CN112504873A - Vertical rotor blade torsional rigidity measuring system and measuring method - Google Patents
Vertical rotor blade torsional rigidity measuring system and measuring method Download PDFInfo
- Publication number
- CN112504873A CN112504873A CN202011199963.0A CN202011199963A CN112504873A CN 112504873 A CN112504873 A CN 112504873A CN 202011199963 A CN202011199963 A CN 202011199963A CN 112504873 A CN112504873 A CN 112504873A
- Authority
- CN
- China
- Prior art keywords
- blade
- rotor blade
- loading
- light source
- torsional rigidity
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000012360 testing method Methods 0.000 claims abstract description 41
- 238000005259 measurement Methods 0.000 claims abstract description 20
- 238000003825 pressing Methods 0.000 claims description 14
- 238000004519 manufacturing process Methods 0.000 claims description 5
- 230000001788 irregular Effects 0.000 claims description 3
- 238000012935 Averaging Methods 0.000 claims description 2
- 238000000691 measurement method Methods 0.000 abstract description 6
- 230000008878 coupling Effects 0.000 abstract description 4
- 238000010168 coupling process Methods 0.000 abstract description 4
- 238000005859 coupling reaction Methods 0.000 abstract description 4
- 238000006073 displacement reaction Methods 0.000 abstract description 4
- 230000003321 amplification Effects 0.000 abstract description 3
- 238000005452 bending Methods 0.000 abstract description 3
- 230000007547 defect Effects 0.000 abstract description 3
- 238000003199 nucleic acid amplification method Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 230000005484 gravity Effects 0.000 description 3
- 239000002131 composite material Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/26—Investigating twisting or coiling properties
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0016—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings of aircraft wings or blades
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0041—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by determining deflection or stress
- G01M5/005—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by determining deflection or stress by means of external apparatus, e.g. test benches or portable test systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/06—Special adaptations of indicating or recording means
- G01N3/068—Special adaptations of indicating or recording means with optical indicating or recording means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0001—Type of application of the stress
- G01N2203/0003—Steady
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0021—Torsional
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0075—Strain-stress relations or elastic constants
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/0641—Indicating or recording means; Sensing means using optical, X-ray, ultraviolet, infrared or similar detectors
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0682—Spatial dimension, e.g. length, area, angle
Abstract
The invention relates to the technical field of helicopter rotor tests, in particular to a system and a method for measuring torsional rigidity of a vertical rotor blade. The device comprises a fixed vertical wall (1), a blade pin assembly (2), a blade rotation limiting clamp (3), a blade loading clamp (4), a disc type torque loading device (5), a projection vertical wall (6), a laser light source (7) and a reflector (8). The invention analyzes the defects of the existing engineering measurement method, reduces the bending and twisting coupling of the blade caused by external factors such as the weight of the blade, the weight of a clamp, the application of load and the like by vertically fixing the blade, converts the measured micro-change torsion angle into the displacement measurement of measurement amplification magnitude by the mirror reflection principle, improves the key factor which is most easy to introduce measurement errors in the existing measurement method, and meets the requirement of the current engineering test precision by verifying the subject blade.
Description
Technical Field
The invention relates to the technical field of helicopter rotor tests, in particular to a system and a method for measuring torsional rigidity of a vertical rotor blade.
Background
At present, most of helicopters adopt full composite material blades, the blades are molded and co-cured, certain deviation may exist between the manufacturing and the design of the blades due to the self-dispersity of the composite material and the addition of manual construction, and blade rigidity tests must be carried out in order to verify the conformity between the manufacturing and the design of the blades. And correcting the rotor dynamics calculation model by using the test result, and re-evaluating the rotor system design rationality. Therefore, the reasonability and the accuracy of the test method must be ensured, and an effective test result can be obtained.
At present, in available rotor blade rigidity measurement methods for engineering, the accuracy of flap and shimmy rigidity measurement methods can basically meet model requirements, and the torsional rigidity is difficult to meet engineering measurement requirements. In the existing measuring method, the blades are horizontally arranged, and bending and twisting coupling deformation of the blades can be caused by the factors such as the self gravity of the blades, the gravity of an airfoil-shaped clamp, load loading and the like, so that the torsional rigidity testing precision is greatly influenced. In the existing torsional rigidity measuring method, the general deviation of a measuring result and a design result is large, and the fluctuation of repeated tests is large.
In addition, in the existing testing method, for example, the angle change is directly measured by an angle meter, the surface displacement change of the blade is directly measured by a laser displacement sensor, and the numerical value variation is very small, and the self error of the testing system is a key factor causing the measurement deviation of the torsional rigidity of the blade to be large at present. Therefore, a method for accurately measuring the torsional rigidity of the blade, which can amplify the measurement coefficient and reduce the bending-torsion coupling, is needed.
Disclosure of Invention
The purpose of the invention is: aiming at the defects in the prior art, the invention provides a method for measuring the torsional rigidity of a vertical rotor blade, which solves the problem of large measurement deviation of the torsional rigidity of the existing rotor blade through a reasonable measurement mode and can meet the requirement of engineering test precision.
The technical scheme of the invention is as follows: in order to achieve the above object, according to a first aspect of the present invention, a vertical rotor blade torsional stiffness measurement system is provided, which is characterized by comprising a fixed vertical wall 1, a blade pin assembly 2, a blade rotation limiting clamp 3, a blade loading clamp 4, a disc type torque loading device 5, a projection vertical wall 6, a laser light source 7, and a reflector 8,
the blade pin assembly 2 comprises a blade pin 21 and a mounting plate 22; the mounting plate 22 is fixedly connected to the fixed vertical wall 1 through a fastening device, a bushing hole is formed in the root of the rotor blade to be tested, and the blade pin 21 penetrates through the bushing hole and is matched with the mounting plate 22 to fix the rotor blade to be tested;
the blade rotation limiting clamp 3 is fixedly connected to the blade fixing vertical wall 1 through a fastening device, and the installation position of the blade rotation limiting clamp is positioned below the blade pin assembly 2; the blade rotation limiting clamp 3 comprises an inner pressing plate 31, an outer pressing plate 32, a fastening bolt 33 and a limiting clamp mounting plate 34, the limiting clamp mounting plate 34 is fixedly connected to the fixed vertical wall 1 through a fastening device, the inner pressing plate 31 and the outer pressing plate 32 are connected with the limiting clamp mounting plate 34 through the fastening bolt 33, and a rotor blade to be tested is clamped between the inner pressing plate 31 and the outer pressing plate 32;
one end of the blade tip of the rotor blade to be tested is a loading end, a clamping hole 41 is formed in the middle of the blade loading clamp 4, the inner surface of the clamping hole 41 is matched with the wing shape of the loading end of the rotor blade to be tested, and the blade loading clamp 4 is sleeved at the loading end of the rotor blade to be tested;
the disc type torque loading equipment 5 is fixedly connected to the lower part of the blade loading clamp 4 and is used for generating torque taking the variable pitch axis of the rotor blade to be tested as the center;
a torsional rigidity section to be measured is arranged on the rotor blade to be measured, the upper part and the lower part of the surface of the same side of the variable pitch axis of the torsional rigidity section to be measured are respectively and symmetrically provided with a reflector lens 8, the reflector lenses are marked as a first reflector lens 81 and a second reflector lens 82, the first reflector lens 81 and the second reflector lens 82 are fixedly adhered to the surface of the blade, and the mirror surface of the reflector lens 8 is parallel to the chord line direction of the rotor blade to be measured;
the laser light source 7 generates an incident light source of the lens 8, which is detachably connected to the projection vertical wall 6, and which correspondingly includes a first laser light source 71 and a second laser light source 72, the first reflection lens 81 and the first laser light source 71 are at the same horizontal height, and the second reflection lens 82 and the second laser light source 72 are at the same horizontal height;
an included angle theta is formed between the wall surface of the projection vertical wall 6 and the mirror surface of the lens 8.
In a possible embodiment, the blade rotation limiting clamp 3 is installed at the starting position of the airfoil of the blade to be measured.
In a possible embodiment, the disc torque loading device 5 has a center of torque loading on the pitch axis of the rotor blade to be measured.
In one possible embodiment, the included angle θ is in a range of 0-15 °; the distance from the incident point of the lens 8 to the wall surface of the projection vertical wall 6 is D, and the distance D is larger than or equal to 3 m.
According to a second aspect of the present invention, there is provided a method for measuring torsional rigidity of a vertical rotor blade, using the above system for measuring torsional rigidity of a vertical rotor blade, comprising the steps of:
s1: manufacturing a rotor blade test piece 100; selecting a proper position for the irregular tip to cut off the tip;
s2: designing a corresponding vertical rotor blade torsional stiffness measurement system for the rotor blade test piece 100 manufactured in step S1;
s3: vertically hanging the rotor blade test piece 100 on a wall through the blade pin assembly 2, installing the blade rotation limiting clamp 3 at the initial position of the airfoil shape of the rotor blade test piece 100, installing the blade loading clamp 4 at the torque loading end of the rotor blade test piece 100, and fixedly connecting the disc type torque loading equipment 5 with the blade loading clamp 4 to ensure that the torque loading center is on the variable pitch axis of the rotor blade test piece 100;
s4: selecting a section to be tested of torsional rigidity on the rotor blade test piece 100, and respectively sticking and fixing the first reflector 81 and the second reflector 82 on the pitch axis of the section to be tested of torsional rigidity, wherein the upper and lower symmetrical positions of the surface on the same side ensure that the mirror surface is parallel to the chord line;
s5: mounting the first laser light source 71 and the second laser light source 72 at the same horizontal height position on the projection vertical wall 6 according to the height of the bonding position of the first reflection mirror 81 and the second reflection mirror 82 in the step S4; ensuring that a first laser beam emitted by the first laser light source 71 is reflected by the first reflector 81 to generate a first projection point on a projection wall, and the first projection point is in the same horizontal height plane with the first laser light source 71 and the first reflector 81; the second laser beam emitted by the second laser source 72 is reflected by the second reflector 82 to generate a second projection on the projection wall, and the second projection is also in the same horizontal height plane with the second laser source 72 and the second reflector 82;
s6: respectively recording initial incident angles alpha corresponding to the first laser beam and the second laser beam before carrying out torque loading on a blade loading end through the disc type torque loading equipment (5)1、α2And 1/2 distance delta between the first laser source 71 and the first projection point and between the second laser source 72 and the second projection point01、δ02；
S7: loading a torque on a blade loading end through the disc type torque loading device (5);
s8: respectively recording the corresponding movement distances delta of the first projection point and the second projection point relative to the initial position after the torque is loaded1，δ2；
S9: respectively calculating the torsion angle variation beta of the first reflector 81 and the second reflector 82 by using a torsion angle formula1、β2；
S10: calculating the torsional rigidity of the section to be measured of the torsional rigidity of the rotor blade test piece 100 by using a torsional rigidity calculation formula;
s11: and repeating the steps of S6-S10, loading the torque of the blade at different levels, calculating the torsional rigidity of the blade corresponding to each level of load, and averaging.
In one possible implementationIn this example, in step S5, the incident angle α between the first laser light source 71 and the first mirror 81 is appropriately adjusted and selected according to the size of the area of the projection standing wall 61And the incident angle alpha of the second laser source 72 and the second reflector 822The angle of incidence α1、α2The selection range of (1) is 15-45 degrees.
In one possible embodiment, in the step S9, the variation β of the reflection angle between the first reflective mirror 81 and the second reflective mirror 82 is calculated by using the following torsion angle formulas 1 and 21、β2，
In one possible embodiment, in step S10, the torsional stiffness GJ of the section under test of torsional stiffness of the rotor blade trial 100 is calculated using the following torsional stiffness calculation formula 3;
wherein phi is beta1-β2M is the torque applied to the blade loading end, and Δ L is the vertical distance between the first reflector 81 and the second reflector 82.
The invention has the beneficial effects that: the invention provides a system and a method for measuring torsional rigidity of a vertical rotor blade, which are used for analyzing the defects of the existing engineering measurement method, reducing blade bending and twisting coupling caused by external factors such as blade weight, clamp weight, load application and the like by vertically fixing the blade, converting a measured micro-change torsion angle into displacement measurement of a measurement amplification level by a mirror reflection principle, improving the key factor of the existing measurement method which is most easy to introduce measurement errors, and meeting the requirement of the current engineering test precision by verifying a subject blade.
Drawings
FIG. 1 is a schematic view of the structure of the apparatus of the present invention
FIG. 2 is a schematic representation of the mirror geometry of the present invention under torque loading
Wherein:
1-fixing a vertical wall; 2-blade pin assembly, 21-blade pin, 22-mounting plate; 3-a blade rotation limiting clamp, 31-an inner pressing plate, 32-an outer pressing plate, 33-a fastening bolt and 34-a limiting clamp mounting plate; 4-blade loading fixture, 41-clamping hole; 5-a disc torque loading device; 6-projecting a vertical wall; 7-laser light source, 71-first laser light source, 72-second laser light source; 8-mirror, 81-first mirror, 82-second mirror; 100-rotor blade test piece
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, a system for measuring torsional rigidity of a vertical rotor blade is used for testing torsional rigidity of an airfoil section of the rotor blade, and comprises a fixed vertical wall 1, a blade pin assembly 2, a blade rotation limiting clamp 3, a blade loading clamp 4, a disc type torque loading device 5, a projection vertical wall 6, a laser light source 7 and a reflector 8;
the blade pin assembly 2 comprises a blade pin 21 and a mounting plate 22, the mounting plate 22 is fixedly connected to the fixed vertical wall 1 through a fastening device, a bushing hole is formed in the root of the rotor blade to be tested, the blade pin 21 penetrates through the bushing hole and is matched and fixed with the mounting plate 22, and the blade pin assembly 2 is only used for bearing the gravity of the blade;
referring to fig. 1, the blade rotation limiting clamp 3 is fixedly connected to a blade fixing vertical wall 1 through a fastening device, and the installation position of the blade rotation limiting clamp is located at the lower part of the blade pin assembly 2, specifically, at the initial position of the airfoil profile of the blade to be tested, the blade rotation limiting clamp 3 includes an inner pressure plate 31, an outer pressure plate 32, a fastening bolt 33 and a limiting clamp installation plate 34, the limiting clamp installation plate 34 is fixedly connected to the fixing vertical wall 1 through the fastening device, the inner pressure plate 31 and the outer pressure plate 32 are connected to the limiting clamp installation plate 34 through the fastening bolt 33, the rotor blade to be tested is clamped between the inner pressure plate 31 and the outer pressure plate 32, and the influence of the deformation of the complex transition section of the blade on the testing accuracy is mainly eliminated;
referring to fig. 1, a loading end is arranged at the tip side of a rotor blade to be tested, a clamping hole 41 is formed in the middle of the blade loading clamp 4, the inner surface of the clamping hole 41 is matched with the airfoil shape of the loading end of the rotor blade to be tested, and the blade loading clamp 4 is sleeved at the loading end of the rotor blade to be tested;
referring to fig. 1, the disc torque loading device 5 is fixedly connected to the lower portion of the blade loading fixture 4, and is configured to generate a torque with a variable pitch axis of the rotor blade to be tested as a center, and a torque loading center of the disc torque loading device 5 is on the variable pitch axis of the rotor blade to be tested;
referring to fig. 1, a section to be measured of torsional rigidity is arranged on a rotor blade to be measured, the upper end and the lower end of the same side surface of the section to be measured are respectively provided with a reflection lens 8 which is marked as a first reflection lens 81 and a second reflection lens 82, the first reflection lens 81 and the second reflection lens 82 are adhered and fixed on the surface of the blade, and the lens surface of the first reflection lens 81 and the second reflection lens 82 is basically parallel to the chord line direction of the rotor blade to be;
referring to fig. 1, the laser light source 7 generates an incident light source of the lens 8, which is detachably connected to the projection vertical wall 6, and correspondingly includes a first laser light source 71 and a second laser light source 72, the first reflection lens 81 is at the same level as the first laser light source 71, and the second reflection lens 82 is at the same level as the second laser light source 72;
referring to fig. 1 and 2, an included angle θ is formed between the wall surface of the projection vertical wall 6 and the mirror surface of the lens 8, and the included angle θ is in a range of 0 to 15 degrees; the distance from the incident point of the lens 8 to the wall surface of the projection vertical wall 6 is D, and the distance D is larger than or equal to 3 m.
A method for measuring torsional rigidity of a vertical rotor blade comprises the following steps:
s1: manufacturing a rotor blade test piece 100; the blade tip is cut off by selecting a proper position for the irregular blade tip, so that the torque loading is favorably implemented;
s2: referring to fig. 1, a vertical rotor blade torsional stiffness measurement system is designed;
s3: referring to fig. 1, the rotor blade test piece 100 is vertically hung on a wall through the blade pin assembly 2, the blade rotation limiting clamp 3 is installed at the airfoil starting position of the rotor blade test piece 100, the blade loading clamp 4 is installed at the torque loading end of the rotor blade test piece 100, and the disc type torque loading device 5 is fixedly connected with the blade loading clamp 4 to ensure that the torque loading center is on the variable pitch axis of the rotor blade test piece 100;
s4: referring to fig. 1, a section to be tested of torsional rigidity is selected, the first reflector 81 and the second reflector 82 are respectively adhered and fixed to the upper end and the lower end of the same side surface of the section to be tested of torsional rigidity, and on the variable pitch axis of the rotor blade test piece 100, the mirror surface is ensured to be substantially parallel to the chord line;
s5: referring to fig. 1, according to the height of the adhering position of the first reflecting mirror 81 and the second reflecting mirror 82 in step S4, the first laser source 71 and the second laser source 72 are installed on the projection vertical wall 6 at the same horizontal height position; ensuring that the first laser light source 71, referring to fig. 1 and fig. 2, emits the first laser beam, which is reflected by the first reflecting mirror 81, to generate the first projection point on the projection wall in the same horizontal height plane; the second laser beam emitted by the second laser source 72 is reflected by the second reflector 82 to generate a second projection point on the projection wall, and the second projection point is also in the same horizontal height plane;
preferably, according to the area of the projection vertical wall 6, the incident angle between the first laser source 71 and the first reflector 81 and the incident angle between the second laser source 72 and the second reflector 82 are reasonably adjusted and selected, and the range of the incident angle α is 15-45 °;
s6: referring to fig. 1 and 2, the disc type torque loading device (5) loads the torque of the blade loading end, and before loading, the initial incident angles alpha of the first laser beam and the second laser beam are respectively recorded1、α2And 1/2 distance delta between the first laser source 71 and the first projection point and between the second laser source 72 and the second projection point01、δ02；
S7: referring to fig. 1, the disc type torque loading equipment (5) loads a torque M on a blade loading end, and a torque application center is a variable pitch axis;
s8: referring to fig. 2, the moving distances δ corresponding to the initial positions of the loaded first projection point and the loaded second projection point are recorded respectively1、δ2The method converts the micro torsion angle change of the measured section into the measurement amplification distance, thereby greatly reducing the measurement error;
s9: referring to fig. 2, the variation β of the reflection angle between the first reflective mirror 81 and the second reflective mirror 82 is calculated by using the formula 1-21、β2Repeating the steps 7-9, and taking the average value of the effective measurement results of 3 times;
s10: calculating the torsional rigidity of the section to be measured of the torsional rigidity of the rotor blade test piece 100 by using a torsional rigidity calculation formula;
s11: and carrying out torque loading of different grades on the blades, calculating the torsional rigidity of the corresponding blade under each grade of load, and calculating the average value.
Claims (8)
1. A vertical rotor blade torsional rigidity measuring system is characterized by comprising a fixed vertical wall (1), a blade pin assembly (2), a blade rotation limiting clamp (3), a blade loading clamp (4), a disc type torque loading device (5), a projection vertical wall (6), a laser light source (7) and a reflector (8),
the blade pin assembly (2) comprises a blade pin (21) and a mounting plate (22); the mounting plate (22) is fixedly connected to the fixed vertical wall (1) through a fastening device, a bushing hole is formed in the root of the rotor blade to be tested, and the blade pin (21) penetrates through the bushing hole and is matched with the mounting plate (22) to fix the rotor blade to be tested;
the paddle rotation limiting clamp (3) is fixedly connected to the paddle fixing vertical wall (1) through a fastening device, and the mounting position of the paddle rotation limiting clamp is positioned below the paddle pin assembly (2); the paddle rotation limiting clamp (3) comprises an inner pressing plate (31), an outer pressing plate (32), a fastening bolt (33) and a limiting clamp mounting plate (34), the limiting clamp mounting plate (34) is fixedly connected to the fixed vertical wall (1) through a fastening device, the inner pressing plate (31) and the outer pressing plate (32) are connected with the limiting clamp mounting plate (34) through the fastening bolt (33), and a rotor paddle to be tested is clamped between the inner pressing plate (31) and the outer pressing plate (32);
one end of the blade tip of the rotor blade to be tested is a loading end, a clamping hole (41) is formed in the middle of the blade loading clamp (4), the inner surface of the clamping hole (41) is matched with the wing shape of the loading end of the rotor blade to be tested, and the blade loading clamp (4) is sleeved at the loading end of the rotor blade to be tested;
the disc type torque loading equipment (5) is fixedly connected to the lower part of the blade loading clamp (4) and is used for generating torque taking a variable pitch axis of the rotor blade to be tested as a center;
the rotor blade to be measured is provided with a torsional rigidity section to be measured, the upper part and the lower part of the surface on the same side of the variable pitch axis of the torsional rigidity section to be measured are respectively and symmetrically provided with a reflecting lens (8) which is marked as a first reflecting lens (81) and a second reflecting lens (82), the first reflecting lens (81) and the second reflecting lens (82) are adhered and fixed on the surface of the blade, and the mirror surface of the reflecting lens (8) is parallel to the chord line direction of the rotor blade to be measured;
the laser light source (7) generates an incident light source of the lens (8), is detachably connected to the projection vertical wall (6), and correspondingly comprises a first laser light source (71) and a second laser light source (72), the first reflecting lens (81) and the first laser light source (71) are at the same horizontal height, and the second reflecting lens (82) and the second laser light source (72) are at the same horizontal height;
an included angle theta is formed between the wall surface of the projection vertical wall (6) and the mirror surface of the lens (8).
2. A vertical rotor blade torsional stiffness measurement system according to claim 1 wherein the blade rotation stop clamp (3) is mounted at the blade airfoil starting position to be measured.
3. A vertical rotor blade torsional stiffness measurement system according to claim 1 wherein the disc torque loading device (5) has a center of torque loading on the pitch axis of the rotor blade under test.
4. The system according to claim 1, wherein the included angle θ is in the range of 0-15 °; the distance from the incident point of the lens (8) to the wall surface of the projection vertical wall (6) is D, and the distance D is larger than or equal to 3 m.
5. A method for measuring torsional stiffness of a vertical rotor blade using a system for measuring torsional stiffness of a vertical rotor blade according to any one of claims 1 to 4, comprising the steps of:
s1: manufacturing a rotor blade test piece (100); selecting a proper position for the irregular tip to cut off the tip;
s2: designing a corresponding vertical rotor blade torsional stiffness measurement system for the rotor blade test piece (100) manufactured in the step S1;
s3: vertically hanging the rotor blade test piece (100) on a wall through the blade pin assembly (2), installing the blade rotation limiting clamp (3) at the initial position of the airfoil of the rotor blade test piece (100), installing the blade loading clamp (4) at the torque loading end of the rotor blade test piece (100), and fixedly connecting the disc type torque loading equipment (5) with the blade loading clamp (4) to ensure that the torque loading center is on the variable pitch axis of the rotor blade test piece (100);
s4: selecting a torsional rigidity section to be measured on the rotor blade test piece (100), and respectively sticking and fixing the first reflector lens (81) and the second reflector lens (82) on a variable pitch axis of the torsional rigidity section to be measured at upper and lower symmetrical positions on the same side surface to ensure that a mirror surface is parallel to a chord line;
s5: installing the first laser light source (71) and the second laser light source (72) at the corresponding same horizontal height position on the projection vertical wall (6) according to the height of the pasting position of the first reflection mirror (81) and the second reflection mirror (82) in the step S4; ensuring that a first laser beam emitted by the first laser light source (71) is reflected by the first reflector (81) to generate a first projection point on a projection wall, and the first projection point is in the same horizontal height plane with the first laser light source (71) and the first reflector (81); a second laser beam emitted by the second laser source (72) is reflected by the second reflector (82) to generate a second projection point on a projection wall, and the second laser source (72) and the second reflector (82) are also in the same horizontal height plane;
s6: respectively recording initial incident angles alpha corresponding to the first laser beam and the second laser beam before carrying out torque loading on a blade loading end through the disc type torque loading equipment (5)1、α2And 1/2 distance delta between the first laser light source (71) and the first projection point and between the second laser light source (72) and the second projection point01、δ02；
S7: loading a torque on a blade loading end through the disc type torque loading device (5);
s8: respectively recording the corresponding movement distances delta of the first projection point and the second projection point relative to the initial position after the torque is loaded1，δ2；
S9: respectively calculating the torsion angle variation beta of the first reflector (81) and the second reflector (82) by using a torsion angle formula1、β2；
S10: calculating the torsional rigidity of the section to be measured of the torsional rigidity of the rotor blade test piece (100) by using a torsional rigidity calculation formula;
s11: and repeating the steps of S6-S10, loading the torque of the blade at different levels, calculating the torsional rigidity of the blade corresponding to each level of load, and averaging.
6. A method according to claim 5, wherein in step S5, the angle of incidence α between the first laser source (71) and the first mirror (81) is selected and adjusted according to the area of the projected vertical wall (6)1And an angle of incidence α of the second laser light source (72) with the second mirror (82)2The angle of incidence α1、α2The selection range of (1) is 15-45 degrees.
7. The method of claim 6, wherein in step S9, the variation β of the reflection angle between the first reflector (81) and the second reflector (82) is calculated by the following torsion angle equations (1) and (2), respectively1、β2，
8. A method for measuring torsional rigidity of a vertical rotor blade according to claim 5, wherein in said step S10, the torsional rigidity GJ of the section to be measured of torsional rigidity of said rotor blade test piece (100) is calculated using the following torsional rigidity calculation formula (3);
wherein phi is beta1-β2M is the torque applied to the blade loading end, and Δ L is the vertical distance between the first (81) and second (82) mirrors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011199963.0A CN112504873B (en) | 2020-10-30 | 2020-10-30 | Vertical rotor blade torsional rigidity measuring system and measuring method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011199963.0A CN112504873B (en) | 2020-10-30 | 2020-10-30 | Vertical rotor blade torsional rigidity measuring system and measuring method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112504873A true CN112504873A (en) | 2021-03-16 |
| CN112504873B CN112504873B (en) | 2022-09-13 |
Family
ID=74954780
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011199963.0A Active CN112504873B (en) | 2020-10-30 | 2020-10-30 | Vertical rotor blade torsional rigidity measuring system and measuring method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112504873B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148225A (en) * | 2021-04-20 | 2021-07-23 | 中国直升机设计研究所 | Testing device and testing method for fixing and rotating helicopter blades |
| CN113514346A (en) * | 2021-07-15 | 2021-10-19 | 湖南大学 | Device and method for measuring shear modulus of material |
| US20230266216A1 (en) * | 2022-02-23 | 2023-08-24 | Bell Textron Inc. | Apparatus for introducing test loads to a rotor blade |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4226536A (en) * | 1979-02-23 | 1980-10-07 | Dreyfus Marc G | Electro-optical contour measuring system |
| US4422757A (en) * | 1981-08-13 | 1983-12-27 | Hughes Helicopters, Inc. | Apparatus and method for optical phasing of helicopter main rotor blades |
| US4864863A (en) * | 1988-04-22 | 1989-09-12 | United Technologies Corporation | Mechanism for testing helicopter rotor blade fatigue properties |
| US5815302A (en) * | 1995-10-11 | 1998-09-29 | Hughes Electronic | Viewing apparatus with a counterbalanced and articulated mirror |
| US7322250B1 (en) * | 2002-04-09 | 2008-01-29 | Rockwell Automation Technologies, Inc. | System and method for sensing torque on a rotating shaft |
| JP2010149602A (en) * | 2008-12-24 | 2010-07-08 | Kawasaki Heavy Ind Ltd | Method and device for detecting rotor blade displacement of rotor craft |
| DE102011000054A1 (en) * | 2011-01-07 | 2012-07-12 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Torsion sensor for detecting torsional stiffness of rotor blade used in helicopter rotor, has surface elements that are aligned and distributed radially around torque shaft, while connectors are provided in inter-connected state |
| CN104748693A (en) * | 2015-03-31 | 2015-07-01 | 南京航空航天大学 | Blade profile torsion stiffness measurement system based on binocular stereo vision |
| CN204495552U (en) * | 2015-04-07 | 2015-07-22 | 中国直升机设计研究所 | A kind of aerofoil profile clamping device for measuring blade twist rigidity |
| CN104792630A (en) * | 2015-04-27 | 2015-07-22 | 中国直升机设计研究所 | Test method for testing torsional rigidity of flexible beam |
| KR20160123606A (en) * | 2015-04-16 | 2016-10-26 | 한양대학교 산학협력단 | System and method for analysing vibration characteristic |
| CN207717311U (en) * | 2017-12-01 | 2018-08-10 | 中国直升机设计研究所 | A kind of helicopter blade torsion rigidity measurer |
-
2020
- 2020-10-30 CN CN202011199963.0A patent/CN112504873B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4226536A (en) * | 1979-02-23 | 1980-10-07 | Dreyfus Marc G | Electro-optical contour measuring system |
| US4422757A (en) * | 1981-08-13 | 1983-12-27 | Hughes Helicopters, Inc. | Apparatus and method for optical phasing of helicopter main rotor blades |
| US4864863A (en) * | 1988-04-22 | 1989-09-12 | United Technologies Corporation | Mechanism for testing helicopter rotor blade fatigue properties |
| US5815302A (en) * | 1995-10-11 | 1998-09-29 | Hughes Electronic | Viewing apparatus with a counterbalanced and articulated mirror |
| US7322250B1 (en) * | 2002-04-09 | 2008-01-29 | Rockwell Automation Technologies, Inc. | System and method for sensing torque on a rotating shaft |
