontal stroke of panel 11 and 12
To edge in the case of being formed without gap relative to pipeline 47 shaping lateral surfaces displacement.
The additional lateral gap for boundary layer blowing-off closed by door 23 can be disposed in and be positioned at
Fixing scanning in wedge-like portion 22 in critical cross-section region.This door can be entered by counter plate 11,12
The mechanism of row Synchronization Control is controlled.Such as, kinematic mechanisms 42 can be applied, this kinesiology
Mechanism 42 is relevant to the axis 9 of anterior adjustable panel 11 by pivoted door by bar and control crank
Even.
Above-mentioned transverse slot in wedge-like portion and perforation are favorably improved the air intake duct under supersonic speed
Energy.
Rear portion adjustable panel 12 has tap 39, so that being positioned at rear portion adjustable panel 12
Pressure equal (level) in the chamber of top and pipeline.It is positioned at the top of adjustable panel 11,12
Chamber be divided into two half-unit by the covering 45 of the form in folding separator, this covers
Part 45 for by pass through perforation, laterally blowing gap 15 between adjustable panel,
And tap 39 enters into and has the air of different pressures in the space above panel and separate.
This covering 45 includes two hinged flat panel top panels and bottom panel.
Top panel is hinged to the structure of rear portion adjustable panel control mechanism compartment 46, and bottom faces
Plate is hinged to rear portion adjustable panel.In order to provide the kinesiology performance of covering 45, this covers
Rotation axis 32,33,34 space orientation of part 45 so that they have and are positioned at rear portion adjustable
An intersection point on the rotation axis 10 of panel 12.
For realizing as follows to having the method that the air intake duct scanning edge is adjusted.
Under subsonic flight speed, the adjustable panel 11 and 12 of air intake duct is in maximum critical
In sectional position (by retracted position shown in solid in figure), thus provide critical cross-section region,
In this critical cross-section region, the most there is not ultrasonic flow velocity.
Under supersonic flight speed, aircraft propelling system efficiency is slowed down with the flowing in air intake duct
Efficiency is relevant.Supersonic Flow in air intake duct is slowed in shock wave 26,27,28, this
A little shock waves 26,27,28 occur in air-flow when flowing around the wedge-like portion of scanning of deceleration system.
Along with supersonic flight speed increase, adjustable panel 11 with 12 from corresponding with subsonic flight
Position synchronously deflects.The synchronization deflection of panel 11,12 by be in anterior adjustable panel 11 with
Mechanical linkage between rear portion adjustable panel 12 provides via bar 43.Thus, rear portion
The rotation by this mechanism of adjustable panel 12 simultaneously drives this front portion adjustable panel 11.Before
The rotation towards the drift angle of the level increasing wedge-like portion of portion's adjustable panel 11 increases from these
Flowing deceleration intensity in the shock wave of level.Simultaneously, the rotation of front panel 12 reduces
Critical cross-section area.The flowing increase of deceleration intensity and reducing at air intake duct of critical cross-section area
There is in performance good effect.
Up to the deceleration of subsonic flowing is in the normal shock wave 29 being positioned at inlet mouth
Realize.This subsonic flow is finally decelerated in subsonic diffuser 25 and is disappeared by electromotor
Consume.
Steady in all of state of flight and under all of engine power state of air intake duct
Fixed operation is by the utilizability of the gas bypassing 30 in oblique shock wave 28 and by deceleration system
Wedge-like portion level on perforation and be between anterior adjustable panel and rear portion adjustable panel
The boundary layer blowing-off system of form of transverse slot guaranteed.
Transverse slot 15 is formed at the position being different from retracted position of adjustable panel 11 and 12
Place.When making panel 11 and 12 indentation, there is not gap 15.This effect is by adjustable
The rotation axis 9 and 10 of whole panel orthoselection in space is so that they have intersection point 36
Realize.
Additionally, the deceleration wedge-like portion 22 that boundary layer blowing-off is fixing by being positioned at (having fix level)
On critical cross-section region in and the additional lateral gap that is adjusted by door 23 realize being can
Can.
When the position of adjustable panel 11 and 12 is different from retracted position, additional lateral gap leads to
Often it is opened in supersonic mode.When adjustable panel 11 and 12 is in retracted position
Time, described additional lateral gap is closed by door 23.
