CN105606333B - A kind of small deformation wind-tunnel balance - Google Patents
A kind of small deformation wind-tunnel balance Download PDFInfo
- Publication number
- CN105606333B CN105606333B CN201610126091.2A CN201610126091A CN105606333B CN 105606333 B CN105606333 B CN 105606333B CN 201610126091 A CN201610126091 A CN 201610126091A CN 105606333 B CN105606333 B CN 105606333B
- Authority
- CN
- China
- Prior art keywords
- balance
- rod
- type
- strut
- small deformation
- 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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
Abstract
A kind of small deformation wind-tunnel balance, including the gentle strut in rod-type day：The rod-type balance both ends are pyramidal structure, the centre at rod-type balance both ends is day flat elements, the day flat elements are pyramidal structure, big end position is provided with five component elements in pyramidal structure, small end position is provided with resistance element, the strut includes tapered front end and waits straight section, the rod-type balance is matched by the conical surface with the tapered front end of strut and utilizes chock to tense, the rod-type balance is arranged at the interior intracavitary of tested model, and the minimum diameter of the tested mould impression is more than the maximum gauge of rod-type balance.The present invention breaches traditional equal diameter balance strut design method and three-stage rod-type day flat structure, two are increased balance diameter, shorten balance length, balance deformation is small, improve the rigidity and bearing capacity of balance, it can be widely applied in the wind tunnel test balance development that shock loading is big or vibration is violent, there is good practicality and promotional value.
Description
Technical field
The invention belongs to aerospace dynamometer check aerodynamics force measurement technical field, in particular for temporarily rushing formula high speed and super
Model and rod-type balance branch lever system high vibration problem when high-speed wind tunnel dynamometer check starts and cut-offs, utilize taper balance member
Part structure improves balance and strut overall stiffness with measuring cell compact layout, strengthens model supporting system antivibration kinetic force, into
The accurate six components aerodynamics force measurement of dummy vehicle of row more safety and stability.
Background technology
Temporarily rush in formula high-speed wind tunnel dynamometer check, start and cut-off process gas and shock wave scan caused by impact carry
Lotus is probably several times even more than ten times, and dispersion degree is very big of balance range, it is difficult to measurement and control.Shake caused by shock loading
Dynamic amplitude and rigidity, model weight, the blowing mode of balance and strut have substantial connection, and to experiment safety, measurement accuracy
Constitute a serious threat with the service life of balance.Certain impact can be reduced by modes such as model loss of weight, reduction ram compressions to carry
Lotus, but limited be subject to structure and wind-tunnel facilities, effect is unsatisfactory.The firm of balance and strut is improved in limited design space
Degree and bearing capacity are another effective methods.
Common rod-type balance diameter is generally equal with the straight section diameter such as strut, and with mould impression have it is enough between
Gap, with ensure model be subject to aerodynamic loading balance and strut deform after model do not produce space interference with balance strut.It is subject to mould
Type trailing space size limits and enough clearance requirements, and balance and branch shank diameter are smaller, support system insufficient rigidity.And model
Body central space is sufficient, and material unnecessary in mold cavity can be also removed sometimes for loss of weight.Due to balance and strut front end etc.
The gap of diameter, mould impression and balance is excessive, and balance and strut do not make full use of the space in mold cavity when designing,
Cause balance rigidity and bearing capacity deficiency.In addition, three sections of measuring cells, length and material after in before the generally use of rod-type balance
Cutting is serious, further loss balance rigidity.
The content of the invention
The present invention is not abundant in order to solve equal diameter three-stage rod-type balance rigidity and bearing capacity deficiency and balance design
The defects of using mould impression space, there is provided a kind of small deformation wind-tunnel balance and strut, using unique mentality of designing and
The rigidity and bearing capacity of rod-type balance and branching rod structure strengthening system, improve the safety and stability of wind-tunnel balance,
Extend the service life of balance.
To achieve these goals, the technical solution adopted by the present invention is：
A kind of small deformation wind-tunnel balance, including the gentle strut in rod-type day：
The rod-type balance both ends are pyramidal structure, and the centre at rod-type balance both ends is day flat elements,
The day flat elements are pyramidal structure, and big end position is provided with five component elements in pyramidal structure, close to small
End position is provided with resistance element,
The strut includes tapered front end and waits straight section, and the rod-type balance is matched with the tapered front end of strut by the conical surface
And tensed using chock, the rod-type balance is arranged at the interior intracavitary of tested model,
The minimum diameter of the tested mould impression is more than the maximum gauge of rod-type balance.
In the above-mentioned technical solutions, the taper phase of the taper of the tapered front end of the strut and the day flat elements of rod-type balance
Deng.
