CN110132528A - It is a kind of temporarily to rush formula supersonic wind tunnel sonic boom measurement experimental rig and measuring method - Google Patents
It is a kind of temporarily to rush formula supersonic wind tunnel sonic boom measurement experimental rig and measuring method Download PDFInfo
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Abstract
Formula supersonic wind tunnel sonic boom measurement experimental rig and measuring method are temporarily rushed the invention discloses a kind of, it aims to overcome that and sonic boom measurement test is being carried out using the temporary formula supersonic wind tunnel that rushes, it is existing to carry out test result accuracy not high problem when sonic boom measures test using probe.It includes the first test chamber siding, the second test chamber siding, measurement probe, measurement probe attachment device, model attachment device, reference probe, the fixed device of reference probe etc. that this, which temporarily rushes formula supersonic wind tunnel sonic boom measurement experimental rig,.Using the device of the application, can be effectively protected model, measurement probe and its support device start in supersonic wind tunnel/stage of cut-offfing will not deform because bearing big shock loading, protect small-range differential pressure pick-up not to be damaged.Meanwhile sonic boom measurement can be carried out using the present invention with model movement and the mobile two ways of measurement probe and tested, to effectively improve the accuracy of sonic boom measurement result under the premise of keeping test integral layout constant.
Description
Technical field
The present invention relates to aerospace wind tunnel test fields, specially a kind of temporarily to rush the measurement test of formula supersonic wind tunnel sonic boom
Device and measuring method.
Background technique
When sonic boom refers to that the aircraft speed of service reaches supersonic speed, a series of wave systems that aircraft shape generates are distally
Influence is interfered with each other in communication process, the preceding shock wave for covering Vehicle nose together finally accumulated trails aircraft with together with
The rear shock of tail portion.When this wave system travels to ground, what is be humanly perceptible shows as the thunderous loud noise of two sound.
As an independent experimental technique, sonic boom measurement test refers to obtains aircraft generation by way of test
Boom characteristics.The basic ideas of sonic boom measurement test are, for a certain trystate of dummy vehicle, to pass through change of flight device
Model and measuring device obtain in the relative position along flight track line direction and are generated wave system by model under flight track line
The variation characteristic of pressure when interference compared to non-interference data.Table is specifically included that for the trystate of fixed configuration model
Levy the vertical of the model mass center and measurement position of the angle of attack that model attitude changes and roll angle and characterization model sonic boom propagation distance
To distance.
Change of flight device model and measuring device it is usual in the mode of the relative position along flight track line direction there are two types of:
One is keeping position of the model in wind-tunnel not change during test, measuring device is changed in wind-tunnel by movement mechanism
Relative position, thus obtain complete model wave system influence mode；One is keep measuring device in wind-tunnel during test
In position do not change, relative position of the model in wind-tunnel is changed by movement mechanism, to obtain complete model wave system shadow
Loud mode.
It is a kind of type testing mode of sonic boom measurement test, which using static probe as main measuring device
Representative configuration figure in wind-tunnel is as shown in Figure 1.In Fig. 1,1 be test chamber wainscot, 2 be test chamber lower wall panels, 3
It is model attachment device for model, 4,5 be model actuation mechanism (it is mobile that it is used for Controlling model), and 6 be measurement probe, and 7 be survey
Measure probe attachment device, 8 (if by the way of test is moved using model, 8 can for probe fixture or probe actuation mechanism
It to be probe fixture, is connect with test section siding, is also possible to probe actuation mechanism, be only failure to actuate in test；Such as
Fruit test is by the way of probe movement, then 8 be probe actuation mechanism, passes through the part and controls probe movement), 9 is with reference to spies
Needle, 10 be the fixed device of reference probe.
Measuring probe 6 and reference probe 9 is needles shape, quiet away from end of probe certain position Vertrical probe surface layout
Hole is pressed, pipeline is passed through external pipeline cut-in pressure measuring device by the pipeline connection along axis perforation in static pressure hole and probe,
Realize pressure measurement.
Before on-test, model 3 is connect by model attachment device 4 with model actuation mechanism 5, and measurement probe 6 passes through survey
Amount probe attachment device 7 is connect with probe fixture or probe actuation mechanism 8, and reference probe 9 is filled by reference to probe is fixed
It sets 10 to connect with test section siding, be remained stationary during test.
