CN109186922A - A kind of wind tunnel test methods of helicopter co-axis double propeller hub model - Google Patents
A kind of wind tunnel test methods of helicopter co-axis double propeller hub model Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a kind of wind tunnel test methods of helicopter co-axis double propeller hub model, belong to propeller hub wind tunnel test methods field, can carry out big advance than coaxial double-rotary wing propeller hub model flow mechanism and pneumatic interference test.Testing stand is installed in wind-tunnel first, and passes through the coaxial synchronous return motion of testing stand implementation model；Then the level of vibration of testing stand, and the dynamic characteristic of development test platform are monitored in real time by vibration monitoring system；By the six power element of box type balance measurement model, by the flow field of PIV flow field survey systematic survey model, by electronic scanning pressure system or the surface pressing of pressure sensor measurement model；During test, the component of coaxial double-rotary wing propeller hub model can be replaced as needed, the aerodynamic characteristic of the model to study different shapes or different flowing control modes；Finally obtain the aerodynamic characteristic of the model.The present invention solves the problems, such as the aerodynamic characteristic measurement of the coaxial double-rotary wing propeller hub model of rotation.
Description
Technical field
The present invention relates to propeller hub wind tunnel test methods field, more particularly to study rotatable, different propeller hub shapes with
And apply the wind tunnel test methods of the coaxial double-rotary wing propeller hub model of flow control technique.
Background technique
Coaxial rigid rotor technology can significantly improve the flying speed of helicopter, but there are two direction of rotation for its rotor hub system
Opposite propeller hub, complex contour, and higher than common rotor hub, separated after by rotor wake, rotor shaft stream influenced it is serious,
Its resistance usually accounts for 50% or so of full machine resistance, and big propeller hub resistance is that the coaxial rigid rotor high-speed helicopter maximum of limitation flies
An important factor for scanning frequency degree and ultimate run are promoted, therefore, reduces coaxial rigid rotor system propeller hub resistance, is to realize that the type is straight
One of the critical issue that the machine of liter high speed, big voyage must solve.
However, since the country is in the starting stage to the research of coaxial rigid rotor propeller hub, though carry out simple wind
Hole experimental study, such as " the coaxial rigid rotor helicopter hub drag characteristic test of the such as He Long, Wang Chang, Tang Min Nanjing [J] boat
Empty space flight college journal, 2016,48 (4): 530-535.(DOI:10.16356/j.1005-2615.2016.04.013) ", but
It is that the wind tunnel test has the disadvantage that propeller hub moulded dimension is less than normal, and revolving speed is low, test Reynolds number is less than normal, and test result accuracy is not
Height, and it is only capable of measuring whole aerodynamic force, it is unable to the aerodynamic force of independent measurement difference component；Between test model component gap compared with
Greatly, its propeller hub exact shape is caused not to be inconsistent with aerodynamic configuration；System, propeller hub shape only do not include that upper and lower propeller hub is whole to test method
Stream cover+and without jackshaft radome fairing+tower seat, upper and lower rotor hub fairing system+jackshaft radome fairing+tower seat does not include upper and lower propeller hub+nothing
The case where jackshaft radome fairing, blade root and application flow control technique, and model attitude angle only has (pitch angle, side
Sliding angle, roll angle are 0 °)；Test measurement content only includes dynamometry and model surface FLOW VISUALIZATION, does not include PIV space flow field
Surface pressure measurement between measurement and component.
Summary of the invention
The technical problem to be solved by the present invention is to be directed to the defect of background technique, " a kind of DCB Specimen is same based on existing
Walk inversion set " (Publication No. 206074222U, publication date 2017-4-5), it is coaxial double to establish a kind of full-scale helicopter
The wind tunnel test methods of rotor hub model are beneficial to carry out coaxial double-rotary wing comprehensively in the case where ensuring to test safety
The pneumatic research of propeller hub, while improving test result accuracy.