When making panel extend, covering 45 starts to open at, and this covering 45 will pass through tap
Air in 39 chambeies entering into the top being positioned at rear portion adjustable panel 12 with by perforation and position
Laterally blowing gap 15 between adjustable panel 11 and 12 enters into and is positioned at anterior adjustable
Air in the chamber of the top of panel 11 is separated.
Method for adjusting required for protection ensure that the intrinsic aerodynamic of height of air intake duct
Characteristic, the configuration of this air intake duct concurrently facilitates parallel four limits Seen from the front by entrance
Scanning of the level in shape shape and all edges of entrance and deceleration wedge-like portion reduces this air intake duct
Radar perceptibility.Allow to shine relative to radar for forming the selection of the orientation of the element of this entrance
The bright structure guiding them, so that the radar signal deflection reflected from this structure and eliminate angle
Reflector.
Claims (4)
1., for the method adjusting supersonic inlet, described method includes changing critical cross-section
Area and the position of shock wave,
It is characterized in that, for changing described in the area of described critical cross-section and the position of described shock wave
Flexible mistake makes anterior adjustable panel and rear portion adjustable panel rotate simultaneously and realize, and described front portion can
Adjust rotation axis and the intersection coincidence of panel, described intersection be scan in wedge-like portion one the
One-level and the intersection of the second level, described intersection is not perpendicular to impact air-flow, and described rear portion is adjustable
In the region of the trailing edge that the rotation axis of whole panel is positioned at described rear portion adjustable panel and be oriented
Make the described rotation axis of described rear portion adjustable panel and the described of described anterior adjustable panel
Rotation axis has intersection point,
Wherein, when described anterior adjustable panel and described rear portion adjustable panel rotate, described before
The transverse edge of portion's adjustable panel and the transverse edge of described rear portion adjustable panel are both relative to pipe
The lateral surfaces displacement of the shaping in road, and not at the transverse edge of described anterior adjustable panel with described
The transverse edge of gap and portion's adjustable panel the most in the rear is formed between the lateral surfaces shaped
And form gap between the lateral surfaces of described shaping.
Method the most according to claim 1, it is characterised in that at described anterior adjustable panel
During rotating with described rear portion adjustable panel, be in plan view described anterior adjustable panel with
The orientation of the transverse slot between the adjustable panel of described rear portion does not change, and described transverse slot
Position overlap with a straight line, described straight line crosses the described rotation axis of described anterior adjustable panel
With the described intersection point of the described rotation axis of described rear portion adjustable panel, wherein, described transverse slot
There is the arbitrary possible position for described anterior adjustable panel and described rear portion adjustable panel
Close to rectangular shape.
Method the most according to claim 1, it is characterised in that when described anterior adjustable panel
When rotating with described rear portion adjustable panel, the panel of covering is around the rotation axis of described covering
Rotate, and the rotation axis of the described panel of described covering is oriented such that described covering
The described rotation axis of the described rotation axis self of described panel and described rear portion adjustable panel it
Between there is common intersection point.
Method the most according to claim 1, wherein, when described anterior adjustable panel and described
When rear portion adjustable panel rotates, the position change of pivoted door, wherein, described pivoted door with described before
Adjustable panel movement ground in portion connects and closes in the region being positioned at described critical cross-section not
Additional lateral gap in adjustable deceleration wedge-like portion.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2011116972/06A RU2460892C1 (en) | 2011-04-29 | 2011-04-29 | Method of adjusting supersonic air intake |
| RU2011116972 | 2011-04-29 | ||
| 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 CN103797229A (en) | 2014-05-14 |
| CN103797229B true CN103797229B (en) | 2016-10-26 |
Family
ID=46938991
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201280032672.XA Active 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) |
Families Citing this family (6)
| 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) |
| 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 |
| CN114450224A (en) * | 2019-07-01 | 2022-05-06 | 张传瑞 | Aerodynamic techniques and methods for performing quieter supersonic flight |
| 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 |
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| 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 |
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| 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 |
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2011
- 2011-04-29 RU RU2011116972/06A patent/RU2460892C1/en active
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2012
- 2012-04-28 CN CN201280032672.XA patent/CN103797229B/en active Active
- 2012-04-28 WO PCT/RU2012/000342 patent/WO2012148319A1/en active Application Filing
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|---|---|---|---|---|
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103797229A (en) | 2014-05-14 |
| RU2460892C1 (en) | 2012-09-10 |
| WO2012148319A1 (en) | 2012-11-01 |
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