CN114235360B - Analysis method for measured load phase relation of helicopter blade - Google Patents
Analysis method for measured load phase relation of helicopter blade Download PDFInfo
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- 238000004458 analytical method Methods 0.000 title claims abstract description 24
- 238000012360 testing method Methods 0.000 claims abstract description 9
- 238000005452 bending Methods 0.000 claims description 33
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- 230000009466 transformation Effects 0.000 claims description 9
- 230000002159 abnormal effect Effects 0.000 claims description 4
- 238000005457 optimization Methods 0.000 abstract description 4
- 239000013585 weight reducing agent Substances 0.000 abstract description 3
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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
- G01M13/00—Testing of machine parts
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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
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- B64F5/60—Testing or inspecting aircraft components or systems
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- 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
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
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- 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
- G01N2203/0005—Repeated or cyclic
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- 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
- G01N2203/0023—Bending
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- 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
- G01N2203/0676—Force, weight, load, energy, speed or acceleration
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Abstract
The invention provides an analysis method of a measured load phase relation of a helicopter blade, which comprises the following steps: identifying the flight attitude of the helicopter according to the flight parameters; under the flight attitude, segmenting load data of the helicopter blades at intervals of a preset data quantity; wherein the preset data amount comprises 2 K K is an integer greater than zero; determining a first frequency of the payload data from a fourier transform; wherein the amplitude corresponding to the first frequency is the largest; acquiring a phase angle of the load data according to the first frequency; determining a phase difference of the load data from the phase angle; the invention provides an analysis method of a phase relation based on the measured load of a helicopter blade, and the obtained phase relation can be used for blade strength calculation, test loading scheme formulation and structure weight reduction optimization, and has great engineering application prospect.
Description
Technical Field
The invention belongs to the technical field of helicopter structural fatigue design, and particularly relates to an analysis method for a measured load phase relation of a helicopter blade.
Background
The main load born by the helicopter blade in flight is centrifugal force, waving bending moment and shimmy bending moment. Centrifugal force is mainly generated by blade rotation, is generally only related to rotor rotation speed, and is basically constant because the rotor rotation speed of the helicopter is basically unchanged during flight. The flapping bending moment and the shimmy bending moment are closely related to the flying state, and the load cycle characteristics are quite obvious, and are generally integer multiples of the rotating speed of the rotor wing. And the waving bending moment and the shimmy bending moment have certain phase relation, and the phase relation is different in different flight states. The different phase relations have great influence on load analysis, strength calculation and test result evaluation of the helicopter blade.
The conventional helicopter blade is generally and unevenly distributed in load analysis, strength calculation and test result evaluation, and the flapping bending moment and the shimmy bending moment are considered to be in phase, namely the flapping bending moment and the shimmy bending moment reach peak values and valley values simultaneously in one load period. The phase processing method is relatively conservative, does not truly reflect the loading condition of the blade, causes a larger gap between theoretical calculation and test results and actual flight results, and meanwhile, the traditional phase processing method does not utilize the weight reduction optimization of the structure.
Disclosure of Invention
Aiming at the technical problems, the invention provides an analysis method for a measured load phase relation of a helicopter blade, which comprises the following steps:
identifying the flight attitude of the helicopter according to the flight parameters;
under the flight attitude, segmenting load data of the helicopter blades at intervals of a preset data quantity; wherein the preset data amount comprises 2 K K is an integer greater than zero;
determining a first frequency of the payload data from a fourier transform; wherein the amplitude corresponding to the first frequency is the largest;
acquiring a phase angle of the load data according to the first frequency; and determining the phase difference of the load data according to the phase angle.
Preferably, the flight attitude includes flat fly, climb, hover, turn, and descent; the flight parameters include pitch angle, roll angle, speed, altitude, and heading angle.
Preferably, the segmenting the load data of the helicopter blade at intervals of a preset data amount includes:
segmenting the waving bending moment of the helicopter blade at intervals of a first preset data volume;
segmenting the shimmy bending moment of the helicopter blade at intervals of a second preset data volume; wherein the first preset data amount is the same as the second preset data amount.
Preferably, after the segmenting the load data of the helicopter blade with the preset data amount as an interval, the method further comprises:
and acquiring the amplitude and the phase of the load data at different frequencies according to Fourier transformation.
Preferably, after identifying the flight attitude of the helicopter according to the flight parameters, the method further comprises:
clearing abnormal load data; wherein the abnormal load data is data which is inconsistent with actual expectations in a section of test data.
Preferably, the determining the phase difference of the load data according to the phase angle includes:
determining the phase difference of the waving bending moment and the shimmy bending moment according to the first phase angle and the second phase angle; wherein the first phase angle is the phase angle of the flap bending moment and the second phase angle is the phase angle of the lag bending moment.
Preferably, the determining the phase difference of the load data according to the phase angle further includes:
if the phase difference is negative, the phase difference is added by 360 DEG according to the periodicity of the trigonometric function.
Preferably, after the phase difference of the load data is determined according to the phase angle, the method further includes:
and counting the phase difference by adopting a probability density function, and obtaining the phase difference with the largest occurrence number.
The beneficial technical effects of the invention are as follows:
the invention provides an analysis method of a phase relation based on the measured load of a helicopter blade, and the obtained phase relation can be used for blade strength calculation, test loading scheme formulation and structure weight reduction optimization, and has great engineering application prospect.
Drawings
FIG. 1 is a flow chart of a method for analyzing measured load phase relationship of a helicopter blade provided by an embodiment of the invention;
FIG. 2 is a graph of probability distribution of a main blade root flapping bending moment and a shimmy bending moment phase difference in a climbing state provided by an embodiment of the invention;
FIG. 3 is a graph of load before data skip clearing provided by an embodiment of the present invention;
FIG. 4 is a graph of load after data jump cleaning provided by an embodiment of the present invention;
fig. 5 is a load time domain diagram and a load frequency domain diagram provided by an embodiment of the present invention.
Detailed Description
Referring to fig. 1-5, the analysis method based on the phase relation of the measured load of the helicopter blade is used for guiding the loading phase relation between different loads in the strength test scheme and obtaining the strength calculation result which is closer to the flight reality, and provides design reference for the structural optimization design.
The technical scheme of the invention is as follows: according to the method, the existing actual measurement blade load data is subjected to flight state division, data processing and Fourier mathematical transformation to finally obtain the load phase relation. The specific steps are shown in the attached figure 1, and the following is briefly described:
[1] flight status division
The flight state identification is carried out according to flight parameter data of the helicopter, and the flight attitude of the helicopter is generally identified by adopting flight parameter data such as pitch angle, roll angle, speed, altitude, course angle and the like. When combined with the helicopter, most of the load phases are in stable states such as flat flight, climbing, hovering, turning, descending and the like, and the analysis of the load phase relationship in the stable states is more meaningful. The flight status classification thus primarily identifies these steady states.
[2] Jump point cleaning process
Jump points, also called outlier points, outlier points refer to some measurement points that are relatively few in a piece of test data and that are significantly larger in and out of the nearby measurement values than actually expected. By clearing the jump points, the data curve is smoother and more approximate to the true value.
[3] Data segmentation
In order to acquire more data points and more accurate load phase relation, a longer flight state is generally divided into a plurality of data segments, the number of points in each data segment is generally to the power of 2 k, and in order to obtain the phase relation of different load channels, load data segments should be kept consistent.
[4] Fourier transform
And (3) carrying out Fourier transformation on the data points segmented by the skip point clearing step [2] and the data segment step [3] to obtain the amplitude and the phase of the load data under different frequencies.
Because the actual measurement load is discretized, the analysis precision depends on the data sampling frequency and the number of analysis data points participating in Fourier transformation, the number of the Fourier transformation analysis data points can be taken as 2 k according to experience, and the sampling rate of the actual measurement load data of a certain machine is f. Therefore, the frequency resolution=f/2≡k, and the frequency points that can be directly obtained are shown in table 1.