The present invention uses following technical scheme to solve above-mentioned technical problem:
A kind of wind tunnel test methods of helicopter co-axis double propeller hub model, specifically comprise the following steps:
Step 1, coaxial double-rotary wing propeller hub rig for model test is installed in wind-tunnel, and passes through coaxial double-rotary wing propeller hub model test
The coaxial synchronous return motion of platform realization coaxial double-rotary wing propeller hub model；
Step 2, it monitors the level of vibration of coaxial double-rotary wing propeller hub rig for model test in real time by vibration monitoring system, carries out ground
Resonance analyzing and testing stand row's vibration work, guarantee not resonate when propeller hub model test；
Step 3, by the six power element of box type balance systematic survey coaxial double-rotary wing propeller hub model, pass through PIV flow field survey system
The flow field for measuring coaxial double-rotary wing propeller hub model, obtains each of coaxial double-rotary wing propeller hub model by surface pressure measurement systematic survey
The surface pressing of component；
Step 4, as needed replacement coaxial double-rotary wing propeller hub model component, using step 1 to step 3 obtain different shapes or
The aerodynamic characteristic of the coaxial double-rotary wing propeller hub model of difference flowing control mode；
Step 5, the aerodynamic characteristic of the coaxial double-rotary wing propeller hub model is obtained.
As a kind of further preferred scheme of the wind tunnel test methods of helicopter co-axis double propeller hub model of the present invention,
In step 3, the box type balance system is the force snesor that can measure six power element of coaxial double-rotary wing propeller hub model, and the power passes
Sensor is fixedly mounted on the bottom of coaxial double-rotary wing propeller hub rig for model test.
As a kind of further preferred scheme of the wind tunnel test methods of helicopter co-axis double propeller hub model of the present invention,
The PIV flow field survey system is by particle seeding device, illumination laser, isochronous controller, digital camera and data processing system
System composition, wherein particle seeding device, illumination laser, digital camera pass through measurement respectively and obtain data, and isochronous controller is used for
It is transmitted in data processing system after data are synchronized, obtains the flow field velocity cloud atlas and streamline in different tests state flow field section
Figure.
As a kind of further preferred scheme of the wind tunnel test methods of helicopter co-axis double propeller hub model of the present invention,
The surface pressure measurement system is made of pressure tap, pressure sensor and data processing system, and wherein pressure sensor is set
It sets in pressure tap, data transfer is obtained to the surface of each component of coaxial double-rotary wing propeller hub model into data processing system
Pressure.
As a kind of further preferred scheme of the wind tunnel test methods of helicopter co-axis double propeller hub model of the present invention,
The vibration monitoring system is made of acceleration transducer, kinetic analyzer, and wherein acceleration transducer is tested measurement
The acceleration information of platform is transmitted to kinetic analyzer, to obtain the level of vibration of coaxial double-rotary wing propeller hub rig for model test.
As a kind of further preferred scheme of the wind tunnel test methods of helicopter co-axis double propeller hub model of the present invention,
The coaxial double-rotary wing propeller hub model revolving speed is 0 ~ 3000rpm, and wind speed is 0 ~ 300m/s, and pitch angle is -15 ° ~ 15 °, yaw angle
It is -180 ° ~ 180 °, roll angle is -15 ° ~ 15 °.
As a kind of further preferred scheme of the wind tunnel test methods of helicopter co-axis double propeller hub model of the present invention,
The component for replacing coaxial double-rotary wing propeller hub model as needed in step 4, so that the coaxial double-rotary wing propeller hub mode shape
Specifically include following several structures: upper and lower propeller hub+tower seat, upper and lower rotor hub fairing system+tower seat, upper and lower rotor hub fairing system+blade root
+ tower seat, upper and lower rotor hub fairing system+jackshaft radome fairing+tower seat, or upper and lower rotor hub fairing system+blade root+jackshaft radome fairing
+ tower seat；Wherein, the upper and lower rotor hub fairing system is oval revolving body, and the cross section of jackshaft radome fairing is aerofoil profile shape, tower
Seat is the radome fairing with streamline shape that can wrap up retarder.
As a kind of further preferred scheme of the wind tunnel test methods of helicopter co-axis double propeller hub model of the present invention,
In step 4, the flowing control includes passive flowing control and active Flow Control；Passive flowing control includes vortex
Device flowing control, Gurney wing flap (GF) flowing control and groove flowing control；Active Flow Control includes blowing/inspiratory flow
Dynamic control, synthesizing jet-flow flowing control, plasma flow control.
As a kind of further preferred scheme of the wind tunnel test methods of helicopter co-axis double propeller hub model of the present invention,
Increase blade root on rotor hub fairing system, to obtain influence of the rotor blade root to different propeller hub model aerodynamic characteristics.
As a kind of further preferred scheme of the wind tunnel test methods of helicopter co-axis double propeller hub model of the present invention,
The jackshaft radome fairing does not rotate, and does not contact with upper and lower propeller hub, can increase force snesor inside it, individually to survey
Measure its aerodynamic loading；Increased separately in the inner barrel and outer barrel of the coaxial double-rotary wing propeller hub rig for model test elastic coupling and
Torsion balance can measure the required horsepower when rotation of upper and lower propeller hub respectively.
The invention adopts the above technical scheme compared with prior art, has following technical effect that
Test model of the present invention be it is full-scale, it is suitable with the Reynolds number of true helicopter；Dynamometry and surface flow can not only be carried out
Display measurement, the space flow field quantitative measurment and model surface pressure measurement of the coaxial double-rotary wing propeller hub that can be also rotated；It can
The aerodynamic characteristic measurement for carrying out different propeller hub postures and flowing control, is carried out outside coaxial rigid rotor high-speed helicopter propeller hub
One of the effective ways of shape optimization.
Detailed description of the invention
Fig. 1 is the flow chart of the wind tunnel test methods of helicopter co-axis double propeller hub model of the invention.
Fig. 2 is the dynamometer check scheme schematic diagram of wind tunnel test methods of the invention.
Fig. 3 is that the rectification of helicopter co-axis double propeller hub model of the present invention (upper and lower propeller hub+tower seat) is illustrated
Figure.
Fig. 4 is the whole of helicopter co-axis double propeller hub model of the present invention (upper and lower rotor hub fairing system+tower seat)
Flow diagram.
Fig. 5 is helicopter co-axis double propeller hub model of the present invention (upper and lower rotor hub fairing system+blade root+tower
Seat) rectification schematic diagram.
Fig. 6 is helicopter co-axis double propeller hub model of the present invention (upper and lower rotor hub fairing system+blade root+centre
Axis radome fairing+tower seat) rectification schematic diagram.
Marked in the figure: 1- wind tunnel test air intake vent, 2- tests turntable, 3- testing stand support stand, 4- balance system, 5- wind
It keeps off, rotor hub fairing system under 6-, the upper rotor hub fairing system of 7-, 8- wind tunnel test air outlet, 9- blade root, 10- jackshaft radome fairing, 11-
Tower seat.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to embodiments and specification
Attached drawing carries out clear, complete description to technical solution of the present invention, it is clear that specific embodiment described herein is only to solve
The present invention is released, is not intended to limit the present invention.
Those skilled in the art can understand that unless otherwise defined, all terms used herein (including skill
Art term and scientific term) there is meaning identical with the general understanding of those of ordinary skill in fields of the present invention.Also
It should be understood that those terms such as defined in the general dictionary should be understood that have in the context of the prior art
The consistent meaning of meaning will not be explained in an idealized or overly formal meaning and unless defined as here.
The present invention proposes a kind of wind tunnel test methods of helicopter co-axis double propeller hub model, specifically includes following step
It is rapid:
Step 1, coaxial double-rotary wing propeller hub rig for model test is installed in wind-tunnel, and passes through coaxial double-rotary wing propeller hub model test
The coaxial synchronous return motion of platform realization coaxial double-rotary wing propeller hub model；The coaxial double-rotary wing propeller hub rig for model test it is specific
Structure is detailed in Publication No. 206074222U, and " a kind of DCB Specimen is synchronous to be inverted the utility model patent that publication date is 2017-4-5
Device ", the testing stand can realize coaxial, synchronous, the synchronized reversion of upper and lower propeller hub.
Step 2, it monitors the level of vibration of coaxial double-rotary wing propeller hub rig for model test in real time by vibration monitoring system, and grinds
Study carefully the vibration characteristics of coaxial double-rotary wing propeller hub rig for model test；
Step 3, by the six power element of box type balance systematic survey coaxial double-rotary wing propeller hub model, pass through PIV flow field survey system
The flow field for measuring coaxial double-rotary wing propeller hub model is pressed by the surface of surface pressure measurement systematic survey coaxial double-rotary wing propeller hub model
Power；
The box type balance system is the force snesor that can measure six power element of coaxial double-rotary wing propeller hub model, and is fixedly mounted on altogether
The bottom of axis DCB Specimen propeller hub rig for model test.
The PIV flow field survey system is by particle seeding device, illumination laser, isochronous controller, digital camera and number
It is formed according to processing system, can measure and obtain the flow field velocity cloud atlas and motion pattern in different tests state flow field section.
Step 4, the component for replacing coaxial double-rotary wing propeller hub model as needed, to study different shapes or different flowings
The aerodynamic characteristic of the coaxial double-rotary wing propeller hub model of control mode；
Step 5, the aerodynamic characteristic of the coaxial double-rotary wing propeller hub model is obtained.
The surface pressure measurement system is by pressure tap and scanning valve, pressure sensor or pressure sensitive paint and data processing
System composition, can measure and obtain the surface pressing of different components.
The vibration monitoring system is made of acceleration transducer, kinetic analyzer.
The coaxial double-rotary wing propeller hub model revolving speed be 0 ~ 3000rpm, wind speed be 0 ~ 300m/s, pitch angle be -15 ° ~
15 °, yaw angle is -180 ° ~ 180 °, and roll angle is -15 ° ~ 15 °.
As shown in Figures 3 to 6, the coaxial double-rotary wing propeller hub mode shape specifically includes following several structures: upper and lower paddle
Hub+tower seat, upper and lower rotor hub fairing system+tower seat, upper and lower rotor hub fairing system+blade root+tower seat, upper and lower rotor hub fairing system+jackshaft
Radome fairing+tower seat, or upper and lower rotor hub fairing system+blade root+jackshaft radome fairing+tower seat；And upper and lower rotor hub fairing system is
Oval revolving body, the cross section of jackshaft radome fairing are aerofoil profile shape, tower seat be can wrap up the devices such as retarder with outside streamline
The radome fairing of shape.
In step 4, the flowing control includes passive flowing control and active Flow Control；Passive flowing, which controls, includes
Vortex generator flowing control, Gurney wing flap (GF) flowing control and groove flowing control；Active Flow Control includes
Blow/inspiratory flow control, synthesizing jet-flow flowing control, plasma flow control.
Increase blade root on rotor hub fairing system, to obtain influence of the rotor blade root to different propeller hub model aerodynamic characteristics.
The jackshaft radome fairing does not rotate, and does not contact with upper and lower propeller hub, can increase force snesor inside it, uses
With its aerodynamic loading of independent measurement；Elastic shaft coupling is increased separately in the inner barrel and outer barrel of coaxial double-rotary wing propeller hub rig for model test
Section and torsion balance can measure the required horsepower when rotation of upper and lower propeller hub respectively.
As shown in Figure 1, specific steps are as follows:
A) installation coaxial double-rotary wing propeller hub rig for model test is in test chamber, and connects wind tunnel test system；
B) function and stability inspection are carried out to each subsystem, and to balance system, PIV measuring system, surface pressure measurement system
System is checked, inspection/calibration result is provided；
C) propeller hub model system is installed, by vibration monitoring system measuring test-bed vibration characteristics, carry out ground resonance analysis and
Testing stand row's vibration work, guarantees not resonate when propeller hub model test；
D) harmony, function and the integrality between propeller hub model structure are checked, it is ensured that upper and lower propeller hub can effectively be realized coaxial same
Walk return motion；
E) it is enabled to open motor, acquires initial reading and saves；
F) testing stand starts, and testing stand revolving speed is made to be raised to working speed；
G) wind-tunnel is driven, and wind speed is transferred to given value；
H) propeller hub model attitude is manipulated, to reach required pitch angle, yaw angle and roll angle；
I) information such as data aerodynamic force, flow field, pressure are acquired, handles and exports result；
J) change wind speed or propeller hub model attitude, arrive next test value, repeat f) ~ i), finish all examinations of same propeller hub model
It tests a little；
K) wind-tunnel stops, and then testing stand stops；
L) change propeller hub mode shape or apply flowing control；Repeat e) ~ k), finish all testing sites of same propeller hub model.
Specific embodiment is as follows:
A kind of one embodiment of the wind tunnel test methods of helicopter co-axis double propeller hub model of the present invention.As shown in Fig. 2,
Coaxial double-rotary wing propeller hub rig for model test is installed on test chamber first, and connects wind tunnel test system；Check that each point is
The function and stability of system, and balance system, PIV measuring system, surface pressure measurement system are checked, and provide inspection
Look into/calibration result；Propeller hub model as shown in Figure 3 (upper and lower propeller hub+without jackshaft radome fairing+tower seat) is installed, by vibration monitoring
Systematic survey testing stand vibration characteristics, and carry out ground resonance analysis and testing stand row's vibration work, it is ensured that propeller hub model test
When do not resonate；Check harmony, function and the integrality between propeller hub model structure, it is ensured that upper and lower propeller hub can be effectively real
Existing coaxial synchronous return motion；Then, open motor, acquire initial reading and save (if model concentricity is not high, can be in the slow-speed of revolution
In the case of acquire initial reading, influenced to reduce eccentric bring)；Testing stand starting, makes testing stand revolving speed be raised to working speed
(moment pays attention to vibration monitoring system in the process, if stage body vibration is greater than 0.2g, need to carry out dynamic balancing inspection)；Wind-tunnel is driven, will
Wind speed is transferred to given value；Rotation test turntable, manipulation propeller hub model reach required yaw angle；Acquire data aerodynamic force, flow field,
The information such as pressure handle and export result；Change wind speed or propeller hub model attitude, arrive next test value, continues to acquire after stablizing,
Finish all testing sites of same propeller hub model；Finally, wind-tunnel stops, then testing stand stops.
Behind all testing sites for finishing same propeller hub model, change propeller hub mode shape (as shown in figure 4, upper and lower propeller hub is whole
Stream cover+without jackshaft radome fairing+tower seat, as shown in figure 5, upper and lower rotor hub fairing system+blade root+without jackshaft radome fairing+tower seat,
Upper and lower rotor hub fairing system+blade root+jackshaft radome fairing+tower seat etc. as shown in Figure 6), meanwhile, upper and lower propeller hub rectification also can be changed
The shape of the components such as cover, jackshaft radome fairing, tower seat, is combined into different propeller hub built-up patterns, according to above-mentioned test side
Method is tested.
To carry out coaxial double-oar hub model flowing control research, can to propeller hub model carry out adaptability reform, and
Corresponding position applies flowing control, carries out correlative study according to above-mentioned test method.
Note: PIV space flow field measurement method can be found in " Huang Mingqi, Wu Jie, He Long, Lan Bo rotor model floating state
Blade tip whirlpool characteristic research [J] Harbin Institute of Technology's journal 2018,50 (4): 124-130.(DOI:10.11918/
J.issn.0367-6234.201703089) ".
Embodiment 2
Compared with Example 1, in addition to testing stand support stand 3 is different, other structures are identical with method.Its testing stand branch
Support rack 3 replace with six degree of freedom platform, not only can maneuvering test model yaw angle change, can also be achieved test model pitching
Content of the test is enriched in the change at angle, roll angle.
Meanwhile this method can not only carry out the wind tunnel test of coaxial double-oar hub model, can also carry out after removing a propeller hub
The wind tunnel test of independent propeller hub model, in addition can also carry out independent propeller hub model, independent jackshaft radome fairing and independent tower seat
Profile optimization wind- tunnel investigation.
Embodiments of the present invention are explained in detail above in conjunction with attached drawing, but the invention is not limited to above-mentioned
Embodiment within the knowledge of a person skilled in the art can also be before not departing from present inventive concept
It puts and makes a variety of changes.
Claims (10)
1. a kind of wind tunnel test methods of helicopter co-axis double propeller hub model, which is characterized in that specifically comprise the following steps:
Step 1, coaxial double-rotary wing propeller hub rig for model test is installed in wind-tunnel, and passes through coaxial double-rotary wing propeller hub model test
The coaxial synchronous return motion of platform realization coaxial double-rotary wing propeller hub model；
Step 2, it monitors the level of vibration of coaxial double-rotary wing propeller hub rig for model test in real time by vibration monitoring system, carries out ground
Resonance analyzing and testing stand row's vibration work, guarantee not resonate when propeller hub model test；
Step 3, by the six power element of box type balance systematic survey coaxial double-rotary wing propeller hub model, pass through PIV flow field survey system
The flow field for measuring coaxial double-rotary wing propeller hub model, obtains each of coaxial double-rotary wing propeller hub model by surface pressure measurement systematic survey
The surface pressing of component；
Step 4, as needed replacement coaxial double-rotary wing propeller hub model component, using step 1 to step 3 obtain different shapes or
The aerodynamic characteristic of the coaxial double-rotary wing propeller hub model of difference flowing control mode；
Step 5, the aerodynamic characteristic of the coaxial double-rotary wing propeller hub model is obtained.
2. a kind of wind tunnel test methods of helicopter co-axis double propeller hub model according to claim 1, feature exist
In:
In step 3, the box type balance system is the force snesor that can measure six power element of coaxial double-rotary wing propeller hub model, described
Force snesor is fixedly mounted on the bottom of coaxial double-rotary wing propeller hub rig for model test.
3. a kind of wind tunnel test methods of helicopter co-axis double propeller hub model according to claim 1, feature exist
In: the PIV flow field survey system is by particle seeding device, illumination laser, isochronous controller, digital camera and data processing
System composition, wherein particle seeding device, illumination laser, digital camera pass through measurement respectively and obtain data, and isochronous controller is used
It is transmitted in data processing system after synchronizing data, obtains the flow field velocity cloud atlas and stream in different tests state flow field section
Line chart.
4. a kind of wind tunnel test methods of helicopter co-axis double propeller hub model according to claim 1, feature exist
In: the surface pressure measurement system is made of pressure tap, pressure sensor and data processing system, wherein pressure sensing
Device is arranged in pressure tap, and data transfer is obtained to each component of coaxial double-rotary wing propeller hub model into data processing system
Surface pressing.
5. a kind of wind tunnel test methods of helicopter co-axis double propeller hub model as described in claim 1, it is characterised in that:
The vibration monitoring system is made of acceleration transducer, kinetic analyzer, and wherein acceleration transducer is tested measurement
The acceleration information of platform is transmitted to kinetic analyzer, to obtain the level of vibration of coaxial double-rotary wing propeller hub rig for model test.
6. a kind of wind tunnel test methods of helicopter co-axis double propeller hub model as described in claim 1, it is characterised in that:
The revolving speed of the coaxial double-rotary wing propeller hub model is 0 ~ 3000rpm, and wind speed is 0 ~ 300m/s, and pitch angle is -15 ° ~ 15 °, is breakked away
Angle is -180 ° ~ 180 °, and roll angle is -15 ° ~ 15 °.
7. a kind of wind tunnel test methods of helicopter co-axis double propeller hub model according to claim 1, feature exist
In: the component of coaxial double-rotary wing propeller hub model is replaced as needed in step 4, so that outside the coaxial double-rotary wing propeller hub model
Shape specifically includes following several structures: upper and lower propeller hub+tower seat, upper and lower rotor hub fairing system+tower seat, upper and lower rotor hub fairing system+paddle
Root+tower seat, upper and lower rotor hub fairing system+jackshaft radome fairing+tower seat, or upper and lower rotor hub fairing system+blade root+jackshaft rectification
Cover+tower seat；Wherein, the upper and lower rotor hub fairing system is oval revolving body, and the cross section of jackshaft radome fairing is aerofoil profile shape,
Tower seat is the radome fairing with streamline shape that can wrap up retarder.
8. a kind of wind tunnel test methods of helicopter co-axis double propeller hub model according to claim 1, feature exist
In: in step 4, the flowing control includes passive flowing control and active Flow Control；Passive flowing control includes vortex
Generator flowing control, Gurney wing flap flowing control and groove flowing control；Active Flow Control includes blowing/inspiratory flow
Control, synthesizing jet-flow flowing control, plasma flow control.
9. a kind of wind tunnel test methods of helicopter co-axis double propeller hub model according to claim 7, feature exist
In: increase blade root on rotor hub fairing system, to obtain influence of the rotor blade root to different propeller hub model aerodynamic characteristics.
10. a kind of wind tunnel test methods of helicopter co-axis double propeller hub model according to claim 2 or 7, special
Sign is: the jackshaft radome fairing does not rotate, and does not contact with upper and lower propeller hub, increases force snesor inside it, to list
Solely measure its aerodynamic loading；Elastic shaft coupling is increased separately in the inner barrel and outer barrel of the coaxial double-rotary wing propeller hub rig for model test
Section and torsion balance, for measuring the required horsepower when rotation of upper and lower propeller hub respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811364801.0A CN109186922A (en) | 2018-11-16 | 2018-11-16 | A kind of wind tunnel test methods of helicopter co-axis double propeller hub model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811364801.0A CN109186922A (en) | 2018-11-16 | 2018-11-16 | A kind of wind tunnel test methods of helicopter co-axis double propeller hub model |
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|---|---|
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109738152A (en) * | 2019-03-25 | 2019-05-10 | 重庆恩倍克科技有限公司 | A kind of dip angle organization convenient for wind tunnel test |
| CN110239743A (en) * | 2019-07-17 | 2019-09-17 | 中国空气动力研究与发展中心低速空气动力研究所 | The method of controlling security of dynamical system in helicopter W.T test |
| CN110261057A (en) * | 2019-07-03 | 2019-09-20 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system |
| CN110514386A (en) * | 2019-08-05 | 2019-11-29 | 中国航空工业集团公司哈尔滨空气动力研究所 | One kind being based on motor-driven ducted tail rotor experiment supporting device |
| CN110686856A (en) * | 2019-09-30 | 2020-01-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Vibration monitoring, early warning and safety protection system for wind tunnel test bed of helicopter 2 m-diameter rotor |
| CN111189608A (en) * | 2020-02-26 | 2020-05-22 | 重庆大学 | Counter-rotating propeller test device |
| CN112224446A (en) * | 2020-10-16 | 2021-01-15 | 中国直升机设计研究所 | High-speed coaxial dual-rotor blade tip distance measuring method based on phase distance measuring principle |
| CN112229596A (en) * | 2020-09-15 | 2021-01-15 | 中国空气动力研究与发展中心低速空气动力研究所 | Coaxial rigid rotor wing lift force offset wind tunnel test method and system |
| CN112345193A (en) * | 2020-10-29 | 2021-02-09 | 中国航天空气动力技术研究院 | Wind tunnel test measuring system for aerodynamic performance of contra-rotating propeller fan of open rotor engine |
| CN112632695A (en) * | 2020-12-11 | 2021-04-09 | 中国直升机设计研究所 | Ground resonance modeling and analyzing method for transverse double-rotor helicopter |
| CN113460299A (en) * | 2021-09-02 | 2021-10-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet structure for reducing drag of coaxial rigid rotor hub and using method thereof |
| CN113567083A (en) * | 2021-09-22 | 2021-10-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Multi-component aerodynamic interference characteristic test simulation method for full-motion horizontal tail helicopter |
| CN115371949A (en) * | 2022-10-25 | 2022-11-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Arrangement structure of transmission shafting and balance of coaxial rotor wing test device |
| CN115655642A (en) * | 2022-12-09 | 2023-01-31 | 中国空气动力研究与发展中心低速空气动力研究所 | Test method for effectively evaluating aerodynamic performance of helicopter rotor |
| CN116124407A (en) * | 2023-04-10 | 2023-05-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Test method for obtaining influence of radar wake on aerodynamic characteristics of helicopter tail piece |
| CN117419885A (en) * | 2023-12-19 | 2024-01-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Scissor type tail rotor wind tunnel test bed |
| US12060148B2 (en) | 2022-08-16 | 2024-08-13 | Honeywell International Inc. | Ground resonance detection and warning system and method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102012308A (en) * | 2010-05-19 | 2011-04-13 | 北京航空航天大学 | Method and device for jointly and synchronously measuring velocity/pressure during pitching/rolling movement of model |
| DE102011012601A1 (en) * | 2011-02-28 | 2012-08-30 | Airbus Operations Gmbh | Force measuring system, method for detecting forces and moments on a rotating body and wind tunnel with a arranged therein and at least one propeller having model with a force measuring system |
| CN104889808A (en) * | 2015-06-08 | 2015-09-09 | 洛阳理工学院 | Anti-resonance principle based intelligent vibration isolating machine tool |
| CN105004466A (en) * | 2015-08-05 | 2015-10-28 | 北京航空航天大学 | High-precision non-contact pneumatic frictional resistance measuring method and measuring device |
| CN206074222U (en) * | 2016-09-30 | 2017-04-05 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of DCB Specimen synchronization inversion set |
| CN106768792A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of method for carrying out rotor model testing stand dynamic balancing adjustment |
| CN107618675A (en) * | 2017-07-26 | 2018-01-23 | 南京航空航天大学 | A kind of test system and control method for tiltrotor total state blowing experiment |
-
2018
- 2018-11-16 CN CN201811364801.0A patent/CN109186922A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102012308A (en) * | 2010-05-19 | 2011-04-13 | 北京航空航天大学 | Method and device for jointly and synchronously measuring velocity/pressure during pitching/rolling movement of model |
| DE102011012601A1 (en) * | 2011-02-28 | 2012-08-30 | Airbus Operations Gmbh | Force measuring system, method for detecting forces and moments on a rotating body and wind tunnel with a arranged therein and at least one propeller having model with a force measuring system |
| CN104889808A (en) * | 2015-06-08 | 2015-09-09 | 洛阳理工学院 | Anti-resonance principle based intelligent vibration isolating machine tool |
| CN105004466A (en) * | 2015-08-05 | 2015-10-28 | 北京航空航天大学 | High-precision non-contact pneumatic frictional resistance measuring method and measuring device |
| CN206074222U (en) * | 2016-09-30 | 2017-04-05 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of DCB Specimen synchronization inversion set |
| CN106768792A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | A kind of method for carrying out rotor model testing stand dynamic balancing adjustment |
| CN107618675A (en) * | 2017-07-26 | 2018-01-23 | 南京航空航天大学 | A kind of test system and control method for tiltrotor total state blowing experiment |
Non-Patent Citations (3)
| Title |
|---|
| 何龙: "高速直升机共轴双桨毂阻力特性研究", 《中国优秀硕士学位论文全文数据库工程科技II辑》 * |
| 何龙等: "共轴刚性旋翼直升机桨毂阻力特性试验", 《南京航空航天大学学报》 * |
| 吴光辉、陈迎春主编: "《大型客机计算流体力学应用与发展》", 31 December 2009, 上海：上海交通大学出版社 * |
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| CN109738152B (en) * | 2019-03-25 | 2020-10-27 | 嘉兴市宏晖五金制品有限公司 | Inclination mechanism convenient for wind tunnel test |
| CN109738152A (en) * | 2019-03-25 | 2019-05-10 | 重庆恩倍克科技有限公司 | A kind of dip angle organization convenient for wind tunnel test |
| CN110261057A (en) * | 2019-07-03 | 2019-09-20 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of lifting airscrew, fuselage and tail-rotor built-up pattern wind tunnel test system |
| CN110239743A (en) * | 2019-07-17 | 2019-09-17 | 中国空气动力研究与发展中心低速空气动力研究所 | The method of controlling security of dynamical system in helicopter W.T test |
| CN110514386A (en) * | 2019-08-05 | 2019-11-29 | 中国航空工业集团公司哈尔滨空气动力研究所 | One kind being based on motor-driven ducted tail rotor experiment supporting device |
| CN110686856A (en) * | 2019-09-30 | 2020-01-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Vibration monitoring, early warning and safety protection system for wind tunnel test bed of helicopter 2 m-diameter rotor |
| CN111189608A (en) * | 2020-02-26 | 2020-05-22 | 重庆大学 | Counter-rotating propeller test device |
| CN112229596A (en) * | 2020-09-15 | 2021-01-15 | 中国空气动力研究与发展中心低速空气动力研究所 | Coaxial rigid rotor wing lift force offset wind tunnel test method and system |
| CN112224446B (en) * | 2020-10-16 | 2022-06-21 | 中国直升机设计研究所 | High-speed coaxial dual-rotor blade tip distance measuring method based on phase distance measuring principle |
| CN112224446A (en) * | 2020-10-16 | 2021-01-15 | 中国直升机设计研究所 | High-speed coaxial dual-rotor blade tip distance measuring method based on phase distance measuring principle |
| CN112345193A (en) * | 2020-10-29 | 2021-02-09 | 中国航天空气动力技术研究院 | Wind tunnel test measuring system for aerodynamic performance of contra-rotating propeller fan of open rotor engine |
| CN112632695A (en) * | 2020-12-11 | 2021-04-09 | 中国直升机设计研究所 | Ground resonance modeling and analyzing method for transverse double-rotor helicopter |
| CN112632695B (en) * | 2020-12-11 | 2022-12-06 | 中国直升机设计研究所 | Ground resonance modeling and analyzing method for transverse double-rotor helicopter |
| CN113460299A (en) * | 2021-09-02 | 2021-10-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet structure for reducing drag of coaxial rigid rotor hub and using method thereof |
| CN113567083A (en) * | 2021-09-22 | 2021-10-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Multi-component aerodynamic interference characteristic test simulation method for full-motion horizontal tail helicopter |
| CN113567083B (en) * | 2021-09-22 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Multi-component aerodynamic interference characteristic test simulation method for full-motion horizontal tail helicopter |
| US12060148B2 (en) | 2022-08-16 | 2024-08-13 | Honeywell International Inc. | Ground resonance detection and warning system and method |
| CN115371949A (en) * | 2022-10-25 | 2022-11-22 | 中国航空工业集团公司哈尔滨空气动力研究所 | Arrangement structure of transmission shafting and balance of coaxial rotor wing test device |
| CN115371949B (en) * | 2022-10-25 | 2023-07-21 | 中国航空工业集团公司哈尔滨空气动力研究所 | Arrangement structure of transmission shaft system and balance of coaxial rotor wing test device |
| CN115655642A (en) * | 2022-12-09 | 2023-01-31 | 中国空气动力研究与发展中心低速空气动力研究所 | Test method for effectively evaluating aerodynamic performance of helicopter rotor |
| CN116124407A (en) * | 2023-04-10 | 2023-05-16 | 中国空气动力研究与发展中心低速空气动力研究所 | Test method for obtaining influence of radar wake on aerodynamic characteristics of helicopter tail piece |
| CN117419885A (en) * | 2023-12-19 | 2024-01-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Scissor type tail rotor wind tunnel test bed |
| CN117419885B (en) * | 2023-12-19 | 2024-03-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Scissor type tail rotor wind tunnel test bed |
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