In the above-mentioned technical solutions, the maximum gauge of the tapered front end of the strut and the minimum of day flat elements pyramidal structure
Diameter is equal.
In the above-mentioned technical solutions, the diameter phase of the straight section such as the minimum diameter of the tapered front end of the rod-type balance and strut
Deng.
In the above-mentioned technical solutions, five component elements include symmetrically arranged girder construction more than four groups, on axis
Piece beam be measuring cell, the column beam positioned at all quadrants is load bearing beam.
In the above-mentioned technical solutions, the resistance element of the rod-type balance includes a pair of of the Y for being symmetrical with balance axis arrangement
Shape measuring cell and two groups of resistance support shrapnels.
In the above-mentioned technical solutions, the resistance support shrapnel is two groups of variable cross-section bullets for being symmetrical with balance axis arrangement
Piece.
In the above-mentioned technical solutions, every group of support elastic sheet equal strength, width match with day flat elements tapered shape.
The present invention operation principle be：Using model balance strut system variant feature, make full use of mould impression sufficient
Space, increases balance diameter as far as possible, shortens balance length, reduces scale material cutting, reaches strengthening system rigidity and carrying energy
The purpose of power.Specifically, after model is subject to aerodynamic loading, die body can regard rigid body as and be basically unchanged shape, deformation master in itself
To be produced by balance and strut.After being deformed, most probable and model touching are the straight sections such as model afterbody inner cavity and strut, and
Mould impression inner space is more sufficient.Therefore, mould impression remaining space can be made full use of, increases balance diameter, to subtract
Few balance stand under load deformation.In addition, two other key factor for influencing balance deformation is balance length and material cutting degree, because
This can shorten balance leement duration, and rigidity is further improved using two-part balance topology layout.
The invention has the advantages that：First, having developed the model balance strut system design cooling load of uniqueness, breach
Traditional equal diameter balance strut design method and three-stage rod-type day flat structure.Two are increased balance diameter, shorten balance
Length, balance deformation is small, improves the rigidity and bearing capacity of balance.Third, effective suppression system vibration, improves experiment
Safety and stability, extends balance service life, improves the overall performance of balance strut.Fourth, expand balance design
Space, reduces balance design difficulty, is conducive to balance component structure and layout optimization design.Fifth, it can be widely applied to impact
During the wind tunnel test balance that load is big or vibration is violent is developed, there is good practicality and promotional value.
Brief description of the drawings
Fig. 1 is a kind of small deformation wind-tunnel balance assembling schematic diagram of the present invention；
Fig. 2 is a kind of small deformation wind-tunnel balance structure diagram of the present invention；
Fig. 3 is the A-A sectional views of Fig. 2；
Fig. 4 is the B-B sectional views of Fig. 2；
In figure：1. model, 11. inner cavities, 12. afterbody inner cavities, 2. rod-type day flat elements, 21. big ends, 22. 5 component elements,
221. measuring cells, 222. load bearing beams, 23. resistance elements, 231. elastic support sheets, 232. Y-shaped measuring cells, 24. small ends,
3. strut, 31. tapered front ends, 32. grade straight sections.
Embodiment
Fig. 1 is a kind of small deformation wind-tunnel balance assembling schematic diagram of the present invention.A kind of small deformation of the present invention
Wind-tunnel balance mainly includes the gentle strut in rod-type day, and the rod-type balance is tensed with strut by cone match chock,
Bullet is located inside mould impression.The rod-type day flat elements maximum gauge is slightly less than model afterbody inner cavity minimum diameter,
While rod-type balance element diameter is increased, facilitate the installation and dismounting of model.The rod-type day flat elements conical section
Minimum diameter is more than straight section diameter, the numerical value such as strut and is calculated by the taper constraints such as balance and strut front end.
Fig. 2 is a kind of small deformation wind-tunnel balance structure diagram of the present invention.The rod-type day flat elements are in cone
Shape, is more than the end diameter close to model afterbody, in the big end of rod-type day flat elements close to the outside diameter of dummy head
Side sets five component elements, and small end side sets resistance element.
Fig. 3 is the A-A sectional views of Fig. 2, and five component elements of rod-type balance are to be symmetrical arranged girder construction more than four groups, position
It is measuring cell in the piece beam on axis, the column beam positioned at all quadrants is load bearing beam.
Fig. 4 is the B-B sectional views of Fig. 2, and the resistance element of the rod-type balance is be symmetrical with balance axis arrangement one
It is right " Y " shape measuring cells.The resistance support shrapnel of the rod-type balance is two groups of variable cross-sections for being symmetrical with balance axis arrangement
Shrapnel, every group of support elastic sheet are designed by the principle of equal strength, and width is adapted to day flat elements tapered shape.