TABLE 1
| Sequence number | Frequency point (Hz) | Sequence number | Frequency point (Hz) |
| 1 | 1×f/2^k | 13 | 13×f/2^k |
| 2 | 2×f/2^k | 14 | 14×f/2^k |
| 3 | 3×f/2^k | 15 | 15×f/2^k |
| 4 | 4×f/2^k | 16 | 16×f/2^k |
| 5 | 5×f/2^k | 17 | 17×f/2^k |
| 6 | 6×f/2^k | 18 | 18×f/2^k |
| 7 | 7×f/2^k | 19 | 19×f/2^k |
| 8 | 8×f/2^k | 20 | 20×f/2^k |
| 9 | 9×f/2^k | 21 | 21×f/2^k |
| 10 | 10×f/2^k | 22 | 22×f/2^k |
| 11 | 11×f/2^k | 23 | 23×f/2^k |
| 12 | 12×f/2^k | …… | …… |
[5] Load frequency component analysis
The cyclic characteristics of the structural loads of the helicopter are quite obvious and are generally integer multiples of the rotor speed. As shown in fig. 3, the period of the load is obvious, and as can be seen from the frequency domain diagram, the main frequency component is the frequency corresponding to 1 time of the rotating speed, namely 4.3Hz.
[6] Extraction phase angle
And (3) extracting phase angle information of different load channels according to the component analysis result of the step (5) and frequency point data accurately obtained by Fourier transformation of the step (4). Table 2 is the phase angle of each data segment corresponding to the bending moment of waving and shimmy of the root of a main blade of a certain type obtained by analysis.
TABLE 2
[7] Phase relation analysis
The phase difference calculation is based on a certain load, the phase angle of the reference load is subtracted by the phase angle of another load, if the result is negative, the phase difference result can be added to 360 according to the periodicity of the trigonometric function, so that the phase difference falls between 0 and 360 degrees. That is, if the bending moment=a×cos (ωt), the shimmy bending moment=b×cos (ωt—Φ), Φ is the obtained phase difference. Table 4 shows the phase relation of the obtained bending moment of the root of the main blade of a certain machine and the bending moment of the lag.
TABLE 4 Table 4
[8] Probability statistics
And (3) counting the phase checking data result obtained in the step [7] by adopting a probability density function. The most frequently occurring phase relationship obtained from probability statistics. Therefore, the phase relation can be adopted for the calculation of the blade strength and the establishment of the experimental loading scheme in the state.
The present invention will be described in further detail with reference to examples. An analysis method for the measured load phase relation of a helicopter blade comprises the following steps:
[1] flight status division
And (3) carrying out flight state identification according to the flight parameter data, wherein for climbing, the time period of 1804 s-1903 s of the flight can be obtained to be in a climbing state according to a height change curve by combining the speed, the roll angle, the pitch angle and the course angle.
[2] Jump point cleaning process
See fig. 3-4 before and after clearing a data jump point of a channel.
[3] Data segmentation
The sampling rate 1024 of the load data is known from the data state division in step [1], the total climbing state time is 99s, the total number of data points=99×1024= 101376, and k=12 is taken from the data segment, so the number of data points per segment is 4096. The load data of the whole climb state can be divided into 101376/4096=24 data segments.
[4] Fourier transform
And (3) carrying out Fourier transformation on the data points segmented by the skip point clearing and the step (3) to obtain amplitude and phase information of the load data under different frequencies. The number of the Fourier transform analysis data points can be taken as 2≡12=4096 according to experience, and the sampling rate of the actual measurement load data of a certain type of machine is 1000Hz. Thus frequency resolution=1000/4096= 0.244141.
[5] Load frequency component analysis
The main frequency components of the flapping bending moment and the shimmy bending moment of the root of the main blade are frequencies corresponding to 1 time of rotating speed, the rotating speed of the rotor wing is 258 revolutions per minute, and 1-order frequency=258/60=4.3 Hz.
[6] Extraction phase angle
And (3) extracting phase angle information of different load channels according to the component analysis result of the step (5) and frequency point data accurately obtained by Fourier transformation of the step (4).
