CN206362518U - A kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function - Google Patents
A kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function Download PDFInfo
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- CN206362518U CN206362518U CN201621465795.4U CN201621465795U CN206362518U CN 206362518 U CN206362518 U CN 206362518U CN 201621465795 U CN201621465795 U CN 201621465795U CN 206362518 U CN206362518 U CN 206362518U
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Abstract
The utility model discloses a kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function, belong to flow tunnel testing device design field.The device includes framework, spring beam, hinge axis, secured adjusted piece, transition adjustment sheet, pivoted eyelid, push rod, arc-shaped guide rail, ball-screw module, servomotor, reductor, stay wire sensor etc..The track installation of arc-shaped guide rail is on the transition adjustment sheet connected firmly with framework, the sliding block of arc-shaped guide rail is connected with pivoted eyelid, push rod is driven to walk by the straight-line motion mechanism being made up of servomotor, reductor, ball-screw module, realize adjustment sheet rotate, produce can consecutive variations Angle of Shock Waves oblique shock wave.The utility model has the function of accurate adjustment Flow Field in Wind Tunnel, can be applied to shock wave reflection, continuous change Mach number research project, it can also be used to the supersonic wind tunnel special test such as pressure measurement, air intake duct, effectively expands the ability of wind tunnel test.
Description
Technical field
The utility model is related to a kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function, available for swashing
Wave reflection, continuously the supersonic wind tunnel special test project such as change Mach number, pressure measurement, air intake duct, belong to flow tunnel testing device design
Field.
Background technology
Shock wave is as aerodynamic basic physical phenomenon, with important physical significance and research value, swashs
Wave reflection phenomenon has been constantly subjected to extensive concern as aerodynamics important field of research in physical study.
Fig. 1 (a)~Fig. 1 (f) be wedge in two-dimensional flow field, to flow Ma1 and forward shock situation of change, wherein, Fig. 1
(a) be when come flow Ma1 it is some just beyond velocity of sound when, wedge front appearance one detached shock wave；Fig. 1 (b) be Ma1 speed after
Continuous to rise, detached shock wave is drawn close to wedge, bent；Fig. 1 (c) is that Ma1 speed continues to rise, and shock wave is unexpected from vitro position
Wedge leading edge is attached to, oblique shock wave AN is formed；Fig. 1 (d) is that Ma1 speed continues to rise, and shock wave AN β angles reduce therewith.With this phase
Corresponding relation also has：Fig. 1 (e) is the certain Ma1 of correspondence, there is a maximum wedge angle δ max, if wedge angle δ ＜ δ
Max, just forms the oblique shock wave AN for being attached to wedge leading edge together；If Fig. 1 (f) is wedge angle δ ＞ δ max, is just formed and stand in point together
Split the arch detached shock wave of leading edge；
As Fig. 1 (c), Fig. 1 (d), Fig. 1 (f), the velocity attitude variable quantity of gas is δ, i.e. air-flow side after shock wave
To, oblique shock wave formula calculating that shock wave after Mach number and Angle of Shock Waves can according to ideal gas parallel with wedge inclined-plane：
In formula：
Ma1=free stream Mach numbers
Mach number after Ma2=shock waves
δ=wedge angle
β=Angle of Shock Waves
γ=specific heat ratio, 1.40 are taken as air
As Fig. 1 (a), Fig. 1 (b), Fig. 1 (e), the calculating in whole flow field is very complicated, it is impossible to use definite meter
Calculate formula and calculate Mach number and Angle of Shock Waves after shock wave, it is necessary to use tricks fluid operator Mechanics Calculation or to verify by wind tunnel test.
