CN110186634B - Heat load fatigue test method for helicopter rotor blade deicing-preventing electric heating assembly - Google Patents
Heat load fatigue test method for helicopter rotor blade deicing-preventing electric heating assembly Download PDFInfo
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- CN110186634B CN110186634B CN201910434750.2A CN201910434750A CN110186634B CN 110186634 B CN110186634 B CN 110186634B CN 201910434750 A CN201910434750 A CN 201910434750A CN 110186634 B CN110186634 B CN 110186634B
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- 238000005485 electric heating Methods 0.000 title claims abstract description 48
- 238000009661 fatigue test Methods 0.000 title claims abstract description 17
- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000010438 heat treatment Methods 0.000 claims abstract description 58
- 238000012360 testing method Methods 0.000 claims abstract description 36
- 238000004088 simulation Methods 0.000 claims abstract description 23
- 230000002159 abnormal effect Effects 0.000 claims abstract description 8
- 230000001133 acceleration Effects 0.000 claims description 17
- 238000012417 linear regression Methods 0.000 claims description 3
- 238000010998 test method Methods 0.000 claims description 2
- 230000005856 abnormality Effects 0.000 claims 1
- 230000007257 malfunction Effects 0.000 claims 1
- 238000005516 engineering process Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 229910000570 Cupronickel Inorganic materials 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- YOCUPQPZWBBYIX-UHFFFAOYSA-N copper nickel Chemical group [Ni].[Cu] YOCUPQPZWBBYIX-UHFFFAOYSA-N 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
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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 fatigue test method for an anti-icing and electric heating assembly of a helicopter rotor blade is characterized in that a strain gauge and the electric heating assembly are firstly adhered to the surface of a blade simulation piece, then the blade simulation piece is clamped on a vibration table clamp, thirdly, the strain gauge is connected with strain testing equipment, and a temperature sensor in the electric heating assembly is connected with a heating and temperature control system. And carrying out frequency sweep vibration test on the blade simulation piece by using a vibration table to measure a first-order natural frequency. And then the vibration table vibrates at a first-order natural frequency, the heating resistance state and the temperature sensor fault state are monitored by a computer, if one of the heating resistance state and the temperature sensor fault state is abnormal, the system stops heating, and timing is stopped. The fatigue testing device can effectively test the fatigue life of the electric heating assembly, and is convenient for analyzing the fatigue strength of the electric heating assembly.
Description
Technical Field
The invention relates to a helicopter technology, in particular to an electric heating technology for a helicopter rotor blade, and specifically relates to a fatigue test method for an anti-icing electric heating assembly of the helicopter rotor blade.
Background
When a helicopter flies in an icing-prone area, the icing phenomenon can be generated on the surface of a rotor blade of the helicopter, so an anti-icing and deicing system needs to be installed on the surface of the rotor blade, and the current mainstream anti-icing and deicing technology is an electrothermal anti-icing and deicing technology. The resistance is the heating body of the electrothermal ice preventing and removing system. The heating resistance material in the electric heating assembly is copper-nickel alloy. Before the electric heating assembly is installed on the surface of a helicopter rotor blade, ground tests are carried out on the electric heating assembly to test the fatigue life of the electric heating assembly. For decades, no complete test method for the fatigue life and fatigue characteristics of helicopter rotor blade electric heating assemblies is formed at home and abroad. The invention provides a method for testing the fatigue life and fatigue property of an electric heating assembly in an electric heating deicing system.
Disclosure of Invention
The invention aims to solve the problem that the design and the manufacture of the existing helicopter blade anti-icing electric heating system are influenced due to the fact that a corresponding fatigue test technology is lacked, and provides a fatigue test method for a helicopter rotor blade anti-icing electric heating assembly, so that the fatigue life and the reliability of the helicopter rotor blade electric heating assembly can be effectively tested, and first-hand information is provided for the design and the manufacture of the helicopter blade anti-icing electric heating system.
The technical scheme of the invention is as follows:
a helicopter rotor blade anti-icing and electric heating assembly fatigue test method is characterized by comprising the following steps:
the first step is as follows: adhering an electric heating assembly of a helicopter rotor for testing and a strain gauge on the surface of a blade simulation piece;
the second step is that: clamping a blade simulation piece on a table top clamp of a vibration table in a vibration test system, wherein the clamping position is the middle position of the blade simulation piece;
the third step: enabling the vibration test system to be in a working state, carrying out frequency sweep vibration test on the blade simulation piece by using the vibration table, and measuring the first-order natural frequency of the blade simulation piece in the clamping state;
the fourth step: connecting the strain gauge with strain testing equipment by a quarter-bridge circuit, vibrating the vibrating table at the first-order natural frequency measured in the third step, sequentially adjusting the vibration acceleration of the vibrating table from small to large, recording the strain value epsilon of the strain gauge corresponding to each acceleration value a, and calculating a relational expression epsilon = x a + y of a and epsilon by a linear regression method, wherein x and y are calculated coefficients.
The fifth step: determining the maximum strain value epsilon required for fatigue testrCalculating the vibration acceleration a required by the vibration table through the relation epsilon = x multiplied by a + y obtained in the fourth stepr。
And a sixth step: connecting a temperature sensor and a heating resistor in the electric heating assembly with a heating and temperature control system; the heating and temperature control system controls the heating of the electric heating component, and the vibration table is subjected to vibration acceleration a obtained in the fifth step according to the first-order natural frequency measured in the third steprAnd a computer in the vibration, heating and temperature control system records the temperature value of each temperature sensor, the working state of each group of heating resistors in the heating assembly and the heating time of the system.
The seventh step: and monitoring the state of the heating resistor and the state of the temperature sensor by using a computer in the heating and temperature control system, and stopping heating and timing if one of the heating resistor and the temperature sensor is abnormal.
Eighth step: and after the heating and temperature control system stops heating, recording the working time and the vibration cycle number of the system, namely the fatigue life of the electric heating assembly, and ending the test.
And the computer control system in the heating and temperature control system records the temperature value of each temperature sensor every 5 s.
The heating resistor and the temperature sensor are abnormal, namely the current of the heating resistor is interrupted and the temperature sensor gives a fault alarm.
The invention has the beneficial effects that:
the fatigue test method for the electric heating assembly for preventing ice from being removed by the helicopter rotor blade can effectively test the fatigue life of the electric heating assembly and is convenient for analyzing the fatigue strength of the electric heating assembly.
Drawings
FIG. 1 is a schematic diagram of a fatigue testing system of the present invention.
FIG. 2 is a schematic diagram of the position of the electric heating assembly and the strain gauge attachment according to the present invention.
Fig. 3 is a schematic view of the clamp of the present invention.
Fig. 4 is a graph of strain versus acceleration for the present invention.
Detailed Description
The invention is further described below with reference to the figures and examples.
As shown in fig. 1-4.
Fig. 1 shows a ground fatigue test system according to the present invention, which includes a vibration test system, an electrical heating assembly (test piece), a blade simulation piece, a strain gauge, a strain test device, a data acquisition system, and a heating and temperature control system, wherein the electrical heating assembly includes a heating resistor and a temperature sensor, the vibration test system includes a vibration table, and the vibration table provides an excitation source for the vibration of the blade simulation piece, and has frequency sweep and fixed frequency functions.
The invention discloses a fatigue test method for an anti-icing and electric heating assembly of a helicopter rotor blade, which comprises the following steps:
the first step is as follows: the helicopter rotor electric heating assembly is pasted in the middle of the surface of the blade simulation piece, and the strain gauge is pasted in the middle of the surface of the electric heating assembly, as shown in figure 2. The specification of the blade simulation piece in the embodiment is 1400mm
200mm
31mm, and the material is glass fiber reinforced plastic.
The second step is that: and clamping the blade simulation piece on a vibration table top clamp in a vibration test system, wherein the clamping position is the middle position of the blade simulation piece, and the clamping mode is as shown in figure 3.
The third step: and (3) enabling the vibration test system to be in a working state, carrying out frequency sweep vibration test on the blade simulation piece by using the vibration table, and measuring the first-order natural frequency of the blade simulation piece in the clamping state. The first order natural frequency of the blade simulator in this example was measured to be 31.2 Hz.
The fourth step: connecting the strain gauge with strain testing equipment by a quarter-bridge circuit, vibrating the vibrating table at a first-order natural frequency of 31.2Hz measured in the third step, adjusting the vibration acceleration of the vibrating table from small to large, recording strain values of the strain gauge corresponding to each vibration acceleration to obtain a strain-acceleration relation graph shown in FIG. 4, wherein a relation formula of the strain epsilon and the acceleration a can be calculated by a linear regression method, and the strain-acceleration relation graph is obtained in the embodiment:
ε=1550.4a+5.694
the fifth step: determining the maximum strain value epsilon required for fatigue testrThe vibration acceleration a required for the vibration table is calculated by the relation e =1550.4a +5.694 obtained in the fourth step, to be 1300 mu erIs 0.83.
And a sixth step: connecting a temperature sensor inside the electric heating assembly with a heating and temperature control system; and (3) enabling the heating and temperature control system to provide single-phase alternating current for the electric heating assembly, vibrating the vibration table at the first-order natural frequency of 31.2Hz measured in the third step and the vibration acceleration of 0.83 obtained in the fifth step, setting the test time to be 72 hours, and recording the temperature value of each temperature sensor and the working state of each group of heating resistors in the heating assembly by a computer in the heating and temperature control system.
The seventh step: and a computer control system in the heating and temperature control system records the temperature value of each temperature sensor (once recording for 5 s), the working state of each group of heating resistors in the heating assembly, and strain testing equipment records the strain value of the surface strain gauge of the blade simulation piece. Monitoring the state of the heating resistor and the state of the temperature sensor from a computer software interface, if one of the heating resistor and the temperature sensor is abnormal, namely, the current of the heating resistor is interrupted and the temperature sensor gives a fault alarm, stopping heating of the system and stopping timing; if no abnormity occurs, the heating is automatically stopped after the set heating time is reached, and the fatigue life time is determined to be longer than the set time. The test can be continued until one indication is abnormal without setting the test time during the specific implementation, and the recorded time is the service life of the electric heating assembly and the vibration cycle number.
Eighth step: and after the heating and temperature control system stops heating, recording the working time and the vibration cycle number of the system, namely the fatigue life of the electric heating assembly, and ending the test.
The fatigue test method for the deicing-preventing electric heating assembly of the helicopter rotor blade can effectively test the hot load fatigue life of the electric heating assembly, and is convenient for analyzing the fatigue strength of the electric heating assembly.
The parts not involved in the present invention are the same as or can be implemented using the prior art.
Claims (3)
1. A test method for hot load fatigue of an electric heating component for preventing ice from being removed by a helicopter rotor blade is characterized by comprising the following steps:
the first step is as follows: adhering an electric heating assembly of a helicopter rotor for test on the surface of a blade simulation piece, and adhering a strain gauge on the surface of the electric heating assembly;
the second step is that: clamping a blade simulation piece on a table top clamp of a vibration table in a vibration test system, wherein the clamping position is the middle position of the blade simulation piece;
the third step: connecting the strain gauge with strain testing equipment by a quarter-bridge circuit, and connecting a temperature sensor and a heating resistor in the electric heating assembly with a heating and temperature control system;
the fourth step: carrying out a frequency sweep vibration test on the blade simulation piece by using a vibration table, and measuring the first-order natural frequency of the blade simulation piece in the clamping state;
the fifth step: vibrating the vibrating table at the first-order natural frequency measured in the fourth step, gradually increasing the vibration acceleration of the vibrating table from small to large, and recording the strain value epsilon of the surface strain gauge of the blade simulation piece and the vibration acceleration a of the vibrating table by using strain testing equipment; calculating a relation between the strain value epsilon and the vibration acceleration a of the vibration table by using a linear regression method: ε = x × a + y, where x and y are the calculated coefficients;
and a sixth step: determining the strain value epsilon of the fatigue test of the electric heating component according to the requirement of the fatigue testrCalculating the required vibration acceleration a according to the relation between the strain value epsilon and the vibration acceleration a of the vibration table obtained in the fifth step, wherein the relation is epsilon = x multiplied by a + yr；
The seventh step: the heating and temperature control system heats the electric heating assembly and controls the temperature within the temperature range required by the test; starting a vibration test system, setting the test duration, and adjusting the vibration table to have a first-order natural frequency and acceleration arVibrating; the heating and temperature control system records and monitors the states of the heating resistor and the temperature sensor, and if one of the heating resistor and the temperature sensor is abnormal, the system stops heating and stops timing;
eighth step: and after the heating and temperature control system stops heating, recording the working time and the vibration cycle number of the system, namely the fatigue life of the electric heating assembly, and ending the test.
2. The method as claimed in claim 1, wherein the abnormality of the heating resistor and the temperature sensor is a current interruption of the heating resistor and a malfunction alarm of the temperature sensor.
3. The method of claim 1, wherein the vibration table is set to a first order natural frequency and a vibration acceleration arAnd in the vibration time period, the computer of the vibration table records and monitors the state of the heating resistor and the state of the temperature sensor, if one of the heating resistor and the temperature sensor is abnormal, the system stops heating and stops timing, the recorded time and the vibration cycle number are the fatigue life of the electric heating assembly, and if the state of the heating resistor and the state of the temperature sensor are not abnormal in the set time period, the fatigue life of the electric heating assembly is considered to be larger than the set time period and the vibration cycle number.
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| 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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| 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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| CN110186634B true CN110186634B (en) | 2021-04-09 |
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| CN112731036B (en) * | 2020-12-25 | 2024-06-18 | 武汉航空仪表有限责任公司 | Main rotor heating fault detection system and detection method for rotor deicing 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 |
| CN113420366B (en) * | 2021-04-20 | 2022-09-06 | 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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| GB0019434D0 (en) * | 2000-08-09 | 2000-09-27 | Rolls Royce Plc | A device and method for fatigue testing of materials |
| GB0412591D0 (en) * | 2004-06-05 | 2004-07-07 | Rolls Royce Plc | An apparatus and a method for testing attachment features of components |
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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 |
| 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 |
| 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 |
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