CN114112351A - Main blade airfoil section calibration device - Google Patents
Main blade airfoil section calibration device Download PDFInfo
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- CN114112351A CN114112351A CN202111382130.2A CN202111382130A CN114112351A CN 114112351 A CN114112351 A CN 114112351A CN 202111382130 A CN202111382130 A CN 202111382130A CN 114112351 A CN114112351 A CN 114112351A
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- Prior art keywords
- main blade
- airfoil section
- blade airfoil
- test piece
- fixing device
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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
- 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
- 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
- G01N3/02—Details
- G01N3/04—Chucks
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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
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive 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
- G01N2203/0003—Steady
-
- 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
- G01N2203/003—Generation of the force
- G01N2203/0032—Generation of the force using mechanical means
- G01N2203/0033—Weight
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- Chemical & Material Sciences (AREA)
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- Immunology (AREA)
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a main blade airfoil section calibration device, which comprises: the first fixing device is used for fixing one end of the test piece; wherein the test piece comprises a main blade airfoil section; a second fixing device for fixing the middle of the main blade airfoil section, the main blade airfoil section being passable through the second fixing device; the second fixture, comprising: the second sliding device can slide along the ground; the loading platform is arranged on the second sliding device; the first sliding device is arranged on the loading platform; the test piece clamping device is arranged on the first sliding device and used for clamping the middle part of the main blade airfoil section; the test piece holding device is movable in a chord line direction of the main blade airfoil section.
Description
Technical Field
The invention belongs to the technical field of helicopter fatigue tests, and particularly relates to a main blade airfoil section calibration device.
Background
The fatigue test of the main blade airfoil section is an important fatigue test in the field of helicopters, and as a composite material long arm structure, at the initial stage of the test, the main blade airfoil section fatigue test needs to obtain the flapping, shimmying and bending moment of the main blade through calibration. For the asymmetric structure of the main blade, a method of fixing one end and applying a standard load to the other end is generally adopted for calibration.
However, during calibration, because the method of applying load at one end is single-ended fixed, the farther the arm length is from the loading point, the larger the applied calibration bending moment is, that is, the closer the bending moment is to the fixed support point, the larger the bending moment is, and the closer the bending moment is to the loading point, the smaller the bending moment is.
The calibration method has little influence on shorter blades, but has limited bearing capacity on blades with longer length and smaller rigidity. If the applied calibration load is small, the calibration bending moment close to the loading point is small, the strain is small, and the error is large; if the applied calibration load is larger, the applied bending moment far away from the loading point is larger, and the bearing capacity of the test piece can be exceeded, so that damage is caused. Therefore, in order to avoid damage, the calibration method generally has smaller calibration load; in addition, the calibration method can not meet the requirement of calibrating bending moments of different sections and the like.
Disclosure of Invention
In view of the above technical problem, the present invention provides a main blade airfoil section calibration apparatus, including:
the first fixing device is used for fixing one end of the test piece; wherein the test piece comprises a main blade airfoil section;
a second fixing device for fixing the middle of the main blade airfoil section, the main blade airfoil section being passable through the second fixing device.
Preferably, the second fixing device includes:
the second sliding device can slide along the ground;
the loading platform is arranged on the second sliding device;
the first sliding device is arranged on the loading platform;
and the test piece clamping device is arranged on the first sliding device and used for clamping the middle part of the main blade airfoil section.
Preferably, the main blade airfoil section can pass through the test piece clamping device, the test piece clamping device is installed on an arc section of the middle part of the main blade airfoil section, and the test piece clamping device can move along the chord line direction of the main blade airfoil section.
Preferably, the first fixing device includes:
the ground fixing device is arranged on the ground;
and the clamping assembly is arranged on the ground fixing device.
Preferably, the first fixing device further comprises:
the rotary fixing device is arranged in the clamping assembly and used for fixing one end of the main blade airfoil section;
and one end of the main blade airfoil section is connected with the rotary fixing device through the first pin shaft.
Preferably, the rotating and fixing device can drive the main blade airfoil section to rotate 360 degrees along the installation central axis of the main blade airfoil section in the length direction.
Preferably, the method further comprises the following steps:
the loading rod is arranged at the other end of the test piece;
and the load applying device is arranged at the end part of the loading rod and is used for applying load.
Preferably, the loading rod is connected with the other end of the test piece through a second pin shaft; the load applying means comprises an actuator or a standard weight applying means.
The invention has the beneficial technical effects that:
the calibration device provided by the invention can realize equal bending moment calibration of different sections, avoid damage to the end far away from the loading point and improve the calibration bending moment.
Drawings
Fig. 1 is a schematic structural diagram of a calibration apparatus provided in an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of another calibration apparatus provided in the embodiment of the present invention;
wherein: the test piece clamping device comprises a main paddle wing section 1, a first pin shaft 2, a rotating fixing device 3, a second pin shaft 4, a loading rod 5, a clamping assembly 6, a ground fixing device 7, a test piece clamping device 8, a first sliding device 9, a loading platform 10, a second sliding device 11 and a load applying device 12.
Detailed Description
The technical problems to be solved by the invention are as follows: a novel main blade airfoil section calibration device solves the problem that in a loading calibration mode with one fixed end and one fixed end, loading of bending moments of different sections and the like cannot be achieved, and improves the calibration bending moment close to a loading point.
