CN106595997A - Method for measuring relative torsion angles of sections of helicopter propeller blade - Google Patents
Method for measuring relative torsion angles of sections of helicopter propeller blade Download PDFInfo
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- CN106595997A CN106595997A CN201611068486.8A CN201611068486A CN106595997A CN 106595997 A CN106595997 A CN 106595997A CN 201611068486 A CN201611068486 A CN 201611068486A CN 106595997 A CN106595997 A CN 106595997A
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- helicopter blade
- measuring point
- level change
- measured
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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
- G01M5/0016—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings of aircraft wings or blades
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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
- G01M5/0075—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings by means of external apparatus, e.g. test benches or portable test systems
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Length Measuring Devices By Optical Means (AREA)
Abstract
The present invention discloses a method for measuring the relative torsion angles of the sections of a helicopter propeller blade. The method for measuring the relative torsion angles of the sections of the helicopter propeller-blade includes the following steps that: step 1, a torque is applied to the helicopter propeller blade, the horizontal change distances of specific measurement points of the front edge section to be measured of the helicopter propeller blade and the horizontal change distances of specific measurement points of the back edge section to be measured of the helicopter propeller blade are measured, a first angle is calculated according to a first formula, and a second angle is calculated according to a second formula; and step 2, the relative torsion angles of the sections of the helicopter propeller blade are calculated according to a third formula and the data obtained in the step 1. According to the method for measuring the relative torsion angles of the sections of the helicopter propeller blade of the invention, a laser displacement sensor is not adopted to obtain vertical displacement distances, while, more accurate horizontal displacement distances are measured; and the torsion angles can be calculated according to the accurate horizontal displacement distances. The method is more accurate compared with the prior art.
Description
Technical field
The present invention relates to helicopter blade technical field, more particularly to a kind of measurement helicopter blade section relative torsion
The method at angle.
Background technology
Prior art is typically employed in outer moment of couple MφUnder effect, tested section is measured by laser displacement sensor interval
Vertical displacement distance at two sections of left and right, and by calculating the relative torsional angle between two sections, it is straight so as to calculate
The relative torsional deflection of machine blade unit length is risen, and then the interval average torsional rigidity of the section is calculated using formula.
The shortcoming of prior art is：
There is error in the first, installation of laser displacement sensor, it is difficult to ensure that sensor axis are hung down with the tested surface of tail-rotor leaf
Directly；
2nd, there is measurement error in laser displacement sensor, and in the presence of couple, tail-rotor leaf will twist deformation, this
Sensor position will be caused to change, due to for displacement deformation measurement point and periphery not in same plane, so as to
Resulting shift value is not the shift value produced by torsion angle.
3rd, relative torsional angle is that the deformation values surveyed by four displacement transducers are obtained by conversion, and four displacements are passed
The error that the superposition of sensor error will cause relative torsional angle bigger, which will directly affect result of the test；
4th, due to laser displacement sensor output be voltage signal, so as to bring electromagnetic interference.
Thus, it is desirable to have a kind of technical scheme come overcome or at least mitigate prior art at least one drawbacks described above.
The content of the invention
It is an object of the invention to provide a kind of method of measurement helicopter blade section relative torsional angle is overcoming or extremely
Mitigate at least one drawbacks described above of prior art less.
For achieving the above object, the invention provides a kind of method of measurement helicopter blade section relative torsional angle, institute
The method for stating measurement helicopter blade section relative torsional angle comprises the steps：Step 1：Apply torque for helicopter blade,
The level change distance of measurement helicopter blade leading edge section gauge location survey point to be measured and helicopter blade trailing edge section gauge to be measured
The level change distance of location survey point, and first angle is tried to achieve by the first formula and the second formula tries to achieve second angle；Step
2：Helicopter blade section relative torsional angle is sought by the 3rd formula and the data in step 1.
Preferably, helicopter blade leading edge section gauge location survey point to be measured includes two, is referred to as the survey of the first regulation
Point and the second regulation measuring point；Helicopter blade trailing edge section gauge location survey point to be measured includes two, is referred to as the 3rd rule
Location survey point and the 4th regulation measuring point.
