CN110186634A - A kind of hot load fatigue test method of anti-deicing electric heating assembly of helicopter rotor blade - Google Patents
A kind of hot load fatigue test method of anti-deicing electric heating assembly of helicopter rotor blade Download PDFInfo
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- CN110186634A CN110186634A CN201910434750.2A CN201910434750A CN110186634A CN 110186634 A CN110186634 A CN 110186634A CN 201910434750 A CN201910434750 A CN 201910434750A CN 110186634 A CN110186634 A CN 110186634A
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- electric heating
- vibration
- heating assembly
- shake table
- test
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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
-
- 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
- G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
-
- 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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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
A kind of anti-deicing electric heating assembly fatigue test method of helicopter rotor blade, it is characterized in that foil gauge and electric heating assembly are first pasted onto blade simulating piece surface, again by blade simulating piece clamping on shake table clamp, third, foil gauge is connected with strain testing equipment, electric heating assembly internal temperature sensor is connected with heating and temperature control system.Frequency sweep vibration test is carried out to paddle simulating piece using shake table, measures first natural frequency.It vibrates shake table with first natural frequency again, by computer monitoring adding thermal resistance state and temperature sensor fault state, if the two, which has at one, abnormal, system stopping heating occurring, and stops timing.The present invention is capable of the fatigue life of validity test electric heating assembly, analyzes convenient for the fatigue strength to electric heating assembly.
Description
Technical field
The present invention relates to a kind of Helicopter Technology, especially a kind of helicopter rotor blade electric-heating technology, specifically
It is a kind of anti-deicing electric heating assembly fatigue test method of helicopter rotor blade.
Background technique
For helicopter in icing Yi Fa area's flight, helicopter rotor blade surface can generate icing phenomenon, so in rotor
Blade surface need to be equipped with anti-deicing system, and a kind of anti-clearing ice technology of mainstream is the anti-clearing ice technology of electric heating at present.Resistance is electricity
The Heating body of the anti-deicing system of heat.Adding thermal resistance material is corronil in electric heating assembly.Electric heating assembly is mounted on
Before helicopter rotor blade surface, ground experiment need to be carried out to it to test its fatigue life.For decades, both at home and abroad to straight
A set of perfect test method has not yet been formed in the fatigue life and fatigue properties for rising machine rotor blade electric heating assembly.The present invention is
Test method is provided for the fatigue life and fatigue properties of the electric heating assembly in the anti-deicing system of electric heating.
Summary of the invention
The purpose of the present invention is lack corresponding fatigue test skill for the anti-deicing electric heating system of current helicopter blade
Art and influence manufacture and design the problem of, invent a kind of anti-deicing electric heating assembly fatigue test method of helicopter rotor blade, with
Fatigue life and reliability convenient for validity test helicopter rotor blade electric heating assembly add for the anti-deicing electricity of helicopter blade
Hot systems, which manufacture and design, provides the firsthand information.
The technical scheme is that
A kind of anti-deicing electric heating assembly fatigue test method of helicopter rotor blade, it is characterized in that it the following steps are included:
Step 1: by test lifting airscrew electric heating assembly and strain gauge adhesion on blade simulating piece surface；
Step 2: clip position is blade mould by blade simulating piece clamping on vibration experiment internal vibration platform table top fixture
Quasi- part middle position；
Step 3: keeping vibration experiment in running order, frequency sweep vibration examination is carried out to blade simulating piece using shake table
It tests, measures the first natural frequency of paddle simulating piece under the clamp position；
Step 4: foil gauge is connected with strain testing equipment with a quarter bridge circuit, by shake table to be surveyed in third step
The first natural frequency vibration obtained, successively adjusts shake table vibration acceleration from small to large, records corresponding to each acceleration value a
Foil gauge strain value ε, relational expression ε=x × a+y of a and ε is calculated by linear regression method, x and y is calculated in formula
Coefficient.
Step 5: determining maximum strain value ε required by fatigue testr, pass through the relational expression ε=x obtained in the 4th step
Vibration acceleration a needed for × a+y calculates shake tabler。
Step 6: electric heating assembly internal temperature sensor and adding thermal resistance are connected with heating and temperature control system；
Heating and temperature control system carry out computer heating control to electric heating assembly, and shake table is intrinsic with single order measured in third step
The vibration acceleration a obtained in frequency, the 5th steprIt vibrates, the computer in heating and temperature control system records each temperature
Each group adding thermal resistance working condition, system heating time in the temperature value of sensor, heating component.
Step 7: utilizing heating and computer monitoring adding thermal resistance state and temperature sensor in temperature control system
State if the two, which has at one, abnormal, system stopping heating occurring, and stops timing.
Step 8: System production time and vibration cycles number are recorded after heating and temperature control system stop heating,
That is electric heating assembly fatigue life, off-test.
The every 5s of computer control system records the temperature of primary each temperature sensor in the heating and temperature control system
Angle value.
There is exception and refers to adding thermal resistance current interruptions and temperature sensor event in the adding thermal resistance and temperature sensor
Barrier alarm.
Beneficial effects of the present invention:
The anti-deicing electric heating assembly fatigue test method of helicopter rotor blade of the invention, being capable of validity test electric heating assembly
Fatigue life, analyzed convenient for the fatigue strength to electric heating assembly.
Detailed description of the invention
Fig. 1 is fatigue test system schematic diagram of the invention.
Fig. 2 is electric heating assembly and strain gauge adhesion position view of the invention.
Fig. 3 is fixture clamping schematic diagram of the invention.
Fig. 4 is strain of the invention-acceleration relational graph.
Specific embodiment
The present invention is further illustrated with reference to the accompanying drawings and examples.
As shown in Figs 1-4.
Fig. 1 is the actual ground fatigue test system of the present invention, including vibration experiment, electric heating assembly (test
Part), blade simulating piece, foil gauge, strain testing equipment, data collection system, heating and temperature control system, electric heating assembly
Inside includes adding thermal resistance and temperature sensor, and vibration experiment includes shake table, and shake table is that the vibration of blade simulating piece mentions
For exciting source, there is frequency sweep and determine frequency function.
The anti-deicing electric heating assembly fatigue test method of helicopter rotor blade of the invention, includes the following steps:
Step 1: lifting airscrew electric heating assembly is pasted onto blade simulating piece surface middle part position, strain gauge adhesion is existed
Electric heating assembly surface middle part position, as shown in Figure 2.Blade simulating piece specification is 1400mm in the present embodiment200mm
31mm, material are glass reinforced plastic.
Step 2: clip position is by blade simulating piece clamping on the vibration table surface fixture in vibration experiment
Blade simulating piece middle position, method of clamping are as shown in Figure 3.
Step 3: keeping vibration experiment in running order, frequency sweep vibration is carried out to paddle simulating piece using shake table
Test, measures the first natural frequency of paddle simulating piece under the clamp position.The single order of blade simulating piece is intrinsic in the present embodiment
Frequency is measured as 31.2Hz.
Step 4: foil gauge is connected with strain testing equipment with a quarter bridge circuit, by shake table in third step
Measured first natural frequency 31.2Hz vibration, adjusts shake table vibration acceleration from small to large, records each vibration and accelerates
The corresponding foil gauge strain value of degree, obtains strain as shown in Figure 4-acceleration relational graph, the relationship of strain stress and acceleration a
Formula can be calculated by linear regression method, be calculated in the present embodiment:
ε=1550.4a+5.694
Step 5: determining maximum strain value ε required by fatigue testrFor 1300 μ ε, pass through the relational expression ε obtained in the 4th step
Vibration acceleration a needed for=1550.4a+5.694 calculates shake tablerIt is 0.83.
Step 6: electric heating assembly internal temperature sensor is connected with heating and temperature control system；Make heating and temperature
It spends control system and provides single-phase alternating current for electric heating assembly, by shake table with first natural frequency measured in third step
The vibration acceleration 0.83 obtained in 31.2Hz, the 5th step vibrates, and setting test period is 72 hours, heating and temperature control
Computer in system records the temperature value of each temperature sensor, each group adding thermal resistance working condition in heating component.
Step 7: computer control system records the temperature value (5s of each temperature sensor in heating and temperature control system
Record is primary), each group adding thermal resistance working condition in heating component, strain testing equipment records blade simulating piece surface strain piece
Strain value.From computer software interface monitoring adding thermal resistance state and temperature sensor state, if the two has appearance at one different
Often, i.e., adding thermal resistance current interruptions and temperature sensor fault are alarmed, and system stops heating, and stops timing；If not occurring different
Often, then it is automatically stopped heating after reaching setting heating time, and assert that fatigue life time is greater than set fix time.Specific implementation
When can also be not provided with test period, test is gone down always, and until instruction occurs extremely, the time recorded at this time is
The life time and vibration cycles number of electric heating assembly.
Step 8: System production time and vibration cycles number are recorded after heating and temperature control system stop heating,
That is electric heating assembly fatigue life, off-test.
The anti-deicing electric heating assembly fatigue test method of helicopter rotor blade of the invention, being capable of validity test electric heating
The heat of component carries fatigue life, analyzes convenient for the fatigue strength to electric heating assembly.
Part that the present invention does not relate to is the same as those in the prior art or can be realized by using the prior art.
Claims (3)
1. a kind of hot load fatigue test method of anti-deicing electric heating assembly of helicopter rotor blade, it is characterized in that it includes following step
It is rapid:
Step 1: test is pasted onto blade simulating piece surface with lifting airscrew electric heating assembly, by strain gauge adhesion in electricity
On heating component surface；
Step 2: clip position is blade mould by blade simulating piece clamping on vibration experiment internal vibration platform table top fixture
Quasi- part middle position；
Step 3: foil gauge is connected with strain testing equipment with a quarter bridge circuit, electric heating assembly internal temperature is passed
Sensor and adding thermal resistance are connect with heating and temperature control system；
Step 4: carrying out frequency sweep vibration test to paddle simulating piece using shake table, paddle simulating piece under the clamp position is measured
First natural frequency；
Step 5: shake table is vibrated with first natural frequency measured in the 4th step, by the vibration acceleration of shake table from
It is small to being stepped up greatly, strain testing equipment records the strain value ε of blade simulating piece surface strain piece and shake table vibration accelerates
Spend a；The relational expression according to strain value ε and shake table vibration acceleration a: ε=x × a+y, formula is calculated using linear regression method
Middle x and y is calculated coefficient.
Step 6: requiring according to fatigue test, the strain value ε of the fatigue test of electric heating assembly is determinedr, obtained according in the 5th step
Relational expression ε=x × a+y of strain value ε and shake table vibration acceleration a out calculate required vibration acceleration ar。
Step 7: heating and temperature control system heat electric heating assembly, and temperature is controlled the temperature in test requirements document
It spends in range.Vibration experiment is opened, setting test duration adjusts shake table with first natural frequency and acceleration arVibration
It is dynamic；Heating and temperature control system record and monitor adding thermal resistance and temperature sensor state, if the two, which has, there is exception at one,
System stops heating, and stops timing.
Step 8: record System production time and vibration cycles number after heating and temperature control system stop heating, i.e., electricity plus
Hot component fatigue life, off-test.
2. according to the method described in claim 1, it is characterized in that there is abnormal refer to temperature sensor in the adding thermal resistance
Adding thermal resistance current interruptions and temperature sensor fault are alarmed.
3. according to the method described in claim 1, it is characterized in that setting shake table is with first natural frequency and vibration acceleration arVibration
The dynamic time cycle, shake table computer records and monitors adding thermal resistance state and temperature sensor state, if the two has at one
There is abnormal, system stopping heating, and stop timing, recorded time and vibration cycles number are the electric heating assembly tired longevity
Life, adding thermal resistance state and temperature sensor state do not occur exception such as within the time cycle of setting, then it is assumed that electric heating group
Part fatigue life is greater than time cycle and the vibration cycles number of setting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910434750.2A CN110186634B (en) | 2019-05-23 | 2019-05-23 | Heat load fatigue test method for helicopter rotor blade deicing-preventing electric heating assembly |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910434750.2A CN110186634B (en) | 2019-05-23 | 2019-05-23 | Heat load fatigue test method for helicopter rotor blade deicing-preventing electric heating assembly |
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| CN110186634A true CN110186634A (en) | 2019-08-30 |
| CN110186634B CN110186634B (en) | 2021-04-09 |
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| CN201910434750.2A Active CN110186634B (en) | 2019-05-23 | 2019-05-23 | Heat load fatigue test method for helicopter rotor blade deicing-preventing electric heating assembly |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112729147A (en) * | 2020-12-28 | 2021-04-30 | 南京航空航天大学 | Blade strain measurement test system and method under complex environment |
| CN112731036A (en) * | 2020-12-25 | 2021-04-30 | 武汉航空仪表有限责任公司 | System and method for detecting heating fault of main rotor of rotor wing deicing and preventing system |
| 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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| CN107941636A (en) * | 2017-11-08 | 2018-04-20 | 武汉航空仪表有限责任公司 | A kind of fatigue life test system and method for helicopter blade electric heating assembly |
| CN108760540A (en) * | 2018-07-26 | 2018-11-06 | 南京航空航天大学 | Blade fatigue experimental device is carried based on resonance method high frequency heat |
| CN108910083A (en) * | 2018-06-27 | 2018-11-30 | 中国直升机设计研究所 | The vibration experiment and method of helicopter blade heating component reliability test |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112731036A (en) * | 2020-12-25 | 2021-04-30 | 武汉航空仪表有限责任公司 | System and method for detecting heating fault of main rotor of rotor wing deicing and preventing system |
| CN112729147A (en) * | 2020-12-28 | 2021-04-30 | 南京航空航天大学 | Blade strain measurement test system and method under complex environment |
| 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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| CN110186634B (en) | 2021-04-09 |
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