Wedge is placed on shown in signal such as Fig. 2 (a) and Fig. 2 (b) in supersonic wind tunnel.(a) when come flow Ma1 Mach number foot
It is enough big, produce primary shock wave AN, air-flow speed behind δ angles of turning back is changed into Ma2, but still is supersonic.Primary shock wave AN reaches
After wind-tunnel wall, the hole wall of N points also corresponds to the wedge at a δ angle, as long as Ma2 is less low, air-flow can produce one of oblique shock wave again
NQ, the air-flow Ma3 after NQ is just parallel with hole wall.Shock wave NQ is referred to as shock wave AN back wave, and this reflection is referred to as
Regular reflection in straight wall.If (b) Ma2 is not big enough, first of shock wave can not possibly reach hole wall, can no second tiltedly swash
Ripple, reflection wave system at this moment is anticipated as shown, and N points are the meeting points of several shock waves, and this is equivalent to the situation for producing detached shock wave.This
Outside, also the intersecting of all kinds shock wave, reflection the problems such as, the referred to as irregular reflection of shock wave.
In terms of shock wave reflection problem is widely present in the engineer applieds such as supersonic aircraft layout, engine inlets.
When studying problems, typically using dynamometry, pressure testing method, coordinate with observation methods such as schlieren, oil streams, to study particular model
Compare macroscopical shock wave reflection problem.Boundary condition, the internal structure distribution in flow field etc. are formed on shock wave reflection mechanistic
Research, although achieve many understanding, but still have some physical problems etc. to be solved.A kind of shock wave as Fig. 3 illustrates is anti-
The typical internal flow field penetrated, it can be seen that flowing, which is generated, to be clearly separated, and the interaction between shock wave-boundary layer is formd
Complex flowfield.The shock wave reflection phenomenon classification illustrated such as Fig. 4, it can be seen that the external expressive form of shock wave reflection is also a variety of more
Sample.Researcher deepens and expanded understanding on the road of research shock wave reflection, constantly, and Fig. 4 categorised content is also constantly
Enrich and abundant.The mechanism sex chromosome mosaicisms such as boundary condition, the internal structure distribution in the flow field of shock wave reflection are studied, by calculating fluid
The method total calculation of mechanics is very complicated also very difficult, it is necessary to design various types of testing program researchs.
One example of research shock wave reflection application is the structure design of aircraft.If the flow field of Fig. 4 signals is acted on
Aircraft surface, can cause the lasting buffeting of aircraft surface structure, if design is improper, and aircraft surface structure is possible to production
Raw fatigue vibration limitses, or large amplitude vibration destruction.
Mechanism sex chromosome mosaicism for studying shock wave reflection, conventional wind-tunnel measurements technology is to install different on wind-tunnel support
Wedge angle δ model, shock wave structure is observed by means such as schlierens.This method has deficiency, and first is supersonic flow
Mach number interval minimum 0.25, be also not reaching to research shock wave reflection problem required for Mach number step-length precision；Second
It is that the wedge angle δ of model change has step-length span, consecutive variations wedge angle δ mechanism is limited to model volume can not be real
It is existing.
Utility model content
The utility model solve technical problem be：The deficiencies in the prior art are overcome to possess angular adjustment work(there is provided one kind
Can supersonic wind tunnel test section adjusting means, the device can by changing the angle of adjustment sheet, produce in certain angle and
Continuous controllable supersonic flow in velocity interval, to study the principle creation experimental condition of shock wave reflection.
Technical solution of the present utility model is：A kind of supersonic wind tunnel test section regulation for possessing angle regulating function
Device, the adjusting means includes pivoted eyelid, transition adjustment sheet, arc-shaped guide rail, spring beam, push rod, stay wire sensor, horizontal stroke
Beam, hinge axis, framework, secured adjusted piece and straight-line motion mechanism；Wherein, spring beam is fixedly mounted on the bottom of test chamber
Position, framework one end is fixed on spring beam, and the other end expands angle mechanism by hinge axis and wind-tunnel and is connected；Transition adjustment sheet and
Secured adjusted piece is fixedly connected with framework；Crossbeam is fixed on the bottom position of test chamber；Pivoted eyelid one end passes through arc
Shape guide rail is connected with transition adjustment sheet, and the other end is connected by push rod with the straight-line motion mechanism on crossbeam, straight line fortune
Motivation structure drives pivoted eyelid to be rotated relative to transition adjustment sheet one end by push rod；Stay wire sensor main body is fixed on transition
On the side wall of adjustment sheet, bracing wire end is fixed on pivoted eyelid end, is converted into by the displacement for measuring pivoted eyelid end
Angle for pivoted eyelid relative to transition adjustment sheet, linear motion device adjusts pivoted eyelid relative to transition adjustment sheet
Angle to required angle.