Preferably, the level change specifies measuring point apart from the level change distance including the first regulation measuring point, second
The level change distance of level change distance, the level change distance of the 3rd regulation measuring point and the 4th regulation measuring point.
Preferably, first formula is：Wherein, L1 is the first regulation measuring point
Level change distance, the level change distance that L2 is the second regulation measuring point, L12 are the first regulation measuring point and the second regulation measuring point
Air line distance；Always change distance for helicopter blade.
Preferably, second formula is：
Wherein, L3 be the 3rd regulation measuring point level change distance, L4 be the 4th
The level change distance of regulation measuring point；For the torsion angle of helicopter blade leading edge section to be measured；For helicopter blade trailing edge
The torsion angle of section to be measured；L34 is the air line distance of the first regulation measuring point and the second regulation measuring point
Preferably, the 3rd formula is：
Wherein,
The Δ φ is relative torsional angle；Always change distance for helicopter blade；It is to be measured for helicopter blade trailing edge
The torsion angle of section.
Preferably, the level change distance of the helicopter blade trailing edge section gauge location survey point to be measured in the step 1 passes through
Strain field photographic means is obtained.
Preferably, the level change distance of the helicopter blade leading edge section gauge location survey point to be measured in the step 1 passes through
Strain field photographic means is obtained.
The method of the measurement helicopter blade section relative torsional angle of the application is not by way of laser displacement sensor
Vertical displacement distance is obtained, but by measuring more accurate horizontal displacement distance, and calculated by the horizontal displacement distance
Torsion angle is obtained, relative to prior art, more accurately.
Description of the drawings
Fig. 1 is that the flow process of the method for measurement helicopter blade section relative torsional angle according to an embodiment of the invention is illustrated
Figure.
Specific embodiment
To make purpose, technical scheme and the advantage of present invention enforcement clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
A part of embodiment, rather than the embodiment of whole.It is exemplary below with reference to the embodiment of Description of Drawings, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment obtained under the premise of creative work is not made by member, belongs to the scope of protection of the invention.Under
Face combines accompanying drawing and embodiments of the invention is described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinal direction ", " horizontal ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outward " is based on accompanying drawing institute
The orientation for showing or position relationship, are for only for ease of the description present invention and simplify description, rather than indicate or imply the dress of indication
Put or element with specific orientation, with specific azimuth configuration and operation, therefore it is not intended that must be protected to the present invention
The restriction of scope.
Fig. 1 is that the flow process of the method for measurement helicopter blade section relative torsional angle according to an embodiment of the invention is illustrated
Figure.
The method of measurement helicopter blade section relative torsional angle as shown in Figure 1 comprises the steps：
Step 1：Apply torque for helicopter blade, the level for measuring helicopter blade leading edge section gauge location survey point to be measured becomes
Change the level change distance of distance and helicopter blade trailing edge section gauge location survey point to be measured, and first is tried to achieve by the first formula
Angle and the second formula try to achieve second angle；
Step 2：Helicopter blade section relative torsional angle is sought by the 3rd formula and the data in step 1.
In the present embodiment, helicopter blade leading edge section gauge location survey point to be measured includes two, is referred to as the first regulation
Measuring point and the second regulation measuring point；Helicopter blade trailing edge section gauge location survey point to be measured includes two, is referred to as the 3rd regulation
Measuring point and the 4th regulation measuring point.
In the present embodiment, level change distance, second regulation measuring point of the level change distance including the first regulation measuring point
Level change distance, the 3rd regulation measuring point level change distance and the 4th regulation measuring point level change distance.
In the present embodiment, first formula is：Wherein, L1 is the first regulation
The level change distance of measuring point, the level change distance that L2 is the second regulation measuring point, L12 are the first regulation measuring point and the second regulation
The air line distance of measuring point；Always change distance for helicopter blade.