A kind of implementation steps of small deformation wind-tunnel balance of the present invention are further illustrated referring to Fig. 1-4：
The maximum gauge of the straight sections such as strut is estimated that according to the minimum diameter of model afterbody inner cavity and aerodynamic loading,
Ensure there are enough gaps afterbody inner cavity is not touched during experiment with straight sections such as struts.Meanwhile according to model afterbody
The minimum diameter of inner cavity can determine the maximum gauge of the big end of rod-type day flat elements, it is ensured that rod-type day flat elements can be inserted smoothly
Enter mould impression, the installation and dismounting of implementation model.Can according to the length of the preliminary diameter dimension of above-mentioned two and mould impression
To calculate rod-type day flat elements and the identical taper of strut tapered front end, its length is less than the length of mould impression, so as not to
Influence model afterbody inner cavity aerodynamic characteristic.
Further, it is possible to it is other suitably sized to estimate mould impression, it is ensured that before rod-type day flat elements and strut taper
End is internal to have enough gaps not touch with mould impression after stand under load.Since strut tapered front end and rod-type day flat elements are
Variable cross-section slowly increases, and system overall stiffness and comprehensive on the one hand greatly improved on the premise of dismounting is not influenced
Energy；On the other hand slowly varying section is optimized balance stress distribution, enhances the peace of balance and strut coupling part
Quan Xing.
The typical structure of rod-type balance of the present invention as shown in Fig. 2, with reference to Fig. 3 and Fig. 4, according to balance design load and
Other technical indicators, determine length, five component elements, the physical dimension of resistance element of rod-type day flat elements, make balance as far as possible
Element is compact, to further improve balance rigidity.Five component elements use more girder constructions, and each beam section is arranged on as far as possible in Fig. 3
Position away from centroidal principal axis is to improve section bending stiffness.Preferentially, four piece beams positioned at reference axis may be selected as survey
Element is measured, the root column beam for selecting to be arranged symmetrically is as load bearing beam, in order to process and paste strain gauge.
The Y-shaped measuring cell transition of resistance element is round and smooth, prevents stress concentration；Strain gauge is pasted onto the oblique of the beam of uniform strength
On face, to reduce the influence that strain gauge paste position is brought.Each physical dimension of every group of elastic support sheet is true by the principle of equal strength
Fixed, proof stress distribution is than more uniform, without obvious stress concentration.
According to Load Characteristics and specific design objective, five component elements and resistance element may alternatively be other
The flexible member of structure type.
Balance is complicated, and Traditional calculating methods are difficult to more accurately be deformed and displacement result, before processing
Space interference situation after the stand under load of serious analysis and prediction model and strut, reserves certain surplus.Therefore, after the completion of design
Model balance branch lever system need to carry out deformation simulation by finite element emulation software, and adjust relative dimensions so that model
Inner cavity makes full use of, and gap is enough, it is ensured that the straight section such as model afterbody inner cavity and strut is in the situation by limit aerodynamic loading
Under space interference does not occur.
The invention is not limited in foregoing embodiment.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (8)
1. a kind of small deformation wind-tunnel balance, including the gentle strut in rod-type day, it is characterised in that：
The rod-type balance both ends are pyramidal structure, and the centre at rod-type balance both ends is day flat elements,
The day flat elements are pyramidal structure, and big end position is provided with five component elements in pyramidal structure, close to small end
Position is provided with resistance element,
The strut includes tapered front end and waits straight section, and the rod-type balance is matched with the tapered front end of strut by the conical surface and profit
Being tensed with chock, the rod-type balance is arranged at the interior intracavitary of tested model,
The minimum diameter of the tested mould impression is more than the maximum gauge of rod-type balance.
A kind of 2. small deformation wind-tunnel balance according to claim 1, it is characterised in that the tapered front end of the strut
Taper it is equal with the taper of the day flat elements of rod-type balance.
A kind of 3. small deformation wind-tunnel balance according to claim 2, it is characterised in that the tapered front end of the strut
Maximum gauge it is equal with the minimum diameter of day flat elements pyramidal structure.
A kind of 4. small deformation wind-tunnel balance according to claim 3, it is characterised in that the taper of the rod-type balance
The diameter of the straight sections such as the minimum diameter of front end and strut is equal.
5. a kind of small deformation wind-tunnel balance according to claim 1, it is characterised in that five component elements include
Symmetrically arranged girder construction more than four groups, the piece beam on axis are measuring cell, and the column beam positioned at all quadrants is load bearing beam.
