CN109533356A - A kind of shock wave boundary layer interaction controller - Google Patents
A kind of shock wave boundary layer interaction controller Download PDFInfo
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- CN109533356A CN109533356A CN201811389647.2A CN201811389647A CN109533356A CN 109533356 A CN109533356 A CN 109533356A CN 201811389647 A CN201811389647 A CN 201811389647A CN 109533356 A CN109533356 A CN 109533356A
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- shock wave
- static pressure
- boundary layer
- pressure hole
- connecting pipe
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C30/00—Supersonic type aircraft
Abstract
The present invention discloses a kind of shock wave boundary layer interaction controller, comprising: connecting pipe is set to the shock wave upstream static pressure hole of the connecting pipe upstream along the flow direction of body surface air-flow and set on the shock wave downstream static pressure hole in the connecting pipe downstream；Identical with the connecting pipe section pressure equilibrium piston in section is set in the connecting pipe and one end connect with the pressure equilibrium piston, the other end be fixed on the connecting pipe end inner surface of tube wall telescopic element；The telescopic element and the pressure equilibrium piston are used to incude the air-flow entered from shock wave downstream static pressure hole, and the pressure at the aperture balancing shock wave upstream static pressure hole and shock wave downstream static pressure hole by way of mobile to shock wave upstream static pressure hole side.Shock wave boundary layer interaction controller provided by the invention realizes the double control to boundary layer and shock wave, effectively weakens shock wave boundary layer interaction effect.
Description
Technical field
The present invention relates to shock wave control technology fields, more particularly to a kind of shock wave boundary layer interaction controller.
Background technique
For carrying out the aircraft or supersonic inlet of transonic flight, one major problem is that when air-flow is more than sound
One of normal shock wave will be generated when fast.Normal shock wave can bring the suddenly change of pressure, density and speed, this violent variation meeting
Further the boundary layer near object plane is had an impact, leads to the increase or even flow separation of boundary layer thickness；On the other hand,
Since normal shock wave is very sensitive to boundary layer thickness, the variation in boundary layer can influence the position of normal shock wave and strong in turn again
Degree；So mutual nonlinear interaction, will lead to the interference problem for shock wave and boundary layer occur.Serious shock wave and boundary layer
Interference can bring the self-oscillation and flow separation of shock-wave spot and intensity, cause buffeting and the supersonic inlet of aircraft
Surge causes its performance to be greatly reduced, or even seriously threatens the safety of aircraft.
But the pneumatic efficiency of aircraft is equal to speed multiplied by lift resistance ratio, therefore the flight speed of raising aircraft as far as possible
The flight efficiency of aircraft can be improved in degree, saves fuel oil, reduces noxious gas emission.Thus, current large-scale seating plane
Design cruising speed all select slightly below generate buffet flying speed, it may also be said to, aircraft surface shock wave and boundary layer
Interference problem limit the flight boundary of aircraft.If aircraft production can be improved as best one can using relevant technological means
The raw flying speed buffeted, so that it may which the pneumatic efficiency for greatling improve aircraft promotes the safety of aircraft.And for super
For velocity of sound air intake duct, normal shock wave has the compression ratio for being conducive to improve air intake duct, improves the performance of air intake duct.But shock wave
Interference with boundary layer will lead to the unstable of shock-wave spot and intensity, causes flow distortion index to deteriorate, influences engine
Working efficiency, or even shut down, seriously threaten the flight safety of aircraft.
In order to weaken shock wave and boundary layer disturbing effect, currently it is expected in the aircraft or supersonic speed for carrying out transonic flight
The major technique of air intake duct application has: 1) actively blowing and air-breathing control means can by carrying out air blowing or air-breathing to boundary layer
To supplement the momentum of boundary layer loss or siphon away the air-flow of low-momentum, to maintain the full of boundary layer velocity profile, mention
The ability of shock wave sudden change of pressure surface is resisted in high boundary layer, achievees the purpose that weaken shock wave and boundary layer disturbing effect；2) shock wave control
Bulge technology processed, by the way that at the position that shock wave occurs, part changes object geometric shape, so that shock wave is allowed to be compressed in advance,
Weaken the intensity of shock wave, and then weakens shock wave and boundary layer disturbing effect.