| JP2010149602A (en) * | 2008-12-24 | 2010-07-08 | Kawasaki Heavy Ind Ltd | Method and device for detecting rotor blade displacement of rotor craft |
| DE102011000054A1 (en) * | 2011-01-07 | 2012-07-12 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Torsion sensor for detecting torsional stiffness of rotor blade used in helicopter rotor, has surface elements that are aligned and distributed radially around torque shaft, while connectors are provided in inter-connected state |
| CN104748693A (en) * | 2015-03-31 | 2015-07-01 | 南京航空航天大学 | Blade profile torsion stiffness measurement system based on binocular stereo vision |
| CN204495552U (en) * | 2015-04-07 | 2015-07-22 | 中国直升机设计研究所 | A kind of aerofoil profile clamping device for measuring blade twist rigidity |
| KR20160123606A (en) * | 2015-04-16 | 2016-10-26 | 한양대학교 산학협력단 | System and method for analysing vibration characteristic |
| CN104792630A (en) * | 2015-04-27 | 2015-07-22 | 中国直升机设计研究所 | Test method for testing torsional rigidity of flexible beam |
| CN207717311U (en) * | 2017-12-01 | 2018-08-10 | 中国直升机设计研究所 | A kind of helicopter blade torsion rigidity measurer |
Non-Patent Citations (2)
| Title |
|---|
| 熊邦书: "基于立体视觉的直升机桨叶扭转角模拟测量方法", 《应用科学学报》 * |
| 陶宪斌: "某直升机复合材料桨叶疲劳试验提前失效分析", 《科技创新与应用》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148225A (en) * | 2021-04-20 | 2021-07-23 | 中国直升机设计研究所 | Testing device and testing method for fixing and rotating helicopter blades |
| CN113148225B (en) * | 2021-04-20 | 2022-11-22 | 中国直升机设计研究所 | Testing device and testing method for fixing and rotating helicopter blades |
| CN113514346A (en) * | 2021-07-15 | 2021-10-19 | 湖南大学 | Device and method for measuring shear modulus of material |
| US20230266216A1 (en) * | 2022-02-23 | 2023-08-24 | Bell Textron Inc. | Apparatus for introducing test loads to a rotor blade |
| US11761866B2 (en) * | 2022-02-23 | 2023-09-19 | Textron Innovations Inc. | Apparatus for introducing test loads to a rotor blade |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112504873B (en) | 2022-09-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112504873B (en) | Vertical rotor blade torsional rigidity measuring system and measuring method | |
| CN107810321B (en) | Method of measuring loads on a wind turbine | |
| CN108120592A (en) | A kind of test method of helicopter blade static strength | |
| US8161822B2 (en) | Placement of strain sensors in wind turbine blade | |
| US20180180029A1 (en) | Blade load sensing system for a wind turbine | |
| Schneider | Analysis of SPR measurements from HART II | |
| CN109715940B (en) | Method for measuring pitch angle and/or for forming a measuring system for measuring pitch angle | |
| EP2910776A1 (en) | Method for setting a pitch reference point for a wind turbine blade on a rotor | |
| CN103547898A (en) | Method and apparatus for determining loads of a wind turbine blade | |
| CN112525737A (en) | Test device and test method for measuring flapping rigidity of helicopter blade | |
| JP2010071279A (en) | Method for aligning component into wind direction and sensor for determining misalignment of component relative to wind direction | |
| JP2008534918A (en) | Rotor blade cuff measuring instrument | |
| CN108225692B (en) | Test method for measuring overall torsional rigidity of blade | |
| CA2960745C (en) | A system and method for determining deflection of a wind turbine blade | |
| CN110966911A (en) | Device and method for measuring blade angle of aviation propeller | |
| US20220291101A1 (en) | System and method for determining strength of a structure | |
| CN115420444A (en) | Propeller blade rigidity test method and propeller blade rigidity test mechanism | |
| CN111894793B (en) | Wind generating set blade zero position adjusting method and system and wind generator | |
| US20240093672A1 (en) | An apparatus for determining orientation of a segment of a wind turbine blade and a method thereof | |
| CN210863553U (en) | Enameled wire lacquer concentration detection device | |
| CN117871066A (en) | Measuring device and measuring method for torsional rigidity of full-size wind power generation blade | |
| CN114858408B (en) | Test device for testing dynamic oscillation performance of hydrofoil | |
| CN210513033U (en) | One-way high-precision pipe diameter caliper box | |
| Stoddard et al. | Determination of elastic twist in horizontal axis wind turbines (HAWTs) | |
| CN114599494A (en) | Mould system and method for moulding a blade shell of a wind turbine blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | 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 |