For ease of description, it is defined as follows coordinate system:
X-axis is defined in wind-tunnel horizontal flange, and along wind-tunnel axis direction, favorable current is downstream positive；
Y-axis is defined as vertical wind tunnel horizontal flange, and downstream direction is seen, is positive upwards；
Z-axis meets the right-hand rule；
Origin is defined within x, y, z axis intersection point in test chamber entrance section.
It should be noted that default models defined above and measurement probe etc. are mounted on lower wall panels on test chamber,
If being mounted on wind-tunnel left and right sidewall, definition is adjusted accordingly.
For measuring the mobile test method of probe, test basic procedure is as follows:
(a) according to experimental condition, the attitude angle of model is adjusted；
(b) adjustment measurement probe attitude angle guarantees that probe axis is parallel with wind-tunnel axis；
(c) relative position of adjustment model and measurement probe in y-direction has in y-direction to meet model and measurement probe
Have to the requirement of set a distance h；
(d) wind-tunnel starts, and flow field is established；
(e) probe actuation mechanism control measurement probe is along the direction parallel with wind-tunnel axis from the x far from the influence of model sonic boom
It is gradually distance from after gradually moving through model bangzone domain to position；Period detects measurement probe sense by measuring system
The pressure being subject to；During this period, wind-tunnel incoming flow static pressure is measured using reference probe；
(f) wind-tunnel cut-offs；
(g) by data processing, the model boom characteristics in distance model h be can be obtained.
When using model mobile measurement method, other than it will move and survey object and the object being in a fixed position exchange,
Remaining experiment process is consistent.
Boom characteristics signal generally uses " over-voltage " parameter, Δ P/P to characterize, and is defined as follows:
Δ P/P=(Pp-Ps)/Ps；
Wherein, Pp refers to static pressure when a certain measurement position x is influenced by sonic boom；
Ps refers to the static pressure when a certain measurement position x, which is not affected by sonic boom, to be influenced, that is, refers to static pressure.
It should be noted that being given above is theoretical calculation formula, in test, be cannot achieve while obtaining it is a certain
Measurement position x by with static pressure when not influenced by sonic boom.Therefore, it in wind tunnel test, often selects in Flow Field in Wind Tunnel
Uniformity is preferably and a certain position not in model bangzone by device measures the position static pressure, as " over-voltage " ginseng
Reference static pressure when number calculates；Or it is obtained indirectly by certain data processing in a certain measurement position using the measurement result
The static pressure that x is not affected by sonic boom when influencing.
Sonic boom measurement test generally requires model and measurement probe is tested in section in the large-scale direction y,
To obtain model boom characteristics with the propagation changing rule of distance.This distance is generally with the multiple relative to model reference length
Characterization, is defined as h/l, at a distance from h indicates model and measurement probe in y-direction, l expression model reference length.It is achievable
H/l value is bigger, it is meant that more will appreciate that the propagation law of boom characteristics signal.By taking live flying as an example, work as aircraft flight
Height is 10000m, corresponding when the boom characteristics signal generated passes to ground and experienced by people when aircraft length is 100m
H/l=100；Restriction of the wind tunnel test by tunnel size, in order to make h/l reach certain value, so that moulded dimension is compared to normal
It is small much to advise dynamometer check model.For in 2 meters of magnitude supersonic wind tunnels development sonic boom measurement tests, even if not considering wall
Face shock wave reflection and boundary layer influence make the maximum distance of model and measurement probe in y-direction reach 2000mm, even if only
It is required that h/l=5, then the of length no more than 400mm of model reference, this length 1600mm that can satisfy with general measure test model
Size differ greatly.Simultaneously, it is contemplated that boom characteristics signal belongs to weak signal scope, and the peak value of Δ P is in 100Pa~1000Pa
Magnitude, it is ensured that high-precision measurement, it is desirable to which the simulation of model detail is finer, and the minor change of mode shape will be to sound
Quick-fried measurement result generates relatively bigger influence.Meanwhile in order to avoid support interference as far as possible, so that the branch of model and probe
Support arrangement is more elongated thinner compared to routine test support device, and strength and stiffness are smaller.
