CN103149009A - Supersonic isolating section wind tunnel test device - Google Patents
Supersonic isolating section wind tunnel test device Download PDFInfo
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- CN103149009A CN103149009A CN2013100570119A CN201310057011A CN103149009A CN 103149009 A CN103149009 A CN 103149009A CN 2013100570119 A CN2013100570119 A CN 2013100570119A CN 201310057011 A CN201310057011 A CN 201310057011A CN 103149009 A CN103149009 A CN 103149009A
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Abstract
The invention discloses a supersonic isolating section wind tunnel test device, which comprises an air collector which is used for collecting air. The outlet of the air collector is connected with a stabilizing section which is used for stabilizing the air flow field of the air output by the air collector. The outlet of the stabilizing section is connected with a supersonic spray pipe section which is used for accelerating air flow rate. The outlet of the supersonic spray pipe section is connected with an isolating-section-structured experiment section which is used for simulating the isolating section. Air flow in the isolating-section-structured experiment section is exhausted through a diffusion section which is connected with the outlet of the isolating-section-structured experiment section. Since the air collector, the stabilizing section and the supersonic spray pipe section are sequentially arranged in the front of the isolating-section-structured experiment section and the isolating-section-structured experiment section is of a structure with a bend, the influence of an incoming compressed wall surface boundary layer at the upstream of the isolating section is simulated; and by adjusting lip angle, internal channel height and tail throttling degree, the flow mechanisms of the isolating section under different working conditions are simulated.
Description
Technical field
The present invention relates to aloof punching engine field, especially, relate to a kind of flow tunnel testing device of the wind tunnel test for aloof punching engine distance piece.
Background technology
Aircraft can be divided into by flying speed: subsonic flight device (Mach number＜1), transonic speed aircraft (0.8＜Mach number＜1.2), supersonic aircraft (1＜Mach number＜5), hypersonic aircraft (Mach number〉5) etc.Raising along with flying speed, conventional engine can't be competent at the demand of hypersonic aircraft, at this moment people have proposed the concept of scramjet engine, namely at engine interior oxidant gas and fuel in supersonic condition undertissue's burning and from the ejection of aircraft afterbody, thereby produce huge thrust.
As the major impetus device of air suction type hypersonic aircraft, scramjet engine and correlation technique thereof have become the frontline technology position that global various countries researchist competitively fights for.Studies show that, if reach Mach 5 when above when flying speed. still adopt traditional inferior burning ramjet, the air-flow that enters engine is decelerated to subsonic speed, the high stagnation pressure of high stagnation temperature of air-flow will bring very big difficulty to Heat Preservation of material; High static temperature fails to be convened for lack of a quorum and causes firing chamber internal combustion product to occur from solution simultaneously, will absorb a large amount of heat energy from solution, causes the burning capacity release efficiency low, and engine is difficult to produce positive thrust.Should allow in this case the air-flow that enters the firing chamber still keep supersonic speed, and in the burning of supersonic speed condition undertissue, Here it is scramjet engine.For rocket engine, a large advantage of air suction type hypersonic aircraft is exactly self to need not to carry oxygenant, but utilizes the oxygen tissue burning in atmosphere.What the air intake duct in scramjet engine was completed is exactly " air-breathing " this work.As the admission gear of scramjet engine, the effect of air intake duct is to catch the air-flow of certain flow and to its supercharging of slowing down, then flow to the firing chamber, to guarantee tissue burning smoothly in the firing chamber.
As indicated above, be different from traditional inferior burning ramjet, the air that Scramjet Inlet catches, slows down supercharging, then offer the firing chamber still is supersonic speed.Owing to being operated under hypersonic condition, so usually the air intake duct of scramjet engine is called hypersonic inlet.The quality of hypersonic inlet performance is all vital for the normal operation of scramjet engine and whole aircraft.The good hypersonic inlet of design should have following feature: lightweight construction, compression efficiency is high, resistance is little, the air-flow that offers the firing chamber has high-quality (referring to that mainly the air-flow uniformity coefficient is high), can satisfy wide Mach number flight requires (several characteristics that namely can have the front in certain range of Mach numbers), has good firing chamber matching properties (under the different duty in firing chamber, air intake duct can not be subjected to the impact in downstream).