The transition adjustment sheet and secured adjusted piece are fixedly connected by way of compression with framework.
The straight-line motion mechanism includes ball-screw module, reductor, servomotor, and servomotor is connected with reductor
Driving source is formed, reductor is connected with ball-screw module, and motor is switched into the straight of ball-screw module sliding block
Line is moved.
The push rod, stay wire sensor, crossbeam, straight-line motion mechanism are respectively positioned on the side of wind tunnel test support, and pneumatic
Test bracket is not in same vertical plane.
When the angle of the pivoted eyelid and transition adjustment sheet is maximum, push rod is with ball-screw module away from arc-shaped guide rail
The angle in direction is no more than 90 degree close to 90 degree.
The beneficial effect of the utility model compared with prior art is：
(1), the wallboard of the existing supersonic speed test section of the utility model is fixed, and the utility model is in supersonic speed test section
Wallboard on pivoted eyelid is installed, the angle to be formed is rotated by pivoted eyelid, can obtain supersonic wind tunnel experiment institute
The special flow field needed：It is to realize the air velocity consecutive variations in the range of supersonic speed Mach number 1.5~4.5 first, next to that real
Consecutive variations wedge angle δ required for now research shock wave reflection；
(2), the utility model farthest remains the structure of original wind-tunnel wallboard, when pivoted eyelid is 0 °
Wait, the inwall with original wind-tunnel is completely the same, without prejudice to wind-tunnel carries out other experiments；
(3), the fixed form of transition adjustment sheet and secured adjusted piece of the present utility model on framework can improve to compress
Adjustment sheet installs fixed efficiency；
(4), the instantaneous angular velocity direction of the utility model push rod is consistent with pivoted eyelid rotation direction all the time, and pushes up
The instantaneous position of bar is no more than upright projection of the push rod upper end in the straight-line motion mechanism direction of motion all the time, it is ensured that rotate regulation
The slide position of piece and ball-screw module (8) has unique corresponding relation；
(5) when, the utility model pivoted eyelid is located at the position of hard-over, aerodynamic force is maximum, and now push rod with
Ball-screw module (8) angle μ close to 90 °, the linear driving force of straight-line motion mechanism is farthest converted into rotation and adjusted
Nodal plate surrounds the torque turned needed for the heart is rotated, for sleeve mechanism, although the very big but servomotor institute of aerodynamic force now
The driving force very little that need to be provided, so as to effectively reduce the power and volume of servomotor.
(6), the utility model push rod, stay wire sensor, crossbeam, ball-screw module, reductor, servomotor are respectively positioned on
The side of wind tunnel test support, with pneumatic test bracket not in same vertical plane, it is ensured that pivoted eyelid and support
It can move simultaneously without interfering.