In the present embodiment, second formula is：
Wherein, L3 be the 3rd regulation measuring point level change distance, L4 be the 4th
The level change distance of regulation measuring point；For the torsion angle of helicopter blade leading edge section to be measured；For helicopter blade trailing edge
The torsion angle of section to be measured；L34 is the air line distance of the first regulation measuring point and the second regulation measuring point.
In the present embodiment, the 3rd formula is：
Wherein,
The Δ φ is relative torsional angle；Always change distance for helicopter blade；It is to be measured for helicopter blade trailing edge
The torsion angle of section.
In the present embodiment, the helicopter blade trailing edge section gauge location survey point to be measured in the step 1 level change away from
From being obtained by strain field photographic means.
In the present embodiment, the helicopter blade leading edge section gauge location survey point to be measured in the step 1 level change away from
From being obtained by strain field photographic means.
The method of the measurement helicopter blade section relative torsional angle of the application is not by way of laser displacement sensor
Torsion angle is obtained, but by obtaining more accurate parameter using strain field photographic means, and be calculated by the parameter
Torsion angle, relative to prior art, more accurately.
By way of example the application is further elaborated below.It is understood that this is illustrated do not constitute to this
Any restriction of application.
By taking certain type tail propeller-blade section as an example, one section of each selection at section or so 30mm, before and after two section
Edge respectively chooses two displacement measurement points, and (the first regulation measuring point, the second regulation measuring point, the 3rd regulation measuring point and the 4th regulation are surveyed
Point) be respectively A, B, C, D, for 4 measuring points of identical, the horizontal displacement value for measuring 4 measuring point using strain field be respectively L1,
L2, L3 and L4, its test data refer to table 1.As a comparison, prior art is measured 4 measuring point using laser displacement sensor and is hung down
Straight shift value is h1, h2, h3 and h4, and its test data refers to table 2.
Table 1：
Table 2：
As can be seen from Table 1 and Table 2, three tests of displacement of L1, L2, L3 and L4 are obtained using strain field photographic means
Data redundancy and it is linear and can be as accurate as 6 arithmetic point all very well, test data is authentic and valid.Using laser displacement
Sensor obtain vertical change apart from No. three test datas of displacement repeatability of h1, h2, h3 and h4 and be not linearly it is fine,
And as can also be seen from Table 2, as blade is affected by additional bending moment, entirety is moved down, so that h1 and h2 now are folded
The displacement that blade is moved down is added, so the deformation that can not truly reflect measuring point of h1 and h2.Adopt additionally, due to the method
It is optical measurement principle, it is to avoid electromagnetic interference.
Therefore, the torsion angle by level change distance and formula acquisition is more accurate.
It is last it is to be noted that：Above example only to illustrate technical scheme, rather than a limitation.To the greatest extent
Pipe has been described in detail to the present invention with reference to the foregoing embodiments, it will be understood by those within the art that：Which is still
Technical scheme described in foregoing embodiments can be modified, or equivalent is carried out to which part technical characteristic and replace
Change；And these modifications or replacement, do not make the essence of appropriate technical solution depart from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (8)
1. it is a kind of measurement helicopter blade section relative torsional angle method, it is characterised in that the measurement helicopter blade is cutd open
The method of face relative torsional angle comprises the steps：
Step 1：Apply torque for helicopter blade, measure the level change of helicopter blade leading edge section gauge location survey point to be measured away from
From and the level change of helicopter blade trailing edge section gauge location survey point to be measured with a distance from, and first angle is tried to achieve by the first formula
And second formula try to achieve second angle；
Step 2：Helicopter blade section relative torsional angle is sought by the 3rd formula and the data in step 1.
2. the method for measuring helicopter blade section relative torsional angle as claimed in claim 1, it is characterised in that described to go straight up to
Machine blade leading edge section gauge location survey point to be measured includes two, is referred to as the first regulation measuring point and the second regulation measuring point；
Helicopter blade trailing edge section gauge location survey point to be measured includes two, is referred to as the 3rd regulation measuring point and the 4th rule
Location survey point.
3. the method for measuring helicopter blade section relative torsional angle as claimed in claim 2, it is characterised in that the level
Change distance includes that the level change distance of the first regulation measuring point, the level of the second regulation measuring point change distance, the 3rd regulation and survey
The level change distance of the level change distance of point and the 4th regulation measuring point.
4. the method for measuring helicopter blade section relative torsional angle as claimed in claim 3, it is characterised in that described first
Formula is：Wherein, L1 be the first regulation measuring point level change distance, L2 be second advise
The level change distance of location survey point, the air line distance that L12 is the first regulation measuring point and the second regulation measuring point；For helicopter blade
Total change distance.
5. the method for measuring helicopter blade section relative torsional angle as claimed in claim 3, it is characterised in that described second
Formula is：
Wherein, L3 be the 3rd regulation measuring point level change distance, L4 be the 4th regulation
The level change distance of measuring point；For the torsion angle of helicopter blade leading edge section to be measured；It is to be measured for helicopter blade trailing edge
The torsion angle of section；L34 is the air line distance of the first regulation measuring point and the second regulation measuring point.
6. the method for measuring helicopter blade section relative torsional angle as claimed in claim 1, it is characterised in that the described 3rd
Formula is：
Wherein,
The Δ φ is relative torsional angle；Always change distance for helicopter blade；For helicopter blade trailing edge section to be measured
Torsion angle.
7. vibration environmental simulation experiment method in cabin is gone straight up to as claimed in claim 1, it is characterised in that the step
The level change distance of the helicopter blade trailing edge section gauge location survey point to be measured in 1 is obtained by strain field photographic means.
8. vibration environmental simulation experiment method in cabin is gone straight up to as claimed in claim 1, it is characterised in that the step
The level change distance of the helicopter blade leading edge section gauge location survey point to be measured in 1 is obtained by strain field photographic means.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611068486.8A CN106595997A (en) | 2016-11-29 | 2016-11-29 | Method for measuring relative torsion angles of sections of helicopter propeller blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611068486.8A CN106595997A (en) | 2016-11-29 | 2016-11-29 | Method for measuring relative torsion angles of sections of helicopter propeller blade |
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| CN106595997A true CN106595997A (en) | 2017-04-26 |
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| CN201611068486.8A Pending CN106595997A (en) | 2016-11-29 | 2016-11-29 | Method for measuring relative torsion angles of sections of helicopter propeller blade |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108225692A (en) * | 2017-12-01 | 2018-06-29 | 中国直升机设计研究所 | A kind of measurement blade entirety torsional rigidity test of vehicular method |
| CN111319789A (en) * | 2020-04-09 | 2020-06-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Full-size propeller blade icing wind tunnel test method |
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| CN101344383A (en) * | 2008-09-01 | 2009-01-14 | 扬州大学 | Laser amplifying measurement method for bending structure deformation |
| CN104655081A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Method for measuring pre-fastened angle of blade structure |
| CN104748693A (en) * | 2015-03-31 | 2015-07-01 | 南京航空航天大学 | Blade profile torsion stiffness measurement system based on binocular stereo vision |
| CN104792630A (en) * | 2015-04-27 | 2015-07-22 | 中国直升机设计研究所 | Test method for testing torsional rigidity of flexible beam |
-
2016
- 2016-11-29 CN CN201611068486.8A patent/CN106595997A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101344383A (en) * | 2008-09-01 | 2009-01-14 | 扬州大学 | Laser amplifying measurement method for bending structure deformation |
| CN104655081A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Method for measuring pre-fastened angle of blade structure |
| CN104748693A (en) * | 2015-03-31 | 2015-07-01 | 南京航空航天大学 | Blade profile torsion stiffness measurement system based on binocular stereo vision |
| CN104792630A (en) * | 2015-04-27 | 2015-07-22 | 中国直升机设计研究所 | Test method for testing torsional rigidity of flexible beam |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108225692A (en) * | 2017-12-01 | 2018-06-29 | 中国直升机设计研究所 | A kind of measurement blade entirety torsional rigidity test of vehicular method |
| CN111319789A (en) * | 2020-04-09 | 2020-06-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Full-size propeller blade icing wind tunnel test method |
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Application publication date: 20170426 |