Traditional sonic boom measurement experimental rig mainly uses in continuous type ultrasonic speed wind-tunnel, since the type wind-tunnel starts
When shock loading very little, model, probe and its support device, which are exposed in test section, will not generate big deformation.And for temporarily rushing
When wind tunnel operation, there is one of normal shock wave always, with the raising of wind-tunnel stagnation pressure, the stabilization position of normal shock wave in formula supersonic wind tunnel
It sets and gradually shifts to downstream；When normal shock wave settling position is located at test model area downstream, wind-tunnel establishes stable supersonic flow field；
Normal shock wave is inswept model and probe region moment, and model and probe will bear great aerodynamic load and acutely vibration occur
It is dynamic；Wind-tunnel cut-offs the stage after the end of the test, and normal shock wave, which retracts, passes through model and probe region moment, and model and probe are again
It will bear great aerodynamic load and high vibration occur.During test, model and probe absorb impact load, pole repeatedly
It is likely to result in model and probe deforms, to influence the accuracy of sonic boom measurement result.
In addition, since the magnitude of Δ P is far smaller than wind-tunnel incoming flow static pressure, it is general to select in a small amount in order to guarantee measurement accuracy
The differential pressure pick-up of journey measures, and the reference end pressure of sensor is in Flow Field in Wind Tunnel uniformity preferably and not in model sonic boom
A certain position in the zone of influence measures the position static pressure by device, and measurement end pressure is measurement probe measured value.Wind-tunnel start/
The stage of cut-offfing deposits at a time, and measurement end and reference end measured value are respectively from the upstream and downstream of normal shock wave, resulting big
Pressure difference be most likely to damage sensor.
Further, although previous sonic boom measurement test model and measurement probe all has locomitivity, locomitivity
It differs greatly, be only able to satisfy mobile using model and measure the requirement of the mobile one of test method development test of probe.With
For measuring probe nigration mode, actuation mechanism matched with measurement probe often has the freedom degrees such as x, y and the angle of attack
Regulating power, wherein realizing the change of trystate to regulating power using x, y, the regulating power of the angle of attack is mainly used for protecting
Demonstrate,prove the zero-incidence installation requirement of probe；And mechanism matched with model or fixed device, i.e. guarantee model begin during test
Same state is kept eventually, or only has x to the regulating power with the angle of attack, and wherein x is far weaker than measurement probe to regulating power
The x of matched actuation mechanism only has local motion ability to regulating power, does not have to carry out and be surveyed based on the mobile sonic boom of model
Measure test capability.When using the mobile test method of model, situation is similar.
It is that model is in a fixed position always using the advantages of probe nigration mode, the variation of model wave system is opposite
It is fixed；The disadvantage is that, probe is more sensitive to measured value variation, if background pressure fluctuation is larger in measurement probe moving section,
It may influence measurement probe measurement result.It is that measurement probe location is fixed using the advantages of model nigration mode, by
Interference be fixed amount, show as a System level gray correlation in data correction, relatively benefit is managed；The disadvantage is that, model turnover zone
Between if background pressure fluctuates, larger to may cause boom characteristics curve not be the result of corresponding same state.To sum up, two
Kind test method respectively has advantage and disadvantage, and for different situations, the mode that can obtain more reliable test data may be different.
In addition, either carrying out respectively in different wind-tunnel based on two kinds of movement sides in view of the weak signal attribute of boom characteristics
The sonic boom of formula measures test, or is based in same wind-tunnel by changing model and measuring layout realization of the probe in wind-tunnel
The Test and Comparison Study of two kinds of test methods can all introduce many disturbing factors, influence the analysis of test data.
Therefore, have in the test of same phase while can be obtained more preferably using the ability that two kinds of test methods carry out test
Test data, meanwhile, be more favorable to the comparative analysis of test data.
Summary of the invention
Goal of the invention of the invention is: sonic boom measurement test is being carried out using the temporary formula supersonic wind tunnel that rushes to overcome, it is existing
There is test result accuracy not high problem when carrying out sonic boom measurement test using probe, one kind is provided and temporarily rushes formula supersonic wind tunnel
Sonic boom measures experimental rig and measuring method.Using the device of the application, model, measurement probe and its branch can be effectively protected
Support arrangement starts in supersonic wind tunnel/and the stage of cut-offfing will not deform because bearing big shock loading, protect a small amount of path differences
Pressure sensor is not damaged.Meanwhile it can be mobile with model under the premise of keeping test integral layout constant using the present invention
Carry out sonic boom measurement test with the mobile two ways of measurement probe, to effectively improve the accuracy of sonic boom measurement result.