Brief description of the drawings
Fig. 1 (a) is the schematic diagram that free stream Mach number produces detached shock wave in front of velocity of sound, wedge；
Fig. 1 (b) is free stream Mach number shortly past velocity of sound and free stream Mach number slightly larger than Fig. 1 (a), detached shock wave in front of wedge
The schematic diagram bent；
Fig. 1 (c) is that free stream Mach number continues to rise, and shock wave is attached to wedge leading edge, shape suddenly from vitro position in front of wedge
Into oblique shock wave AN schematic diagram；
Fig. 1 (d) is that free stream Mach number continues to rise, the schematic diagram of shock wave AN β angle reduction of the β angles relative to Fig. 1 (c)；
Fig. 1 (e) is the schematic diagram that wedge angle δ ＜ δ max produce oblique shock wave AN；
Fig. 1 (f) is the schematic diagram that wedge angle δ ＞ δ max produce detached shock wave；
Fig. 2 (a) is the regular reflection schematic diagram of oblique shock wave；
Fig. 2 (b) is a kind of irregular reflection schematic diagram of oblique shock wave；
Fig. 3 is oblique shock wave interior flow field schematic diagram；
Fig. 4 is the classification chart of shock wave reflection problem；
Fig. 5 is a kind of supersonic wind tunnel test section adjusting means sectional view for possessing angle regulating function.
Fig. 6 is converted into the stress diagram of pivoted eyelid torque for the driving force of straight-line motion mechanism；
Fig. 7 (a) is the wind tunnel test schematic diagram of research wedge shock wave reflection；
Fig. 7 (b) is the wind tunnel force measurement pressure measurement schematic diagram of research shock wave irregular reflection；
Fig. 8 is air intake duct starting characteristic schematic diagram；
Fig. 9 is the wind tunnel test schematic diagram of research air intake duct starting characteristic.
Embodiment
The utility model is described in detail below in conjunction with the drawings and specific embodiments.
The adjustment sheet of supersonic wind tunnel test section is usually fixed as wind-tunnel inwall during testing, this practicality
The new improvement on the basis of existing adjustment sheet, original a piece of secured adjusted adjustment sheet therein is divided into two layers turns into transition tune
Nodal plate and pivoted eyelid.Transition adjustment sheet is located at lower floor, is pressure with connected mode of the remaining secured adjusted piece on framework
Tightly；Pivoted eyelid, which is located at, installs arc-shaped guide rail between upper strata, with transition adjustment sheet, wherein track base is fixed on transition adjustment sheet
On, guide rail is fixed on pivoted eyelid, and arc-shaped guide rail, which limits transition adjustment sheet, only has unique rotational freedom.Arc
The heart that turns of guide rail is located at the straight line of pivoted eyelid front end and wind-tunnel inwall seam, so as to ensure pivoted eyelid in rotation period
Between, holding is concordant eventually with wind-tunnel inwall all the time for its front end, and rear end rotates around seam all the time.The driving force of rotation derives from straight line
Motion drives push rod walking, so as to drive one end of pivoted eyelid to rotate, is rotated and adjusted using stay wire sensor sensitivity
The displacement of piece one end.
As shown in figure 5, the utility model provides a kind of supersonic wind tunnel test section regulation for possessing angle regulating function
Device, the device includes pivoted eyelid 1, transition adjustment sheet 2, arc-shaped guide rail 3, spring beam 4, push rod 5, stay wire sensor 6, horizontal stroke
Beam 7, hinge axis 11, framework 12, secured adjusted piece 13 and straight-line motion mechanism.The utility model straight-line motion mechanism is by servo
Motor, reductor, ball-screw module composition.For Asia across the super wind-tunnel the characteristics of, its supersonic speed test section is above and below replaceable
Wallboard and affixed side wallboard composition.
Spring beam 4 is fixedly mounted on the bottom position of test chamber, and the one end of framework 12 is fixed on spring beam 4, another
End expands angle mechanism by hinge axis 11 and wind-tunnel and is connected, and expands angle mechanism stretching framework 12 rear end, is connected with the front end of framework 12
Spring beam 4 produce elastic deformation, formed wind tunnel test needed for expand angle, the elastic deformation of spring beam 4 does not interfere with wind-tunnel
The quality in flow field；Transition adjustment sheet 2 and secured adjusted piece 13 are fixedly connected with framework 12, constitute fixed wallboard；Pivoted eyelid 1
One end is connected by arc-shaped guide rail 3 with transition adjustment sheet 2, and described 3 turns of hearts of arc-shaped guide rail are located at pivoted eyelid 1 and spring beam 4
Seam crossing, the other end is connected by push rod 5 with straight-line motion mechanism；Ball-screw module 8, reductor 9 and servomotor 10
It is connected by screw with crossbeam 7, servomotor 10 is connected by screw to form driving source with reductor 9, reductor 9 and rolling
Ballscrew module 8 is connected by positioning key, by the linear motion for switching to the sliding block of ball-screw module 8 of motor；Turn
Dynamic adjustment sheet 1 is fixed by screw with arc-shaped guide rail 3, while being connected to form motor adjustment piece system with spring beam 4.Motor adjustment
Connected and fixed using pin by push rod 5 between piece system and straight-line motion mechanism, the straight line fortune of the sliding block of ball-screw module 8
It is dynamic to drive pivoted eyelid 1 to be rotated relative to the one end of transition adjustment sheet 2 by push rod 5；The main body of stay wire sensor 6 is fixed on ball
On the sliding block of leading screw module 8, bracing wire end is fixed on the angle for being used for measuring the formation of pivoted eyelid 1 in real time on pivoted eyelid 1.
On the one hand, the displacement variable of pivoted eyelid one end is exactly to draw high the variable quantity of sensor rope length, is passed through
TT＆C system reads the increment (Δ Uo) of stay wire sensor output voltage, and now rotates regulation by the detection of high-accuracy water level
The angle (δ) of piece, it is possible to obtain Δ Uo-- δ formula；
On the other hand, as long as the angle of push rod and ball-screw module sliding block is no more than 90 °, ball-screw module sliding block
The angle (δ) of position and pivoted eyelid also has unique corresponding relation, and it is exactly the defeated of servomotor to be reflected in control aspect
Go out umber of pulse (P) unique corresponding with the angle (δ) of pivoted eyelid, when front calibration Δ Uo-- δ formula, servomotor
Certain umber of pulse (P) is all outputed each time, therefore can be obtained by P- Δ Uo-- δ formula.The output arteries and veins of servomotor
It is the control signal sent to rush number (P), and the increment Delta Uo of stay wire sensor voltage is the control signal of feedback, pivoted eyelid
Rotational angle is to calculate to obtain by the increment Delta Uo of stay wire sensor voltage, it is achieved thereby that the closed loop control of servomotor
System.
The transition adjustment sheet 2 and secured adjusted piece 13 are fixedly connected by way of compression with framework 12, can improve tune
Nodal plate installs fixed efficiency.
The push rod 5, stay wire sensor 6, crossbeam 7, ball-screw module 8, reductor 9, servomotor 10 are respectively positioned on wind
The side of hole test bracket, with support not in same vertical plane simultaneously, it is ensured that pivoted eyelid 1 can be moved with support
Without interfering.
The pivoted eyelid 1 is in the hard-over position for bearing maximum airflow load, push rod 5 and ball-screw module 8
Angle close to 90 degree, only need the driving force of very little to achieve that the rotation of adjustment sheet, so that servomotor 10, reductor 9
Torque, power, volume are greatly reduced,
When the pivoted eyelid 1 is located at the position of hard-over, aerodynamic force is maximum, and now push rod 5 and ball-screw
Angle μ of the module 8 away from the direction of arc-shaped guide rail 3 is close to 90.The instantaneous angular velocity direction of push rod is rotated with pivoted eyelid all the time
Direction is consistent, and the instantaneous position of push rod is no more than vertical throwing of the push rod upper end in the straight-line motion mechanism direction of motion all the time
Shadow.
As shown in fig. 6, the linear driving force F of ball-screw module 8lIt is with the relation between the torque M o for turning heart o：
In formula, L was that arc-shaped guide rail turns the heart to the junction distance of hinge axis 11 and framework 12.
Now, cos μ are theoretically close to infinity close to 0, Mo, that is to say, that the linear drives of straight-line motion mechanism
Power FlFarthest it is converted into pivoted eyelid and surrounds the torque M o turned needed for the heart is rotated, for sleeve mechanism, although
Aerodynamic force now is very big but servomotor needed for the driving force very little that provides so that effectively reduce servomotor power and
Volume.
The utility model has the function of accurate adjustment Flow Field in Wind Tunnel, can be applied to shock wave reflection, continuous change Mach number etc.
Research project, it can also be used to the supersonic wind tunnel special test such as pressure measurement, air intake duct, effectively expands the ability of wind tunnel test.Wind
In the process of the test of hole, the main function of said apparatus is to control pivoted eyelid 1 to rotate the angle needed for experiment.
In the wind tunnel test for carrying out shock wave reflection mechanism Journal of Sex Research, the test type that can carry out such as Fig. 7 (a) and 7 (b)
It is shown.
The first is the shock wave reflection that wedge model is studied in wind-tunnel, according to the result of calculation of oblique shock wave formula, is changed
No more than 10 ° of pivoted eyelid angle can just control the speed of the air velocity after shock wave and next jet pipe to overlap,
In the interval of two jet pipe Mach numbers, the Mach number Ma2 after shock wave is consecutive variations, so that in supersonic speed Mach number 1.5
Air velocity consecutive variations are realized in the range of~4.5, the Mach number step-length precision problem needed for research problems is reached；
For second that wedge angle δ changes research to shock wave reflection flow field, now by pivoted eyelid be regarded as model or
Close copy is installed on pivoted eyelid, consecutive variations wedge angle is realized.This method is equivalent to model is vertical with wind-tunnel
The distance in direction is exaggerated one times, is conducive to improving the effect tested.
Supersonic speed ram air duct is an example using shock wave reflection characteristic, and this air intake duct utilizes itself compression knot
Structure, will be converted into potential energy after the supersonic flow multiple reflections of a distant place, reaches the purpose for improving air flow pressure, has punching engine
There is relatively broad Mach number working range.Starting characteristic is the key issue in the design of ram air duct, when air intake duct not
During startup, detached shock wave is formed before import, unnecessary gas overflowing mouthful is outer.And when free stream Mach number reaches startup Mach number,
Gas all bangs into venturi and passed through, and the detached shock wave before import is inhaled into air intake duct expansion segment, it is established that normal working condition,
Air intake duct starts.From discharge coefficient, discharge coefficient now rises to suddenly, as shown in Figure 8.The closing process of air intake duct can
Regard the inverse process of start-up course as, and close Mach number has certain difference with starting Mach number, this difference is called air inlet
The hesitation in road.Air intake duct is set to be in stable scope operation, the startup for being highly desirable to accurate measurement air intake duct is closed
Relevant parameter.
In the wind tunnel test for carrying out ram air duct Study on Startup, as shown in figure 9, the stream after pivoted eyelid
Field Ma2 can realize continuous change Mach number, so that air velocity is continuous for realizing in the range of supersonic speed Mach number 1.5~4.5
Change, reaches the Mach number step-length precision problem needed for research problems.In the inclination flow field of adjustment sheet formation, in wind-tunnel
Air intake duct model is installed, it is possible to complete the experiment of air intake duct startability on support.
The content that the utility model is not described in detail belongs to general knowledge known in this field.
Claims (5)
1. a kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function, it is characterised in that：Including rotating regulation
Piece (1), transition adjustment sheet (2), arc-shaped guide rail (3), spring beam (4), push rod (5), stay wire sensor (6), crossbeam (7), hinge
Axle (11), framework (12), secured adjusted piece (13) and straight-line motion mechanism；Wherein, spring beam (4) is fixedly mounted on wind tunnel test
The bottom position of section, framework (12) one end is fixed on spring beam (4), and the other end expands angle-cutting machine by hinge axis (11) and wind-tunnel
Structure is connected；Transition adjustment sheet (2) and secured adjusted piece (13) are fixedly connected with framework (12)；Crossbeam (7) is fixed on wind tunnel test
The bottom position of section；Pivoted eyelid (1) one end is connected by arc-shaped guide rail (3) with transition adjustment sheet (2), and the other end passes through top
Bar (5) is connected with the straight-line motion mechanism on crossbeam (7), and straight-line motion mechanism is driven by push rod (5) and rotates regulation
Piece (1) rotates relative to transition adjustment sheet (2) one end；Stay wire sensor (6) main body is fixed on the side wall of transition adjustment sheet (2)
On, bracing wire end is fixed on pivoted eyelid (1) end, and the displacement by measuring pivoted eyelid (1) end, which converts to turn into, to be rotated
Adjustment sheet (1) is relative to the angle of transition adjustment sheet (2), and linear motion device regulation pivoted eyelid (1) is relative to transition tune
The angle of nodal plate (2) is to required angle.
2. a kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function according to claim 1, it is special
Levy and be：The transition adjustment sheet (2) and secured adjusted piece (13) are fixedly connected by way of compression with framework (12).
3. a kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function according to claim 1, it is special
Levy and be：The straight-line motion mechanism includes ball-screw module (8), reductor (9), servomotor (10), servomotor
(10) it is connected to form driving source with reductor (9), reductor (9) is connected with ball-screw module (8), by the rotation of motor
Switch to the linear motion of ball-screw module (8) sliding block.
4. a kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function according to claim 3, it is special
Levy and be：The push rod (5), stay wire sensor (6), crossbeam (7), straight-line motion mechanism are respectively positioned on the one of wind tunnel test support
Side, with pneumatic test bracket not in same vertical plane.
5. a kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function according to claim 1, it is special
Levy and be：When the pivoted eyelid (1) and the maximum angle of transition adjustment sheet (2), push rod (5) and ball-screw module (8)
Angle away from arc-shaped guide rail (3) direction is no more than 90 degree close to 90 degree.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106840585A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function |
| CN110940482A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Air-breathing type aircraft continuous variable Mach number force measurement test device |
| RU2722854C1 (en) * | 2019-10-28 | 2020-06-04 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Method of controlling model position in wind tunnel |
| CN114459727A (en) * | 2021-12-30 | 2022-05-10 | 中国人民解放军国防科技大学 | Experimental system and method for SWTBLI unsteady characteristic research |
| CN115541175A (en) * | 2022-12-02 | 2022-12-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Design method of variable attack angle module of small-caliber closed wind tunnel test section |
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2016
- 2016-12-29 CN CN201621465795.4U patent/CN206362518U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106840585A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of supersonic wind tunnel test section adjusting means for possessing angle regulating function |
| RU2722854C1 (en) * | 2019-10-28 | 2020-06-04 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Method of controlling model position in wind tunnel |
| CN110940482A (en) * | 2019-11-13 | 2020-03-31 | 中国航天空气动力技术研究院 | Air-breathing type aircraft continuous variable Mach number force measurement test device |
| CN110940482B (en) * | 2019-11-13 | 2022-06-03 | 中国航天空气动力技术研究院 | Air-breathing type aircraft continuous variable Mach number force measurement test device |
| CN114459727A (en) * | 2021-12-30 | 2022-05-10 | 中国人民解放军国防科技大学 | Experimental system and method for SWTBLI unsteady characteristic research |
| CN115541175A (en) * | 2022-12-02 | 2022-12-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Design method of variable attack angle module of small-caliber closed wind tunnel test section |
| CN115541175B (en) * | 2022-12-02 | 2023-02-03 | 中国空气动力研究与发展中心超高速空气动力研究所 | Design method of small-caliber closed wind tunnel test section variable attack angle module |
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