A kind of 6. small deformation wind-tunnel balance according to claim 1, it is characterised in that the resistance of the rod-type balance
Element includes a pair of of the Y shape measuring cell and two groups of resistance support shrapnels for being symmetrical with balance axis arrangement.
7. a kind of small deformation wind-tunnel balance according to claim 6, it is characterised in that the resistance support shrapnel is
It is symmetrical with two groups of variable cross-section shrapnels of balance axis arrangement.
A kind of 8. small deformation wind-tunnel balance according to claim 6, it is characterised in that every group of support elastic sheet equal strength,
Width matches with day flat elements tapered shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610126091.2A CN105606333B (en) | 2016-03-07 | 2016-03-07 | A kind of small deformation wind-tunnel balance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610126091.2A CN105606333B (en) | 2016-03-07 | 2016-03-07 | A kind of small deformation wind-tunnel balance |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105606333A CN105606333A (en) | 2016-05-25 |
| CN105606333B true CN105606333B (en) | 2018-04-13 |
Family
ID=55986447
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610126091.2A Active CN105606333B (en) | 2016-03-07 | 2016-03-07 | A kind of small deformation wind-tunnel balance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105606333B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106644367B (en) * | 2017-01-13 | 2023-06-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Combined type high-resistance wind tunnel strain balance |
| CN107121258B (en) * | 2017-06-07 | 2023-03-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Balance resistance element structure with optimized stress distribution |
| CN107796593B (en) * | 2017-11-30 | 2023-09-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Universal rod type wind tunnel strain balance pasting quantitative pressurizing system |
| CN108896266B (en) * | 2018-07-17 | 2019-08-02 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of method for arranging of balance measurement route |
| CN108709714B (en) * | 2018-08-08 | 2023-08-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Balance with large rolling moment and small lateral force |
| CN108801581A (en) * | 2018-09-04 | 2018-11-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel force measurement model vibration damping strut based on constrained damping structure |
| CN110441025A (en) * | 2019-08-19 | 2019-11-12 | 中国航空工业集团公司沈阳空气动力研究所 | One kind is for the full machine dynamometric system of the modified double balances of civil aircraft support interference and method |
| CN111157220B (en) * | 2020-03-13 | 2024-03-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Strain type two-component surface friction resistance measuring balance |
| CN112798218B (en) * | 2021-04-12 | 2021-07-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Model and rod balance connecting structure for wind tunnel test |
| CN114323546B (en) * | 2022-03-07 | 2022-05-17 | 中国空气动力研究与发展中心高速空气动力研究所 | High-sensitivity rod-type six-component wind tunnel test balance embedded with different materials |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3878713A (en) * | 1973-11-16 | 1975-04-22 | Gen Dynamics Corp | Wind tunnel balance for supplying compressed fluid to the model |
| US4845993A (en) * | 1988-05-18 | 1989-07-11 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Wind tunnel balance |
| SU1091703A1 (en) * | 1982-08-05 | 1995-05-10 | Институт Теоретической И Прикладной Механики Со Ан Ссср | Device for aerodynamic testings |
| CN101183039A (en) * | 2007-11-30 | 2008-05-21 | 中国航天空气动力技术研究院 | Balance system with inhibition structure |
| CN101726401A (en) * | 2009-12-09 | 2010-06-09 | 中国航空工业第一集团公司沈阳空气动力研究所 | Scale measuring device for pitching dynamic derivative experiment |
| CN102889973A (en) * | 2012-09-29 | 2013-01-23 | 中国航天空气动力技术研究院 | High-precision device for measuring rolling moment based on mechanical bearing support |
| CN103983417A (en) * | 2014-05-22 | 2014-08-13 | 大连理工大学 | Cylindrical put object aerodynamic force detection device and measurement method |
| CN104198154A (en) * | 2014-09-18 | 2014-12-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Double-end force measurement device and double-end measurement method |
| CN204128776U (en) * | 2014-10-27 | 2015-01-28 | 中国航空工业空气动力研究院 | A kind of telescopic bracing cable balance |
| CN104990683A (en) * | 2015-07-21 | 2015-10-21 | 中国空气动力研究与发展中心高速空气动力研究所 | A segmented trace hinge moment balance |
| CN205580703U (en) * | 2016-03-07 | 2016-09-14 | 中国空气动力研究与发展中心高速空气动力研究所 | Little deformation wind -tunnel balance of meeting an emergency |
