CN208476493U - Aeroelastic effect wind tunnel test half model system - Google Patents
Aeroelastic effect wind tunnel test half model system Download PDFInfo
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- CN208476493U CN208476493U CN201820259095.2U CN201820259095U CN208476493U CN 208476493 U CN208476493 U CN 208476493U CN 201820259095 U CN201820259095 U CN 201820259095U CN 208476493 U CN208476493 U CN 208476493U
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Abstract
The utility model provides a kind of aeroelastic effect wind tunnel test half model system, and the aeroelastic effect wind tunnel test half model system includes: the half model being arranged in wind-tunnel and the measuring device that is arranged on the outside of wind-tunnel siding；The half model includes main body and pneumatic aerofoil, the main body is additionally provided with thickened section in the side towards the wind-tunnel siding of the plane of symmetry, for the thickened section close to the wind-tunnel siding, the thickened section is used for the boundary layer thickness for making the spacing between the plane of symmetry and the wind-tunnel siding more than or equal to the wind-tunnel；The measuring device is used to measure the aeroelastic effect effect on the pneumatic aerofoil.Aeroelastic effect wind tunnel test half model system provided by the utility model can be effectively isolated sidewall layer and eliminate gap channelling to the aerodynamic interference of half model, and practicability and economy are high.
Description
Technical field
The utility model relates to wind tunnel test technical field more particularly to a kind of aeroelastic effect wind tunnel test half model systems
System.
Background technique
Aeroelastic effect is that aircraft generates flexible deformation under aerodynamic effect and its aerodynamic characteristic is caused to change
A kind of phenomenon.Aeroelastic effect has larger impact to aerodynamic characteristics of vehicle, may change of flight device geometric shape, influence
The rudder effectiveness and control and stability of aircraft cause lifting surface diverging phenomena such as aerofoil destruction occur.Therefore, pass through experimental study
The aeroelastic effect of aircraft is very necessary.It can be with the aeroelastic effect of exploratory flight device, due to flying by high wind tunnel testing
The Flow Field of row device is symmetrical, therefore has developed half model test method, with the generally object of aircraft, is studied whole
The Longitudinal Aerodynamic Characteristics of a aircraft.Half model test method is haveed the shortcomings that obvious: since half model is longitudinally asymmetric face
It is installed close to wind-tunnel siding, the low speed, low energy air-flow in sidewall layer can impact the test result of half model, and
And when dynamometer check, there are certain gap between the longitudinally asymmetric face of model and hole wall, there must be air-flow to flow through in gap, it is this to alter
Stream can also impact test result.
In the prior art, sidewall layer pair is excluded by model pad method, boundary layer suction method or boundary layer blowing-off method
The interference of half model test method.Fig. 1 is the structural schematic diagram of the half model system for the model pad method that the prior art provides, with reference to figure
Shown in 1, model pad method refers to the cushion block 13 that an equal thickness is encased inside between the plane of symmetry and wind-tunnel siding 12 of half model 11, cushion block
13 are fixed on rotation window 14, and half model 11 is connect by connector 16 with force balance 15, the rotation rotation of window 14 changeable half
The angle of attack of model 11, the setting of cushion block 13 reduce the influence of the low kinetic energy, low flow velocity region of sidewall layer to test result.
Fig. 2 is the structural schematic diagram of the half model system for the boundary layer suction method that the prior art provides, refering to what is shown in Fig. 2, boundary layer is taken out
Suction method is by being arranged getter device 22 in the upstream of half model 21, by 21 place of the half model and its boundary Dong Bi of near zone
Layer is all or part of to be absorbed, and wherein the plane of symmetry of half model 21 is arranged close to wind-tunnel siding 23, and half model 21 passes through connector 24
It is connect with force balance 25, rotation window 26 rotates the angle of attack of changeable half model 21, and getter device 22 inhales the boundary layer of hole wall
It removes, to eliminate or mitigate influence of the boundary layer to test result.Fig. 3 is the half model for the boundary layer blowing-off method that the prior art provides
The structural schematic diagram of system, refering to what is shown in Fig. 3, boundary layer blowing-off method is by passing through blowning installation in the upstream of half model 31
32 are blown into high pressure draught into boundary layer along the wall surface of wind-tunnel siding 33, air-flow velocity are improved, so that boundary layer is thinning, to subtract
Small boundary layer low energy flows the influence to half model test result, and wherein the plane of symmetry of half model 31 is set close to wind-tunnel siding 33
It sets, half model 31 is connect by connector 34 with force balance 35, and rotation window 36 rotates the angle of attack of changeable half model 31.
In model pad method, due between the plane of symmetry and cushion block 13 of half model 11 with the gap of one fixed width, in gap
Channelling can interfere the Characteristics of Flow Around around half model 11, and test result is caused to be distorted.And when using boundary layer suction method, air-breathing dress
The air-breathing rate for setting 22 wants sufficiently large, just can guarantee that the boundary layer of hole wall is fallen in sufficiently suction, for longer half model, it is necessary to
Getter device 22 is all respectively set in the preceding posterior segment of half model, could equably absorb boundary layer, while not influencing the stream of mainstream
It is dynamic.When using boundary layer blowing-off method, selects suitable blowning installation 23 and determine suitable blow gas pressure and air-blowing quantity, make height
Pressure gas stream can be equably blown into, and enable the flow velocity in boundary layer to be close or equal to but be no more than mainstream speed, technology is difficult
Degree is higher, and has limitation to the geometric dimension of half model.
Utility model content
The utility model provides a kind of aeroelastic effect wind tunnel test half model system, can be effectively isolated sidewall layer and
Gap channelling is eliminated to the aerodynamic interference of half model, and practicability and economy are high.
The utility model provides a kind of aeroelastic effect wind tunnel test half model system, comprising: is arranged in half in wind-tunnel
Model and the measuring device being arranged on the outside of wind-tunnel siding；
The half model includes main body and pneumatic aerofoil, and the main body is in the side towards the wind-tunnel siding of the plane of symmetry
It is additionally provided with thickened section, the thickened section is close to the wind-tunnel siding, and the thickened section is for making the plane of symmetry and the wind
Spacing between the siding of hole is greater than or equal to the boundary layer thickness of the wind-tunnel；
The measuring device is used to measure the aeroelastic effect effect on the pneumatic aerofoil.
Aeroelastic effect wind tunnel test half model system provided by the embodiment of the utility model is avoided by the way that thickened section is arranged
Wind tunnel side wall boundary layer and gap channelling only measure gas to the adverse effect of aeroelastic effect half-modcl test, simultaneous measuring apparatus
The aerodynamic force that dynamic aerofoil is subject to, therefore can accurately measure the aeroelastic effect of the pneumatic aerofoil of half model；And compared to tradition
Boundary layer suction method and boundary layer blowing-off method, do not need the complicated air-breathing of setting or blowning installation, economy is high, and structure letter
It is single, technical problem is not present, it is easily operated, to the geometric dimension of half model also there is no limit；The setting of half model and half module
The measurement method of the pneumatic aerofoil of type is easily achieved, and is applicable to different types of half model, practical.
Further, the thickened section perpendicular on wind-tunnel siding direction thickness and the boundary layer thickness phase
Deng.
Further, the profile of the thickened section is identical with the shape of the plane of symmetry.
Further, the measuring device includes rotation window, force balance and connector；The rotation window and the main body
It is fixedly connected, the force balance is connect by the connector with the pneumatic aerofoil, the force balance and the rotation
Window connection.
Further, the first avoid holes are provided in the main body, the connector passes through first avoid holes and institute
State pneumatic aerofoil connection.
Further, be provided with the second avoid holes on the rotation window, the connector pass through second avoid holes and
First avoid holes are connect with the pneumatic aerofoil.
Further, interval setting between the connector and the rotation window, the main body.
Further, there is gap between the main body and the pneumatic aerofoil.
Further, the rotation curtain heading tape moves the half model, the force balance and connector rotation.
Further, the rotation window is driven by driving device.
Aeroelastic effect wind tunnel test half model system provided by the embodiment of the utility model is avoided by the way that thickened section is arranged
Wind tunnel side wall boundary layer and gap channelling only measure gas to the adverse effect of aeroelastic effect half-modcl test, simultaneous measuring apparatus
The aerodynamic force that dynamic aerofoil is subject to, therefore can accurately measure the aeroelastic effect of the pneumatic aerofoil of half model；And compared to tradition
Boundary layer suction method and boundary layer blowing-off method, do not need the complicated air-breathing of setting or blowning installation, economy is high, and structure letter
It is single, technical problem is not present, it is easily operated, to the geometric dimension of half model also there is no limit；The setting of half model and half module
The measurement method of the pneumatic aerofoil of type is easily achieved, and is applicable to different types of half model, practical；It is rotated by control
The angle of attack of the changeable half model of the rotation of window can directly measure the aerodynamic force that pneumatic aerofoil is subject to, structure letter by force balance
It is single, it is easy to accomplish.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is
Some embodiments of the utility model, for those of ordinary skill in the art, in the premise of not making the creative labor property
Under, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is the structural schematic diagram of the half model system for the model pad method that the prior art provides；
Fig. 2 is the structural schematic diagram of the half model system for the boundary layer suction method that the prior art provides；
Fig. 3 is the structural schematic diagram of the half model system for the boundary layer blowing-off method that the prior art provides；
Fig. 4 is the structural schematic diagram of aeroelastic effect wind tunnel test half model system provided by the embodiment of the utility model.
Appended drawing reference:
11- half model 12- wind-tunnel siding
13- cushion block 14- rotates window
15- force balance 16- connector
21- half model 22- getter device
23- wind-tunnel siding 24- connector
25- force balance 26- rotates window
31- half model 32- blowning installation
33- wind-tunnel siding 34- connector
35- force balance 36- rotates window
41- half model 411- main body
The pneumatic aerofoil of 4111- the first avoid holes 412-
413- thickened section 42- measuring device
421- rotates the second avoid holes of window 4211-
422- force balance 423- connector
43- wind-tunnel siding
Specific embodiment
To keep the purpose of this utility model, technical solution and advantage clearer, below in conjunction in the utility model
The technical solution in the utility model is clearly and completely described in attached drawing, it is clear that described embodiment is that this is practical
Novel a part of the embodiment, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, belongs to the model of the utility model protection
It encloses.
Fig. 4 is the structural schematic diagram of aeroelastic effect wind tunnel test half model system provided by the embodiment of the utility model,
Refering to what is shown in Fig. 4, the utility model embodiment provides a kind of aeroelastic effect wind tunnel test half model system, comprising: setting exists
Half model 41 in wind-tunnel and the measuring device 42 that 43 outside of wind-tunnel siding is set；
Half model 41 includes main body 411 and pneumatic aerofoil 412, and main body 411 is in the plane of symmetry towards the one of wind-tunnel siding 43
Side is additionally provided with thickened section 413, and thickened section 413 is close to wind-tunnel siding 43, and thickened section 413 is for making the plane of symmetry and wind-tunnel siding 43
Between spacing be greater than or equal to wind-tunnel boundary layer thickness；
Measuring device 42 is used to measure the aeroelasticity on pneumatic aerofoil 412.
In the utility model embodiment, the setting of thickened section 413 is so that the exact shape of half model 41 is in wind-tunnel siding
Except 43 boundary layers and the zone of influence of gap channelling, this is equivalent to increases one between half model 41 and wind-tunnel siding 43
" cushion block ", but should " cushion block " and half model 41 be it is integrated, such design can be to avoid in " cushion block " and true half model 41
Between form new gap, eliminate the influence for the gap channelling that traditional model pad method generates.
Meanwhile measuring device 42 is only used for measuring the aeroelasticity of pneumatic aerofoil 412, it is meant that the main body of half model 41
411 and pneumatic aerofoil 412 be detached from setting, main body 411, which is only used for providing for pneumatic aerofoil 412, really streams, measurement fill
It sets 42 and does not measure the aerodynamic force that main body 411 is subject to, and only measure the aerodynamic force that pneumatic aerofoil 412 is subject to.Since thickened section 413 increases
The thickness for having added the main body 411 of half model 41 causes the shape of half model 41 to be distorted, if according to conventional half model dynamometry side
The aerodynamic force that the main body 411 of half model 41 and pneumatic aerofoil 412 are subject to is measured together, will lead to the distortion of measurement result by formula.
Therefore, setting measuring device 42 only measures the aeroelasticity of pneumatic aerofoil 412, can eliminate the negative effect of 413 bring of thickened section,
Obtain the aerodynamic data of more accurate pneumatic aerofoil 412.
Specifically, impact of the half model 41 by high-speed flow in wind-tunnel is set, and setting is in 43 outside of wind-tunnel siding
Measuring device 42 streaming for half model 41 will not be impacted, simultaneous measuring apparatus 42, which also has, to be changed half model 41 and meeting
Angle has obtained the aeroelasticity value of pneumatic aerofoil 412 under the air-flow of different angle.
In addition, thickened section 413 is used for the boundary for making the spacing between the plane of symmetry and wind-tunnel siding 43 more than or equal to wind-tunnel
Thickness degree, the boundary layer thickness of wind-tunnel depend on the behavior of boundary layer of wind-tunnel, structure, drive manner and air-flow stagnation pressure with wind-tunnel
Etc. characteristics it is related, and change with the change of test method and condition.The thickness in boundary layer generally within 50 millimeters, because
The thickness of this thickened section 413 is also at 50 millimeters or so, compared to the length dimension of half model 41, the thickness very little of thickened section 413,
Influence to the distortion of the shape of half model 41 is smaller, but thickened section 413 is to being separated out boundary layer to weaken boundary layer to half model
The influence of 41 test result has a significant effect.
In this example, with no restriction to the specific type and shape of half model 41.Half model 41 can be aircraft class half module
Type, main body is the fuselage of aircraft at this time, and pneumatic aerofoil is the wing or empennage of aircraft；Half model 41 or guided missile class half
Model, main body is the bomb body of guided missile at this time, and pneumatic aerofoil is the missile wing of guided missile.Meet based on half model 41 and pneumatic aerofoil
Structure type, while the purpose of aeroelastic effect wind tunnel test is the condition in order to obtain the aeroelastic effect data of pneumatic aerofoil
?.
Aeroelastic effect wind tunnel test half model system provided by the embodiment of the utility model is avoided by the way that thickened section is arranged
Wind tunnel side wall boundary layer and gap channelling only measure gas to the adverse effect of aeroelastic effect half-modcl test, simultaneous measuring apparatus
The aerodynamic force that dynamic aerofoil is subject to, therefore can accurately measure the aeroelastic effect of the pneumatic aerofoil of half model；And compared to tradition
Boundary layer suction method and boundary layer blowing-off method, do not need the complicated air-breathing of setting or blowning installation, economy is high, and structure letter
It is single, technical problem is not present, it is easily operated, to the geometric dimension of half model also there is no limit；The setting of half model and half module
The measurement method of the pneumatic aerofoil of type is easily achieved, and is applicable to different types of half model, practical.
On the basis of the above embodiments, thickened section 413 perpendicular on 43 direction of wind-tunnel siding thickness and boundary layer
Thickness is equal.The boundary layer thickness of wind-tunnel depends on the behavior of boundary layer of wind-tunnel, total with the structure of wind-tunnel, drive manner and air-flow
The characteristics such as pressure are related, and the change of test method and condition also has an impact to boundary layer thickness.It, can be according to wind when practical operation
Hole characteristic calculates theoretic boundary layer thickness so that thickened section 413 perpendicular on 43 direction of wind-tunnel siding thickness with
The boundary layer thickness is equal, and thickened section 413 can be separated out boundary layer to weaken boundary layer to the test result of half model 41.If thickening
The thickness in portion 413 is less than boundary layer thickness, then boundary layer still has larger impact to the test result of half model 41；If thickening
The thickness in portion 413 is greater than boundary layer thickness, and it is more serious that thickened section 413 causes the model of half model 41 to be distorted, to influence to test
As a result, the blocked up waste that will also result in cast material of thickened section 413 simultaneously.
In order to further avoid negative effect of the distortion of model caused by thickened section 413 to test result, thickened section 413
Profile is identical with the shape of the plane of symmetry.If the profile of thickened section 413 is different from the shape of the plane of symmetry, half model 41 will be caused
There are a great differences for Characteristics of Flow Around and the Characteristics of Flow Around of realistic model, seriously inaccurate so as to cause test result.Work as thickened section
When 413 profile is identical with the shape of the plane of symmetry, thickened section 413 only thickness be distorted, caused by negatively affect it is smaller, and survey
Amount device only measures the aerodynamic force of pneumatic aerofoil, eliminates the negative effect to a certain extent.
Specifically, measuring device 42 includes rotation window 421, force balance 422 and connector 423；Rotate window 421 and main body
411 are fixedly connected, and force balance 422 is connect by connector 423 with pneumatic aerofoil 412, force balance 422 and rotation window 421
Connection.
Rotation window 421, to change the angle of attack of half model 41 Yu air-flow, obtains the different angles of attack for driving half model 41 to rotate
Under aeroelastic effect data.In the present embodiment, rotation window 421 is fixedly connected with main body 411, and pneumatic aerofoil 412 passes through connection
Part 423 is connect with force balance 422, i.e., main body 411 is not connected to pneumatic aerofoil 412, and force balance 422 only measures pneumatic aerofoil
412 aerodynamic force.Since force balance 422 is connect with rotation window 421, rotation window 421 drives force balance 422 to rotate, into one
Step drives the rotation of pneumatic aerofoil 412, and then ensure that main body 411 and pneumatic 412 synchronous rotary of aerofoil, and main body 411 is pneumatic
Aerofoil 412, which provides, really to stream.
It is separately positioned for realization body 411 and pneumatic aerofoil 412, it needs to be provided with the first evacuation in main body 411
Hole 4111, connector 423 pass through the first avoid holes 4111 and connect with pneumatic aerofoil 412.
The size of first avoid holes 4111 should be sufficient to accommodate connector 423 completely, and connector 423 passes through the first avoid holes
4111 connect with pneumatic aerofoil 412, and connector 423 is not contacted with main body 411.First avoid holes 4111 cannot be excessive, otherwise
The whole weight imbalance of half model 41 may result in the measurement result distortion of aeroelastic effect.
Further, it rotates and is provided with the second avoid holes 4211 on window 421, connector 423 passes through the second avoid holes 4211
It is connect with the first avoid holes 4111 with pneumatic aerofoil 412.Force balance 422 is connect by connector 423 with pneumatic aerofoil 412,
Since the setting of force balance 422 is in rotation window 421, rotates and be provided with the second avoid holes 4211 on window 421, in order to even
Fitting 423 passes through.First avoid holes 4111 and the second avoid holes 4211 are answering phase perpendicular to the cross sectional shape on wind-tunnel siding 43
Together, the size of the second avoid holes 4211 should be sufficient to accommodate connector 423 completely, while connector 423 does not connect with rotation window 421
Touching.
To guarantee to measure the correctness of load, interval is arranged between connector 423 and rotation window 421, main body 411, i.e.,
Connector 423 and rotation window 421, between main body 411 should there are certain gaps, to guarantee under the action of aerodynamic loading, even
Fitting 423 will not be in contact with rotation window 421, main body 411, and connector 423 is avoided to test with rotation window 421, main body 411
The aerodynamic data mistake that making contact causes measuring device 42 to measure in the process.
In addition, there is gap between main body 411 and pneumatic aerofoil 412.Since half module aeroelastic effect test may not necessarily
The aerodynamic force that measurement main body 411 is subject to, it is only necessary to measure the aerodynamic force that pneumatic aerofoil 412 is subject to, therefore main body 411 and pneumatic aerofoil
There is certain gap between 412, to guarantee under the action of aerodynamic loading, will not be deposited between main body 411 and pneumatic aerofoil 412
It is contacting, thus the aerodynamic data mistake for the pneumatic aerofoil 412 for avoiding measuring device 42 from measuring.
Gap and main body 411 in actual mechanical process, between above-mentioned connector 423 and rotation window 421, main body 411
Gap value between pneumatic aerofoil 412 is in 2-3 millimeters or so.
During test, rotation window 421 drives half model 41, force balance 422 and connector 423 to rotate.Rotate window 421
It can be driven and be rotated by driving device, under the driving force effect of driving device, rotation window 421 drives main body 411 to rotate, together
When rotation window 421 drive force balance 422 rotate, be further driven to the rotation of pneumatic aerofoil 412, and then ensure that main body 411
With pneumatic 412 synchronous rotary of aerofoil.
Aeroelastic effect wind tunnel test half model system provided by the embodiment of the utility model is avoided by the way that thickened section is arranged
Wind tunnel side wall boundary layer and gap channelling only measure gas to the adverse effect of aeroelastic effect half-modcl test, simultaneous measuring apparatus
The aerodynamic force that dynamic aerofoil is subject to, therefore can accurately measure the aeroelastic effect of the pneumatic aerofoil of half model；And compared to tradition
Boundary layer suction method and boundary layer blowing-off method, do not need the complicated air-breathing of setting or blowning installation, economy is high, and structure letter
It is single, technical problem is not present, it is easily operated, to the geometric dimension of half model also there is no limit；The setting of half model and half module
The measurement method of the pneumatic aerofoil of type is easily achieved, and is applicable to different types of half model, practical；It is rotated by control
The angle of attack of the changeable half model of the rotation of window can directly measure the aerodynamic force that pneumatic aerofoil is subject to, structure letter by force balance
It is single, it is easy to accomplish.
Aeroelastic effect wind tunnel test half model system as described above, aeroelastic effect wind tunnel test half model test
Method, comprising:
Change the angle of attack of half model 41；
Under the default angle of attack, the aerodynamic force that pneumatic aerofoil 412 is subject to is measured.
Specifically, the angle of attack of half model 41 is realized by the rotation of rotation window 421；In the driving force effect of driving device
Under, rotation window 421 drives main body 411 to rotate, while rotating window 421 and force balance 422 is driven to rotate, and is further driven to airvane
The rotation in face 412, and then ensure that main body 411 and pneumatic 412 synchronous rotary of aerofoil, main body 411 is that pneumatic aerofoil 412 provides very
Real streams.
The angle of attack determine in the case where, by force balance 422 can be readily available pneumatic aerofoil 412 be subject to it is pneumatic
Power.Since force balance 422 is only directly connect with pneumatic aerofoil 412, pneumatic aerofoil 412 and main body 411 are separately positioned, therefore survey
The data that power balance 422 measures do not include the aerodynamic force of main body 411, and measurement result is accurate and reliable.
The test method of the aeroelastic effect wind tunnel test half model avoids wind by the way that thickened section is arranged on half model
Hole sidewall boundary layer and gap channelling only measure pneumatically the adverse effect of aeroelastic effect half-modcl test, simultaneous measuring apparatus
The aerodynamic force that aerofoil is subject to, therefore can accurately measure the aeroelastic effect of the pneumatic aerofoil of half model；And compared to traditional
Boundary layer suction method and boundary layer blowing-off method do not need the complicated air-breathing of setting or blowning installation, and economy is high, and structure letter
It is single, technical problem is not present, it is easily operated, to the geometric dimension of half model also there is no limit；The setting of half model and half module
The measurement method of the pneumatic aerofoil of type is easily achieved, and is applicable to different types of half model, practical；It is rotated by control
The angle of attack of the changeable half model of the rotation of window can directly measure the aerodynamic force that pneumatic aerofoil is subject to, method letter by force balance
It is single, it is easy to accomplish.
In the description of the present invention, it should be understood that used term " center ", " length ", " width ",
" thickness ", " top ", " bottom end ", "upper", "lower", "left", "right", "front", "rear", "vertical", "horizontal", "inner", "outside" " axis
To ", the indicating positions such as " circumferential direction " or positional relationship be to be based on the orientation or positional relationship shown in the drawings, be merely for convenience of describing
The utility model and simplified description, rather than the position of indication or suggestion meaning or original part must have a particular orientation, with spy
Fixed construction and operation, therefore should not be understood as limiting the present invention.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include one or more of the features.In the description of the present invention, the meaning of " plurality " is at least two, example
Such as two, three, unless otherwise specifically defined.
In the present invention unless specifically defined or limited otherwise, term " installation ", " connected ", " connection ", " Gu
It is fixed " etc. shall be understood in a broad sense, such as may be a fixed connection, may be a detachable connection, or be integrally formed；It can be machinery
Connection is also possible to be electrically connected or can communicate with each other；It can be directly connected, the indirect phase of intermediary can also be passed through
Even, the connection inside two elements or the interaction relationship of two elements can be made.For those of ordinary skill in the art
For, the concrete meaning of above-mentioned term in the present invention can be understood as the case may be.
In the present invention unless specifically defined or limited otherwise, fisrt feature the "upper" of second feature or it
"lower" may include that the first and second features directly contact, and also may include that the first and second features are not direct contacts but lead to
Cross the other characterisation contact between them.Moreover, fisrt feature includes above the second feature " above ", " above " and " above "
One feature is right above second feature and oblique upper, or is merely representative of first feature horizontal height higher than second feature.First is special
Sign is directly below and diagonally below the second feature including fisrt feature under the second feature " below ", " below " and " below ", or only
Indicate that first feature horizontal height is less than second feature.
Finally, it should be noted that the above various embodiments is only to illustrate the technical solution of the utility model, rather than it is limited
System；Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should
Understand: it is still possible to modify the technical solutions described in the foregoing embodiments, or to some or all of
Technical characteristic is equivalently replaced；And these are modified or replaceed, it does not separate the essence of the corresponding technical solution, and this is practical new
The range of each embodiment technical solution of type.
Claims (10)
1. a kind of aeroelastic effect wind tunnel test half model system characterized by comprising be arranged in half model in wind-tunnel and
Measuring device on the outside of wind-tunnel siding is set；
The half model includes main body and pneumatic aerofoil, and the main body is also set in the side towards the wind-tunnel siding of the plane of symmetry
It is equipped with thickened section, the thickened section is close to the wind-tunnel siding, and the thickened section is for making the plane of symmetry and the wind-tunnel wall
Spacing between plate is greater than or equal to the boundary layer thickness of the wind-tunnel；
The measuring device is used to measure the aeroelasticity on the pneumatic aerofoil.
2. half model system according to claim 1, which is characterized in that the thickened section is perpendicular to the wind-tunnel siding
Thickness on direction is equal with the boundary layer thickness.
3. half model system according to claim 2, which is characterized in that the profile of the thickened section and the plane of symmetry
Shape is identical.
4. half model system according to claim 1, which is characterized in that the measuring device includes rotation window, dynamometry day
Gentle connector；The rotation window is fixedly connected with the main body, and the force balance passes through the connector and described pneumatic
Aerofoil connection, the force balance are connect with the rotation window.
5. half model system according to claim 4, which is characterized in that be provided with the first avoid holes, institute in the main body
Connector is stated to connect across first avoid holes with the pneumatic aerofoil.
6. half model system according to claim 5, which is characterized in that the second avoid holes are provided on the rotation window,
The connector passes through second avoid holes and first avoid holes are connect with the pneumatic aerofoil.
7. half model system according to claim 6, which is characterized in that the connector and the rotation window, the master
Interval setting between body.
8. half model system according to claim 7, which is characterized in that have between the main body and the pneumatic aerofoil
Gap.
9. half model system according to claim 6, which is characterized in that the rotation curtain heading tape moves the half model, described
Force balance and connector rotation.
10. half model system according to claim 9, which is characterized in that the rotation window is driven by driving device.
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| CN201820259095.2U CN208476493U (en) | 2018-02-14 | 2018-02-14 | Aeroelastic effect wind tunnel test half model system |
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| CN201820259095.2U CN208476493U (en) | 2018-02-14 | 2018-02-14 | Aeroelastic effect wind tunnel test half model system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108303227A (en) * | 2018-02-14 | 2018-07-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Aeroelastic effect wind tunnel test half model system and test method |
| CN114323540A (en) * | 2021-12-01 | 2022-04-12 | 中国空气动力研究与发展中心低速空气动力研究所 | Half-mode blowing lift-increasing wind tunnel test method and device for conveyor |
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2018
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108303227A (en) * | 2018-02-14 | 2018-07-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Aeroelastic effect wind tunnel test half model system and test method |
| CN108303227B (en) * | 2018-02-14 | 2024-04-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Static aeroelastic wind tunnel test semi-model system and test method |
| CN114323540A (en) * | 2021-12-01 | 2022-04-12 | 中国空气动力研究与发展中心低速空气动力研究所 | Half-mode blowing lift-increasing wind tunnel test method and device for conveyor |
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