CN106226024B - A kind of DCB Specimen wind tunnel test platform - Google Patents
A kind of DCB Specimen wind tunnel test platform Download PDFInfo
- Publication number
- CN106226024B CN106226024B CN201610871006.5A CN201610871006A CN106226024B CN 106226024 B CN106226024 B CN 106226024B CN 201610871006 A CN201610871006 A CN 201610871006A CN 106226024 B CN106226024 B CN 106226024B
- Authority
- CN
- China
- Prior art keywords
- rotor
- angular wheel
- installing frame
- wind tunnel
- tunnel test
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- 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
- G01M9/02—Wind tunnels
-
- 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
- G01M9/02—Wind tunnels
- G01M9/04—Details
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention provides a kind of DCB Specimen wind tunnel test platform, including the secondary rotor driving mechanism of power splitter (2), rotor installing frame (12) and two, described two secondary rotor driving mechanisms are installed on rotor installing frame (12), and it is located at power splitter (2) opposite sides, each pair rotor driving mechanism includes angle retarder (7), head gearbox (9) and rotary-wing transmission axis (10)；Power splitter (2) respectively drives angle retarder (7) synchronization action by two first transmission shafts (6), angle retarder (7) drives head gearbox (9) synchronization action, head gearbox (9) to drive rotary-wing transmission axis (10) relative to rotor installing frame (12) synchronization action by second driving shaft (8).The present invention is applied to DCB Specimen wind tunnel test, can not only realize the synchronization action of DCB Specimen, moreover it is possible to keep lower wind-tunnel blockage percentage, stream field interference is small, improves the reliability of results of wind tunnel.
Description
Technical field
The present invention relates to DCB Specimen wind-tunnel technique field, more particularly, to can realize that DCB Specimen synchronous backward rotates
A kind of DCB Specimen wind tunnel test platform.
Background technology
Deficiency of the current conventional configuration helicopter due to aerodynamic force so that its speed is difficult to be promoted.And by introducing altogether
The characteristics such as axis rigid rotor system and tail portion propulsion device component develops coaxial rigid twin-rotor helicopter, can be from aerodynamic force
Aspect solves the problems, such as that the speed of conventional configuration helicopter is difficult to break through.
For coaxial rigid twin-rotor helicopter, coaxial double-rotary wing therein is typically that synchronous same-speed rotates backward.But
This coaxial rigid twin-rotor helicopter it is high advance than, big reversed flow region, strong radial flow, the completely new rotor gas such as big propeller hub resistance
Dynamic problem proposes stern challenge to the unsteady Aerodynamic characteristics and layout designs of coaxial rigid twin-rotor helicopter.
Wind tunnel test is the economical and efficient means for the complicated aerodynamic characteristic for understanding, grasping the coaxial rigid twin-rotor helicopter of high speed, is passed through
Wind tunnel test can study height and advance than rotor UNSTEADY FLOW (big reversed flow region, strong radial flow, high blade tip Mach number) mechanism,
The substantive characteristics for exploring coaxial rigid rotor and the difference of common rotor Airflow Environment analyzes the aerodynamic interference of coaxial rigid DCB Specimen
Characteristic finds out coaxial rigid DCB Specimen flow mechanism, and then establishes advanced coaxial rigid DCB Specimen aerodynamic design theory and side
Method.Therefore, a kind of DCB Specimen wind tunnel test platform that can realize the rotation of coaxial double-rotary wing synchronous backward is researched and developed, is not only fabricated to
This is low, and also ensures that results of wind tunnel has higher reliability, just seems necessary, also very urgent.
Invention content
The technical problem to be solved by the present invention is to：In view of the problems of the existing technology, a kind of DCB Specimen wind-tunnel examination is provided
Platform is tested, can not only realize the synchronization action of DCB Specimen, and the authenticity of wind tunnel test data, reliability can be improved.