To achieve the goals above, the present invention adopts the following technical scheme:
It is a kind of temporarily to rush formula supersonic wind tunnel sonic boom measurement experimental rig, including the first test chamber siding, the second wind tunnel test
Section siding, measurement probe, measurement probe attachment device, model attachment device, reference probe, ginseng for being connected with model to be measured
Probe fixture is examined, the first test chamber siding is oppositely arranged with the second test chamber siding, first wind
It is constituted between hole test section siding and the second test chamber siding and temporarily rushes formula supersonic wind tunnel test section；
Further include first matched with the first test chamber siding stay room, matched with the second test chamber siding the
Two stay room, the first freedom degree actuating mechanism, the second freedom degree actuating mechanism, the first test section turnover panel, the second test section turnover panel；
The first open slot is provided on the first test chamber siding, the first test section turnover panel setting is in the first opening
On slot and the first test section turnover panel energy opposite first open slot is opened and closed；The measurement probe passes through measurement probe attachment device and the
Single-degree-of-freedom actuating mechanism, which is connected, and the first freedom degree actuating mechanism is by measuring probe attachment device can drive measurement probe real
Existing X-direction, Y-direction, the angle of attack and the movement of rolling angular direction；Described first, which stays room, is arranged in the outer of the first test chamber siding
On wall, described first in the first temporarily providing room is formed between room and the first test chamber siding, first freedom degree acts
Mechanism is arranged in the first temporarily providing room and the first freedom degree actuating mechanism can drive measurement probe to enter by the first open slot
Temporarily rush in formula supersonic wind tunnel test section；
The second open slot is provided on the second test chamber siding, the second test section turnover panel setting is in the second opening
On slot and the second test section turnover panel can opposite second open slot opening and closing；The both ends of the model attachment device respectively with mould to be measured
Type, the second freedom degree actuating mechanism, which are connected, and the second freedom degree actuating mechanism is by model attachment device can drive model to be measured real
Existing X-direction, Y-direction, the angle of attack and the movement of rolling angular direction；Described second, which stays room, is arranged in the outer of the second test chamber siding
On wall, described second in the second temporarily providing room is formed between room and the second test chamber siding, second freedom degree acts
Mechanism is arranged in the second temporarily providing room and the second freedom degree actuating mechanism can drive model to be measured to enter by the second open slot
Temporarily rush in formula supersonic wind tunnel test section；
The reference probe by reference to probe fixture with temporarily rush formula supersonic wind tunnel test section and be connected.
The first test chamber siding is test chamber wainscot, and the second test chamber siding is wind-tunnel
Test section lower wall panels.
The first test chamber siding is test chamber left wall plate, and the second test chamber siding is wind-tunnel
Test section right wall plate.
The first freedom degree actuating mechanism protrudes into and temporarily rushes the part in formula supersonic wind tunnel test section, the second freedom degree is moved
It is protruded into as mechanism and temporarily rushes the part in formula supersonic wind tunnel test section using Streamline Design.
The reference probe is by reference to probe fixture and the first test chamber siding or the second test chamber
The wave system that siding is connected and reference probe position should be such that it generates is from influencing model air-flow flowing nearby.
Using the measuring method of afore-mentioned test device, include the following steps:
A, before test, measurement probe is located at first and stays interior, and model to be measured is located at second and stays interior, the first test section turnover panel, the
Two test section turnover panels remain turned-off respectively；
B, after temporarily rushing formula supersonic wind tunnel supersonic flow field and establishing, the first test section turnover panel, the second test section turnover panel are beaten respectively
It opens, measurement probe, which is stayed in room by the first freedom degree actuating mechanism from first, to be stretched out, and model to be measured is acted by the second freedom degree
Mechanism stays in room from second stretches out；
C, measurement probe by the first freedom degree actuating mechanism, model to be measured by the second freedom degree actuating mechanism be separately operable to
After temporarily rushing the initial trial position of formula supersonic wind tunnel test section, the first test section turnover panel, the second test section turnover panel are closed；
D, according to given trystate, change model attitude to be measured, and start to test according to given test method；
E, after the test, the first test section turnover panel, the second test section turnover panel are opened, and measurement probe is acted by the first freedom degree
Mechanism is recovered to first and stays interior, and model to be measured is recovered to second by the second freedom degree actuating mechanism and stays interior, and turnover panel is closed；
F, it temporarily rushes formula supersonic wind tunnel to cut-off, completes test.