[7] Phase relation analysis
The phase difference calculation is based on a certain load, the phase angle of the reference load is subtracted by the phase angle of another load, if the result is negative, the phase difference result can be added to 360 according to the periodicity of the trigonometric function, so that the phase difference falls between 0 and 360 degrees. I.e. if the bending moment of waving=a×cos (ωt), then the bending moment of shimmy=b×cos (ωt- Φ), Φ is the phase difference obtained.
[8] Probability statistics
And (3) counting the phase checking data result obtained in the step [7] by adopting a probability density function. The most frequently occurring phase relationship obtained from probability statistics is 334.4. Therefore, the phase relation can be adopted for the calculation of the blade strength and the establishment of the experimental loading scheme in the state.
Claims (7)
1. An analysis method of measured load phase relation of a helicopter blade, which is characterized by comprising the following steps:
identifying the flight attitude of the helicopter according to the flight parameters;
under the flight attitude, segmenting load data of the helicopter blades at intervals of a preset data quantity; wherein the preset data amount comprises 2 K K is an integer greater than zero;
determining a first frequency of the payload data from a fourier transform; wherein the amplitude corresponding to the first frequency is the largest;
acquiring a phase angle of the load data according to the first frequency; determining a phase difference of the load data from the phase angle;
the method for segmenting the load data of the helicopter blade by taking the preset data quantity as an interval comprises the following steps:
segmenting the waving bending moment of the helicopter blade at intervals of a first preset data volume;
segmenting the shimmy bending moment of the helicopter blade at intervals of a second preset data volume; wherein the first preset data amount is the same as the second preset data amount.
2. The method of claim 1, wherein the flight attitude comprises flat fly, climb, hover, turn, and descent; the flight parameters include pitch angle, roll angle, speed, altitude, and heading angle.
3. The method of claim 1, wherein after segmenting the load data of the helicopter blade at intervals of a predetermined amount of data, further comprising:
and acquiring the amplitude and the phase of the load data at different frequencies according to Fourier transformation.
4. The method of claim 1, wherein after identifying the attitude of the helicopter based on the flight parameters, further comprising:
clearing abnormal load data; wherein the abnormal load data is data which is inconsistent with actual expectations in a section of test data.
5. The method of claim 1, wherein said determining a phase difference of the load data from the phase angle comprises:
determining the phase difference of the waving bending moment and the shimmy bending moment according to the first phase angle and the second phase angle; wherein the first phase angle is the phase angle of the flap bending moment and the second phase angle is the phase angle of the lag bending moment.
6. The method of claim 5, wherein said determining a phase difference of the load data from the phase angle further comprises:
if the phase difference is negative, the phase difference is added by 360 DEG according to the periodicity of the trigonometric function.
7. The method of claim 6, wherein after said determining the phase difference of the load data from the phase angle, further comprising:
and counting the phase difference by adopting a probability density function, and obtaining the phase difference with the largest occurrence number.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4894787A (en) * | 1988-04-28 | 1990-01-16 | Kaman Aerospace Corporation | Automatic load monitoring system with remote sensing |
| KR20000046441A (en) * | 1998-12-31 | 2000-07-25 | 추호석 | Method for analyzing load/stress for maintaining life span of fuselage of airplane |
| CN110844115A (en) * | 2019-10-18 | 2020-02-28 | 中国直升机设计研究所 | Method for judging effectiveness of data of propeller vortex interference noise and blade flapping load |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4894787A (en) * | 1988-04-28 | 1990-01-16 | Kaman Aerospace Corporation | Automatic load monitoring system with remote sensing |
| KR20000046441A (en) * | 1998-12-31 | 2000-07-25 | 추호석 | Method for analyzing load/stress for maintaining life span of fuselage of airplane |
| CN110844115A (en) * | 2019-10-18 | 2020-02-28 | 中国直升机设计研究所 | Method for judging effectiveness of data of propeller vortex interference noise and blade flapping load |
Non-Patent Citations (2)
| Title |
|---|
| 直升机在俯冲拉起状态下的主桨叶实测载荷分析;王泽峰;李清龙;;航空科学技术(第10期);第 17-21页 * |
| 直升机飞行载荷应用探讨;潘春蛟 等;《直升机技术》;第17-20页 * |
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