CN112504589A - Helicopter composite material main blade airfoil section static strength test system and method - Google Patents
Helicopter composite material main blade airfoil section static strength test system and method Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/027—Specimen mounting arrangements, e.g. table head adapters
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- 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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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Abstract
The invention belongs to the field of static strength tests of helicopter composite material main blades, and relates to a system and a method for testing the static strength of a helicopter blade airfoil section. The invention relates to a helicopter blade airfoil section static strength test system which comprises an airfoil section test piece, a loading actuating cylinder, a centrifugal actuating cylinder, a support column, a force sensor, a strain tester and a fatigue test bed. According to the invention, a fatigue test bed is utilized to apply centrifugal force to the airfoil section test piece, and meanwhile, a strain measuring instrument capable of measuring bending moment is additionally arranged to carry out four-support-column support and double-loading-point loading on the airfoil section test piece, so that the bending moment distribution in a test interval is optimized and adjusted, static strength test loading is carried out on any interval of the main blade airfoil on the fatigue test bed, the technical problem that fatigue cyclic load loading and static loading need to be carried out alternately is solved, and the method has a large practical application value.
Description
Technical Field
The invention belongs to the field of static strength tests of helicopter composite material main blades, and relates to a method for testing the static strength of a helicopter blade airfoil section.
Background
At present, the composite material main blade is widely applied to helicopters of various types, and the typical section of the wing section of the main blade of the helicopter is one of the main parts examined by a static strength test; in accordance with the requirements of CCAR29R2, article 573, fatigue cyclic loading and static strength loading are required to be performed alternately during the damage tolerance test of a composite blade. At present, the full-size fatigue test of the main blade airfoil section is a displacement loading excitation resonance type test, is always in a vibration state, cannot realize static loading on a test bed, and cannot meet the requirements of alternately carrying out fatigue cyclic load loading and static strength loading. The traditional static strength test method for the main blade airfoil section only can divide the main blade airfoil section into small sections, a test bed is separately established for testing, loading is carried out based on a cantilever beam loading mode, and full-size multi-section testing cannot be carried out simultaneously.
In addition, the invention relates to a test method for the static strength of a helicopter blade, which is mainly described in the prior art CN108120592A, is based on the cantilever beam theory, aims at the static strength test method for the root section of a main blade, and can directly use an actuator cylinder to load to carry out the static strength test based on the cantilever beam and only check the root connection area of the blade because the root section of the main blade is small in size and high in overall rigidity. Different from the blade root section, the blade airfoil section is large in size and low in overall rigidity, and the examination area is the whole middle airfoil section of the main blade, and loading cannot be carried out based on the cantilever beam, so that the static strength test of the main blade airfoil section is difficult to realize on the basis of a vibration fatigue test bed in the prior art.
Disclosure of Invention
The purpose of the invention is as follows:
in order to realize the static strength test in the damage tolerance test process of the full-size main blade airfoil section and solve the problem that the static strength test of the composite material main blade airfoil section cannot be carried out on the basis of the vibration fatigue test installation of the main blade, a static strength test system and a static strength test method of the composite material main blade airfoil section of the helicopter are established.
The technical scheme of the invention is as follows: a helicopter blade airfoil section static strength test system comprises an airfoil section test piece, a loading actuating cylinder, a centrifugal actuating cylinder, a support column, a force sensor, a strain tester and a fatigue test bed, wherein the wing section test piece is arranged on a plurality of support columns, force sensors or strain gauges are arranged on the support columns, a loading actuating cylinder and the force sensors are arranged above the wing section test piece, the root part of the wing section test piece is connected with the elastic supporting end of the fatigue test bed, the tip part of the wing section test piece is connected with the force sensors and the centrifugal actuating cylinder through a clamp and then is connected with the fatigue test bed, wherein, the clamp at the tip of the test piece of the airfoil section is connected with an eccentric wheel of a fatigue test stand to realize displacement loading in the fatigue test process, when the static strength of the test piece of the airfoil section is tested, and the middle part and the tip part of the test piece of the airfoil section are simultaneously loaded in the axial direction by the loading actuator cylinder and the centrifugal actuator cylinder respectively.
When the loading actuator cylinder loads the test piece of the airfoil section, the loading actuator cylinder is provided with two loading points, the centers of the two loading points are positioned on the symmetrical center line of the strut, and the area between the two loading points is a test area of the airfoil section.
The supporting columns are at least two pairs, wherein one pair of supporting columns is provided with a force sensor and used for measuring a pressure value, the other pair of supporting columns is provided with a strain tester and used for measuring a bending moment value and a tensile force or pressure value simultaneously, and the supporting columns are symmetrically arranged on the lower base of the supporting columns so as to limit a test interval of the test piece of the airfoil section and solve the bending moment of the test interval under the condition of having a centrifugal force load.
An upper clamping plate and a lower clamping plate are arranged between the outer side pillar and the airfoil section test piece, the clamping plates are matched with the airfoil section test piece in shape and buckle and accommodate the airfoil section test piece, and therefore constraint except for axial direction is provided for the blades.
Be provided with down the cardboard between inboard pillar and the wing section test piece, this cardboard appearance and this section wing section test piece appearance phase-match down to provide vertical restraint.
A flexible layer is arranged between the wing section test piece and the upper clamping plate and the lower clamping plate, so that the wing section test piece is prevented from being damaged.
According to the test method of the helicopter blade airfoil section static strength test system, a fatigue test bed is utilized to apply centrifugal force to an airfoil section test piece, meanwhile, a strain measuring instrument capable of measuring bending moment is additionally arranged to support four supporting columns and load double loading points on the airfoil section test piece, bending moment distribution in a test interval is optimized and adjusted, and static strength test loading is carried out on any interval of a main blade airfoil on the fatigue test bed.
The method for testing the static strength of the airfoil section of the helicopter blade comprises the following steps:
the method comprises the following steps: determining each typical section to be examined through analysis, and calculating and determining the test load of each section;
step two: pasting swing and shimmy strain gages on the main section of the main blade airfoil section, and applying multi-stage swing and shimmy loads respectively to obtain calibration equations of swing bending moment and shimmy bending moment;
step three: strain gage is attached to the outboard A, B post and the axial force (N) of the A, B post is calibrateday、Nby) And bending moment (M)ax，May，Maz，Mbx，Mby，Mbz)；
Step four: mounting the main blade on a fatigue test bed; mounting A, B struts with blade shaped cleats, C, D struts with blade shaped bearing surfaces, and A, B, C, D struts are located on the blade twist axis; installing a loading actuator cylinder and a force sensor at the position E, F on the upper surface of the test piece of the airfoil section;
step five: static Strength test-Preload debugging
Determining a test profile, applying Fy, Fc proportionally to the top and tip of the test part at airfoil section, and testing N at point Aay，Maz，Max，May(ii) a N of B pointby，Mbz，Mbx，Mby(ii) a C point NcyN of point DdyDrawing a bending moment diagram, and determining load distribution through calculation; and by adjusting x1,x2,x3,x4,x5Wherein x is1＝x5,x2＝x4To achieve the needsLoad distribution of (2):
and make Maz-Nayx1Is less than Maz-Nay(x1+x2)-Ncyx2Absolute value of (d);
in the test interval, the proportion of the design load and the test load of each section is higher than that of the design load and the test load of the assessment section;
adjusting the Z-position of the strut ABCD so that Max，May，Mbx，MbyThe numerical value of (A) is as small as possible;
adjusting the installation angle of the main blade to realize the proportion of the main blade swinging, vibrating and bending moment;
step six: static Strength test
Increasing F step by step according to proportiony、FcLoad according to formula Maz-Nay(x1+x2)-Ncyx2Calculating a bending moment value of a test interval, and unloading after meeting the load-holding test requirement;
step seven: and adjusting the test profile, and repeating the processes from the step five to the step six.
The invention has the beneficial effects that: the static strength test in the damage tolerance test process of the main blade airfoil section made of the full-size composite material is realized on the basis of the vibration fatigue test bed of the main blade airfoil section; the centrifugal force loading is realized by fully utilizing the existing test bed centrifugal force loading device; the four-support-column supporting and double-loading-point structure with adjustable positions is adopted, so that the bending moment distribution in a test interval can be optimized and adjusted, no bending moment outside the test interval is ensured, the technical problem that fatigue cyclic load loading and static force loading need to be carried out alternately in the main blade airfoil section damage tolerance test process is solved, and the method can be widely applied to the follow-up static strength test of the main blade airfoil sections of various models.
Drawings
FIG. 1 is a schematic illustration of a helicopter main blade airfoil section patch according to an embodiment of the present invention;
FIG. 2 is a schematic illustration of the experimental loading of the present invention;
FIG. 3 is a schematic view of the bending moment in the test section of the present invention;
FIG. 4 is a schematic view of a flapping bending moment according to an embodiment of the present invention;
figure 5 is a schematic view of a shimmy bending moment according to an embodiment of the present invention,
the test device comprises an airfoil section test piece 1, a loading actuator cylinder 2, a centrifugal actuator cylinder 3, a force sensor 4, a strain tester 5, a strut lower base 6, an elastic support end 7 and a support clamp 8.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application will be described in further detail with reference to the accompanying drawings and specific embodiments.
Example 1:
taking a static strength test of an airfoil section of a main blade of a certain type machine as an example, the load direction is specified as follows: centrifugal force Fc points to the blade tip, the flapping bending moment is that the tension of the upper wing surface of the blade is positive, and the shimmy bending moment is that the tension of the rear edge of the blade is positive. The cross sections determined by analysis to be examined are as follows, 5 cross sections of 1910, 2160, 2420, 2910, 3320 and the like are shown in figure 1, and given design loads are as follows in table 1,
TABLE 1 design load of main blade airfoil section of certain type machine
The examples herein only show the practice of section 2160,
strain gauges are adhered to A, B, C, D four pillars, and the axial force (N) of A, B pillars is calibrated by 5-stage loaday、Nby) And bending moment (M)ax，Maz，Mbx，Mbz) The calibration equation of (1) is that a strain gauge is pasted on the section of the airfoil section of the main blade shown in figure 1, and the swinging and shimmy bending moments are calibrated. The calibration formula is as follows, wherein Y is Kx + b, Y is axial force N (bending moment N.m), and x is strain gaugeThe tested strain value and the fitting coefficient after K and b calibration; the main blade 2160 profile calibration coefficients are as follows in table 2.
TABLE 2 main blade calibration coefficients
| Strain gauge position (mm) | Coefficient of shimmy calibration | Calibration coefficient of waving |
| 2160 | 0.5050 | 1.01 |
Setting the distance x between each strut and the load point1、x2、x3、x4、x5In this embodiment, x3＝100mm，x2＝x4＝100mm,x1＝x5＝200mm。
The drag-flap load ratio of the main blade at the section 2160 is 2.4644, the initial installation angle of the main blade is adjusted to 67.9 degrees, and F is applied to the middle part of the test piece of the airfoil section through the loading actuator cylinderyApplying centrifugal load F to the tip of the test piece of the airfoil section by using a fatigue test benchc42024N, see fig. 2 for a schematic test loading of the present invention.
Test to obtain Nay＝-6350.4N，Maz＝232477.8N，Ncy＝24647.4N，Ndy＝24647.4N，Nby＝-6350N，Mbz232477.8N, and plotting the obtained test bending moment diagram, wherein, a flapping bending moment diagram of a section of the airfoil section test piece 2160 is shown in FIG. 4, and a shimmy bending moment diagram of a section of the airfoil section test piece 2160 is shown in FIG. 5.
The bending moment applied by the test 2160 profile is compared to the target bending moment value in table 3.
Table 32160 results of cross-section comparison
| Cross-sectional position Mm | The design load is 30% | Testing bending moment | Difference between the two |
| Wave N.m | -810 | -811.4 | 0.17％ |
| Shimmy N.m | 1996.2 | 1998.2 | 0.10％ |
And to note that the following requirements need to be met:
1)Maz-Nayx1is less than Maz-Nay(x1+x2)-Ncyx2The analysis results are shown in Table 4 to meet the requirements of the experimental design.
TABLE 4 waving and shimmy contrast
| Cross-sectional position Mm | |Maz-Nayx1| | |Maz-Nay(x1+x2)-Ncyx2| | Meet the situation |
| Waving bending moment N.m | 565.3 | 811.4 | Conform to |
| Pendulum vibration bending moment N.m | 1392.1 | 1998.2 | Conform to |
2) In the test interval, the proportion of the design load and the test load of each section is higher than that of the design load and the test load of the assessment section (2160mm), so that the test load of the non-test interval is lower than the design load, the analysis result is shown in table 5, and the analysis result meets the requirement.
TABLE 5 comparison table of bending moment design value and test value
| Cross-sectional position Mm | 1920mm | 2160mm | 2420mm | Meet the situation |
| Design/test value of waving bending moment | 3.4415 | 3.3275 | 3.6562 | Conform to |
| Pendulum vibration bending moment design value/test value | 4.0900 | 3.3298 | 4.7488 | Conform to |
Increasing F step by step according to proportiony、FcLoad, the value of the test load (in this case F) shown in Table 1 was obtainedc＝140082N，Fy121996N), and unloading after meeting the requirements of the load-holding test.
If the test requirements are not met, adjusting the distance x between each strut and the loading point1、x2、x3、x4、x5And carrying out the loading test again until the design requirement of the test is met.
In conclusion, the invention adopts a four-support-column supporting and double-loading-point structure with adjustable positions for the static strength test of the main blade airfoil section, so that the bending moment distribution in a test interval can be optimized and adjusted, and the test loading is carried out on any interval of the main blade airfoil; the static strength test method can be directly modified on the basis of the existing vibration fatigue test bed without establishing a separate test bed, and a test loading and restraining mode designed based on a four-point bending test method is introduced on the basis of the vibration fatigue test bed, so that the static strength test in the damage tolerance test process of the main blade airfoil section of the full-size composite material is realized, and the static strength test method has obvious technical progress and higher practical application value compared with the prior art.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present invention shall be included in the protection scope of the present invention, and the present invention shall not be detailed in the conventional art.
Claims (8)
1. A helicopter blade airfoil section static strength test system is characterized by comprising an airfoil section test piece, a loading actuating cylinder, a centrifugal actuating cylinder, a strut, a force sensor, a strain tester and a fatigue test bed, wherein the wing section test piece is arranged on a plurality of support columns, force sensors or strain gauges are arranged on the support columns, a loading actuating cylinder and the force sensors are arranged above the wing section test piece, the root part of the wing section test piece is connected with the elastic supporting end of the fatigue test bed, the tip part of the wing section test piece is connected with the force sensors and the centrifugal actuating cylinder through a clamp and then is connected with the fatigue test bed, wherein, the clamp at the tip of the test piece of the airfoil section is connected with an eccentric wheel of a fatigue test stand to realize displacement loading in the fatigue test process, when the static strength of the test piece of the airfoil section is tested, and the middle part and the tip part of the test piece of the airfoil section are simultaneously loaded in the axial direction by the loading actuator cylinder and the centrifugal actuator cylinder respectively.
2. The helicopter blade airfoil section static strength test system of claim 1 wherein the loading ram loads the airfoil section test piece with two load points centered on the strut's center of symmetry.
3. The helicopter blade airfoil section static strength testing system of claim 1 wherein the struts are in at least two pairs, one pair of which is provided with force sensors and the other pair of which is provided with strain gauges, and wherein the struts are symmetrically disposed on the strut sub-base.
4. The helicopter blade airfoil section static strength test system of claim 1, wherein an upper and a lower snap-gauge are provided between the outboard strut and the airfoil section test piece, the snap-gauge being matched with the profile of the airfoil section test piece and retaining the airfoil section test piece.
5. The helicopter blade airfoil section static strength test system of claim 1, characterized in that a lower snap-gauge is disposed between the inboard strut and the airfoil section test piece, the lower snap-gauge profile matching the profile of the airfoil section test piece.
6. The helicopter blade airfoil section static strength test system of claim 1, wherein a flexible layer is disposed between the airfoil section test piece and the upper and lower snap plates.
7. A test method based on a helicopter blade airfoil section static strength test system according to any one of claims 1 to 6 is characterized in that a fatigue test bench is utilized to apply centrifugal force to an airfoil section test piece, meanwhile, a strain gauge capable of measuring bending moment is additionally arranged to perform four-support-column support and double-loading-point loading on the airfoil section test piece, the distribution of the bending moment in a test interval is optimized and adjusted, and static strength test loading is performed on any interval of a main blade airfoil on the fatigue test bench.
8. The helicopter blade airfoil section static strength testing method of claim 7, comprising the steps of:
the method comprises the following steps: determining each typical section to be examined and the test load of each section through analysis;
step two: pasting swing and shimmy strain gages on the main section of the main blade airfoil section, and applying multi-stage swing and shimmy loads respectively to obtain calibration equations of swing bending moment and shimmy bending moment;
step (ii) ofThirdly, the method comprises the following steps: a strain gage is attached to A, B support and the axial force (N) of A, B support is calibrateday、Nby) And bending moment (M)ax，May，Maz，Mbx，Mby，Mbz)；
Step four: mounting the main blade on a fatigue test bed; mounting A, B struts with blade shaped cleats, C, D struts with blade shaped bearing surfaces, and A, B, C, D struts are located on the blade twist axis; installing a loading actuator cylinder and a force sensor at the position E, F on the upper surface of the test piece of the airfoil section;
step five: static Strength test-Preload debugging
Determining a test profile, applying Fy, Fc proportionally to the top and tip of the test part at airfoil section, and testing N at point Aay，Maz，Max，May(ii) a N of B pointby，Mbz，Mbx，Mby(ii) a C point NcyN of point DdyDrawing a bending moment diagram, and determining load distribution through calculation; and by adjusting x1,x2,x3,x4,x5Wherein x is1＝x5,x2＝x4And realizing the required load distribution condition:
and make Maz-Nayx1Is less than Maz-Nay(x1+x2)-Ncyx2Absolute value of (d);
in the test interval, the proportion of the design load and the test load of each section is higher than that of the design load and the test load of the assessment section;
adjusting the Z-position of ABCD so that Max，May，Mbx，MbyThe numerical value of (A) is as small as possible;
adjusting the installation angle of the main blade to realize the proportion of the main blade swinging, vibrating and bending moment;
step six: static Strength test
Increasing F step by step according to proportiony、FcLoad according to formula Maz-Nay(x1+x2)-Ncyx2Calculating a bending moment value of a test interval, and unloading after meeting the load-holding test requirement;
step seven: and adjusting the test profile, and repeating the processes from the step five to the step six.
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| CN113420366A (en) * | 2021-04-20 | 2021-09-21 | 中国直升机设计研究所 | Method for verifying bonding strength of blade anti-icing and deicing heating assembly |
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| CN113420366A (en) * | 2021-04-20 | 2021-09-21 | 中国直升机设计研究所 | Method for verifying bonding strength of blade anti-icing and deicing heating assembly |
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