The technical problem to be solved in the present invention is realized using following technical scheme：A kind of DCB Specimen wind tunnel test platform,
Including the secondary rotor driving mechanism of power splitter, rotor installing frame and two, described two secondary rotor driving mechanisms are installed in rotation
On wing installing frame, and it is located at the opposite sides of power splitter, each pair rotor driving mechanism includes angle retarder, rotor
Retarder and rotary-wing transmission axis；The power splitter respectively drives angle retarder synchronization action by two first transmission shafts,
The angle retarder drives head gearbox synchronization action, the head gearbox to drive rotary-wing transmission axis by second driving shaft
Relative to rotor installing frame synchronization action.
Preferably, further include dip angle organization, the dip angle organization includes torque motor and sliding rail and sliding block, the rotor
Installing frame is movably connected on rack, and the sliding rail is fixedly connected with rack, and the sliding block is fixedly connected with rotor installing frame；When
When the torque motor control rotor installing frame is relative to gantry rotation or stopping, the sliding block limits phase in range in sliding rail
Sliding rail is moved synchronously with rotor installing frame or it is synchronous stop.
Preferably, the slider bottom installs idler wheel, when sliding block moves in sliding rail restriction range relative to sliding rail, institute
Sliding block is stated by forming rolling friction between idler wheel and sliding rail.
Preferably, the power splitter includes the first angular wheel, the second angular wheel and third angular wheel, institute
State the second angular wheel, third angular wheel be located at the first angular wheel opposite sides and respectively with the first angular wheel
Engaged transmission.
Preferably, the angle retarder includes the 4th angular wheel and the 5th angular wheel of intermeshing transmission, institute
It states the 4th angular wheel to be fixedly connected with the first transmission shaft, the 5th angular wheel is fixedly connected with second driving shaft.
Preferably, the head gearbox includes the 6th angular wheel and the 7th angular wheel of intermeshing transmission, institute
The 6th angular wheel stated is fixedly connected with second driving shaft, and the 7th angular wheel is fixedly connected with rotary-wing transmission axis.
Preferably, transmission shaft support is set between the power splitter and angle retarder, and the transmission shaft support is solid
Dingan County is flexibly connected knot between first transmission shaft and transmission shaft support on rotor installing frame by second bearing composition
Structure.
Preferably, transmission shaft support is set between the angle retarder and head gearbox, and the transmission shaft support is solid
Dingan County is flexibly connected knot between the second driving shaft and transmission shaft support on rotor installing frame by second bearing composition
Structure.
Preferably, the opposite sides of the rotor installing frame is respectively fixedly connected with left rotary shaft, right spindle, the left rotary shaft,
Right spindle forms movable connection structure between shaft seating by first bearing respectively, and the shaft seating is fixedly connected on
On rack.
Preferably, the first bearing is oscillating bearing.
Compared with prior art, the beneficial effects of the invention are as follows：It is revolved when being fixedly mounted respectively on two rotary-wing transmission axis
After the wing, by power splitter by a power decomposition of input be two bursts of power outputs, to respectively drive two rotary-wing transmissions
Axis makees synchronization action relative to rotor installing frame, and to realize the synchronization action of DCB Specimen, not only synchronization accuracy is high, and double
The opposite initial orientation angle of rotor is constant all the time；When carrying out DCB Specimen wind tunnel test, only two secondary rotors and part rotor pass
Moving axis is placed in Flow Field in Wind Tunnel, and other component is in other than Flow Field in Wind Tunnel, therefore, lower wind can be kept in wind tunnel test
Hole blockage percentage, stream field interference is small, to make results of wind tunnel have higher reliability, can be used for carrying out coaxal helicopter
The wind- tunnel investigations such as aerodynamic interference, complex flowfield measurement between rotor aeroperformance, upper and lower rotor, are to carry out coaxial rigidity pair
The key foundation equipment of rotor aerodynamic characteristics tests research；In addition, the overall structure of the present invention is relatively easy, implementation cost
It is relatively low.
Description of the drawings
Fig. 1 is a kind of D structure figure of DCB Specimen wind tunnel test platform of the present invention.
Fig. 2 is a kind of front view of DCB Specimen wind tunnel test platform of the present invention.
Fig. 3 is the transmission shaft line structure schematic diagram in a kind of DCB Specimen wind tunnel test platform of the present invention.
Fig. 4 is a kind of transmission principle schematic diagram of DCB Specimen wind tunnel test platform of the present invention.
It is marked in figure：1- racks, 2- power splitters, 3- shaft seatings, 4- driving motors, 5- transmission shaft supports, 6-
One transmission shaft, the angles 7- retarder, 8- second driving shafts, 9- head gearboxes, 10- rotary-wing transmission axis, 11- rotors, 12- rotors peace
It frames up, 13- right spindles, 14- wind-tunnel, 15- torque motors, 16- sliding rails, 17- sliding blocks, the first angular wheels of 21-, the cones of 22- second
Shape gear, 23- third angular wheels, 24- left rotary shafts, 31- first bearings, 40- main shafts, 51- second bearings, 71- the 4th
Angular wheel, the 5th angular wheels of 72-, the 6th angular wheels of 91-, the 7th angular wheels of 92-.
Specific implementation mode
In order to make the purpose , technical scheme and advantage of the present invention be clearer, below in conjunction with the accompanying drawings and specific implementation
The present invention is described in detail for example.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, not
For limiting the present invention.
DCB Specimen wind tunnel test platform as shown in Figure 1 and Figure 2 includes mainly power splitter 2,12 and of rotor installing frame
Two secondary rotor driving mechanisms, described two secondary rotor driving mechanisms are installed on rotor installing frame 12, and are located at power
The opposite sides of decomposer 2, each pair rotor driving mechanism includes angle retarder 7, head gearbox 9 and rotary-wing transmission axis 10.
The rotor installing frame 12 is rectangle frame, and opposite sides is respectively fixedly connected with left rotary shaft 24, right spindle 13, the left-hand rotation
Axis 24, right spindle 13 form movable connection structure between corresponding shaft seating 3 by first bearing 31 respectively, such as Fig. 4 institutes
Show, described two shaft seatings 3 are respectively fixedly connected on the rack 1 of U-shaped structure, and the power splitter 2 includes the
One angular wheel 21, the second angular wheel 22 and third angular wheel 23, second angular wheel 22, third angular wheel 23
Be located at the opposite sides of the first angular wheel 21 and respectively with the engaged transmission of the first angular wheel 21.Using such structure
Design, can make the gravity of rotor installing frame 12 pass through power splitter 2 and pass on rack 1, to avoid in power splitter 2
Gear bears additional load, is conducive to the reliability for improving DCB Specimen wind tunnel test plateform system.
As shown in figure 4, first angular wheel 21 is fixedly connected with 40 one end of main shaft, the main shaft 40
The other end is connect with 4 output end of driving motor, and the driving motor 4 is fixedly mounted on rack 1, and is driven by main shaft 40
Dynamic first angular wheel 21 rotates, to provide input power to power splitter 2.Preferably, in driving motor 4 and master
Elastic coupling can be set between transmission shaft 40, to effectively improve the dynamic property of test platform shafting, it is flat to reduce experiment
The vibration of platform.The angle retarder 7 includes the 4th angular wheel 71 and the 5th angular wheel 72 of intermeshing transmission, described
4th angular wheel 71 is fixedly connected with the first transmission shaft 6, and the 5th angular wheel 72 is fixedly connected with second driving shaft 8.
The head gearbox 9 includes being intermeshed the 6th angular wheel 91 and the 7th angular wheel 92 being driven, and the described the 6th
Angular wheel 91 is fixedly connected with second driving shaft 8, and the 7th angular wheel 92 is fixedly connected with rotary-wing transmission axis 10.Its
In, the angle retarder 7, head gearbox 9 are made of two angular wheel engagements, when being slowed down with power transmission with realizing
Commutation function.
When carrying out DCB Specimen wind tunnel test, rotor 11 is fixedly mounted respectively in the end of two rotary-wing transmission axis 10, and
Keep this two secondary rotor 11 opposite with wind-tunnel 14, as shown in figure 3, from same driving motor 4 to 2 input power of power splitter, passes through
Power splitter 2 resolves into upper and lower two-way power, then exports supreme, inferior horn retarder 7 through two first transmission shafts 6 respectively, with
Respectively drive two sets of 7 synchronization actions of angle retarder, the angle retarder 7 is respectively by two second driving shafts 8 to being corresponding to it
Head gearbox 9 export power, with drive two sets of 9 synchronization actions of head gearbox finally divided by two sets of head gearboxes 9
Not Qu Dong two rotary-wing transmission axis 10 be respectively relative to the movement of 12 synchronous rotary of rotor installing frame, it is secondary finally to realize upper and lower two
The synchronization of rotor 11 rotates backward, and the initial phase of the reference blade of upper and lower two secondary rotors 11 is relative constant, and upper and lower two is secondary
The azimuth of rotor 11 synchronizes, i.e., when the reference blade of the rotor 11 on upper layer reaches a certain azimuth, the ginseng of the rotor 11 of lower layer
The azimuth for examining blade must be fixed a certain value.When the geometric parameter of above-mentioned two secondary rotor driving mechanisms is identical, warp
After identical power transmission shaft road transmission, the synchronization of upper and lower two secondary rotors 11, reversed, rotation at the same speed can ensure that.At this point, due to
Only two secondary rotors 11 and part rotary-wing transmission axis 10 are in the flow field of wind-tunnel 14, other component be in 14 flow field of wind-tunnel with
Outside, as shown in Figure 2.Therefore, lower wind-tunnel blockage percentage can be kept in wind tunnel test, stream field interference is also smaller, to make
Results of wind tunnel has higher authenticity, reliability.
In order to ensure transmission stability, the reliability of two secondary rotor driving mechanisms, as shown in Figure 1, Figure 2, Figure 4 shows, Ke Yi
Increase setting transmission shaft support 5 between power splitter 2 and angle retarder 7, the transmission shaft support 5 is fixedly mounted on rotor peace
It frames up on 12, passes through second bearing 51 between first transmission shaft 6 and transmission shaft support 5 and form movable connection structure.In addition,
Setting transmission shaft support 5 can also be increased between angle retarder 7 and head gearbox 9, the transmission shaft support 5 is fixedly mounted
On rotor installing frame 12, knot is flexibly connected by the composition of second bearing 51 between the second driving shaft 8 and transmission shaft support 5
Structure.Preferably, deep groove ball bearing may be used in the second bearing 51, and joint shaft may be used in the first bearing 31
It holds.Since oscillating bearing has the advantages that support stiffness is high, damping characteristic is good, first bearing 31 can using oscillating bearing
With radially fixed rotor installing frame 12 and automatic aligning.
In order to which the aerodynamic characteristic easily to rigid rotor 11 in 10 different angle of rotary-wing transmission axis is studied,
Setting dip angle organization can be increased on the basis of above-mentioned wind tunnel test platform.The dip angle organization includes rotor installing frame
12, torque motor 15 and sliding rail 16 and sliding block 17, the rotor installing frame 12 by left rotary shaft 24, right spindle 13 respectively with turn
Shaft stool 3, which is formed, to be relatively rotated connection and is movably connected on rack 1, is fixedly connected between the sliding rail 16 and rack 1, described
Sliding block 17 is fixedly connected with rotor installing frame 12.Main motor 4 is fixedly mounted on the left column of rack 1, the main motor 4 drives
Rotor 11 in rotor installing frame 12 synchronizes reversion, and torque motor 15, the power are fixedly mounted on the right column of rack 1
Torque motor 15 drives rotor installing frame 12 to be swung relative to rack 1 by right spindle 13,4 output shaft axis of the main motor and power
15 output shaft axis of torque motor overlaps, and rotor installing frame 12 is around this output shaft axis oscillating.
Permanent magnet may be used in the sliding rail 16, sliding block 17, and sliding rail 16 therein is arc-shaped structure, with sliding block 17
Between mutual suction-operated formed by magnetic force, as shown in Figure 1 and Figure 2.When sliding block 17 limits in range in sliding rail 16 relative to cunning
When rail 16 moves, sliding friction is formed between the sliding block 17 and sliding rail 16.It is rolled it is of course also possible to be installed in 17 bottom of sliding block
Wheel, when sliding block 17 is when sliding rail 16 is limited and move relative to sliding rail 16 in range, the sliding block 17 by idler wheel and sliding rail 16 it
Between form rolling friction.Compared with sliding friction, rolling friction loss is lower, to not only make between sliding block 17 and sliding rail 16
Relative motion is more smooth, and is more advantageous to and improves energy-saving level.Preferably, U-shaped sliding slot is formed on the sliding rail 16,
Clearance fit is formed between the sliding block 17 and U-shaped sliding slot, sliding block 17 can preferably be limited by the U-shaped sliding slot on sliding rail 16
Movement locus, to ensure rotor installing frame 12 relative to 1 stable oscillation of rack.
The torque motor 15 drives the rotor installing frame 12 of wind tunnel test platform relative to rack 1 and around torque motor
15 output shaft axis rotate, to change the inclination angle for being fixed on the rotary-wing transmission axis 10 on rotor installing frame 12.Due to torque electricity
The torque of the exportable different change frequencies of machine 15, so as to realize different frequency rotary-wing transmission axis 10 change of pitch angle, institute
Stating torque motor 15 also can drive rotary-wing transmission axis 10 to generate different fixed angles, so as to realize be fixed on it is a certain specific
Inclination angle.Therefore, by the way that dip angle organization is arranged, it can not only realize the main shaft angle variation of coaxial double-rotary wing different frequency, be used for
Simulate flow field bad border when coaxial rigid rotor Helicopter Maneuver Flight, it may also be used for pneumatic when studying its fixed main shaft inclination angle
Characteristic.
When carrying out dynamic test, magnetic force sliding block 17 sliding rail 16 limit range in relative to sliding rail 16 slide, and with rotation
Wing installing frame 12 moves synchronously, to constrain the transverse movement of the rotor installing frame 12 when dynamic test；Incline when carrying out different main shafts
When the static test at angle, magnetic force sliding block 17 is adsorbed on sliding rail 16, at this point, the sliding block 17 limits in range relatively in sliding rail 16
It remains static in sliding rail 16, i.e., it is synchronous between sliding block 17 and rotor installing frame 12 to stop, so as to avoid rotor from installing
Frame 12 acts on lower swing in wind load.When the rotor installing frame 12 rotates, 12 upper and lower side of rotor installing frame should be avoided as possible
It, can be by increasing rotor peace if the change of pitch angle range of rotary-wing transmission axis 10 is larger along the flow field for entering opening wind tunnel 14
Frame up the height at 12 upper and lower edges, its frame is made not enter 14 flow field of wind-tunnel, dry to avoid 12 upper and lower edge of rotor installing frame
Flow-disturbing field.
In addition, the sliding rail 16, sliding block 17 can also use electromagnet, also, when torque motor 15 controls rotor peace
12 are framed up when being acted relative to 1 stopping of rack, mutual suction-operated is formed by magnetic force between the sliding block 17 and sliding rail 16.
When torque motor 15, which controls rotor installing frame 12, starts action relative to rack 1, the electricity between the sliding block 17 and sliding rail 16
Magnetic pull releases, to keep the relative motion between sliding block 17 and sliding rail 16 more smooth.Since sliding rail 16, sliding block 17 use
Electromagnet, therefore, by being powered off to it, you can the magnetic-adsorption between sliding rail 16 and sliding block 17 is released, to reduce torque motor
15 energy expenditure.
It should be added that protection truss can be installed on rotor installing frame 12, the protection purlin
Frame coats the first transmission shaft 6, second driving shaft 8, to improve safety when DCB Specimen wind tunnel test platform uses.In addition,
Setting oil feeding line can also be increased on rotor installing frame 12, in general, oil inlet is set above the oil feeding line, lower section setting
Oil outlet can spray lubricating oil, with right to power splitter 2, angle retarder 7, head gearbox 9 respectively by oil feeding line
Gear in power splitter 2, angle retarder 7, head gearbox 9 is lubricated, oil cooling, is conducive to improve the examination of DCB Specimen wind-tunnel
Test the service life of platform.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, it is noted that all
All any modification, equivalent and improvement made by within the spirit and principles in the present invention etc. should be included in the guarantor of the present invention
Within the scope of shield.
Claims (9)
1. a kind of DCB Specimen wind tunnel test platform, it is characterised in that：Including dip angle organization, power splitter (2), rotor installing frame
(12) and two secondary rotor driving mechanisms, the dip angle organization includes torque motor (15) and sliding rail (16) and sliding block (17), institute
The two secondary rotor driving mechanisms stated are installed on rotor installing frame (12), and are located at opposite the two of power splitter (2)
Side, the rotor installing frame (12) are movably connected on rack (1), and the sliding rail (16) is fixedly connected with rack (1), the cunning
Block (17) is fixedly connected with rotor installing frame (12), when torque motor (15) control rotor installing frame (12) is relative to rack (1)
When rotation or stopping, the sliding block (17) limits in range in sliding rail (16) relative to sliding rail (16) and rotor installing frame (12)
Move synchronously or synchronize stopping；Each pair rotor driving mechanism includes that angle retarder (7), head gearbox (9) and rotor pass
Moving axis (10)；The power splitter (2) respectively drives angle retarder (7) synchronization action, institute by two first transmission shafts (6)
It states angle retarder (7) and head gearbox (9) synchronization action, head gearbox (9) driving is driven by second driving shaft (8)
Rotary-wing transmission axis (10) is relative to rotor installing frame (12) synchronization action.
2. a kind of DCB Specimen wind tunnel test platform according to claim 1, it is characterised in that：Sliding block (17) the bottom peace
Idler wheel is filled, when sliding block (17) is when sliding rail (16) is limited and moved relative to sliding rail (16) in range, the sliding block (17) passes through rolling
Rolling friction is formed between wheel and sliding rail (16).
3. a kind of DCB Specimen wind tunnel test platform according to claim 1, it is characterised in that：The power splitter
(2) include the first angular wheel (21), the second angular wheel (22) and third angular wheel (23), second angular wheel
(22), third angular wheel (23) be located at the first angular wheel (21) opposite sides and respectively with the first angular wheel
(21) engaged transmission.
4. a kind of DCB Specimen wind tunnel test platform according to claim 1, it is characterised in that：The angle retarder (7)
Include the 4th angular wheel (71) and the 5th angular wheel (72) of intermeshing transmission, the 4th angular wheel (71) and the
One transmission shaft (6) is fixedly connected, and the 5th angular wheel (72) is fixedly connected with second driving shaft (8).
5. a kind of DCB Specimen wind tunnel test platform according to claim 1, it is characterised in that：The head gearbox (9)
Include intermeshing transmission the 6th angular wheel (91) and the 7th angular wheel (92), the 6th angular wheel (91) and
Second driving shaft (8) is fixedly connected, and the 7th angular wheel (92) is fixedly connected with rotary-wing transmission axis (10).
6. a kind of DCB Specimen wind tunnel test platform according to claim 1, it is characterised in that：The power splitter
(2) transmission shaft support (5) is set between angle retarder (7), and the transmission shaft support (5) is fixedly mounted on rotor installing frame
(12) on, movable connection structure is formed by second bearing (51) between first transmission shaft (6) and transmission shaft support (5).
7. a kind of DCB Specimen wind tunnel test platform according to claim 1, it is characterised in that：The angle retarder (7)
Transmission shaft support (5) is set between head gearbox (9), and the transmission shaft support (5) is fixedly mounted on rotor installing frame
(12) on, movable connection structure is formed by second bearing (51) between the second driving shaft (8) and transmission shaft support (5).
8. according to a kind of DCB Specimen wind tunnel test platform of claim 3-7 any one of them, it is characterised in that：The rotor peace
The opposite sides of (12) of framing up is respectively fixedly connected with left rotary shaft (24), right spindle (13), the left rotary shaft (24), right spindle (13)
Movable connection structure is formed by first bearing (31) between shaft seating (3) respectively, the shaft seating (3) is fixed to be connected
It is connected on rack (1).
9. a kind of DCB Specimen wind tunnel test platform according to claim 8, it is characterised in that：The first bearing (31)
It is oscillating bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610871006.5A CN106226024B (en) | 2016-09-30 | 2016-09-30 | A kind of DCB Specimen wind tunnel test platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610871006.5A CN106226024B (en) | 2016-09-30 | 2016-09-30 | A kind of DCB Specimen wind tunnel test platform |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106226024A CN106226024A (en) | 2016-12-14 |
| CN106226024B true CN106226024B (en) | 2018-07-31 |
Family
ID=58075939
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610871006.5A Active CN106226024B (en) | 2016-09-30 | 2016-09-30 | A kind of DCB Specimen wind tunnel test platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106226024B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106768959B (en) * | 2016-12-29 | 2023-09-22 | 山东华成中德传动设备有限公司 | Spiral wing detection device |
| CN106644366A (en) * | 2016-12-29 | 2017-05-10 | 山东华成中德传动设备有限公司 | Test system for influence of airflow on spiral wing |
| CN107290126A (en) * | 2017-08-15 | 2017-10-24 | 中国空气动力研究与发展中心低速空气动力研究所 | The mutual pull wind tunnel test platform dip angle organization of one kind conjugation |
| CN107830987B (en) * | 2017-12-04 | 2024-04-12 | 中国航空工业集团公司沈阳空气动力研究所 | Six-degree-of-freedom mechanism store strut for capture track test based on bevel gear transmission |
| CN109612681B (en) * | 2018-11-16 | 2020-07-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Aerodynamic interference measurement method of coaxial rigid rotor model of helicopter |
| 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 |
| CN110844113B (en) * | 2019-10-12 | 2022-06-03 | 中国直升机设计研究所 | Rigid coaxial dual-rotor test bed capable of simultaneously measuring upper rotor load and lower rotor load |
| CN111175014B (en) * | 2020-02-28 | 2020-09-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Balance system and method for accurately measuring rotor wing pneumatic load |
| CN113203538B (en) * | 2021-05-25 | 2022-09-13 | 中国航空工业集团公司哈尔滨空气动力研究所 | Device for inhibiting vibration of mirror image supporting rod |
| 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 |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288381A (en) * | 2011-05-05 | 2011-12-21 | 西北工业大学 | Wing tip support device for wind tunnel test |
| CN102353512A (en) * | 2011-07-22 | 2012-02-15 | 北京航空航天大学 | Attack angle control method based on synchronous operation of multiple motors and multifunctional supporting device |
| CN102901623A (en) * | 2012-10-24 | 2013-01-30 | 哈尔滨东安发动机（集团）有限公司 | Device for testing coaxial inversion rotor wing of helicopter |
| CN104913912A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Hanging type coaxial contrarotating rotor wing testing device |
| CN105158004A (en) * | 2015-09-29 | 2015-12-16 | 华东师范大学 | Rotor aircraft test platform |
| CN105547676A (en) * | 2015-12-25 | 2016-05-04 | 北京航空航天大学 | Multifunctional swing-arm type rotor wing test stand |
| CN206114252U (en) * | 2016-09-30 | 2017-04-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Dual -rotor wind -tunnel test platform |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001083037A (en) * | 1999-09-16 | 2001-03-30 | Mitsubishi Heavy Ind Ltd | Test device for blade |