It can be seen that the major defect of above-mentioned technological means is just for boundary for the interference problem of shock-boundary
Layer or shock wave carry out single control, actively blow and are mainly used for improving the flow regime in boundary layer with suction technology, and shock wave
Control bulge technology is mainly used for weakening the intensity of shock wave, thus they have in the application potential of shock wave boundary layer interaction control
Limit, cannot achieve the effect that satisfied.And there are also some other disadvantages for they: although 1) actively air blowing and suction technology can mention
The ability of shock wave sudden change of pressure surface is resisted in high boundary layer itself, but needs additionally to add the system of a set of air blowing or air-breathing, is increased
The complexity of construction weight and system, and need additional energy input, it is less economical；2) since shock wave controls bulge skill
Art is to realize that shock wave controls by changing the curvature of body surface, to boundary layer there are certain disturbance, works as shock-boundary
When interfering stronger, the application effect that shock wave controls bulge is bad, and current main application field is the design of aircraft drag reduction,
Supersonic inlet is not possible to be applied at present since shock wave control bulge can reduce inlet channel cross-sectional area.
Therefore, the invention proposes a kind of novel shock-boundary that can carry out double control to boundary layer and shock wave is dry
Controller is disturbed, by designing the connecting pipe with telescopic element and pressure equilibrium piston, the pressure in shock wave downstream is transferred to sharp
On the other hand wave upstream then utilizes the sudden change of pressure surface of shock wave itself to weaken the intensity of shock wave, realize shock wave downstream suction
With shock wave upstream air blowing effect, to enhance the momentum in boundary layer, under double control effect, reached effectively reduce it is sharp
The purpose of wave boundary layer disturbing effect.
Summary of the invention
The object of the present invention is to provide a kind of shock wave boundary layer interaction controller, for solve at present only to boundary layer or
Shock wave carries out the problem that single control keeps the effect of shock wave boundary layer interaction control limited.
To achieve the above object, the present invention provides following schemes:
A kind of shock wave boundary layer interaction controller, the shock wave boundary layer interaction controller includes: connecting pipe, along object
The flow direction of airflow on surface is set to the shock wave upstream static pressure hole of the connecting pipe upstream and is set to the connecting pipe downstream
Shock wave downstream static pressure hole；
The connecting pipe is the silent pipeline in both ends, and shock wave downstream static pressure hole passes through the connecting pipe and institute
State the connection of shock wave upstream static pressure hole；
Be arranged in the connecting pipe identical with the connecting pipe section pressure equilibrium piston in section and one end and
The pressure equilibrium piston connection, the other end are fixed on the telescopic element of the inner surface of tube wall of the end of the connecting pipe；Institute
It states telescopic element and the pressure equilibrium piston and is used to incude the air-flow from the entrance of shock wave downstream static pressure hole, and by institute
State the aperture that the mobile mode in shock wave upstream static pressure hole side balances shock wave upstream static pressure hole and shock wave downstream static pressure hole
The pressure at place；The connecting pipe airless when passing through the pressure equilibrium piston be located at shock wave upstream static pressure hole and described
In the connecting pipe between shock wave downstream static pressure hole.
Optionally, guide rod is vacantly set in the connecting pipe, and the both ends of the guide rod are fixed on the connecting pipe
On tube wall, the guide rod passes through the pressure equilibrium piston, moves the pressure equilibrium piston along the guide rod.
Optionally, shock wave downstream static pressure hole is one, and shock wave upstream static pressure hole is multiple.
Optionally, shock wave downstream static pressure hole is placed in the downstream for acting on the normal shock wave of the body surface, described
Shock wave upstream static pressure hole is placed in the upstream of the normal shock wave, and shock wave downstream static pressure hole is located at the side of normal shock wave generation
Interlayer interferes control area downstream least significant end, and shock wave upstream static pressure hole is located at the friendship of the normal shock wave and the body surface
1~2 times of the position that distance at boundary is local boundary layer thickness δ, shock wave downstream static pressure hole and the shock wave upstream are quiet
Pressing the distance between hole is 10~15 times of local boundary layer thickness δ.
Optionally, shock wave downstream static pressure hole is circular hole, and diameter is local boundary layer thickness δ.
Optionally, shock wave upstream static pressure hole is circular hole, and diameter is 2~3 times of local boundary layer thickness δ.
Optionally, the quantity in shock wave upstream static pressure hole and diameter are determined by the design objective of aircraft or air intake duct,
The design objective includes that flight Mach number, buffeting Mach number, lift resistance ratio, total pressure recovery coefficient and inlet duct flow field distortion refer to
Number.
Optionally, the section of the connecting pipe is circle, and diameter is greater than or equal to the side of boundary layer interference control area
5 times of interlayer average thickness.
Optionally, in no pressure difference, the pressure equilibrium piston is located at the corresponding company in shock wave upstream static pressure hole
The side threaded a pipe.
Optionally, the telescopic element is spring, and the coefficient of stiffiness of the spring is k,
Wherein S is the pressure equilibrium piston cross-section area, and △ x is the movement of the pressure equilibrium piston
Distance, △ p are shock wave downstream static pressure hole, the pressure difference at shock wave upstream static pressure hole,
Δ p=p2-p1, p1For the pressure at shock wave upstream static pressure hole, p2For the pressure at shock wave downstream static pressure hole
By force.
Compared with prior art, the invention discloses following technical effects:
The invention proposes the novel shock wave boundary layer interaction controller that a kind of pair of boundary layer and shock wave carry out double control,
By designing the connecting pipe with telescopic element and pressure equilibrium piston, the air-flow in shock wave downstream pushes telescopic element and pressure flat
Weigh piston downstream on shock wave, and the pressure in shock wave downstream is transferred to shock wave upstream, so that the intensity of shock wave is weakened, it is another
Aspect then utilizes the sudden change of pressure surface of shock wave itself, realizes shock wave downstream suction and shock wave upstream air blowing effect, realizes shock wave boundary
The automatic control of layer interference, to enhance the momentum in boundary layer, and does not need additional energy input.In double control effect
Under, achieve the purpose that effectively reduce shock wave boundary layer interaction effect, and the curvature without changing object plane, avoid to boundary
The unfavorable interference of layer.
Detailed description of the invention
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the invention
Example, for those of ordinary skill in the art, without any creative labor, can also be according to these attached drawings
Obtain other attached drawings.
Fig. 1 is the structural schematic diagram of shock wave boundary layer interaction of embodiment of the present invention controller；
Fig. 2 is application schematic diagram of shock wave boundary layer interaction of the embodiment of the present invention controller on wing；
Fig. 3 is application schematic diagram of shock wave boundary layer interaction of the embodiment of the present invention controller in supersonic inlet.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
In order to make the foregoing objectives, features and advantages of the present invention clearer and more comprehensible, with reference to the accompanying drawing and specific real
Applying mode, the present invention is described in further detail.
Shock wave boundary layer interaction controller provided by the invention can be applied to need to improve the aircraft table of buffet margin
Face or the supersonic inlet inner surface for needing to be improved performance, by theory analysis, numerical simulation or are experimentally determined it
Main shock wave and boundary layer interference region, typical airliner are mainly wing middle section along the region of tangential 50%-80%, are surpassed
Velocity of sound air intake duct is generally supersonic airstream and slows to subsonic region, and it is dry to install shock-boundary of the invention in this region
Controller is disturbed,
Embodiment 1:
As shown in the structural schematic diagram of shock wave boundary layer interaction controller Fig. 1 of the invention, wherein shock wave side of the invention
Interlayer interference suppressor is mounted in the inner space 8 of aircraft or air intake duct, comprising: connecting pipe 4, along body surface 1
The flow direction of air-flow is set to the shock wave upstream static pressure hole 2 of 4 upstream of connecting pipe and the shock wave set on 4 downstream of connecting pipe
Downstream static pressure hole 3；
Connecting pipe 4 is the silent pipeline in both ends, and shock wave downstream static pressure hole 3 is quiet by connecting pipe 4 and shock wave upstream
Hole 2 is pressed to be connected to；
Section pressure equilibrium piston 6 identical with 4 section of connecting pipe and one end and pressure are set in connecting pipe 4
The connection of dummy piston 6, the other end are fixed on the telescopic element 5 of the inner surface of tube wall of the end of connecting pipe 4；5 He of telescopic element
Pressure equilibrium piston 6 is used to incude the air-flow from the entrance of shock wave downstream static pressure hole 3, and by 2 sidesway of shock wave upstream static pressure hole
Dynamic mode balances the pressure at the aperture in shock wave upstream static pressure hole 2 and shock wave downstream static pressure hole 3；4 airless of connecting pipe is logical
Out-of-date, pressure equilibrium piston 6 is located in the connecting pipe 4 between shock wave upstream static pressure hole 2 and shock wave downstream static pressure hole 3.
