CN106762149A - A kind of hypersonic inlet self-starting energy force checking device - Google Patents
A kind of hypersonic inlet self-starting energy force checking device Download PDFInfo
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- CN106762149A CN106762149A CN201710031306.7A CN201710031306A CN106762149A CN 106762149 A CN106762149 A CN 106762149A CN 201710031306 A CN201710031306 A CN 201710031306A CN 106762149 A CN106762149 A CN 106762149A
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- guide rail
- sprue
- flow passage
- inner flow
- hypersonic inlet
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- 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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of hypersonic inlet self-starting energy force checking device, including：Guide rail, one end of the guide rail in the inner flow passage of hypersonic inlet model, and the guide rail and the inner flow passage diameter parallel；Sprue, is slidingly disposed at the guide rail；In the presence of the inner flow passage interior air-flow, the sprue in the inner flow passage can be along the slide to the inner flow passage outside.Above-mentioned hypersonic inlet self-starting energy force checking device, can not only control the forms of motion of sprue, and can reclaim sprue, reuse it, it is ensured that the repeatability of sprue ponding process.
Description
Technical field
The present invention relates to hydrodynamics technology field, more particularly to a kind of hypersonic inlet self-starting ability detection dress
Put.
Background technology
Air-breathing hypersonic vehicle with supersonic combustion (super burn) punching engine as power set, for obtain compared with
Good performance, it is desirable to which the hypersonic inlet as the capture of its air-flow, compression member has good self-starting ability, that is, work as
After causing the inoperative factor of air intake duct to eliminate, it is not necessary to which extra auxiliary starter measure, air intake duct can also revert to starting
State (is restarted).However, free stream Mach number is too low, the angle of attack is excessive, the excessively high flight of air intake duct back-pressure and Manipulative Factors, all may be used
Air intake duct can be caused inoperative, flight safety is had a strong impact on.Meet with flight test the inoperative risk of air intake duct to reduce,
The self-starting ability of hypersonic inlet is detected in the wind tunnel experiment of ground, skill is tested as an important wind tunnel experiment
Art.
In view of hypersonic wind tunnel continuous difficulty for controllably changing free stream Mach number in a blowing experiment, generally exists
Under conditions of fixed free stream Mach number, air intake duct self-starting ability test experience is carried out.During the experiment of conventional hypersonic wind tunnel
Between it is more long, up to the second to tens of second-times, by actuation mechanisms such as traditional stepper motor, magnetic valves, carry out air intake duct from
Kinetic force test experience is relatively easy.There is scholar in conventional hypersonic wind tunnel, by the lip cover of mobile air intake duct, continuously change
Become the angle of attack of air intake duct, the choke plug cone of mobile air intake duct downstream simulation air intake duct back-pressure, in air intake duct downstream injection high pressure gas
The measures such as body segment stream, first force air intake duct inoperative, then remove the inoperative factor of corresponding air intake duct, and air intake duct is recurred
Act to assert that air intake duct has the foundation of self-starting ability under similar conditions.
Ground impulse type wing tunnel test apparatus with shock tunnel as representative, it is relatively low with its construction and operating cost,
The method of operation flexibly, can provide the advantage of high-enthalpy flow for large scale air intake duct, in hypersonic aircraft research field hair
Wave important effect.However, the experimental period of shock tunnel is of short duration, generally only millisecond is conventional superb to several ms magnitude
Air intake duct self-starting ability detection technique in velocity of sound wind-tunnel, it is impossible to which direct " transplanting " is applied to shock tunnel.Therefore, shock wave wind
Hole faces the challenge of air intake duct self-starting ability test experience method.
In the prior art, some scholars force air inlet to be said by setting quick sliding valve at inlet throat
It is existing inoperative, and the self-starting ability of air intake duct is detected in shock tunnel.However, this quick sliding valve, not only its skill
Art difficulty is big, and also needs to specially be designed for specific air intake duct configuration, and its versatility is limited.Also scholar passes through
Distance piece lower wall surface in air intake duct downstream is pre-placed lightweight tamper, first forces air intake duct inoperative, thing to be occluded occur
Runner recovers unimpeded after being blown air intake duct, then detects the self-starting ability of air intake duct.Although this detection method is easy,
It is that the geometry of lightweight tamper is irregular, and the modes of emplacement of tamper is more random, and the movement law of tamper is indefinite,
The forms of motion of tamper can not be controlled effectively, and tamper is reused after cannot also reclaiming.These factors, result in blocking
Thing action effect it is repeatable poor.In addition, some scholars close air intake port using installation polyester fiber diaphragm in advance,
First force air intake duct inoperative；Then, polyester fiber diaphragm is ruptured using pulse high-energy igniter in experimentation, opens air inlet
Road is exported, and detects the self-starting ability of air intake duct.However, this test device is tested every time to need to reinstall polyester fiber diaphragm,
And bring certain puzzlement to control mode and security using pulse high-energy igniter.Therefore, with shock tunnel as generation
In the impulse type wind-tunnel of table, the experimental technique of hypersonic inlet self-starting ability detection needs further to improve.
The content of the invention
It is an object of the invention to provide a kind of hypersonic inlet self-starting energy force checking device, the hypersonic air inlet
Road self-starting energy force checking device can be reused, and can force air intake duct not at the initial stage of the effective experimental period of shock tunnel
Start, and the self-starting ability of hypersonic inlet is checked in the effective experimental period of shock tunnel.
To achieve the above object, the present invention provides a kind of hypersonic inlet self-starting energy force checking device, including：
Guide rail, one end of the guide rail in the inner flow passage of hypersonic inlet model, and the guide rail with it is described
The diameter parallel of inner flow passage；
Sprue, is slidingly disposed at the guide rail；In the presence of the inner flow passage interior air-flow, in the inner flow passage
The sprue can be along the slide to the inner flow passage outside.
Relative to the hypersonic inlet self-starting energy force checking device that above-mentioned background technology, the present invention are provided, guide rail
One end be located in the inner flow passage of hypersonic inlet model, and sprue is slidingly disposed at guide rail；Opened in shock tunnel
Before beginning hypersonic inlet self-starting ability test experience, sprue is located in inner flow passage, and sprue causes the blocking of inner flow passage, enters
Air flue appearance is inoperative, and multiple periodically shock wave oscillation fluidised forms occurs；Meanwhile, sprue is made in the inner flow passage air-flow of air intake duct
Under, moved to the outlet of air intake duct in quasi-one-dimensional form along guide rail；In effective experimental period of shock tunnel, sprue
It is blown the outlet of air intake duct；The inner flow passage of air intake duct recovers unimpeded, then can be in effective experimental period of the shock tunnel
Interior, can observation air intake duct return to starting state, detect the self-starting ability of air intake duct；After shock tunnel experiment terminates, block up
Block is still located on guide rail, and the outward appearance of sprue is good, can reuse.Core of the invention is to be limited using guide rail
The direction of motion of sprue, and then air intake duct self-starting ability can be detected；And the sprue after detecting can be repeated
Use, sprue is pushed into inner flow passage along guide rail；It is arranged such, can not only controls the forms of motion of sprue, and
Sprue can be reclaimed, it is reused, it is ensured that the repeatability of sprue ponding process.
Preferably, the inner flow passage is horizontally disposed with the guide rail.
Preferably,
The hypersonic inlet model is specially two dimensional inlet, and the cross section of the inner flow passage is rectangular, institute
State sprue specially rectangle sprue；Or,
The hypersonic inlet model is specially interior rotatable air intake duct, and the inner flow passage circular in cross-section,
The sprue is specially circular cone sprue.
Preferably, the congestion degree of the inner flow passage is between 50%~80%.
Preferably, the guide rail can specially use the hollow guide rail used as skin backing pressure probe, and the guide rail
The other end be provided with to detect the pressure sensor of the skin backing pressure in the inner flow passage.
Preferably, the guide rail is provided with to buffer when the sprue is along when institute outside the slide to the inner flow passage
The bolster of the impulsive force having.
Preferably, also including being used to the end seat for fixing the bolster and the guide rail, the end seat is in vertical direction
Column is provided with, and the end of the column is fixed by bracket base.
Preferably, the sprue is provided with the through hole passed through for the guide rail, and the through hole inner wall smooth.
Preferably, the end seat is adjustable relative to the position of the column.
Preferably, the guide rail is two with the number of the through hole, and the geomery of two guide rails is identical.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
The accompanying drawing to be used needed for having technology description is briefly described, it should be apparent that, drawings in the following description are only this
Inventive embodiment, for those of ordinary skill in the art, on the premise of not paying creative work, can also basis
The accompanying drawing of offer obtains other accompanying drawings.
A kind of signal of hypersonic inlet self-starting energy force checking device that Fig. 1 is provided by the embodiment of the present invention
Figure；
Fig. 2 is to be not provided with the schematic diagram of two dimensional inlet in Fig. 1；
The signal of another hypersonic inlet self-starting energy force checking device that Fig. 3 is provided by the embodiment of the present invention
Figure.
Wherein：
In Figure of description 1：1- two dimensional inlets, 2- solid guide rails, 3- rectangles sprue, 4- guiderail bases, 5- cushion pads
Block, 6- supports, 7- bracket bases；
In Figure of description 2：2- solid guide rails, 3- rectangles sprue, 101- through holes；
In Figure of description 3：Rotatable air intake duct, 103- hollow guide rails, 104- circular cones sprue, 105- hollow guide rails in 102-
Base, 106- buffer units, 107- vertical racks, 108- pressure sensors.
Specific embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation is described, it is clear that described embodiment is only a part of embodiment of the invention, rather than whole embodiments.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
In order that those skilled in the art more fully understand the present invention program, below in conjunction with the accompanying drawings and specific implementation
The present invention is described in further detail for mode.
Refer to Fig. 1, Fig. 2 and Fig. 3, a kind of hypersonic inlet self-starting that Fig. 1 is provided by the embodiment of the present invention
The schematic diagram of energy force checking device；Fig. 2 is to be not provided with the schematic diagram of two dimensional inlet in Fig. 1；Fig. 3 is carried by the embodiment of the present invention
The schematic diagram of another hypersonic inlet self-starting energy force checking device for supplying.
A kind of hypersonic inlet self-starting energy force checking device that the present invention is provided, mainly includes guide rail and sprue.
One end of guide rail in the inner flow passage of hypersonic inlet model, and guide rail and inner flow passage diameter parallel；And sprue
It is slidingly disposed at guide rail；In the presence of inner flow passage interior air-flow, the sprue in inner flow passage can be along slide to institute
State outside inner flow passage.
Hypersonic inlet model can be two dimensional inlet, or Sidewall-compression inlet, it is three-dimensional in it is rotatable enter
Air flue, the inner flow passage of hypersonic inlet model includes compression section and distance piece in air intake duct.The rigidity of guide rail should be good, its
External diameter is smaller, the smooth outer surface of guide rail, preferably straight guide rail, and the cross section of guide rail can be circular or annular.Sprue
It is the rigid sprue of the less geometric shape rule of quality；Sprue is shaped as square, cuboid, triangular prism, cylinder, circle
Cone or spherosome；The cross sectional dimensions of sprue, span-wise length are both less than the cross section of hypersonic inlet model inner flow passage
Size, span-wise length；For the quality and geometric shape of sprue, can be according to the duration of congestion of shock tunnel requirement of experiment and height
The inner flow passage geometric format of Supersonic Inlet model is chosen.
Before beginning hypersonic inlet self-starting ability test experience in shock tunnel, sprue is located in inner flow passage,
Now sprue causes the blocking of inner flow passage, and air intake duct appearance is inoperative, and multiple periodically shock wave oscillation fluidised forms occurs；Together
When, sprue is moved in quasi-one-dimensional form along guide rail under the inner flow passage airflow function of air intake duct to the outlet of air intake duct；
In effective experimental period of shock tunnel, sprue is blown the outlet of air intake duct；The inner flow passage of air intake duct recovers unimpeded, then may be used
In effective experimental period of the shock tunnel, can observation air intake duct return to starting state, detection air intake duct from
Kinetic force；After shock tunnel experiment terminates, sprue is still located on guide rail, and the outward appearance of sprue is good, can reuse.
Core of the invention is that the direction of motion of sprue is limited using guide rail, and then can be to air intake duct self-starting energy
Power is detected；And the sprue after detecting can be reused, and sprue is pushed into inner flow passage along guide rail；So
Set, can not only control the forms of motion of sprue, and sprue can be reclaimed, reuse it, it is ensured that sprue
The repeatability of ponding process.According to different test needs, inner flow passage can be horizontally disposed with guide rail, it is also possible to will be interior
Runner is inclined relative to horizontal certain angle and sets with guide rail.
A kind of hypersonic inlet self-starting energy force checking device that Figure of description 1 is provided by the embodiment of the present invention
Schematic diagram, another hypersonic inlet self-starting energy force checking device that accompanying drawing 3 is provided by the embodiment of the present invention
Schematic diagram.
In Figure of description 1, the inner flow passage cross section of two dimensional inlet 1 is rectangle, and the exhibition of two dimensional inlet 1 is to width
54mm, is highly 10mm；Solid guide rail 2 is the length identical rod irons of two external diameter 2mm, and two solid guide rails 2 are parallel to entering
The inner flow passage axis of air flue and it is symmetrical arranged, two exhibitions of solid guide rail 2 are to spacing 20mm；Rectangle sprue 3 is rectangular shape,
Physical dimension is 6mm (flow direction) × 6mm (transverse direction) × 50mm (open up to), and quality is 2.05g, in the windward side of rectangle sprue 3
Heart line both sides are symmetrical arranged two internal diameter 2.5mm, and the through hole of spacing 20mm, the via through holes of rectangle sprue 3 penetrate solid guide rail 2, and
Can be slided along solid guide rail 2, the outlet 40mm of the windward side of rectangle sprue 3 apart from air intake duct 1.Guiderail base 4 be blunt wedge-
The assembly of rectangular parallelepiped form, for fixing and supporting solid guide rail 2；Cushion pad 5 is the thick rectangle silica gel pads of 2mm, tightly
Close to guiderail base 4；Support 6 is threaded rod, for fixed and supporting guide base 4；Bracket base 7 is rectangular shape, is used
In fixed support 6.
Its operation principle is that, at the initial stage of the effective experimental period of shock tunnel, rectangle sprue 3 causes two dimensional inlet 1
Inner flow passage is blocked；Two dimensional inlet 1 occurs inoperative, and multiple periodically shock wave oscillation fluidised forms occurs；Meanwhile, rectangle sprue
3 under the inner flow passage airflow function of two dimensional inlet 1, along solid guide rail 2 in quasi-one-dimensional form going out to two dimensional inlet 1
Mouth is mobile；In effective experimental period of the shock tunnel, rectangle sprue 3 is blown the outlet of two dimensional inlet 1；Binary is entered
The inner flow passage of air flue 1 recovers unimpeded, then can observe the energy of two dimensional inlet 1 in effective experimental period of the shock tunnel
It is no to return to starting state, detect the self-starting ability of two dimensional inlet 1；After the shock tunnel experiment terminates, rectangle sprue 3
On solid guide rail 2, the outward appearance of rectangle sprue 3 is good, can reuse.The above-mentioned embodiment rectangular for inner flow passage,
Certainly, the specific size of above-mentioned all parts can be decided according to the actual requirements with position relationship, however it is not limited to mentioned above.
Figure of description 2 is to be not provided with the schematic diagram of two dimensional inlet in Fig. 1, and the He of solid guide rail 2 is given in more detail
The geometric position of rectangle sprue 3, the rectangle sprue 3 is provided with two through holes passed through for described two solid guide rails 2
101, and described two through holes 101 inner wall smooth.In specific embodiment, two internal diameters of through hole 101 are all 2.5mm, two
The exhibition of through hole 101 is 20mm to spacing.Operation principle：Rectangle sprue 3 penetrates two solid guide rails 2, square by two through holes 101
Shape sprue 3 can be slided along two solid guide rails 2.
In Figure of description 3, compared with the embodiment of accompanying drawing 1, the method used by both is similar to, and the air intake duct of application is by two
First air intake duct has changed interior rotatable air intake duct into.The test device of hypersonic interior rotatable air intake duct self-starting ability detection includes：
Interior rotatable air intake duct 102, hollow guide rail 103, circular cone sprue 104, hollow guide rail base 105, buffer unit 106, vertical rack
107 and pressure sensor 108.
Wherein, the outlet of interior rotatable air intake duct 102 is the circle of internal diameter 35mm；Hollow guide rail 103 is for an external diameter
5mm, internal diameter are the steel pipe of 3mm, also serve as skin backing pressure probe and use；Circular cone sprue 104 is 20 degree of semi-cone angle, base diameter 24mm's
Circular cone, its quality is 5g；The through hole of internal diameter 5.2mm is set at the axis of circular cone sprue 104, and circular cone sprue 104 is through described logical
Hole penetrates hollow guide rail 103, it is possible to slided along hollow guide rail 103, rotatable air intake duct in the vertex distance of circular cone sprue 104
102 outlet 45mm；Hollow guide rail base 105 is the assembly of blunt wedge-rectangular parallelepiped form, for fixing and supporting hollow guide rail
103, and be connected with vertical rack 107；Buffer unit 106 is the thick silica gel pads of 2mm, is close to hollow guide rail base 105；It is perpendicular
Straight bracket 107 is two threaded rods of equal length, for fixing and supporting hollow guide rail base 105；Pressure sensor 108 is pacified
Bottom loaded on hollow guide rail base 105, the pressure-sensing device of pressure sensor 108 with also serve as the sky that skin backing pressure probe is used
The endoporus of heart guide rail 103 is connected, for measuring skin backing pressure.
The operation principle of the embodiment is similar to the above, and both differs primarily in that, hollow guide rail 103 also serves as skin backing pressure
Probe is used, and pressure sensor 108 can be in the experimentation of the self-starting ability of interior rotatable air intake duct 102 detection, in monitoring
The change of the inner flow passage skin backing pressure of rotatable air intake duct 102.By above-mentioned as can be seen that in the first of the effective experimental period of shock tunnel
Phase, sprue is located in inner flow passage, and then forms the blocking to inner flow passage；According to actual needs, can be by the congestion degree of inner flow passage
Control between 50%~80%, to be tested.Certainly, according to actual needs, the congestion degree of inner flow passage can also be it
His number range.
In Figure of description 3, guide rail can specially use the hollow guide rail 103 used as skin backing pressure probe, and lead
The other end of rail is provided with to detect the pressure sensor 108 of the skin backing pressure in inner flow passage.And for given by Figure of description 1
Embodiment, its guide rail can also be hollow guide rail 103, and its function is identical with effect.
Hypersonic inlet self-starting energy force checking device of the invention, bolster and guide rail are fixed using end seat,
End seat in the vertical direction is provided with column, and the end of column is fixed by bracket base.By Figure of description 1 to accompanying drawing 3
As can be seen that in Figure of description 1 and Figure of description 2, guiderail base 4 is end seat, cushion pad 5 is bolster, branch
Frame 6 is column；In Figure of description 3, hollow guide rail base 105 is end seat, and buffer unit is bolster, vertical rack
107 are column.Certainly, in order to realize the fixation to guide rail, other devices can also be used, however it is not limited to described herein.
In order to realize that sprue is slidingly disposed at guide rail, be provided with sprue with the through hole passed through for guide rail by the present invention, and
The inner wall smooth of through hole；Such as Figure of description 2, rectangle sprue 3 is provided with two through holes of inner wall smooth 101, two solid guide rails 2
Each through hole 101 is each passed through, slip of the rectangle sprue 3 relative to solid guide rail 2 is realized；Two shape chis of solid guide rail 2
It is very little identical.In order to improve the widely applicable property of hypersonic inlet self-starting energy force checking device of the present invention, end seat relative to
The position of column is adjustable, and then adjusts the height and position of guide rail.
For the embodiment given by Figure of description 1 and accompanying drawing 2, experimentation is as follows：
Before shock tunnel experiment, quality, cross sectional dimensions and the suitable rectangle sprue 3 of span-wise length should be selected first,
Through two through holes 101 for running through on the windward side of rectangle sprue 3, length identical is penetrated parallel in hypersonic inlet model
Two solid guide rails 2 that runner axisymmetrical is set.
Hypersonic inlet self-starting energy force checking device of the invention is installed on hypersonic inlet model
Downstream, and relative with the outlet of hypersonic inlet model, and make solid guide rail 2 and rectangle sprue 3 be in it is hypersonic enter
In the inner flow passage of air flue model, it is ensured that guiderail base 4 keeps suitable distance with the outlet of hypersonic inlet model, it is to avoid
Guiderail base 4 blocks the outlet of hypersonic inlet model.
Then guiderail base 4 is adjusted, makes the center line of solid guide rail 2 and rectangle sprue 3 and hypersonic inlet model
Inner flow passage axis coaxle, it is ensured that rectangle sprue 3 can be slid at cushion pad 5 along solid guide rail 2；Regulation rectangle sprue
3 position on solid guide rail 2, it is ensured that rectangle sprue 3 is suitable with the distance of hypersonic inlet mold exit.
After shock tunnel experiment is started, at the initial stage of the effective experimental period of shock tunnel, rectangle sprue 3 causes ultrasound high
The inner flow passage of fast air intake duct is blocked, and hypersonic inlet appearance is inoperative, and multiple periodically shock wave oscillation fluidised forms occurs,
Meanwhile, in the presence of hypersonic inlet inner flow passage air-flow, rectangle sprue 3 along the guide rail, with quasi- motion in one dimension
Form, moves to the outlet of hypersonic inlet model.
In the effective experimental period of shock tunnel, rectangle sprue 3 is blown the inner flow passage of hypersonic inlet, ultrasound high
After the inner flow passage of fast air intake duct recovers unimpeded, then hypersonic air inlet can be observed in effective experimental period of shock tunnel
Can road return to starting state, detect the self-starting ability of hypersonic inlet.
After shock tunnel experiment terminates, rectangle sprue 3 is rested near the cushion pad 5, and the outward appearance of rectangle sprue 3 is good
It is good, can reuse.
Hypersonic inlet self-starting energy force checking device of the invention, simple structure is reusable；When directly entering
When row hypersonic inlet flow field shoots, the characteristics of motion of sprue can be additionally obtained, for the school of fluid structurecoupling problem
Test.
Hypersonic inlet self-starting energy force checking device provided by the present invention is described in detail above.This
Apply specific case in text to be set forth principle of the invention and implementation method, the explanation of above example is only intended to
Help understands the method for the present invention and its core concept.It should be pointed out that for those skilled in the art,
Without departing from the principles of the invention, some improvement and modification can also be carried out to the present invention, these are improved and modification also falls
Enter in the protection domain of the claims in the present invention.
Claims (10)
1. a kind of hypersonic inlet self-starting energy force checking device, it is characterised in that including：
Guide rail, one end of the guide rail is in the inner flow passage of hypersonic inlet model, and the guide rail and the interior stream
The diameter parallel in road；
Sprue, is slidingly disposed at the guide rail；In the presence of the inner flow passage interior air-flow, the institute in the inner flow passage
State sprue can be along the slide to the inner flow passage outside.
2. hypersonic inlet self-starting energy force checking device according to claim 1, it is characterised in that the interior stream
Road is horizontally disposed with the guide rail.
3. hypersonic inlet self-starting energy force checking device according to claim 1, it is characterised in that
The hypersonic inlet model is specially two dimensional inlet, and the cross section of the inner flow passage is rectangular, described stifled
Block is specially rectangle sprue；Or,
The hypersonic inlet model is specially interior rotatable air intake duct, and the inner flow passage circular in cross-section, it is described
Sprue is specially circular cone sprue.
4. hypersonic inlet self-starting energy force checking device according to claim 3, it is characterised in that the interior stream
The congestion degree in road is between 50%~80%.
5. the hypersonic inlet self-starting energy force checking device according to Claims 1 to 4 any one, its feature exists
In the guide rail can be specially provided with the hollow guide rail used as skin backing pressure probe, and the other end of the guide rail
It is used to detect the pressure sensor of the skin backing pressure in the inner flow passage.
6. hypersonic inlet self-starting energy force checking device according to claim 5, it is characterised in that the guide rail
It is provided with to buffer the bolster of the impulsive force having when outside the sprue is along the slide to the inner flow passage.
7. hypersonic inlet self-starting energy force checking device according to claim 6, it is characterised in that also including use
With the fixed bolster and the end seat of the guide rail, the end seat in the vertical direction is provided with column, and the column
End is fixed by bracket base.
8. hypersonic inlet self-starting energy force checking device according to claim 6, it is characterised in that the sprue
Be provided with the through hole passed through for the guide rail, and the through hole inner wall smooth.
9. hypersonic inlet self-starting energy force checking device according to claim 7, it is characterised in that the end seat
Position relative to the column is adjustable.
10. hypersonic inlet self-starting energy force checking device according to claim 8, it is characterised in that described to lead
Rail is two with the number of the through hole, and the geomery of two guide rails is identical.
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| CN107830985A (en) * | 2017-10-11 | 2018-03-23 | 中国科学院力学研究所 | A kind of air intake duct determines congestion degree self-starting experimental rig |
| CN109946037A (en) * | 2019-04-25 | 2019-06-28 | 中国空气动力研究与发展中心高速空气动力研究所 | Simulate the sprue mobile device and application of the variation of support interferences amount |
| CN110057535A (en) * | 2019-05-27 | 2019-07-26 | 中国空气动力研究与发展中心 | Shock tunnel judges the wall surface silk thread Method of flow visualization and system of intake duct starting |
| CN111272432A (en) * | 2020-03-13 | 2020-06-12 | 合肥工业大学 | Air inlet pulsation back pressure generation test device based on cam and jet flow mechanism |
| CN115326350A (en) * | 2022-10-14 | 2022-11-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Motor-driven wind tunnel jet flow test equivalent simulation device and application method thereof |
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