For foregoing problems, the application provides one kind and temporarily rushes formula supersonic wind tunnel sonic boom measurement experimental rig and measurement side
Method.In the experimental rig of the application, first stay room, second stay room is respectively arranged in outside test section inner cavity, for wind-tunnel start/
Cut-off the stage when, store model to be measured, measurement probe and matched first freedom degree actuating mechanism, the second freedom degree actuating mechanism
Space is provided；The first open slot, the second open slot is respectively set on first test chamber siding, the second test chamber siding
(i.e. fluting among siding), to replace the original solid wall siding of test section, and as model when testing and measurement probe by staying room
Into the channel of test section inner cavity；First test section turnover panel, the second test section turnover panel protrude into examination in measurement probe and model respectively
Closing when section inner cavity is tested is tested, for filling the gap between siding and multiple-degree-of-freedom mechanism.In the application, built in Flow Field in Wind Tunnel
When vertical and off-test, the first test section turnover panel, the second test section turnover panel are stayed open, respectively measurement probe and model to be measured
It enters and leaves and stays the reserved channel in room；Model to be measured realizes the direction x, the direction y, the angle of attack and roll angle by the second freedom degree actuating mechanism
Variation, the mobile test method of model both may be implemented, model appearance can also be used for when using probe nigration mode
The adjustment of state and position.The variation that probe realizes x, y, the angle of attack and roll angle by the first freedom degree actuating mechanism is measured, both
The mobile test method of measurement probe may be implemented, it can also be when using model nigration mode, for measuring probe appearance
The adjustment of state and position.
In the application, the first test section turnover panel, the second test section turnover panel in off position when, except be freedom degree actuating mechanism
It is mobile that there are outside necessary channel, it is desirable that and siding and the gap of freedom degree actuating mechanism are small as far as possible, meanwhile, the first test section turns over
Plate, the second test section turnover panel are bonded as far as possible with test section unslotted part, to reduce the interference to Flow Field in Wind Tunnel.In addition, model
With measurement probe when the position stayed in room should ensure that turnover panel is opened, it will not be interfered with model to be measured and measurement probe.Together
When, high precision design is respectively adopted in the first freedom degree actuating mechanism, the second freedom degree actuating mechanism, advantageously ensures that practical examination
It tests state and given theoretical test state is as consistent as possible, to reduce influence of the difference to test result of trystate.Into
One step, the first freedom degree actuating mechanism, the second freedom degree actuating mechanism protrude into test section lumen portion and are meeting intensity requirement guarantor
Answered under the premise of confirmatory test safety it is as small as possible, and use Streamline Design, minimize the interference to Flow Field in Wind Tunnel.
It in the application, is only required to meet wind-tunnel in chamber size when starting/cut-off the stage, model to be measured, measurement probe
And the space requirement of matched first freedom degree actuating mechanism, the second freedom degree actuating mechanism, without as many biographies
System wind tunnel reservoir structure room need it is sufficiently large and in being wrapped in test section, to keep test section inner cavity air-flow patency and stability.
In the application, the use of the first freedom degree actuating mechanism, the second freedom degree actuating mechanism be can be realized in same wind
Under the premise of keeping test integral layout constant in hole, it is provided simultaneously with mobile using model and measures the mobile two kinds of test sides of probe
Formula, to carry out the ability of sonic boom measurement test.Meanwhile first freedom degree actuating mechanism, the second freedom degree actuating mechanism use,
On the one hand on the other hand the demand that can satisfy trystate change improves and eliminates model, measurement probe and its mating connection
The ability of device installation error can preferably guarantee the consistency of actual tests state Yu given trystate.Further,
On the one hand the use of single-degree-of-freedom actuating mechanism, the second freedom degree actuating mechanism can satisfy and carry out empty wind using measurement probe
The needs of hole background pressure measurement test；On the other hand, can during guarantee test, a set of freedom degree actuating mechanism occur therefore
Barrier, when needing promptly to cut-off, another set of freedom degree actuating mechanism returns to safety to control model connected to it or measurement probe
Position is unlikely to damage all experimental rigs.
Further, it is tested using the application, is conducive to the progress of test, and reduce the standard for influencing test result to the greatest extent
The disturbing factor of true property.
In conclusion carrying out sonic boom measurement test using the application, model and measurement probe can be avoided because bearing repeatedly
The problem of shock loading deforms and small-range differential pressure pick-up is damaged because measuring normal shock wave front and back pressure difference；It can be
Under the premise of test integral layout is constant, has and model movement is respectively adopted and measures what the mobile two ways development of probe was tested
Ability；The installation error that model, measurement probe and its jointed complete set can effectively be eliminated, makes actual tests state and wants
The trystate asked is consistent as far as possible, and the standard based on the sonic boom measurement result for temporarily rushing the acquisition of formula supersonic wind tunnel is effectively ensured
True property and reliability.
Detailed description of the invention
Examples of the present invention will be described by way of reference to the accompanying drawings, in which:
Fig. 1 is in the prior art, using static probe as main measuring device, to carry out a kind of typical examination of sonic boom measurement test
Proved recipe formula.
Fig. 2 is the schematic diagram that model and measurement probe income are stayed room and turnover panel kept to open by apparatus of the present invention.
Fig. 3 is the schematic diagram that model and measurement probe are protruded into test section and turnover panel kept to close by apparatus of the present invention.
Fig. 4 is the A direction view of Fig. 3.
Fig. 5 is the B direction view of Fig. 3.
Marked in the figure: 1, test chamber wainscot, 2, test chamber lower wall panels, 3, model, 4, model attachment device,
5, model actuation mechanism, 6, measurement probe, 7, measurement probe attachment device, 8, probe fixture or probe actuation mechanism, 9,
Reference probe, 10, the fixed device of reference probe, 11, first stays room, the 12, first freedom degree actuating mechanism, the 13, first test section
Turnover panel, 14, second stays room, the 15, second freedom degree actuating mechanism, the 16, second test section turnover panel.
Specific embodiment
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
Any feature disclosed in this specification unless specifically stated can be equivalent or with similar purpose by other
Alternative features are replaced.That is, unless specifically stated, each feature is an example in a series of equivalent or similar characteristics
?.
Embodiment 1
As shown, the formula supersonic wind tunnel sonic boom measurement experimental rig that temporarily rushes of the present embodiment includes the first test chamber wall
Plate, the second test chamber siding, measurement probe, measurement probe attachment device, the model for being connected with model to be measured are connect
The fixed device of device, reference probe, reference probe, the first test chamber siding is opposite with the second test chamber siding to be set
It sets, is constituted between the first test chamber siding and the second test chamber siding and temporarily rush formula supersonic wind tunnel test section.This reality
It applies in example, the first test chamber siding is test chamber wainscot, and the second test chamber siding is wind tunnel test
Section lower wall panels.
The experimental rig of the present embodiment further includes that first matched with test chamber wainscot stays room and wind tunnel test
What section lower wall panels matched second stay room, the first freedom degree actuating mechanism, the second freedom degree actuating mechanism, the first test section turn over
Plate, the second test section turnover panel.
In the present embodiment, it is provided with the first open slot on test chamber wainscot, the setting of the first test section turnover panel is the
On one open slot, measurement probe is connected by measuring probe attachment device with the first freedom degree actuating mechanism.First setting in room
On the outer wall of test chamber wainscot, first stays and forms the first temporarily providing room between room and test chamber wainscot, and the
Single-degree-of-freedom actuating mechanism is arranged in the first temporarily providing room.In the structure, the first test section turnover panel energy opposite first open slot
Opening and closing, the first freedom degree actuating mechanism can drive measurement probe to realize X-direction, Y-direction, the angle of attack by measuring probe attachment device
And the movement of rolling angular direction；First freedom degree actuating mechanism can drive measurement probe super into formula is temporarily rushed by the first open slot
In velocity of sound test chamber, to realize corresponding stretching and withdraw.
Meanwhile test chamber lower wall panels are arranged with the second open slot, the setting of the second test section turnover panel is in the second opening
On slot, the both ends of model attachment device are connected with model to be measured, the second freedom degree actuating mechanism respectively and the second freedom degree acts
Mechanism can drive model realization X-direction to be measured, Y-direction, the angle of attack and the movement of rolling angular direction by model attachment device.Second
On the outer wall that test chamber lower wall panels are arranged in room, second, which stays formation second between room and test chamber lower wall panels, is kept in
Space, the second freedom degree actuating mechanism are arranged in the second temporarily providing room.
Reference probe is connected by reference to probe fixture with test chamber wainscot.
In the present embodiment, the first open slot, the second test chamber wall are set on the first test chamber siding respectively
Second open slot is set on plate, to substitute the original solid wall siding of wind-tunnel, collectively forms airflow channel with original left and right sidewall.Together
When, it is located at outside test section inner cavity in room and is connect with test section siding, end face seal is installed not have external gas when guarantee test
Stream enters test section inner cavity by installing end face, and model is connect by model attachment device with the second freedom degree actuating mechanism, the
Two degrees of freedom actuating mechanism is mounted on second and stays interior；Probe is measured to act by measurement probe attachment device and the first freedom degree
Mechanism connection, the first freedom degree actuating mechanism are mounted on first and stay interior；Reference probe is by reference to probe fixture and wind
The connection of hole test section wainscot, remains stationary during test.
Based on the measuring method of afore-mentioned test device, include the following steps:
A, before test, measurement probe is located at first and stays interior, and model to be measured is located at second and stays interior, the first test section turnover panel, the
Two test section turnover panels remain turned-off respectively；
B, after temporarily rushing formula supersonic wind tunnel supersonic flow field and establishing, the first test section turnover panel, the second test section turnover panel are beaten respectively
It opens, measurement probe, which is stayed in room by the first freedom degree actuating mechanism from first, to be stretched out, and model to be measured is acted by the second freedom degree
Mechanism stays in room from second stretches out；
C, measurement probe by the first freedom degree actuating mechanism, model to be measured by the second freedom degree actuating mechanism be separately operable to
After temporarily rushing the initial trial position of formula supersonic wind tunnel test section, the first test section turnover panel, the second test section turnover panel are closed；
D, according to given trystate, change model attitude to be measured, and start to test according to given test method；
E, after the test, the first test section turnover panel, the second test section turnover panel are opened, and measurement probe is acted by the first freedom degree
Mechanism is recovered to first and stays interior, and model to be measured is recovered to second by the second freedom degree actuating mechanism and stays interior, and turnover panel is closed；
F, it temporarily rushes formula supersonic wind tunnel to cut-off, completes test.
The principle that the present invention improves sonic boom measurement test result accuracy is based on following two points: one allows for one side sound
Quick-fried measurement test either model still measures probe size and is much smaller than routine test model, but fine to the simulation of mode shape
Change and require to be much higher than routine test again, while probe, as a kind of presser sensor measuring device, the change of shape equally influences it
Measured value；On the other hand, it temporarily rushes formula supersonic wind tunnel and starts/inswept the test section of normal shock wave that certainly exists of the stage of cut-offfing, and make mould
Type and measurement probe bear the risk that extreme shock load has deformation.In order to solve the contradiction between above-mentioned two aspect, lead to
It crosses the device of the invention realization to start/cut-off the stage in wind-tunnel, model and measurement probe income is stayed into room, built in supersonic flow field
It is entered back into air-flow after vertical, model and measurement probe is made to avoid absorbing impact load repeatedly and deforming.Meanwhile using this hair
Bright, the differential pressure pick-up for also avoiding small-range starts/cut-offs the stage because outranging pressure before and after measurement normal shock wave in wind-tunnel
Power and damage.In addition, belonging to weak signal scope for boom signature, measurement result is influenced apparent feelings by background pressure distribution
Condition, the application are realized and are being guaranteed by the multiple-degree-of-freedom mechanism using two sets of mutually independent high precision wide range long strokes
Under the premise of test integral layout is constant, measures and tests using model movement and the mobile two ways progress sonic boom of measurement probe,
So that selecting optimum way under different operating conditions, obtaining more reliable test result and be possibly realized.
The invention is not limited to specific embodiments above-mentioned.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (6)
1. a kind of temporarily rush formula supersonic wind tunnel sonic boom measurement experimental rig, including the examination of the first test chamber siding, the second wind-tunnel
Test a section siding, measurement probe, measurement probe attachment device, the model attachment device for being connected with model to be measured, reference probe,
Reference probe fixes device, and the first test chamber siding is oppositely arranged with the second test chamber siding, and described first
It is constituted between test chamber siding and the second test chamber siding and temporarily rushes formula supersonic wind tunnel test section；
It is characterized in that, further including that first matched with the first test chamber siding stays room and the second test chamber wall
Plate match second stay room, the first freedom degree actuating mechanism, the second freedom degree actuating mechanism, the first test section turnover panel, second
Test section turnover panel；
The first open slot is provided on the first test chamber siding, the first test section turnover panel setting is in the first opening
On slot and the first test section turnover panel energy opposite first open slot is opened and closed；The measurement probe passes through measurement probe attachment device and the
Single-degree-of-freedom actuating mechanism, which is connected, and the first freedom degree actuating mechanism is by measuring probe attachment device can drive measurement probe real
Existing X-direction, Y-direction, the angle of attack and the movement of rolling angular direction；Described first, which stays room, is arranged in the outer of the first test chamber siding
On wall, described first in the first temporarily providing room is formed between room and the first test chamber siding, first freedom degree acts
Mechanism is arranged in the first temporarily providing room and the first freedom degree actuating mechanism can drive measurement probe to enter by the first open slot
Temporarily rush in formula supersonic wind tunnel test section；
The second open slot is provided on the second test chamber siding, the second test section turnover panel setting is in the second opening
On slot and the second test section turnover panel can opposite second open slot opening and closing；The both ends of the model attachment device respectively with mould to be measured
Type, the second freedom degree actuating mechanism, which are connected, and the second freedom degree actuating mechanism is by model attachment device can drive model to be measured real
Existing X-direction, Y-direction, the angle of attack and the movement of rolling angular direction；Described second, which stays room, is arranged in the outer of the second test chamber siding
On wall, described second in the second temporarily providing room is formed between room and the second test chamber siding, second freedom degree acts
Mechanism is arranged in the second temporarily providing room and the second freedom degree actuating mechanism can drive model to be measured to enter by the second open slot
Temporarily rush in formula supersonic wind tunnel test section；
The reference probe by reference to probe fixture with temporarily rush formula supersonic wind tunnel test section and be connected.
2. temporarily rushing formula supersonic wind tunnel sonic boom measurement experimental rig according to claim 1, which is characterized in that first wind
Hole test section siding is test chamber wainscot, and the second test chamber siding is test chamber lower wall panels.
3. according to claim 1 or claim 2 temporarily rush formula supersonic wind tunnel sonic boom measurement experimental rig, which is characterized in that described the
One test chamber siding is test chamber left wall plate, and the second test chamber siding is test chamber right wall plate.
4. the according to claim 1 or 2 or 3 formula supersonic wind tunnel sonic booms that temporarily rush measure experimental rig, which is characterized in that described
First freedom degree actuating mechanism protrudes into the part temporarily rushed in formula supersonic wind tunnel test section, the second freedom degree actuating mechanism protrudes into temporarily
The part in formula supersonic wind tunnel test section is rushed using Streamline Design.
5. any one is described according to claim 1 ~ 4 temporarily rushes formula supersonic wind tunnel sonic boom measurement experimental rig, which is characterized in that institute
State reference probe be connected by reference to probe fixture with the first test chamber siding or the second test chamber siding and
The wave system that reference probe position should be such that it generates is from influencing model air-flow flowing nearby.
6. using the measuring method of any one of preceding claims 1 ~ 5 experimental rig, which is characterized in that including walking as follows
It is rapid:
A, before test, measurement probe is located at first and stays interior, and model to be measured is located at second and stays interior, the first test section turnover panel, the
Two test section turnover panels remain turned-off respectively；
B, after temporarily rushing formula supersonic wind tunnel supersonic flow field and establishing, the first test section turnover panel, the second test section turnover panel are beaten respectively
It opens, measurement probe, which is stayed in room by the first freedom degree actuating mechanism from first, to be stretched out, and model to be measured is acted by the second freedom degree
Mechanism stays in room from second stretches out；
C, measurement probe by the first freedom degree actuating mechanism, model to be measured by the second freedom degree actuating mechanism be separately operable to
After temporarily rushing the initial trial position of formula supersonic wind tunnel test section, the first test section turnover panel, the second test section turnover panel are closed；
D, according to given trystate, change model attitude to be measured, and start to test according to given test method；
E, after the test, the first test section turnover panel, the second test section turnover panel are opened, and measurement probe is acted by the first freedom degree
Mechanism is recovered to first and stays interior, and model to be measured is recovered to second by the second freedom degree actuating mechanism and stays interior, and turnover panel is closed；
F, it temporarily rushes formula supersonic wind tunnel to cut-off, completes test.
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