CN106762149B - 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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- CN106762149B CN106762149B CN201710031306.7A CN201710031306A CN106762149B CN 106762149 B CN106762149 B CN 106762149B CN 201710031306 A CN201710031306 A CN 201710031306A CN 106762149 B CN106762149 B CN 106762149B
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- guide rail
- sprue
- flow passage
- inner flow
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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)
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- 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 are set in the inner flow passage of hypersonic inlet model, and the guide rail is parallel with the axis of the inner flow passage；Sprue is slidingly disposed at the guide rail；Under the action of the inner flow passage interior air-flow, the sprue in the inner flow passage can be slid into along the guide rail outside the inner flow passage.Above-mentioned hypersonic inlet self-starting energy force checking device, can not only control the forms of motion of sprue, but also can recycle sprue so that it can reuse, and ensure 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
It puts.
Background technology
Using supersonic combustion (super burn) punching engine as the Air-breathing hypersonic vehicle of power plant, for obtain compared with
Good performance, it is desirable that the hypersonic inlet as the capture of its air-flow, compression member has good self-starting ability, that is, works as
After the factor for causing air intake duct inoperative is eliminated, additional auxiliary starter measure is not needed to, 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, seriously affect flight safety.The inoperative risk of air intake duct is met in flight test in order to reduce,
The self-starting ability of hypersonic inlet is detected in the wind tunnel experiment of ground, becomes an important wind tunnel experiment test skill
Art.
In view of hypersonic wind tunnel continuous difficulty for controllably changing free stream Mach number in a blowing experiment, usually 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 longer, up to the second to tens of second-times, by actuation mechanisms such as traditional stepper motor, solenoid 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
It acts to assert foundation of the air intake duct with self-starting ability under similar conditions.
It is relatively low with its construction and operating cost using shock tunnel as the ground impulse type wing tunnel test apparatus of representative,
The method of operation is flexible, the advantages of can providing high-enthalpy flow for large scale air intake duct, is sent out in hypersonic aircraft research field
Wave important role.However, the experimental period of shock tunnel is of short duration, usually only millisecond is conventional superb to several ms magnitude
Air intake duct self-starting ability detection technique in velocity of sound wind-tunnel, can not directly " transplanting " 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, certain scholars force air inlet to be said by setting quick sliding valve at inlet throat
It is existing inoperative, and detect in shock tunnel the self-starting ability of air intake duct.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 versatility is limited.Also scholar passes through
Distance piece lower wall surface in air intake duct downstream is pre-placed lightweight tamper, and air intake duct is first forced inoperative, object to be occluded occur
Runner restores unimpeded after being blown out 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, the modes of emplacement of tamper is more random, and the movement law of tamper is indefinite,
The forms of motion of tamper cannot be controlled effectively, and tamper reuses after cannot also recycling.These factors result in blocking
The repeatability of object function and effect is poor.In addition to this, certain 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 during the experiment, opens air inlet
Road exports, and detects the self-starting ability of air intake duct.However, experiment needs to reinstall polyester fiber diaphragm this test device every time,
And certain puzzlement is brought to control mode and safety using pulse high-energy igniter.Therefore, using shock tunnel as generation
In the impulse type wind-tunnel of table, the experimental method needs of hypersonic inlet self-starting ability detection further improve.
Invention content
The object of the present invention is to provide a kind of hypersonic inlet self-starting energy force checking device, the hypersonic air inlets
Self-starting energy force checking device in road may be reused, and can force air intake duct not at the initial stage of the effective experimental period of shock tunnel
It starts, and the self-starting ability of hypersonic inlet is examined 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 are set in the inner flow passage of hypersonic inlet model, and the guide rail with it is described
The axis of inner flow passage is parallel；
Sprue is slidingly disposed at the guide rail；Under the action of the inner flow passage interior air-flow, in the inner flow passage
The sprue can be slid into outside the inner flow passage along the guide rail.