Wherein, guide rod 7 is vacantly set in connecting pipe 4, and the both ends of guide rod 7 are fixed on the tube wall of connecting pipe 4, guide rod
7 pass through pressure equilibrium piston 6, move pressure equilibrium piston 6 along guide rod 7, and guide rod 7 controls the mobile side of pressure equilibrium piston 6
To.
Wherein, shock wave downstream static pressure hole 3 is one, and shock wave upstream static pressure hole 2 is multiple.Shock wave downstream static pressure hole 3 and swash
Wave upstream static pressure hole 2 can be directly arranged on connecting pipe 4, and it is quiet can also to connect shock wave downstream by shock wave downstream static pressure hole pipeline
Hole 3 and connecting pipe 4 are pressed, shock wave upstream static pressure hole 2 and connecting pipe 4 are connected by shock wave upstream static pressure hole pipeline, swashed at this time
Shock wave upstream static pressure hole diaphragm is set between multiple shock wave upstream static pressures hole 2 in the pipeline of wave upstream static pressure hole.
Wherein, shock wave downstream static pressure hole 3 is placed in the downstream for acting on the normal shock wave of the body surface, described to swash
Wave upstream static pressure hole 2 is placed in the upstream of the normal shock wave, and shock wave downstream static pressure hole 3 is located at the side of normal shock wave generation
Interlayer interferes control area downstream least significant end, and shock wave upstream static pressure hole 2 is located at the normal shock wave and the body surface
The distance of intersection is 1~2 times of the position of local boundary layer thickness δ.
Wherein, shock wave downstream static pressure hole 3 is circular hole, and to reduce stress concentration, and diameter is local boundary layer thickness δ.
Wherein, shock wave upstream static pressure hole 2 is circular hole, and to reduce stress concentration, and diameter is local boundary layer thickness δ's
2~3 times.
Wherein, the quantity in shock wave upstream static pressure hole 2 and diameter are determined by the design objective of aircraft or air intake duct, described to set
Counting index includes flight Mach number, buffeting Mach number, lift resistance ratio, total pressure recovery coefficient and inlet duct flow field distortion index.
Wherein, the section of connecting pipe 4 is circle, and the boundary layer that diameter is greater than or equal to boundary layer interference control area is flat
5 times of equal thickness, to ensure that the pressure in shock wave downstream can smoothly be transferred to shock wave upstream.
Wherein, when the body surface for being equipped with shock wave boundary layer interaction controller of the invention has air-flow process, but inflow
Shock wave upstream static pressure hole 2 is identical with the pressure of the air-flow in shock wave downstream static pressure hole 3, i.e., without pressure difference when, pressure equilibrium piston 6 is located at
The side of the corresponding connecting pipe 4 in shock wave upstream static pressure hole 2.
Wherein, telescopic element 5 is spring, and the coefficient of stiffiness of the spring is k,
Wherein S is 5 area of section of pressure equilibrium piston, and △ x is 5 moving distance of pressure equilibrium piston, △ p
For the pressure difference at shock wave downstream static pressure hole 3, shock wave upstream static pressure hole 2,
Δ p=p2-p1, p1For the pressure at shock wave upstream static pressure hole 2, p2For the pressure at shock wave downstream static pressure hole 3.
As shown in Fig. 2, application schematic diagram of the shock wave boundary layer interaction controller of the embodiment of the present invention on wing, wherein arrow
Head direction indicates direction of flow, and the region that dotted line surrounds is supersonic zone, and normal shock wave 22, which acts on, to be mounted on wing 21
Shock wave boundary layer interaction controller of the embodiment of the present invention, the shock wave downstream static pressure hole 3 positioned at 22 downstream of normal shock wave perceive under shock wave
Flow field pressure is swum, and downstream pressure is transferred to by shock wave upstream by connecting pipe 4, the upstream of connecting pipe 4 passes through on shock wave
Play pipe road is connected with 3 shock wave upstream static pressure holes 2 being isolated by shock wave upstream static pressure hole diaphragm, flows into shock wave downstream static pressure hole 3
Air-flow push the pressure equilibrium piston 6 in connecting pipe 4, pressure equilibrium piston 6 is along guide rod 7 to 2 side of shock wave upstream static pressure hole
To movement, it is connected to shock wave upstream static pressure hole 2 by connecting pipe 4 with shock wave downstream static pressure hole 3, realizes ventilation.In Fig. 2, swash
Wave downstream static pressure hole 3 is placed in the downstream for acting on the normal shock wave 22 on 21 surface of wing, and shock wave upstream static pressure hole 2 is placed in normal shock
The upstream of wave 22, shock wave downstream static pressure hole 3 are located at the boundary layer interference control area downstream least significant end of the generation of normal shock wave 22, shock wave
Upstream static pressure hole 2 is located at 2 times of the position that normal shock wave 22 is local boundary layer thickness δ at a distance from the intersection on 21 surface of wing
It sets；The distance between shock wave downstream static pressure hole 3 and shock wave upstream static pressure hole 2 are 10 times of local boundary layer thickness δ, make the side
Interlayer interference control area is located between shock wave downstream static pressure hole 3 and shock wave upstream static pressure hole 2；Shock wave downstream static pressure hole 3 is circle
Bore dia is local boundary layer thickness δ, and shock wave upstream static pressure hole 2 is circular hole, and diameter is 2 times of local boundary layer thickness δ, connection
The section of pipeline 4 is circle, and diameter is 6 times of the boundary layer average thickness that control area is interfered in boundary layer, and 3 shock wave upstreams are quiet
Hole 2 is pressed, weak, medium and intense shock wave is respectively corresponded, after shock wave generates, shock wave downstream static pressure hole 3 can pass flow field mesohigh
It is handed to shock wave upstream static pressure hole 2, under the action of pressure, pressure equilibrium piston 6 is mobile to 2 direction of shock wave upstream static pressure hole,
Mobile position is determined by the intensity of shock wave, and when shock wave is stronger, pressure equilibrium piston 6 is moved to 2 direction of shock wave upstream static pressure hole
Dynamic displacement is with regard to big, and when shock wave is weaker, pressure equilibrium piston 6 is to the mobile displacement in 2 direction of shock wave upstream static pressure hole with regard to small.
When weak shock, the only first shock wave upstream static pressure hole 2 in the right is ventilated in Fig. 2, medium is swashed when shock wave is increased to
When wave, the two shock wave upstream static pressure holes 2 in the right are ventilated in Fig. 2, and when intense shock wave, three shock wave upstream static pressure holes 2 are logical simultaneously in Fig. 2
Gas makes downstream high pressure be transferred to upstream low-pressure region, can play the role of weakening shock strength, to reduce shock wave boundary
Layer annoyance level；Also, under the action of pressure difference, shock wave downstream static pressure hole 3 can generate gettering effect, shock wave upstream static pressure hole
2 can generate air blowing effect, so as to improve the velocity profile in boundary layer, improve its ability for resisting shock wave sudden change of pressure surface,
Further reduce shock wave boundary layer interaction effect.
Embodiment 2
If Fig. 3 is application schematic diagram of shock wave boundary layer interaction of the embodiment of the present invention controller in supersonic inlet,
Wherein arrow direction indicates direction of flow, normal shock wave 32 and oblique shock wave 31 is produced in air intake duct 33, normal shock wave 32 acts on
The shock wave boundary layer interaction controller of the embodiment of the present invention being mounted in air intake duct arm face 34, the shock wave positioned at 32 downstream of normal shock wave
Downstream static pressure hole 3 perceives shock wave downstream flow field pressure, and downstream pressure is transferred to shock wave upstream by connecting pipe 4, is connected to
The upstream of pipeline 4 is connected by shock wave upstream line with 3 shock wave upstream static pressure holes 2 being isolated by shock wave upstream static pressure hole diaphragm
It connects, the air-flow for flowing into shock wave downstream static pressure hole 3 pushes the pressure equilibrium piston 6 in connecting pipe 4 quiet to shock wave upstream along guide rod 7
It presses 2 direction of hole mobile, is connected to shock wave upstream static pressure hole 2 by connecting pipe 4 with shock wave downstream static pressure hole 3, realizes ventilation.Figure
Shock wave downstream static pressure hole 3 is placed in the downstream for acting on the normal shock wave 32 on 33 surface of air intake duct in 3, and shock wave upstream static pressure hole 2 is put
It is placed in the upstream of normal shock wave 32, shock wave downstream static pressure hole 3 is located at the boundary layer interference control area downstream of the generation of normal shock wave 32 most
End, it is local boundary layer thickness δ that shock wave upstream static pressure hole 2, which is located at normal shock wave 32 at a distance from the intersection on 33 surface of air intake duct,
1 times of position；The distance between shock wave downstream static pressure hole 3 and shock wave upstream static pressure hole 2 are the 15 of local boundary layer thickness δ
Times, it is located at boundary layer interference control area between shock wave downstream static pressure hole 3 and shock wave upstream static pressure hole 2；Shock wave downstream
Static pressure hole 3 is circular hole, and a diameter of local boundary layer thickness δ, shock wave upstream static pressure hole 2 is circular hole, a diameter of locality boundary
3 times of thickness degree δ, the section of connecting pipe 4 are circle, the boundary layer average thickness of a diameter of boundary layer interference control area
5 times, 3 shock wave upstream static pressure holes respectively correspond weak, medium and intense shock wave, when normal shock wave generate after, shock wave downstream static pressure
Flow field mesohigh can be transferred to shock wave upstream static pressure hole 2 by hole 3, and under the action of pressure, pressure equilibrium piston 6 is to shock wave upstream
2 direction of static pressure hole is mobile, and the position of movement is determined by the intensity of shock wave, and when shock wave is stronger, pressure equilibrium piston 6 is to shock wave
The mobile displacement in 2 direction of upstream static pressure hole is with regard to big, and when shock wave is weaker, pressure equilibrium piston 6 is to 2 direction of shock wave upstream static pressure hole
Mobile displacement is with regard to small.
When weak shock, the only first shock wave upstream static pressure hole 2 in the right is ventilated in Fig. 3, medium is swashed when shock wave is increased to
When wave, the two shock wave upstream static pressure holes 2 in the right are ventilated in Fig. 3, and when intense shock wave, three shock wave upstream static pressure holes 2 are logical simultaneously in Fig. 3
Gas, downstream high pressure can be transferred to upstream low-pressure region, can play the role of weakening shock strength, to reduce shock wave boundary
Layer annoyance level；Also, under the action of pressure difference, shock wave downstream static pressure hole 3 can generate gettering effect, shock wave upstream static pressure hole
2 can generate air blowing effect, so as to improve the velocity profile in boundary layer, improve its ability for resisting shock wave sudden change of pressure surface,
Further reduce shock wave boundary layer interaction effect.
A shock wave boundary layer interaction controller of the invention has been used may be used also in Fig. 2 and Fig. 3 in practical applications
Multiple shock wave boundary layer interaction controllers of the present invention are arranged using continuous or discrete way along the spanwise direction vertical with flowing to,
It need to guarantee that the central axes of connecting pipe 4 are vertical with normal shock wave plane simultaneously, to reach Optimal Control effect.
Shock wave boundary layer interaction controller of the present invention is respectively in the upstream for the boundary layer interference region that normal shock wave is formed under
Trip design shock wave upstream static pressure hole 2 and shock wave downstream static pressure hole 3, and the connection of connecting pipe 4 is carried out, by the transmitting of pressure, subtract
Weak shock strength, and using the pressure difference of shock wave itself, downstream suction and upstream air blowing effect are realized, boundary is improved
The flow regime of layer, realizes the double control to shock wave and boundary layer, can more efficiently weaken shock wave boundary layer interaction
Effect reduces the ill-effect of shock wave boundary layer interaction.
And flexible member is driven using the pressure difference of shock wave itself in shock wave upstream design multiple shock wave upstream static pressures hole 2
Part and pressure equilibrium piston, realize the automatic control of shock wave boundary layer interaction, and simple and reliable for structure, do not need additional energy
Amount input, and the curvature without changing object plane, avoid the unfavorable interference to boundary layer.
Used herein a specific example illustrates the principle and implementation of the invention, and above embodiments are said
It is bright to be merely used to help understand method and its core concept of the invention；At the same time, for those skilled in the art, foundation
Thought of the invention, there will be changes in the specific implementation manner and application range.In conclusion the content of the present specification is not
It is interpreted as limitation of the present invention.
Claims (10)
1. a kind of shock wave boundary layer interaction controller, which is characterized in that the shock wave boundary layer interaction controller includes: communicating pipe
Road, the shock wave upstream static pressure hole for being set to the connecting pipe upstream along the flow direction of body surface air-flow are connected to set on described
The shock wave downstream static pressure hole of pipe downstream；
The connecting pipe is the silent pipeline in both ends, and shock wave downstream static pressure hole is swashed by the connecting pipe with described
The connection of wave upstream static pressure hole；
Be arranged in the connecting pipe identical with the connecting pipe section pressure equilibrium piston in section and one end with it is described
The connection of pressure equilibrium piston, the other end are fixed on the telescopic element of the inner surface of tube wall of the end of the connecting pipe；It is described to stretch
Contracting element and the pressure equilibrium piston are used to incude the air-flow entered from shock wave downstream static pressure hole, and by swashing to described
The mobile mode in wave upstream static pressure hole side balances at the aperture in shock wave upstream static pressure hole and shock wave downstream static pressure hole
Pressure；The connecting pipe airless when passing through the pressure equilibrium piston be located at shock wave upstream static pressure hole and the shock wave
In the connecting pipe between downstream static pressure hole.
2. shock wave boundary layer interaction controller according to claim 1, which is characterized in that vacantly set in the connecting pipe
Guide rod is set, the both ends of the guide rod are fixed on the tube wall of the connecting pipe, and the guide rod passes through the pressure equilibrium piston,
Move the pressure equilibrium piston along the guide rod.
3. shock wave boundary layer interaction controller according to claim 1, which is characterized in that shock wave downstream static pressure hole is
One, shock wave upstream static pressure hole is multiple.
4. shock wave boundary layer interaction controller according to claim 1, which is characterized in that put in shock wave downstream static pressure hole
It is placed in the downstream for acting on the normal shock wave of the body surface, shock wave upstream static pressure hole is placed in the upper of the normal shock wave
Trip, shock wave downstream static pressure hole is located at the boundary layer interference control area downstream least significant end of normal shock wave generation, described to swash
It is the 1~2 of local boundary layer thickness δ at a distance from the intersection of the body surface that wave upstream static pressure hole, which is located at the normal shock wave,
Position again.
5. shock wave boundary layer interaction controller according to claim 1, which is characterized in that shock wave downstream static pressure hole is
Circular hole, diameter are local boundary layer thickness δ.
6. shock wave boundary layer interaction controller according to claim 1, which is characterized in that shock wave upstream static pressure hole is
Circular hole, diameter are 2~3 times of local boundary layer thickness δ.
7. shock wave boundary layer interaction controller according to claim 1, which is characterized in that shock wave upstream static pressure hole
Quantity and diameter are determined that the design objective includes flight Mach number, buffets Mach by the design objective of aircraft or air intake duct
Number, lift resistance ratio, total pressure recovery coefficient and inlet duct flow field distortion index.
8. shock wave boundary layer interaction controller according to claim 1, which is characterized in that the section of the connecting pipe is
Circle, diameter are greater than or equal to 5 times of the boundary layer average thickness of boundary layer interference control area.
9. shock wave boundary layer interaction controller according to claim 1, which is characterized in that in no pressure difference, the pressure
Dummy piston is located at the side of the corresponding connecting pipe in shock wave upstream static pressure hole.
10. shock wave boundary layer interaction controller according to claim 1, which is characterized in that the telescopic element is spring,
The coefficient of stiffiness of the spring is k,
Wherein S is the pressure equilibrium piston cross-section area, and △ x is the moving distance of the pressure equilibrium piston,
△ p is shock wave downstream static pressure hole, the pressure difference at shock wave upstream static pressure hole, Δ p=p2-p1, p1For on the shock wave
Swim the pressure at static pressure hole, p2For the pressure at shock wave downstream static pressure hole.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112572810A (en) * | 2020-11-25 | 2021-03-30 | 北京空天技术研究所 | Air inlet passage boundary layer separation eliminating device and aircraft |
| CN112849388A (en) * | 2021-01-27 | 2021-05-28 | 北京理工大学 | Transonic buffeting control structure based on wing trailing edge vent hole |
| CN114263533A (en) * | 2021-12-20 | 2022-04-01 | 中国人民解放军国防科技大学 | Shock wave/boundary layer interference control device based on secondary flow circulation array and self-adaptive control method |
| CN114458448A (en) * | 2022-01-26 | 2022-05-10 | 南京航空航天大学 | Self-adaptive suction orifice plate for inhibiting shock wave boundary layer interference |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0719116A (en) * | 1993-06-30 | 1995-01-20 | Tech Res & Dev Inst Of Japan Def Agency | Supersonic air intake device |
| CN101033763A (en) * | 2007-03-13 | 2007-09-12 | 南京航空航天大学 | Controller for profile of shock wave |
| CN104149967A (en) * | 2014-08-07 | 2014-11-19 | 西北工业大学 | Low-Reynolds-number airfoil profile with cooperative fluidic control, and control method thereof |
| CN105173064A (en) * | 2015-09-22 | 2015-12-23 | 党会学 | Method for controlling transonic-speed buffering by tangential narrow-slit gas blowing and gas blowing device |
| CN106014684A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Combined flow control method and structure for improving SERN for TBCC |
| CN106122189A (en) * | 2016-07-18 | 2016-11-16 | 南京航空航天大学 | A kind of hypersonic precursor based on structure partial pressure differential disturbance turns twists control method |
-
2018
- 2018-11-21 CN CN201811389647.2A patent/CN109533356A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0719116A (en) * | 1993-06-30 | 1995-01-20 | Tech Res & Dev Inst Of Japan Def Agency | Supersonic air intake device |
| CN101033763A (en) * | 2007-03-13 | 2007-09-12 | 南京航空航天大学 | Controller for profile of shock wave |
| CN104149967A (en) * | 2014-08-07 | 2014-11-19 | 西北工业大学 | Low-Reynolds-number airfoil profile with cooperative fluidic control, and control method thereof |
| CN105173064A (en) * | 2015-09-22 | 2015-12-23 | 党会学 | Method for controlling transonic-speed buffering by tangential narrow-slit gas blowing and gas blowing device |
| CN106014684A (en) * | 2016-05-30 | 2016-10-12 | 西北工业大学 | Combined flow control method and structure for improving SERN for TBCC |
| CN106122189A (en) * | 2016-07-18 | 2016-11-16 | 南京航空航天大学 | A kind of hypersonic precursor based on structure partial pressure differential disturbance turns twists control method |
Non-Patent Citations (1)
| Title |
|---|
| 苏纬仪: "一种抑制激波-边界层相互作用的新型无源被动控制", 《空气动力学学报》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112572810A (en) * | 2020-11-25 | 2021-03-30 | 北京空天技术研究所 | Air inlet passage boundary layer separation eliminating device and aircraft |
| CN112849388A (en) * | 2021-01-27 | 2021-05-28 | 北京理工大学 | Transonic buffeting control structure based on wing trailing edge vent hole |
| CN114263533A (en) * | 2021-12-20 | 2022-04-01 | 中国人民解放军国防科技大学 | Shock wave/boundary layer interference control device based on secondary flow circulation array and self-adaptive control method |
| CN114458448A (en) * | 2022-01-26 | 2022-05-10 | 南京航空航天大学 | Self-adaptive suction orifice plate for inhibiting shock wave boundary layer interference |
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