-
2016
- 2016-03-07 CN CN201610126091.2A patent/CN105606333B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3878713A (en) * | 1973-11-16 | 1975-04-22 | Gen Dynamics Corp | Wind tunnel balance for supplying compressed fluid to the model |
| SU1091703A1 (en) * | 1982-08-05 | 1995-05-10 | Институт Теоретической И Прикладной Механики Со Ан Ссср | Device for aerodynamic testings |
| US4845993A (en) * | 1988-05-18 | 1989-07-11 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Wind tunnel balance |
| CN101183039A (en) * | 2007-11-30 | 2008-05-21 | 中国航天空气动力技术研究院 | Balance system with inhibition structure |
| CN101726401A (en) * | 2009-12-09 | 2010-06-09 | 中国航空工业第一集团公司沈阳空气动力研究所 | Scale measuring device for pitching dynamic derivative experiment |
| CN102889973A (en) * | 2012-09-29 | 2013-01-23 | 中国航天空气动力技术研究院 | High-precision device for measuring rolling moment based on mechanical bearing support |
| CN103983417A (en) * | 2014-05-22 | 2014-08-13 | 大连理工大学 | Cylindrical put object aerodynamic force detection device and measurement method |
| CN104198154A (en) * | 2014-09-18 | 2014-12-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Double-end force measurement device and double-end measurement method |
| CN204128776U (en) * | 2014-10-27 | 2015-01-28 | 中国航空工业空气动力研究院 | A kind of telescopic bracing cable balance |
| CN104990683A (en) * | 2015-07-21 | 2015-10-21 | 中国空气动力研究与发展中心高速空气动力研究所 | A segmented trace hinge moment balance |
| CN205580703U (en) * | 2016-03-07 | 2016-09-14 | 中国空气动力研究与发展中心高速空气动力研究所 | Little deformation wind -tunnel balance of meeting an emergency |
Non-Patent Citations (3)
| Title |
|---|
| 四分量片式铰链力矩天平技术及风洞实验应用研究;刘喜贺 等;《实验流体力学》;20110430;第25卷(第2期);第88-91页 * |
| 杆式风洞应变天平动态解耦-补偿;杨双龙 等;《仪器仪表学报》;20110731;第32卷(第7期);第1598-1605页 * |
| 高速风洞拐角六分量天平研制;叶镜明;《南京航空学院学报》;19880630;第20卷(第2期);第110-117页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105606333A (en) | 2016-05-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105606333B (en) | A kind of small deformation wind-tunnel balance | |
| CN106644367A (en) | Compound large-resistance wind-tunnel strain balance | |
| CN108181083A (en) | Small-range high lift-drag ratio force balance applied to low density wind tunnel | |
| EP2983099B1 (en) | Method for determining reduction factor of axial load bearing capacity of a cylindrical shell structure in a rocket | |
| CN105823615B (en) | A kind of small asymmetric reentry body aerodynamics force measurement device of mechanical bearing support | |
| CN103063401B (en) | Preparation method of steel truss arch bridge wind tunnel test model | |
| CN205580703U (en) | Little deformation wind -tunnel balance of meeting an emergency | |
| CN105160067A (en) | Method for checking strength performances of variable-pitch bearing and hub connecting bolt and variable-pitch bearing and vane connecting bolt of fan | |
| CN112362294A (en) | Coaxial parallel axial load measuring high-precision wind tunnel force measuring balance | |
| CN110207944B (en) | High-precision resistance measuring method and device for wind tunnel experiment | |
| CN111006845B (en) | High-speed wind tunnel test simulation method for grid rudder with large scaling | |
| Laird et al. | Finite element modeling of wind turbine blades | |
| CN111521369A (en) | Six-component ring type wind tunnel balance | |
| CN105300595A (en) | Balance loading head with calibration of connected model and loading method | |
| Wang et al. | Design of a pulse-type strain gauge balance for a long-test-duration hypersonic shock tunnel | |
| CN105527069A (en) | Transonic wind tunnel test supporting device, installation method and application thereof | |
| CN205449433U (en) | Experimental strutting arrangement of transonic wind tunnel | |
| CN108398228B (en) | Air-floating strain balance | |
| Zhao et al. | Numerical study of total temperature effect on hypersonic boundary layer transition | |
| CN206362520U (en) | A kind of big resistance wind-tunnel balance of combined type | |
| Kumar et al. | Nose bluntness for side-force control on circular cones at high incidence | |
| CN108414188A (en) | It is a kind of to be used for and hang together the six component strain balance of double struts for playing CTS experiments | |
| CN104477404B (en) | A kind of ground validation method of fuselage main force support structure part under big load | |
| Bogdanov et al. | Development of the six-component rotating shaft balances for counter rotating open rotor testing | |
| CN104699912A (en) | Strength calculation method of hub and spindle connecting bolt of wind generator set |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |