CN206132348U - Wind tunnel test rotor operating mechanism - Google Patents
Wind tunnel test rotor operating mechanism Download PDFInfo
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- CN206132348U CN206132348U CN201621100008.6U CN201621100008U CN206132348U CN 206132348 U CN206132348 U CN 206132348U CN 201621100008 U CN201621100008 U CN 201621100008U CN 206132348 U CN206132348 U CN 206132348U
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- wind tunnel
- tunnel test
- rotating ring
- control mechanism
- rotor
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model provides a wind tunnel test rotor operating mechanism, including a plurality of linear drive ware (1), irrotational ring (3), spherical hinge chain (5) and rotatory ring (8), activity hinge joint between linear drive ware (1) and the irrotational ring (3), irrotational ring (3) is connected with spherical hinge chain (5) and is central around moving around spherical hinge chain (5), rotatory ring (8) just rotates for irrotational ring (3) with irrotational ring (3) swing joint, rotatory ring (8) and pull rod (4) one end activity hinge joint, rotor installation department (6) activity hinge joint on pull rod (4) other end and rotor transmission axle (7), spherical hinge chain (5) are run through in rotor transmission axle (7). Utilize the utility model discloses simple, safe and reliable are not only controld to the total distance of controllable rotor, feather, and dynamic characteristic is better moreover, and it is high to control the precision, especially, compact structure, the volume is less, when being applied to the wind tunnel test, can make the wind tunnel test data more reliable.
Description
Technical field
This utility model is related to helicopter W.T test technical field, more particularly, to can realize rotor always away from and rotor
A kind of wind tunnel test rotor control mechanism of cyclic pitch control.
Background technology
The application of helicopter not only intricately can carry out landing, hovering operation under condition in the wild without the need for airport environment, and
Also there is good low-altitude maneuver performance, the task that fixed wing airplane cannot be completed can be performed, therefore, helicopter is each in the army and the people
It is obtained in individual field and is increasingly widely applied.
At present, the rotor aerodynamics problem complicated for helicopter, relies primarily on wind tunnel test and is simulated research.So
And, as the manipulation of lifting airscrew is complex, its blade not only needs to produce periodicity change in angle of attack with azimuth, so as to
Balance paddle is faced left right asymmetric air-flow, and, when different lift requirements are needed, in addition it is also necessary to correspondingly change rotor total
Away to provide different lift.But, due to the not only bulky of the rotor control system on helicopter, and manipulate it is complicated,
The rotor control being not directly applicable during wind tunnel test.Therefore, based on existing helicopter rotor operation system, design is a kind of
Special wind tunnel test rotor control mechanism, and the reliability of wind tunnel test data is can guarantee that, it is efficiently and effectively to study straight
The key of the complicated aerodynamics problem of the machine of liter.
Utility model content
The technical problems to be solved in the utility model is：For the problem that prior art is present, there is provided a kind of wind tunnel test
Rotor control mechanism, not only manipulates simply, and wind tunnel test data can be made when wind tunnel test is applied to more reliable.
The technical problems to be solved in the utility model employs the following technical solutions to realize：A kind of wind tunnel test rotor control
Mechanism, including some Linear actuators, not rotating ring and spherical linkage and rotating ring, the Linear actuator and not rotating ring
Between be movably hinged, the not rotating ring is connected with spherical linkage and around spherical linkage center moving, and the rotating ring is revolved with not
Change is flexibly connected and rotates relative to not rotating ring, and the rotating ring is movably hinged with pull bar one end, the pull bar other end
It is movably hinged with the rotor installation portion on rotary-wing transmission axle, the rotary-wing transmission axle runs through spherical linkage.
Preferably, described some Linear actuators are movably hinged with balance upper flat plate respectively.
Preferably, described some Linear actuators are uniformly divided with juxtaposition on the same plane of balance upper flat plate
Cloth.
Preferably, also including guide, the guide is run through spherical linkage and the relative knot that slides is formed between spherical linkage
Structure, the rotary-wing transmission axle run through guide.
Preferably, anti-rotation connecting key is set between described guide and spherical linkage, and the spherical linkage connects along anti-rotation
Connect key and make linear slide relative to guide.
Preferably, described rotating ring and not between rotating ring by bearing formed relatively rotate structure.
Preferably, described Linear actuator arranges 3.
Preferably, described Linear actuator is actuator.
Preferably, described Linear actuator is cylinder.
Preferably, described Linear actuator is electric cylinder.
Compared with prior art, the beneficial effects of the utility model are：Rotor installation portion on rotary-wing transmission axle is fixed
After connecting rotor, when the synchronized displacement of some Linear actuators, rotating ring and pull bar can be promoted also to move same displacement,
Such that it is able to realize rotor each equal angular change of blade angle of attack, that is, change rotor always away from；When some Linear actuators according to
According to certain rule friction speed it is differential when, can promote not rotating ring around spherical linkage occur planar tilt, so as to be rotated ring send out
It is raw to incline, and then backward stick action is driven, such that it is able to realize feather.Therefore, can be realized by this utility model
Rotor not only manipulates simple, safe and reliable always away from the manipulation with feathering, and dynamic characteristic is preferably, manipulates high precision；Separately
Outward, as building block of the present utility model is less, between part, annexation is simple, therefore, rotor behaviour of the present utility model
It is the compact overall structure of vertical mechanism, simple, use, safeguard and facilitate, especially its small volume, is being applied to wind tunnel test
When, its interference to Flow Field in Wind Tunnel is also less, so that blockage percentage during wind tunnel test is greatly reduced, finally so that wind tunnel test
Data are more reliable, and this utility model can also be used for the rotor control in the helicopter W.T tests such as conventional list rotor, close coupled type.
Description of the drawings
Fig. 1 is a kind of D structure figure of wind tunnel test rotor control mechanism of this utility model.
Fig. 2 is a kind of front view of wind tunnel test rotor control mechanism of this utility model.
Labelling in figure：1- Linear actuators, 2- balance upper flat plates, 3- not rotating rings, 4- pull bars, 5- spherical linkages, 6- rotations
Wing installation portion, 7- rotary-wing transmission axles, 8- rotating rings, 9- guides.
Specific embodiment
In order that the purpose of this utility model, technical scheme and advantage become more apparent, below in conjunction with the accompanying drawings and specifically
Embodiment is described in detail to this utility model.It should be appreciated that specific embodiment described herein is only to explain this
Utility model, is not used to limit this utility model.
Wind tunnel test rotor control mechanism as shown in Figure 1 and Figure 2, including some Linear actuators 1, not rotating ring 3 and
Spherical linkage 5 and rotating ring 8, wherein, the bottom of each Linear actuator 1 is movably hinged with balance upper flat plate 2 respectively, each
The outfan of individual Linear actuator 1 is movably hinged between rotating ring 3 respectively with not；Described not rotating ring 3 is connected with spherical linkage 5
Connect, and can be around any moving in 5 center of spherical linkage；Described rotating ring 8 be not flexibly connected between rotating ring 3, and can phase
For rotating ring 3 is not rotated；Preferably, described rotating ring 8 and not between rotating ring 3 by bearing formed relatively rotate knot
Structure, not only can make the overall structure of rotor control mechanism more compact, and ensure that rotating ring 8 and not between rotating ring 3
Relative rotation flexible movements degree.Described rotating ring 8 is movably hinged with 4 one end of pull bar, 4 other end of the pull bar and rotor
Rotor installation portion 6 on power transmission shaft 7 is movably hinged, and described rotary-wing transmission axle 7 runs through spherical linkage 5, the number of the pull bar 4
It is identical with the number of rotor installation portion 6, and mutually form one-to-one relationship.The rotating ring 8 and pull bar 4 are with rotary-wing transmission
Axle 7 is rotated together with, and some Linear actuators 1, not rotating ring 3, spherical linkage 5 are not rotated with rotary-wing transmission axle 7.
Above-mentioned rotor control mechanism needs the rotor installation portion 6 on rotary-wing transmission axle 7 when wind tunnel test is applied to
On be fixedly connected rotor, the rotating ring 8 and pull bar 4 (include being fixedly connected on rotor installation portion 6 with rotary-wing transmission axle 7
On rotor) rotate together with.In this rotary course, when some Linear actuators 1 produce synchronized displacement, not rotating ring 3 are made
Upper and lower translation is produced, drives spherical linkage 5 also to move same displacement by not rotating ring 3, such that it is able to promoting rotating ring 8 and drawing
Bar 4 also moves same displacement, and makes all rotor installation portions 6 around the axis rotation equal angular of rotor installation portion 6, so as to realize
Rotor each blade angle of attack angularly changes, that is, change rotor always away from.In order to ensure that rotating ring 3 does not drive spherical linkage 5
Mobile same displacement, with improve rotor always away from manipulation precision, can by guide 9 run through spherical linkage 5 and with spherical linkage 5 it
Between form relative slide construction, described rotary-wing transmission axle 7 runs through guide 9, and described guide 9 is not rotated with rotary-wing transmission axle 7,
As shown in Figure 1 and Figure 2.Further, in order to prevent from relatively rotating between guide 9 and spherical linkage 5, can be with guide 9
Anti-rotation connecting key is set between spherical linkage 5, so that spherical linkage 5 is only made along the anti-rotation connecting key relative to guide 9
Linear slide.
When some Linear actuators 1 are differential according to certain rule friction speed, can promote not rotating ring 3 around spherical linkage 5
Generation planar tilt, so as to 8 run-off the straight of ring is rotated, and then drives 4 corresponding actions of pull bar, drives difference by pull bar 4
Axis different rotation angle of the rotor installation portion 6 around rotor installation portion 6, such that it is able to realize the difference of each blade angle of attack of rotor
Angle change, that is, realize feather.Concrete rotor control angle and the corresponding relation of 1 displacement of Linear actuator, can pass through
The instruments such as dipmeter carry out demarcating, and be determined.In order to improve the manipulation precision of feather, generally, described line
Property driver 1 arrange 3, and the Linear actuator 1 uniformly divides with juxtaposition on the same plane of balance upper flat plate 2
Cloth.
Wind tunnel test rotor control mechanism of the present utility model, Linear actuator therein 1 can adopt actuator, also may be used
Using cylinder or to adopt electric cylinder.When wind tunnel test is carried out, corresponding action displacement is exported by Linear actuator 1,
Can not only manipulate rotor always away from, obtain different rotor lifts, can also carry out feather manipulation, it is left so as to balance rotor
The adverse effect that right airflow asymmetry is caused so as to can be used for the rotation in the helicopter W.T tests such as conventional list rotor, close coupled type
The wing is manipulated, and not only manipulates simple, safe and reliable, and dynamic characteristic is preferably, manipulates high precision；Further, since this utility model
Building block it is less, between part, annexation is simple, therefore, the overall structure of rotor control mechanism of the present utility model is tight
Gather, simply, use, safeguard and facilitate, especially its small volume, when wind tunnel test is applied to, which is done to Flow Field in Wind Tunnel
Disturb also less, so that blockage percentage during wind tunnel test is greatly reduced, finally cause wind tunnel test data more reliable.
Preferred embodiment of the present utility model is the foregoing is only, not to limit this utility model, should be referred to
Go out, all any modification, equivalent and improvement made within spirit of the present utility model and principle etc. all should be included
Within protection domain of the present utility model.
Claims (10)
1. a kind of wind tunnel test rotor control mechanism, it is characterised in that：Including some Linear actuators (1), not rotating ring (3) with
And spherical linkage (5) and rotating ring (8), the Linear actuator (1) and it is not movably hinged between rotating ring (3), it is described not revolve
Change (3) is connected with spherical linkage (5) and around spherical linkage (5) center moving, and the rotating ring (8) is living with not rotating ring (3)
Dynamic to connect and rotate relative to not rotating ring (3), the rotating ring (8) is movably hinged with pull bar (4) one end, the pull bar (4)
The other end is movably hinged with the rotor installation portion (6) on rotary-wing transmission axle (7), and the rotary-wing transmission axle (7) is through spherical linkage
(5)。
2. a kind of wind tunnel test rotor control mechanism according to claim 1, it is characterised in that：Described some linear drive
Dynamic device (1) is movably hinged with balance upper flat plate (2) respectively.
3. a kind of wind tunnel test rotor control mechanism according to claim 2, it is characterised in that：Described some linear drive
Dynamic device (1) is uniformly distributed with juxtaposition on the same plane of balance upper flat plate (2).
4. a kind of wind tunnel test rotor control mechanism according to claim 2 or 3, it is characterised in that：Also include guide
(9), the guide (9) relative slide construction of formation through spherical linkage (5) and between spherical linkage (5), the rotor are passed
Moving axis (7) is through guide (9).
5. a kind of wind tunnel test rotor control mechanism according to claim 4, it is characterised in that：Described guide (9) with
Anti-rotation connecting key is set between spherical linkage (5), and the spherical linkage (5) makees straight relative to guide (9) along anti-rotation connecting key
Line slides.
6. a kind of wind tunnel test rotor control mechanism according to any one of claim 1-3, it is characterised in that：Described rotation
Change (8) and not between rotating ring (3) by bearing formed relatively rotate structure.
7. a kind of wind tunnel test rotor control mechanism according to any one of claim 1-3, it is characterised in that：Described line
Property driver (1) arrange 3.
8. a kind of wind tunnel test rotor control mechanism according to claim 7, it is characterised in that：Described Linear actuator
(1) it is actuator.
9. a kind of wind tunnel test rotor control mechanism according to claim 7, it is characterised in that：Described Linear actuator
(1) it is cylinder.
10. a kind of wind tunnel test rotor control mechanism according to claim 7, it is characterised in that：Described Linear Driving
Device (1) is electric cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621100008.6U CN206132348U (en) | 2016-09-30 | 2016-09-30 | Wind tunnel test rotor operating mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621100008.6U CN206132348U (en) | 2016-09-30 | 2016-09-30 | Wind tunnel test rotor operating mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206132348U true CN206132348U (en) | 2017-04-26 |
Family
ID=58571966
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621100008.6U Active CN206132348U (en) | 2016-09-30 | 2016-09-30 | Wind tunnel test rotor operating mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206132348U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106168531A (en) * | 2016-09-30 | 2016-11-30 | 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 wind tunnel test rotor control mechanism |
| CN109229420A (en) * | 2018-09-01 | 2019-01-18 | 哈尔滨工程大学 | A kind of helicopter tail rotor testing stand feather effort formation |
-
2016
- 2016-09-30 CN CN201621100008.6U patent/CN206132348U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106168531A (en) * | 2016-09-30 | 2016-11-30 | 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 wind tunnel test rotor control mechanism |
| CN109229420A (en) * | 2018-09-01 | 2019-01-18 | 哈尔滨工程大学 | A kind of helicopter tail rotor testing stand feather effort formation |
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