| US20170267338A1 (en) * | 2014-10-01 | 2017-09-21 | Sikorsky Aircraft Corporation | Acoustic signature variation of aircraft utilizing a clutch |
-
2016
- 2016-09-30 CN CN201610871006.5A patent/CN106226024B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288381A (en) * | 2011-05-05 | 2011-12-21 | 西北工业大学 | Wing tip support device for wind tunnel test |
| CN102353512A (en) * | 2011-07-22 | 2012-02-15 | 北京航空航天大学 | Attack angle control method based on synchronous operation of multiple motors and multifunctional supporting device |
| CN102901623A (en) * | 2012-10-24 | 2013-01-30 | 哈尔滨东安发动机（集团）有限公司 | Device for testing coaxial inversion rotor wing of helicopter |
| CN104913912A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Hanging type coaxial contrarotating rotor wing testing device |
| CN105158004A (en) * | 2015-09-29 | 2015-12-16 | 华东师范大学 | Rotor aircraft test platform |
| CN105547676A (en) * | 2015-12-25 | 2016-05-04 | 北京航空航天大学 | Multifunctional swing-arm type rotor wing test stand |
| CN206114252U (en) * | 2016-09-30 | 2017-04-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Dual -rotor wind -tunnel test platform |
Non-Patent Citations (3)
| Title |
|---|
| "共轴刚性旋翼直升机桨毂阻力特性试验";何龙 等;《南京航空航天大学学报》;20160831;第48卷(第4期);530-535 * |
| "共轴双旋翼及孤立旋翼自转气动特性试验研究";姬乐强 等;《实验流体力学》;20131031;第27卷(第5期);7-10+24 * |
| "共轴式直升机上下旋翼之间气动干扰的风洞实验研究";邓彦敏 等;《航空学报》;20030131;第24卷(第1期);10-14 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106226024A (en) | 2016-12-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106226024B (en) | A kind of DCB Specimen wind tunnel test platform | |
| CN106168530B (en) | A kind of wind tunnel test platform dip angle organization | |
| CN206114252U (en) | Dual -rotor wind -tunnel test platform | |
| CN109612681B (en) | Aerodynamic interference measurement method of coaxial rigid rotor model of helicopter | |
| CN106289707B (en) | A kind of wind tunnel test platform transmission mechanism | |
| US11428605B2 (en) | Experimental system and method capable of simulating non-inertial system of gear transmission | |
| CN206311296U (en) | A kind of wind tunnel test platform transmission mechanism | |
| CN206132349U (en) | Wind -tunnel test platform inclination mechanism | |
| CN108945420A (en) | A kind of four axis tilting rotor mechanisms and method of verting based on unmanned plane | |
| WO2021129180A1 (en) | Coaxial helicopter and control method | |
| CN106441787B (en) | A kind of DCB Specimen synchronization inversion set | |
| CN104787327B (en) | A kind of multi-rotor aerocraft of changeable wheelbase | |
| CN107215454A (en) | A kind of NEW TYPE OF COMPOSITE roll attitude control system and method | |
| CN203094442U (en) | Tilting four-rotor aircraft | |
| CN105784316A (en) | High-rigidness embedded device for multi-body separation test of hypersonic wind tunnel | |
| CN107290126A (en) | The mutual pull wind tunnel test platform dip angle organization of one kind conjugation | |
| CN207050947U (en) | One kind is conjugated mutual pull wind tunnel test platform dip angle organization | |
| CN110207939A (en) | A kind of real-time test mechanism for changing model mean angle of attack | |
| CN105197240A (en) | Differential variable-amplitude flapping wing driving mechanism and driving method | |
| CN111060277A (en) | Helicopter tail rotor simulation test device and vortex ring verification method | |
| CN107985583A (en) | Tilting rotor wing unmanned aerial vehicle | |
| CN106698156A (en) | Elevator | |
| CN203638109U (en) | Special motion distribution device for ground test equipment of foldable double wing plate bracket of aircraft | |
| CN203627080U (en) | Double-blade type wind power generation apparatus | |
| CN208855867U (en) | A kind of four axis tilting rotor mechanisms based on unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |