CN105890854B - A kind of stiffness measurement method of helicopter flexible beam fatigue test - Google Patents
A kind of stiffness measurement method of helicopter flexible beam fatigue test Download PDFInfo
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- CN105890854B CN105890854B CN201610201496.8A CN201610201496A CN105890854B CN 105890854 B CN105890854 B CN 105890854B CN 201610201496 A CN201610201496 A CN 201610201496A CN 105890854 B CN105890854 B CN 105890854B
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- flexible beam
- rigidity
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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
- 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
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- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention relates to a kind of stiffness measurement method of helicopter flexible beam fatigue test, method of the invention increases the processing links to stiffness measurement data, will centrifuge the larger measurement data of fluctuation and rejects, improves the stability of stiffness measurement result；In addition test load spectrum is had modified, level-one zero load is increased before stiffness measurement, flexible beam is made to be in unstressed state and is kept for 1 hour, and flexible beam is allowed to cool down, the experimental enviroment for ensureing each stiffness measurement is identical as the experimental enviroment of initial stiffness, improves the accuracy of stiffness measurement result.
Description
Technical field：
The invention belongs to Aeronautical Test Technologies, are related to helicopter flexible beam fatigue test.
Background technology
Certain test number (TN) is often run during helicopter flexible beam batch production sampling observation fatigue test to need to measure flexible beam
Rigidity, and whether terminated and whether flexible beam quality qualified according to the experiment of stiffness measurement result judgement.Helicopter flexible beam
Fatigue test waves direction displacement load(ing) point including 1,1 centrifugal force load(ing) point and 1 wave direction force measurement point, tests
Rigidity is measured in journey to need to apply 4 different displacement load to the direction of waving of flexible beam, while being centrifuged in flexible beam
Force direction applies the power load of 250 newton, and flexible beam centrifuges the power load of 250 newton of force direction in flexible beam stiffness measurement mistake
Need to be always maintained at stabilization in journey, it, which will wave direction, under the collective effect of flexible beam transfer lotus in place and centrifugal force load to generate
One is waved force value, records every transfer lotus and its corresponding flexible beam waves direction force value, then according to displacement load value and
Wave the rigidity that force value calculates flexible beam.There are 2 disadvantages for current this stiffness measurement method：1. when due to test run from
Mental and physical efforts load is 9000N, so the force snesor range and hydraulic servo actuator tonnage selected are larger, causes to measure rigidity mistake
250 newton that force direction applies are centrifuged in journey and are difficult to keep stable, and the fluctuation of flexible beam centrifugal force can cause in identical displacement
Flexible beam waves direction force value and also generates fluctuation under load, keeps stiffness measurement data error larger；2. helicopter flexible beam fatigue
Experiment continuous operation causes flexible beam fever to soften, and the flexible beam rigidity data that test run process measures is less than true stiffness,
The illusion for causing flexible beam Stiffness too fast causes test result inaccurate, to affect the judgement to flexible beam quality.
The content of invention
The purpose of invention
The object of the present invention is to provide a kind of stiffness measurement methods of improved helicopter flexible beam fatigue test, improve straight
Rise the stiffness measurement stability and measurement accuracy of machine flexible beam fatigue test.
Technical solution
A kind of stiffness measurement method of helicopter flexible beam fatigue test is provided, is as follows：
Step 1: building helicopter flexible beam fatigue test environment, the initial stiffness of flexible beam is measured；
Step 2: running helicopter flexible beam fatigue test 20,000 times；
Step 3: the load of the fatigue test returns to zero, so that flexible beam is in the state that do not stress and keep the state extremely
Few 1 hour so that flexible beam cooling；
Step 4: repeatedly measuring the rigidity data of flexible beam, each rigidity data includes centrifugation force value and centrifugation force value pair
Direction displacement, force value is corresponding waves force value for centrifugation for waving of answering；
Step 5: the rigidity data measured step 4 is handled, 240 newton are in by force value is centrifuged in rigidity data
Rigidity data between~260 newton is picked out；
Step 6: calculating the rigidity of flexible beam using the select rigidity data of step 5, and whether judge rigidity
Less than the 90% of flexible beam initial stiffness, if it is stop experiment；Otherwise return to step two continues to test.
The feature of the present invention in increasing step 3 and step 5 in helicopter flexible beam fatigue test stiffness measurement process,
Improve stiffness measurement precision.
The effect of invention
Advantages of the present invention improves the stability of flexible beam stiffness measurement result, greatly reduces measurement error.
Specific implementation mode
The embodiment of the present invention：
Step 1: building helicopter flexible beam fatigue test environment, the initial stiffness of flexible beam is measured；
Step 2: running helicopter flexible beam fatigue test 20,000 times；
Step 3: the load of the fatigue test returns to zero, so that flexible beam is in the state that do not stress and keep the state extremely
Few 1 hour so that flexible beam cooling；
Step 4: repeatedly measuring the rigidity data of flexible beam, each rigidity data includes：Centrifuge force value and centrifugation force value
It is corresponding to wave that direction shift value, force value is corresponding waves force value for centrifugation；
Step 5: the rigidity data measured step 4 is handled, 240 newton are in by force value is centrifuged in rigidity data
Rigidity data between~260 newton is picked out；
Step 6: calculating the rigidity of flexible beam using the select rigidity data of step 5, and whether judge rigidity
Less than the 90% of flexible beam initial stiffness, if it is stop experiment；Otherwise return to step two continues to test.
In particular, the initial stiffness is positive rigidity, the rigidity data is positive rigidity data.
In particular, the initial stiffness is negative sense rigidity, the rigidity data is negative sense rigidity data.
Especially, initially positive rigidity is 232.45N/m to flexible beam.
Especially, initial negative sense rigidity is 220.12N/m.
Claims (5)
1. a kind of stiffness measurement method of helicopter flexible beam fatigue test, is as follows：
Step 1: building helicopter flexible beam fatigue test environment, the initial stiffness of flexible beam is measured；
Step 2: running helicopter flexible beam fatigue test 20,000 times；
Step 3: the load of the fatigue test returns to zero, so that flexible beam is in the state that do not stress and keep the state at least 1 small
When, so that flexible beam cools down；
Step 4: repeatedly measuring the rigidity data of flexible beam, each rigidity data includes：Centrifuge force value, with centrifuge force value it is corresponding
Wave that direction shift value, force value is corresponding waves force value with centrifugation；
Step 5: to step 4 measure rigidity data handle, will in rigidity data centrifuge force value be in 240 newton~
Rigidity data between 260 newton is picked out；
Step 6: calculating the rigidity of flexible beam using the select rigidity data of step 5, and judge whether rigidity is less than
The 90% of flexible beam initial stiffness if it is stops experiment；Otherwise return to step two continues to test.
2. a kind of stiffness measurement method of helicopter flexible beam fatigue test according to claim 1, it is characterised in that：Institute
The initial stiffness stated is positive rigidity, and the rigidity data is positive rigidity data.
3. a kind of stiffness measurement method of helicopter flexible beam fatigue test according to claim 1, it is characterised in that：Institute
The initial stiffness stated is negative sense rigidity, and the rigidity data is negative sense rigidity data.
4. a kind of stiffness measurement method of helicopter flexible beam fatigue test according to claim 2, it is characterised in that：It is soft
Property beam initially positive rigidity is 232.45N/m.
5. a kind of stiffness measurement method of helicopter flexible beam fatigue test according to claim 3, it is characterised in that：Just
Beginning negative sense rigidity is 220.12N/m.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610201496.8A CN105890854B (en) | 2016-04-01 | 2016-04-01 | A kind of stiffness measurement method of helicopter flexible beam fatigue test |
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| CN201610201496.8A CN105890854B (en) | 2016-04-01 | 2016-04-01 | A kind of stiffness measurement method of helicopter flexible beam fatigue test |
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| CN105890854A CN105890854A (en) | 2016-08-24 |
| CN105890854B true CN105890854B (en) | 2018-07-24 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108169015B (en) * | 2017-12-01 | 2020-06-09 | 中国直升机设计研究所 | Tail rotor flexible beam torque loading test device |
| CN110884681B (en) * | 2019-12-04 | 2022-05-06 | 中国直升机设计研究所 | Bearing-free rotor tail rotor flexible beam static test load characterization and debugging method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2052787C1 (en) * | 1992-06-29 | 1996-01-20 | Московский вертолетный завод им.М.Л.Миля | Bed for dynamic testing of beam-type constructions of propeller of flying vehicles |
| CN104215444A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Centrifugal force loading device for flexible beam of bearingless rotor wing |
| CN204495642U (en) * | 2015-04-07 | 2015-07-22 | 中国直升机设计研究所 | A kind of flexible beam stiffness measurement device |
-
2016
- 2016-04-01 CN CN201610201496.8A patent/CN105890854B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2052787C1 (en) * | 1992-06-29 | 1996-01-20 | Московский вертолетный завод им.М.Л.Миля | Bed for dynamic testing of beam-type constructions of propeller of flying vehicles |
| CN104215444A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Centrifugal force loading device for flexible beam of bearingless rotor wing |
| CN204495642U (en) * | 2015-04-07 | 2015-07-22 | 中国直升机设计研究所 | A kind of flexible beam stiffness measurement device |
Non-Patent Citations (2)
| Title |
|---|
| 《基于VCCT复合材料柔性梁疲劳寿命研究》;鲁国富 等;《中国机械工程》;20100131;第21卷(第2期);第229-233页 * |
| 《无轴承尾桨柔性梁设计和试验验证》;黄珺 等;《直升机技术》;20140131(第178期);第35-38页 * |
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