Relative to above-mentioned background technology, hypersonic inlet self-starting energy force checking device provided by the invention, guide rail
One end be located in the inner flow passage of hypersonic inlet model, and sprue is slidingly disposed at guide rail；It is 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, into
Air flue appearance is inoperative, and multiple periodic shock wave oscillation fluidised forms occurs；Meanwhile sprue is made in the inner flow passage air-flow of air intake duct
Under, moved along outlet of the guide rail to air intake duct in the form of quasi-one-dimensional；In effective experimental period of shock tunnel, sprue
It is blown out the outlet of air intake duct；The inner flow passage of air intake duct restores unimpeded, then can be in effective experimental period of the shock tunnel
Interior, can observation air intake duct be restored to starting state, detect the self-starting ability of air intake duct；After shock tunnel is tested, block up
Block is still located on guide rail, and the appearance of sprue is good, can be reused.The core of the present invention is, is 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 repeat
It uses, sprue is pushed into along guide rail in inner flow passage；So set, the forms of motion of sprue can be not only controlled, but also
Sprue can be recycled so that it can reuse, ensure that the repeatability of sprue ponding process.
Preferably, the inner flow passage and the guide rail are horizontally disposed.
Preferably,
The hypersonic inlet model is specially two dimensional inlet, and the cross section of the inner flow passage is rectangular, institute
It is specially rectangle sprue to state sprue；Alternatively,
The specially interior rotatable air intake duct of the hypersonic inlet model, and the circular in cross-section of the inner flow passage,
The sprue is specially circular cone sprue.
Preferably, the congestion degree of the inner flow passage is between 50%~80%.
Preferably, the guide rail be specially can be to the hollow guide rail that is used as skin backing pressure probe, and the guide rail
The other end be equipped with to the pressure sensor that detects the skin backing pressure in the inner flow passage.
Preferably, the guide rail is equipped with to buffer when the sprue slides into when institute outside the inner flow passage along the guide rail
The bolster for the impact force having.
Preferably, the end seat to the fixation bolster and the guide rail is further included, the end seat is in vertical direction
Column is equipped with, and the end of the column is fixed by bracket base.
Preferably, the sprue is equipped with the through-hole passed through for the guide rail, and the inner wall smooth of the through-hole.
Preferably, the end seat is adjustable relative to the position of the column.
Preferably, the number of the guide rail and the through-hole is two, and the geomery of two guide rails is identical.
Description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, to embodiment or will show below
There is attached drawing needed in technology description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of invention, for those of ordinary skill in the art, without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
The signal of a kind 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 the schematic diagram that two dimensional inlet is not provided 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- stents, 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-
Pedestal, 106- buffer units, 107- vertical racks, 108- pressure sensors.
Specific embodiment
Below in conjunction with the attached drawing in the embodiment of the present invention, the technical solution in the embodiment of the present invention is carried out clear, complete
Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, those of ordinary skill in the art are obtained every other without making creative work
Embodiment shall fall within the protection scope of the present invention.
In order to which those skilled in the art is made to more fully understand the present invention program, below in conjunction with the accompanying drawings and it is embodied
The present invention is described in further detail for mode.
It please refers to Fig.1, a kind of hypersonic inlet self-starting that Fig. 2 and Fig. 3, Fig. 1 are provided by the embodiment of the present invention
The schematic diagram of energy force checking device；Fig. 2 is the schematic diagram that two dimensional inlet is not provided 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 supplied.
A kind of hypersonic inlet self-starting energy force checking device provided by the invention mainly includes guide rail and sprue.
One end of guide rail is set in the inner flow passage of hypersonic inlet model, and guide rail is parallel with the axis of inner flow passage；And sprue
It is slidingly disposed at guide rail；Under the action of inner flow passage interior air-flow, the sprue in inner flow passage can slide into institute along guide rail
It states outside inner flow passage.
Hypersonic inlet model can be two dimensional inlet or Sidewall-compression inlet, in three-dimensional it is rotatable into
Air flue, the inner flow passage of hypersonic inlet model include compression section and distance piece in air intake duct.The rigidity of guide rail should be good,
Outer diameter is smaller, the smooth outer surface of guide rail, preferably straight guide rail, and the cross section of guide rail can be round or circular ring shape.Sprue
Rigid sprue for the smaller geometric shape rule of quality；The shape of sprue is 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；It, can be according to the duration of congestion and height of shock tunnel requirement of experiment for the quality and geometric shape of sprue
The inner flow passage geometric format of Supersonic Inlet model is chosen.
Before starting hypersonic inlet self-starting ability test experience in shock tunnel, sprue is located in inner flow passage,
Sprue causes the blocking of inner flow passage at this time, and air intake duct appearance is inoperative, and multiple periodic shock wave oscillation fluidised forms occurs；Together
When, sprue moves under the inner flow passage airflow function of air intake duct along outlet of the guide rail to air intake duct in the form of quasi-one-dimensional；
In effective experimental period of shock tunnel, sprue is blown out the outlet of air intake duct；The inner flow passage of air intake duct restores unimpeded, then may be used
In effective experimental period of the shock tunnel, observation air intake duct can be restored to starting state, detect air intake duct from
Kinetic force；After shock tunnel is tested, sprue is still located on guide rail, and the appearance of sprue is good, can be reused.
The core of the present invention is, using the direction of motion of guide rail limitation sprue, and then can be to air intake duct self-starting energy
Power is detected；And the sprue after detecting may be reused, and sprue is pushed into along guide rail in inner flow passage；So
Setting, can not only control the forms of motion of sprue, but also can recycle sprue so that it can reuse, ensure that sprue
The repeatability of ponding process.According to different test needs, inner flow passage can be horizontally disposed with guide rail, can also be by
Runner is inclined relative to horizontal certain angle with guide rail and sets.
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 attached 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；The identical rod iron of length that solid guide rail 2 is two outer diameter 2mm, two solid guide rails 2 be parallel into
It the inner flow passage axis of air flue and is symmetrical arranged, the exhibitions of two solid guide rails 2 is to spacing 20mm；Rectangle sprue 3 is rectangular shape,
Geometric dimension is 6mm (flow direction) × 6mm (transverse direction) × 50mm (open up to), quality 2.05g, in the windward side of rectangle sprue 3
Heart line both sides are symmetrical arranged two internal diameter 2.5mm, the through-hole of spacing 20mm, and 3 via through holes of rectangle sprue penetrate solid guide rail 2, and
It 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 for blunt wedge-
The assembly of rectangular parallelepiped form, for fixing and supporting solid guide rail 2；Cushion pad 5 is the rectangle silica gel pad of 2mm thickness, tightly
Against guiderail base 4；Stent 6 is threaded rod, for fixing and supporting guiderail base 4；Bracket base 7 is rectangular shape, is used
In fixing bracket 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 blocks；Two dimensional inlet 1 occurs inoperative, and multiple periodic 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 the form of quasi-one-dimensional going out to two dimensional inlet 1
Mouth is mobile；In effective experimental period of the shock tunnel, rectangle sprue 3 is blown out the outlet of two dimensional inlet 1；Binary into
The inner flow passage of air flue 1 restores unimpeded, then can observe 1 energy of two dimensional inlet in effective experimental period of the shock tunnel
It is no to be restored to starting state, detect the self-starting ability of two dimensional inlet 1；After the shock tunnel experiment, rectangle sprue 3
On solid guide rail 2, the 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 described above.
Figure of description 2 is the schematic diagram that two dimensional inlet is not provided in Fig. 1, gives solid guide rail 2 He in more detail
The geometric position of rectangle sprue 3, the rectangle sprue 3 are equipped with two through-holes passed through for described two solid guide rails 2
101, and the inner wall smooth of described two through-holes 101.In specific embodiment, the internal diameter of two through-holes 101 is all 2.5mm, two
The exhibition of through-hole 101 to spacing be 20mm.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 attached drawing 1, the method used in the two is similar, 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 pedestal 105, buffer unit 106, vertical rack
107 and pressure sensor 108.
Wherein, circle of the outlet of interior rotatable air intake duct 102 for internal diameter 35mm；Hollow guide rail 103 is that an outer diameter is
5mm, the steel pipe that internal diameter is 3mm, also serve as the use of skin backing pressure probe；Circular cone sprue 104 is 20 degree of semi-cone angle, base diameter 24mm's
Circular cone, quality 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, and can be slided along hollow guide rail 103, rotatable air intake duct in 104 vertex distance of circular cone sprue
102 outlet 45mm；Hollow guide rail pedestal 105 is the assembly of blunt wedge-rectangular parallelepiped form, for fixing and supporting hollow guide rail
103, and connect with vertical rack 107；Buffer unit 106 is the silica gel pad of 2mm thickness, is close to hollow guide rail pedestal 105；It is perpendicular
Threaded rod of the straight bracket 107 for two equal lengths, for fixing and supporting hollow guide rail pedestal 105；Pressure sensor 108 is pacified
Bottom loaded on hollow guide rail pedestal 105, the pressure-sensing device of pressure sensor 108 is with also serving as the sky that skin backing pressure probe uses
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 the main distinction of the two is, hollow guide rail 103 also serves as skin backing pressure
Probe uses, and pressure sensor 108 can be inside in the experimentation of rotatable 102 self-starting ability of air intake duct detection, in monitoring
The variation of rotatable 102 inner flow passage skin backing pressure of air intake duct.By above-mentioned as can be seen that in the first of the effective experimental period of shock tunnel
Phase, sprue are located in inner flow passage, and then form the blocking to inner flow passage；It according to actual needs, can be by the congestion degree of inner flow passage
Control is between 50%~80%, to be tested.Certainly, according to actual needs, the congestion degree of inner flow passage can also be it
His numberical range.
In Figure of description 3, guide rail is specially can be to the hollow guide rail 103 that is used as skin backing pressure probe, and leads
The other end of rail is equipped with the pressure sensor 108 to detect the skin backing pressure in inner flow passage.And for given by Figure of description 1
Embodiment, guide rail may be hollow guide rail 103, and function is identical with effect.
The hypersonic inlet self-starting energy force checking device of the present invention fixes bolster and guide rail using end seat,
End seat is equipped with column in the vertical direction, and the end of column is fixed by bracket base.Pass through Figure of description 1 to attached drawing 3
As can be seen that in Figure of description 1 and Figure of description 2, guiderail base 4 is end seat, and cushion pad 5 is bolster, is propped up
Frame 6 is column；In Figure of description 3, hollow guide rail pedestal 105 is end seat, and buffer unit is bolster, vertical rack
107 be 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, sprue is equipped 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 sets the through-hole 101 there are two inner wall smooth, two solid guide rails 2
Each through-hole 101 is each passed through, realizes slip of the rectangle sprue 3 relative to solid guide rail 2；The shape ruler of two solid guide rails 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 attached 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 perforative through-holes 101 on 3 windward side of rectangle sprue, penetrate that length is identical to be parallel in hypersonic inlet model
Two solid guide rails 2 of runner axisymmetrical setting.
The hypersonic inlet self-starting energy force checking device of the present invention is installed on hypersonic inlet model
Downstream, and opposite with the outlet of hypersonic inlet model, and make solid guide rail 2 and rectangle sprue 3 be in it is hypersonic into
In the inner flow passage of air flue model, it is ensured that guiderail base 4 and the outlet of hypersonic inlet model keep suitable distance, 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 into along solid guide rail 2 at cushion pad 5；Adjust 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 high ultrasound
The inner flow passage of fast air intake duct blocks, and hypersonic inlet appearance is inoperative, and multiple periodic shock wave oscillation fluidised forms occurs,
Meanwhile under the action of hypersonic inlet inner flow passage air-flow, rectangle sprue 3 is along the guide rail, with quasi- motion in one dimension
Form is moved to the outlet of hypersonic inlet model.
In the effective experimental period of shock tunnel, rectangle sprue 3 is blown out the inner flow passage of hypersonic inlet, high ultrasound
After the inner flow passage of fast air intake duct restores unimpeded, then hypersonic air inlet can be observed in effective experimental period of shock tunnel
Can road be restored to starting state, detect the self-starting ability of hypersonic inlet.
After shock tunnel is tested, rectangle sprue 3 is rested near the cushion pad 5, and the appearance of rectangle sprue 3 is good
It is good, it may be reused.
The hypersonic inlet self-starting energy force checking device of the present invention, it is simple in structure, it is reusable；When directly into
When row hypersonic inlet flow field is shot, the characteristics of motion of sprue can be additionally obtained, for the school of fluid structurecoupling problem
It tests.
Hypersonic inlet self-starting energy force checking device provided by the present invention is described in detail above.This
Specific case is applied in text to be expounded the principle of the present invention and embodiment, the explanation of above example is only intended to
It facilitates the understanding of the method and its core concept of the invention.It should be pointed out that for those skilled in the art,
Without departing from the principles of the invention, can also to the present invention some improvement and modification can also be carried out, these improvement and modification are also fallen
Enter in the protection domain of the claims in the present invention.
Claims (8)
1. a kind of hypersonic inlet self-starting energy force checking device, which is characterized in that including：
Guide rail, one end of the guide rail are set in the inner flow passage of hypersonic inlet model, and the guide rail and the interior stream
The axis in road is parallel；
Sprue is slidingly disposed at the guide rail；Under the action of the inner flow passage interior air-flow, the institute in the inner flow passage
Stating sprue can slide into along the guide rail outside the inner flow passage；
The guide rail is specially can be to the hollow guide rail that is used as skin backing pressure probe, and the other end of the guide rail is equipped with
To detect the pressure sensor of the skin backing pressure in the inner flow passage；
The inner flow passage is horizontally disposed with the guide rail.
2. hypersonic inlet self-starting energy force checking device according to claim 1, which is characterized 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；Alternatively,
The specially interior rotatable air intake duct of the hypersonic inlet model, and the circular in cross-section of the inner flow passage, it is described
Sprue is specially circular cone sprue.
3. hypersonic inlet self-starting energy force checking device according to claim 2, which is characterized in that the interior stream
The congestion degree in road is between 50%~80%.
4. hypersonic inlet self-starting energy force checking device according to claim 1, which is characterized in that the guide rail
Equipped with buffering the bolster of the possessed impact force when the sprue is slid into along the guide rail outside the inner flow passage.
5. hypersonic inlet self-starting energy force checking device according to claim 4, which is characterized in that further include use
With the end seat of the fixation bolster and the guide rail, the end seat is equipped with column in the vertical direction, and the column
End is fixed by bracket base.
6. hypersonic inlet self-starting energy force checking device according to claim 4, which is characterized in that the sprue
Equipped with the through-hole passed through for the guide rail, and the inner wall smooth of the through-hole.
7. hypersonic inlet self-starting energy force checking device according to claim 5, which is characterized in that the end seat
Position relative to the column is adjustable.
8. hypersonic inlet self-starting energy force checking device according to claim 6, which is characterized in that the guide rail
Number with the through-hole is two, and the geomery of two guide rails is identical.
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| CN107830985B (en) * | 2017-10-11 | 2019-06-28 | 中国科学院力学研究所 | A kind of air intake duct determines congestion degree self-starting experimental rig |
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| 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 |
| CN111272432B (en) * | 2020-03-13 | 2021-07-02 | 合肥工业大学 | Air inlet pulsation back pressure generation test device based on cam and jet flow mechanism |
| CN115326350B (en) * | 2022-10-14 | 2022-12-27 | 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 test equivalent simulation device and application method thereof |
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| DE10253579A1 (en) * | 2002-11-15 | 2004-06-03 | Eads Astrium Gmbh | Air intake for engines and their manufacture |
| CN102507203B (en) * | 2011-11-03 | 2014-01-15 | 中国科学院力学研究所 | Shockwave wind tunnel-based self-starting test device for hypersonic air inlet channel |
| CN103149009B (en) * | 2013-02-22 | 2015-10-21 | 中国人民解放军国防科学技术大学 | Supersonic speed distance piece flow tunnel testing device |
| CN104899418B (en) * | 2015-04-24 | 2016-07-13 | 南京航空航天大学 | The inoperative frequency of oscillation Forecasting Methodology of mixed pressure formula supersonic speed, hypersonic inlet |
| CN105157948B (en) * | 2015-09-14 | 2016-08-17 | 南京航空航天大学 | A kind of flow testing system being applicable to supersonic speed/hypersonic runner and method of testing |
| CN106121825B (en) * | 2016-07-28 | 2018-03-13 | 西安航天动力试验技术研究所 | Engine inlets blanking cover and its open and close system |
| CN206448877U (en) * | 2017-01-17 | 2017-08-29 | 中国科学技术大学 | A kind of hypersonic inlet self-starting energy force checking device |
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