The composition of scramjet engine has comprised air intake duct, distance piece, firing chamber and jet pipe.The effect of air intake duct is collect gas and gas is carried out precompression, makes gas deceleration, supercharging.The firing chamber is the place of gas and fuel generation supersonic combustion, and there is High Temperature High Pressure in its inside, and the chemical energy of fuel is converted into the mechanical energy of gas, ejection aircraft after gas accelerates through jet pipe afterwards and produce larger thrust.Distance piece is one section gas passage between air intake duct and firing chamber, although its structure is simple, plays an important role.Very complicated flow phenomenon occurs after entering air intake duct in gas in distance piece, comprise shock wave, shock wave string, Shock/Boundary-Layer interaction, boundary-layer separation etc.Its effect is the high temperature and high pressure environment of isolation in the firing chamber, prevents that the air intake duct obstruction and the engine that cause thus from not starting, and distance piece provides that gas further slows down, the place of supercharging in addition, is conducive to gas and fuel and fully mixes, burns.
On structure, distance piece is one section pipeline of accepting air intake duct and firing chamber, but on aerodynamic angle, it is the place of ultrasonic gas generation Complex Phenomena in Vertical Bell Jar.Distance piece performance quality directly has influence on the performance of scramjet engine, so the research work of distance piece, especially experimental study enjoy the concern of researcher and model department.The experimental study of carrying out distance piece needs corresponding testing equipment essentially.From existing documents and materials, the scheme of design isolated section testing equipment is divided into two classes usually: a class is independent distance piece model of design and it is put in large-scale conventional wind tunnel test cabin, comes gas velocity and the flow phenomenon of distance piece inside in the Reality simulation situation by existing conventional wind-tunnel; Another kind of distance piece parts identical with existing conventional test chamber two ends flange size that are one of design, and these parts are replaced original conventional test chamber, thus consist of an integral body with other parts of wind-tunnel and then for experimental measurement.But all there is certain deficiency in this two schemes: the advantage of first kind scheme is that modelling is simple, cost is low, but distance piece is an independent model, it breaks away from other assembly of air intake duct, and the internal flow of its simulation and truth exist than big difference; The advantage of Equations of The Second Kind scheme is can simulate to a certain extent the air intake duct of distance piece upstream to the impact of distance piece by existing wind-tunnel, comparatively approaching with truth, but in this case, the geometric shape of distance piece is restricted, and can't carry out the distance piece experimental study of a large amount of multi-states, multi-configuration.
Summary of the invention
The object of the invention is to provide a kind of supersonic speed distance piece flow tunnel testing device, with solve existing distance piece wind tunnel test can't real simulation the impact of upstream air intake duct and the technical matters that operating mode is limited, test efficiency is low of distance piece simulation.
For achieving the above object, the technical solution used in the present invention is as follows:
A kind of supersonic speed distance piece flow tunnel testing device, comprise: the gas collector that is used for collecting gas, the outlet of gas collector connects the stable section of the air velocity distribution that is used for stabilizing gas gatherer output gas, the outlet of stable section is connected with for the supersonic nozzle section of accelerating air-flow velocity, the outlet of supersonic nozzle section is connected with the experimental section for the distance piece configuration of simulation distance piece, and the air-flow warp in the experimental section of distance piece configuration is discharged with the diffuser that the outlet of the experimental section of distance piece configuration is connected.
further, the experimental section of distance piece configuration comprises: Slab under the distance piece that the main body of the pipeline configuration of turning back for band and geometric parameter are adjustable, under distance piece, Slab comprises dull and stereotyped reaching and the dull and stereotyped lip plate that is rotationally connected, the lip plate is provided with the first rotary rail assembly, the corresponding second rotary rail assembly that is provided with on flat board, the rotation center of the first rotary rail assembly and the second rotary rail assembly the lip plate around with faceted pebble that flat board is connected on, the lip plate is fixed to installing plate through lip plate studdle, flat board is fixed to installing plate through adjusting screw(rod), installing plate is used for being fixedly connected with and sealing the bottom of main body with the bottom of main body.
Further, the side wall surface of main body and/or upper wall surface are provided with the view window for detection of the Experiments of Optics data, and view window adopts optical glass to make.
Further, the throttling degree regulating device of regulating afterbody throttling degree is sent out in the rear end of main body.
Further, throttling degree regulating device comprises screw rod, and an end of screw rod stretches out the outside of main body, and the other end of screw rod is positioned at the inside of main body and is connected with choke block, and choke block is positioned at dull and stereotyped top and relative with flat board.
Further, throttling degree regulating device also comprises the cover plate that is provided with inner chamber, the upper wall surface of cover plate and main body is sealedly and fixedly connected, the threaded hole cooperation of the inner cavity top of screw rod through being positioned at cover plate extends into inner chamber, the end that screw rod is positioned at inner chamber is penetrated with a card extender that is provided with through hole, and choke block is fixedly connected with card extender, and the internal face of the through hole on card extender is shiny surface, by rotary screw, under the situation of not rotating card extender and choke block and then regulate the height of choke block.
Further, the experimental section of gas collector, stable section, supersonic nozzle section and distance piece configuration all connects by flange seal between any two, and the height of flange is adjustable.
Further, stable section comprises to be stablized leading portion and stablizes back segment, stablize between leading portion and stable back segment and be connected by flange seal, and before stable, intersegmental part is provided with for reducing the filter screen from the pulse characteristic of the gas of gas collector, and the internal face of stablize back segment is provided with for the pressure transducer of measurement gas air pressure pops one's head in.
Further, gas collector is provided with the butterfly valve that opens and closes for controlling wind-tunnel in the porch.
Further, the internal face of supersonic nozzle section is the plane in the horizontal direction, for being the curved surface that first shrinks the trend distribution of expanding afterwards, this curved surface is adopt based on cubic spline curve configuration center line Mach number and adopt the characteristic line method design in vertical direction.
The present invention has following beneficial effect:
Supersonic speed distance piece flow tunnel testing device of the present invention, by the place ahead at the experimental section of distance piece configuration set gradually gas collector, stable section and, the supersonic nozzle section, and the structure that the experimental section of distance piece configuration adopts band to turn back, thereby simulated the impact in wall boundary layer of the precursor compression of distance piece upstream, improved the experimental study level to the distance piece that is applied to aloof punching engine, and in the present invention, the supersonic nozzle section can be replaced according to testing requirements, thereby simulates the test figure of distance piece under different air-flow velocities.
Further, the experimental section of the distance piece configuration that adopts in the present invention is the adjustable structure of parameter, the angle of pitch by regulating the lip plate, dull and stereotyped height, and the height of choke block can realize lip angle, the inner passage height to distance piece, the adjusting of afterbody throttling degree, thereby flow mechanism more convenient, efficient and that carry out economically distance piece different operating modes (different distance piece entrance, exit conditions) under is studied.
Except purpose described above, feature and advantage, the present invention also has other purpose, feature and advantage.The below is with reference to figure, and the present invention is further detailed explanation.
Description of drawings
The accompanying drawing that consists of the application's a part is used to provide a further understanding of the present invention, and illustrative examples of the present invention and explanation thereof are used for explaining the present invention, do not consist of improper restriction of the present invention.In the accompanying drawings:
Fig. 1 is the structural representation of the supersonic speed distance piece flow tunnel testing device of the preferred embodiment of the present invention;
Fig. 2 is the schematic top plan view of Fig. 1;
Fig. 3 is another structural representation of the supersonic speed distance piece flow tunnel testing device of the preferred embodiment of the present invention;
Fig. 4 is the structural representation of body Model under distance piece in the preferred embodiment of the present invention;
Fig. 5 is the perspective view of the supersonic speed distance piece flow tunnel testing device of the preferred embodiment of the present invention;
Fig. 6 is the local enlarged diagram of regional A in Fig. 5; And
Fig. 7 is the structural representation of throttling degree regulating device in the preferred embodiment of the present invention.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are elaborated, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
see figures.1.and.2, the preferred embodiments of the present invention provide a kind of supersonic speed distance piece flow tunnel testing device, comprise: the gas collector 10 that is used for collecting gas, the outlet of gas collector 10 connects the stable section 20 of the air velocity distribution that is used for stabilizing gas gatherer 10 output gases, the outlet of stable section 20 is connected with for the supersonic nozzle section 30 of accelerating air-flow velocity, the outlet of supersonic nozzle section 30 is connected with the experimental section 40 for the distance piece configuration of simulation distance piece, the diffuser 50 that air-flow warp in the experimental section 40 of distance piece configuration is connected with the outlet of the experimental section 40 of distance piece configuration is discharged.Wherein the experimental section 40 of distance piece configuration refers to have the experimental section of similar distance piece internal geometrical characteristics form.Flow tunnel testing device of the present invention has been constructed the upstream components of the air intake duct structure of simulation distance piece upstream due to the experimental section 40 that adopts gas collector 10, stable section 20, supersonic nozzle section 30 and distance piece configuration, thereby makes the experimental section 40 of distance piece configuration can simulate more realistically the wind-tunnel flow mechanism of distance piece.
preferably, with reference to Fig. 3 and Fig. 4, the experimental section 40 of distance piece configuration comprises: Slab 42 under the distance piece that the main body 41 of the pipeline configuration of turning back for band and geometric parameter are adjustable, it is in order to simulate air intake duct and the turnover of isolating between the road in aloof punching engine that main body 41 adopts the pipeline configuration of band turnover, make main body 41 closer to truth, under distance piece, Slab 42 comprises that dull and stereotyped 422 reach and the dull and stereotyped 422 lip plates 421 that are rotationally connected, preferably, lip plate 421 is provided with the first rotary rail assembly 421a, on dull and stereotyped 422, the end adjacent with lip plate 421 is provided with the second rotary rail assembly 422a, the rotation center of the first rotary rail assembly 421a and the second rotary rail assembly 422a critically designs and processes at seam crossing, namely design dull and stereotyped 422 with faceted pebble that lip plate 421 is connected on.By coordinating of the first rotary rail assembly 421a and the second rotary rail assembly 422a, lip plate 421 can be around rotating with dull and stereotyped 422 faceted pebbles that are connected up and down, guarantees not occur when rotation between lip plate 421 and flat board 422 crack.Lip plate 421 is fixed on installing plate 423 through lip plate studdle 424, and dull and stereotyped 422 are fixed to installing plate 423 through adjusting screw(rod) 425, and installing plate 423 is used for being fixedly connected with and sealing the bottom of main body 41 with the bottom of main body 41.Lip plate studdle 424 and adjusting screw(rod) 425 are all fixing with installing plate 423 through nut 426.Like this, can realize control to the angle of pitch of lip plate 421 by the height of regulating lip plate studdle 424, enter the size at the lip angle of distance piece inside with control, the situation that causes distance piece entrance lip angle to change when changing with simulated flight device flight attitude; Can realize dull and stereotyped 422 height is regulated by the height of regulating adjusting screw(rod) 425, and dull and stereotyped 422 with the upper wall surface 412 of main body 41 and be positioned at the common structure that consists of similar distance piece internal gas flow passages of side wall surface 411 of both sides, therefore can regulate the height of distance piece internal gas flow passage by regulating dull and stereotyped 422 height.
Preferably, with reference to Fig. 5 and Fig. 6, afterbody in main body 41 also is provided with a throttling degree regulating device 43, this throttling degree regulating device 43 comprises screw rod 431, one end of screw rod 431 stretches out the outside of main body 41, the other end of screw rod 431 is positioned at the inside of main body 41 and is connected with choke block 432, and choke block 432 is positioned at dull and stereotyped 422 top and relative with dull and stereotyped 422.As shown in Figure 6, choke block 432 is pushed the inside of main body 41, relative to the air-flow in the middle of flowing through is formed throttling with the flat board 422 of Slab under distance piece 42.The height of gas passage is H, and the height that choke block 432 enters this gas passage is h, and throttling degree Δ H/h is continuous variable under the adjusting of screw rod 431, can satisfy the demand that under different condition, experimental study arranges the throttling degree.
with reference to Fig. 7, in specific embodiment, throttling degree regulating device 43 comprises the cover plate 433 that is provided with inner chamber 433a, the bottom of cover plate 433 is provided with seal groove 433c, seal groove 433c is sealedly and fixedly connected by the upper wall surface 412 of packing washer and main body 41, the threaded hole 433b at the inner chamber 433a top of screw rod 431 through being positioned at cover plate 433 coordinates and extends into inner chamber 433a, the end that screw rod 431 is positioned at inner chamber 433a is penetrated with a card extender 434, as shown in Figure 7, card extender 434 is provided with a through hole 434a, and the internal face of through hole 434a is shiny surface, screw rod 431 runs through through hole 434a, the bottom head of screw rod 431 is greater than through hole 434a, choke block 432 is fixedly connected with by a plurality of lock-screws 435 with card extender 434.the assembling mode of throttle regulator 43 is as follows: first card extender 434 is inserted in the bottom of screw rod 431, then with lock-screw 435, that choke block 432 is fixing with card extender 434, again choke block 432 and card extender 434 are pushed the inner chamber 433a of cover plate 433, the threaded hole 433b that screw rod 431 screws on cover plate 433, due to screw rod 431 only with cover plate 433 on threaded hole 433b interlock, by rotary screw 431, screw rod 431 with the cooperation of threaded hole 433b under will rotatablely move and be converted to the up and down rectilinear motion, the card extender 434 and the choke block 432 that are positioned at screw rod 431 bottoms can not rotate along with the rotation of screw rod 431, only can do the up and down rectilinear motion under the thrust of screw rod 431, upper wall surface 412 sealings of cover plate 433 by place packing washer and main body 41 in seal groove 433c, guaranteed the impermeability requirement of whole wind tunnel experiment.
Simulated the inner structure of distance piece due to Slab under distance piece 42, and geometric parameter is adjustable, specifically comprises the adjusting of lip angle, gas passage and tail gas throttling degree, thereby under different operating modes, carrying out efficiently wind tunnel experiment provides convenience at a high speed; On the other hand, detect optical data in process of the test in order to facilitate, further, offer be used to the watch window that high-quality optical glass is installed on two side wall surfaces 411 of main body 41, due in actual applications, the pipeline of main body 41 for turning back, for example in a preferred embodiment, the place that turns back of main body 41 is from the horizontal by 16 angles of spending, and optical glass is difficult to be processed into the profile of turning back with 16 degree, therefore the height of two side wall surfaces 411 of main body 41 will be higher than upper wall surface 412.Preferably, also offer on the upper wall surface 412 of main body 41 for the installation window that the difference in functionality upper plate is installed, but the high organic glass upper plate of degree thoroughly as mounting strap wall pressure hole on upper wall surface 412, this organic glass upper plate has 16 degree turns back, and can be used in simultaneously the pressure distribution of measuring the distance piece interior flow field.In addition, if upper plate is replaced with high-quality optical glass, can be used for seeing through laser, and then carry out the fine structure image that NPLS (Nano-tracer Planar Laser Scattering, the scattering of nanometer spike planar laser) tested and obtained the distance piece flow field.
In specific embodiment, with reference to Fig. 1, Fig. 3 and Fig. 5, the experimental section 40 of distance piece configuration and diffuser 50 are arranged on horizontal stand 60, the experimental section 40 of gas collector 10, stable section 20, supersonic nozzle section 30 and distance piece configuration all connects by flange seal between any two, and all be fixed on by trimming rack 62 at the flange between gas collector 10, stable section 20 and supersonic nozzle section 30 and be positioned on horizontal stand 60 on the tilted supporter 61 with inclined ramp, supersonic nozzle section 30 is fixed on horizontal stand 60 by trimming rack 62.
Preferably, gas collector 10 is the pipeline of one section circle side of turning, and entrance 11 is circular, and outlet 12 be that square, square size is consistent with the flange in downstream, and entrance 11 is with dish valves 13.Gas collector 10 Main Functions are to collect gas with the source of the gas as downstream flow, can control the operation of whole wind-tunnel simultaneously and close.
Preferably, stable section 20 comprises to be stablized leading portion 21 and stablizes back segment 22, stablize between leading portion 21 and stable back segment 22 and be connected by flange seal, and stable leading portion 21 inside are provided with for reducing the filter screen from the pulse characteristic of the gas of gas collector 10, the internal face of stablizing back segment 22 is provided with for the pressure transducer of measurement gas air pressure pops one's head in, and enters nozzle section stagnation pressure size before to detect gas.Although two sections stable section length are not long, for air current flow, gas is tended towards stability in the motion of inside.
Preferably, supersonic nozzle section 30 is two-dimensional ultrasound speed jet pipe, and internal face is the plane in the horizontal direction, in vertical direction for being the curved surface 31 that first shrinks the trend distribution of expanding afterwards.Curved surface 31 is for having adopted characteristic curve method for designing based on cubic spline curve configuration axis Mach Number Distribution to design.Gas enters supersonic nozzle section 30 when inner, first shrinks because in vertical direction upper and lower wall is the trend of expanding afterwards, and gas constantly is accelerated to supersonic speed and sprays this section from subsonic speed.The key that determines the gas spouting velocity is the ratio that this section goes out open height and throat (middle, as to be retracted to minimum place), and after the ejection of decision gas, the factor of the homogeneity in flow field, stability etc. is the method for designing of upper and lower wall.The upper and lower wall that adopts this method to design can guarantee that the flow field after the gas ejection is very even, actual Mach number (characterizing the dimensionless physical quantity of gas velocity) reaches design Mach number 99%.And just can produce the air-flow of friction speed by changing different nozzle sections, to satisfy the test needs.In addition, gas forms boundary layer and experimental section motion downstream and development at the nozzle section wall, and precursor compressing surface boundary layer that can Scramjet Inlet that is virtually reality like reality makes this testing table more near truth.
The workflow of supersonic speed distance piece flow tunnel testing device of the present invention is as follows:
A. gas enters test air tunnel through gas collector 10;
B. flowing through when stablize leading portion 21 and stablizing back segment 22 through the gas of gas collector 10 output, the pressure of gas, speed, the isoparametric pulsation of density reduce, and gas is more stable, is conducive to produce stable flow process for experimental study;
C. the gas through stable section 20 outputs enters supersonic nozzle section 30, because having, the inwall upper lower wall surface in vertical direction of supersonic nozzle section 30 first shrinks the profile of expanding afterwards, gas acutely accelerates to supersonic speed when flowing through this section, and in concrete test, this supersonic nozzle section 30 can be replaced, and makes air-flow accelerate to different speed by replacing nozzle section;
D. the supersonic flow after accelerating enters the experimental section 40 of distance piece configuration, because this section adopts the distance piece configuration, so supersonic flow can occur in the passage of this section and flow field structure like real scramjet engine distance piece inner classes;
E. can obtain the distance piece flow field of different qualities by regulating lip angle, distance piece internal channel height, afterbody throttling degree, to satisfy the demand of experimental study;
F. last gas is discharged through the diffuser 50 of wind-tunnel afterbody.
Supersonic speed distance piece flow tunnel testing device of the present invention, set gradually gas collector 10, stable section 20 and supersonic nozzle section 30 by the place ahead at the experimental section 40 of distance piece configuration, and the structure that the experimental section 40 of distance piece configuration adopts band to turn back, thereby simulated the impact in wall boundary layer of the precursor compression of distance piece upstream, improved the experimental study level to the distance piece that is applied to aloof punching engine, and in the present invention, supersonic nozzle section 30 can be replaced according to testing requirements, thereby simulates the test figure of distance piece under different air-flow velocities.Further, the experimental section 40 of the distance piece configuration that adopts in the present invention is the adjustable structure of parameter, the angle of pitch by regulating lip plate 421, dull and stereotyped 422 height, and the height of choke block 432 can realize lip angle, the inner passage height to distance piece, the adjusting of afterbody throttling degree, thereby more convenient, efficient and carry out economically the flow mechanism research of distance piece under different operating modes.
The above is only the preferred embodiments of the present invention, is not limited to the present invention, and for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (10)
1. supersonic speed distance piece flow tunnel testing device, it is characterized in that, comprise: the gas collector (10) that is used for collecting gas, the outlet of described gas collector (10) connects and is used for stablizing the stable section (20) that described gas collector (10) is exported the air velocity distribution of gas, the outlet of described stable section (20) is connected with for the supersonic nozzle section (30) of accelerating air-flow velocity, the outlet of described supersonic nozzle section (30) is connected with the experimental section (40) for the distance piece configuration of simulation distance piece, air-flow warp in the experimental section of described distance piece configuration (40) is discharged with the diffuser (50) that the outlet of the experimental section (40) of described distance piece configuration is connected.
2. supersonic speed distance piece flow tunnel testing device according to claim 1 is characterized in that:
the experimental section of described distance piece configuration (40) comprising: Slab (42) under the distance piece that the main body (41) of the pipeline configuration of turning back for band and geometric parameter are adjustable, Slab under described distance piece (42) comprises flat board (422) and the lip plate (421) that is rotationally connected with described flat board (422), described lip plate (421) is provided with the first rotary rail assembly (421a), the upper corresponding second rotary rail assembly (422a) that is provided with of described flat board (422), the rotation center of described rotary rail assembly (421a) and described the second rotary rail assembly (422a) described lip plate (421) around with faceted pebble that described flat board (422) is connected on, described lip plate (421) is fixed to installing plate (423) through lip plate studdle (424), described flat board (422) is fixed to installing plate (423) through adjusting screw(rod) (425), described installing plate (423) is used for being fixedly connected with and sealing with the bottom of described main body (41) bottom of described main body (41).
3. supersonic speed distance piece flow tunnel testing device according to claim 2 is characterized in that:
The side wall surface (411) of described main body (41) and/or upper wall surface (412) are provided with the view window for detection of the Experiments of Optics data, and described view window adopts optical glass to make.
4. supersonic speed distance piece flow tunnel testing device according to claim 2 is characterized in that:
The rear end of described main body (41) is provided with the throttling degree regulating device (43) of regulating afterbody throttling degree.
5. supersonic speed distance piece flow tunnel testing device according to claim 4 is characterized in that:
Described throttling degree regulating device (43) comprises screw rod (431), one end of described screw rod (431) stretches out the outside of described main body (41), the other end of described screw rod (431) is positioned at the inside of described main body (41) and is connected with choke block (432), and described choke block (432) is positioned at the top of described flat board (422) and relative with described flat board (422).
6. supersonic speed distance piece flow tunnel testing device according to claim 5 is characterized in that:
described throttling degree regulating device (43) also comprises the cover plate (433) that is provided with inner chamber (433a), described cover plate (433) is sealedly and fixedly connected with the upper wall surface (412) of described main body (41), the threaded hole (433b) at described inner chamber (433a) top of described screw rod (431) through being positioned at described cover plate (433) coordinates and extends into described inner chamber (433a), the end that described screw rod (431) is positioned at described inner chamber (433a) is penetrated with a card extender (434) that is provided with through hole (434a), described choke block (432) is fixedly connected with described card extender (434), the internal face of the described through hole (434a) on described card extender (434) is shiny surface, by rotating described screw rod (431), under the situation of not rotating described card extender (434) and described choke block (432) and then regulate the height of described choke block (432).
7. supersonic speed distance piece flow tunnel testing device according to claim 1 is characterized in that:
The experimental section (40) of described gas collector (10), stable section (20), supersonic nozzle section (30) and distance piece configuration all connects by flange seal between any two, and the height of described flange is adjustable.
8. supersonic speed distance piece flow tunnel testing device according to claim 1 is characterized in that:
Described stable section (20) comprises stable leading portion (21) and stablizes back segment (22), be connected by flange seal between described stable leading portion (21) and described stable back segment (22), and described stable leading portion (21) inside is provided with for reducing the filter screen from the pulse characteristic of the gas of described gas collector (10), and the internal face of described stable back segment (22) is provided with the pressure transducer probe for measurement gas air pressure.
9. supersonic speed distance piece flow tunnel testing device according to claim 1 is characterized in that:
Described gas collector (10) is provided with the butterfly valve (13) that opens and closes for controlling wind-tunnel in the porch.
10. supersonic speed distance piece flow tunnel testing device according to claim 1 is characterized in that:
The internal face of described supersonic nozzle section (30) is the plane in the horizontal direction, for being the curved surface (31) that first shrinks the trend distribution of expanding afterwards, this curved surface (31) is adopt based on cubic spline curve configuration center line Mach number and adopt the characteristic line method design in vertical direction.
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| CN106762149A (en) * | 2017-01-17 | 2017-05-31 | 中国科学技术大学 | A kind of hypersonic inlet self-starting energy force checking device |
| CN107992105A (en) * | 2017-12-25 | 2018-05-04 | 中国航天空气动力技术研究院 | A kind of flow control system and its control method |
| CN108709715A (en) * | 2018-05-25 | 2018-10-26 | 西北工业大学 | A kind of adjustable sub--super shear layer research experiment device of incoming parameter wide scope |
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| CN106762149A (en) * | 2017-01-17 | 2017-05-31 | 中国科学技术大学 | A kind of hypersonic inlet self-starting energy force checking device |
| CN107992105B (en) * | 2017-12-25 | 2023-10-17 | 中国航天空气动力技术研究院 | Flow control system and control method thereof |
| CN107992105A (en) * | 2017-12-25 | 2018-05-04 | 中国航天空气动力技术研究院 | A kind of flow control system and its control method |
| CN108709715A (en) * | 2018-05-25 | 2018-10-26 | 西北工业大学 | A kind of adjustable sub--super shear layer research experiment device of incoming parameter wide scope |
| CN108709715B (en) * | 2018-05-25 | 2019-04-19 | 西北工业大学 | A kind of adjustable sub--super shear layer research experiment device of incoming flow parameter wide scope |
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| CN110017963A (en) * | 2019-05-14 | 2019-07-16 | 国电环境保护研究院有限公司 | Modular multi-function atmospheric boundary layer wind tunnel |
| CN110017963B (en) * | 2019-05-14 | 2024-02-06 | 国电环境保护研究院有限公司 | Modularized multifunctional air boundary layer wind tunnel |
| CN111792061A (en) * | 2020-06-30 | 2020-10-20 | 中国航天空气动力技术研究院 | Pneumatic thermal test device and method utilizing shock wave boundary layer interference |
| CN112555027A (en) * | 2020-12-12 | 2021-03-26 | 西北工业大学 | Self-adaptive control method for shock wave seal of hypersonic air inlet |
| CN115307862A (en) * | 2022-10-11 | 2022-11-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel mixed heating gas jet flow test device |
| CN115307862B (en) * | 2022-10-11 | 2022-12-09 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel mixed heating gas jet flow test device |
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