Referring to fig. 1-2, the technical solution of the present invention: a novel main blade airfoil section calibration device comprises:
the loading object of the calibration device is a main blade airfoil section 1 or other test pieces (hereinafter referred to as test pieces 1) similar to the main blade airfoil section, and one end of each test piece 1 is fixed on the rotary fixing device 3 through a first pin shaft 2 (which can be other fixing devices). The clamping assembly 6 fixes the rotary fixing device 3 through clamping, and when the rotary fixing device clamping assembly 6 is loosened, the rotary fixing device 3 can drive the test piece 1 to rotate 360 degrees along the central installation axis in the length direction of the test piece 1; the clamping component 6 is clamped, and the rotary fixing device 3 is fixed with the test piece 1.
In the embodiment of the application, the clamping assembly 6 is fixed on the ground of the test plant through a ground fixing device 7. The other end of the test piece 1 is fixed to a loading rod 5 via a second pin 4 (which may be another fixing device), and the loading rod 5 may pass through a load applying device 12 (which may be a standard weight applying device or other force load performing mechanism, such as an actuator).
The test piece 1 is in the cord direction of the test piece 1 when the fixed end points to the loading end, a test piece clamping device 8 is arranged on a cord section at the middle position of the test piece 1, the test piece clamping device 8 is fixed on the test piece 1 from top to bottom or from left to right, the test piece clamping device 8 is loosened, and the test piece clamping device 8 can move in the cord direction of the test piece 1 and is used for clamping the test piece under any section; the test piece clamping device 8 can be fixed on the first sliding device 9, the test piece clamping device 8 can rotate along with the test piece 1 along the mounting central axis which can be fixed on the test piece 1 along the length direction of the test piece 1 by 360 degrees before being fixed on the first sliding device 9, and when the test piece clamping device 8 is fixed on the first sliding device 9, the mounting central axis of the test piece 1 along the length direction of the test piece 1 is fixed in angle relative to the horizontal plane direction. The first sliding device 9 is fixed on the follow-up loading platform 10 through bolts, the second sliding device 11 is installed below the follow-up loading platform 10, and the second sliding device 11 can move along the horizontal direction of the ground.
The key points of the invention are as follows:
1. the novel main blade airfoil section calibration device not only realizes equal bending moment loading calibration of different sections, but also can avoid damage of a fixed end section calibration load value to a test piece body when the loading end section calibration load is overlarge;
2. the device can realize that any section of a test piece applies a calibration load at any angle;
3. the test piece clamping device 8 and the first sliding device 9 of the device are used for solving the problem that different sections are fixed at any angle, and the possibility that the section calibration load value of the fixed end is damaged to a test piece body when the section calibration load of the loading end is too large is avoided.
The specific implementation method of the invention comprises the following steps:
the invention is described in further detail below with reference to the accompanying figures 1-2:
the loading object of the calibration device is a main blade airfoil section 1 or other test pieces (hereinafter referred to as test pieces 1) similar to the main blade airfoil section, and one end of each test piece 1 is fixed on the rotary fixing device 3 through a first pin shaft 2 (which can be other fixing devices). The clamping assembly 6 fixes the rotary fixing device 3 through clamping, and when the clamping assembly 6 is loosened, the rotary fixing device 3 can drive the test piece 1 to rotate 360 degrees along the central installation axis in the length direction of the test piece 1; the clamping component 6 is clamped, and the rotary fixing device 3 is fixed with the test piece 1. The clamping assembly 6 is fixed on the ground of the test plant through a ground fixing device 7.
Wherein, the other end of the test piece 1 is fixed on the loading rod 5 through a second pin 4 (which may be other fixing device), and the loading rod 5 can pass through a load applying device 12 (which may be a standard weight applying device or other force load executing mechanism, such as an actuator). The test piece 1 is in the cord direction of the test piece 1 when pointing to the loading end along the fixed end, a test piece clamping device 8 is arranged on a cord section at the middle position of the test piece 1, the test piece clamping device 8 is fixed on the test piece 1 from top to bottom or from left to right, the test piece clamping device 8 is loosened, and the test piece clamping device 8 can move along the cord direction of the test piece 1 and is used for clamping the test piece under any section; the test piece clamping device 8 can be fixed on the first sliding device 9, the test piece clamping device 8 can rotate along with the test piece 1 along the mounting central axis which can be fixed on the test piece 1 along the length direction of the test piece 1 by 360 degrees before being fixed on the first sliding device 9, and when the test piece clamping device 8 is fixed on the first sliding device 9, the mounting central axis of the test piece 1 along the length direction of the test piece 1 is fixed in angle relative to the horizontal plane direction. The first sliding device 9 is fixed on the follow-up loading platform 10 through bolts, the second sliding device 11 is installed below the follow-up loading platform 10, and the second sliding device 11 can move along the horizontal direction of the ground. Wherein the second slide 11 is a ground slide.
The novel main blade airfoil section calibration device not only realizes the equal-bending moment loading calibration of different sections, but also can avoid the damage of the fixed end section calibration load value to the test piece body when the loading end section calibration load is overlarge, and can improve the calibration bending moment.
Claims (8)
1. A main blade airfoil section calibration device is characterized by comprising:
the first fixing device is used for fixing one end of the test piece; wherein the test piece comprises a main blade airfoil section;
a second fixing device for fixing the middle of the main blade airfoil section, the main blade airfoil section being passable through the second fixing device.
2. The main blade airfoil section calibration apparatus of claim 1, wherein said second fixture comprises:
the second sliding device can slide along the ground;
the loading platform is arranged on the second sliding device;
the first sliding device is arranged on the loading platform;
and the test piece clamping device is arranged on the first sliding device and used for clamping the middle part of the main blade airfoil section.
3. The main blade airfoil section calibration device according to claim 2, wherein said main blade airfoil section is passable through said test piece holding device, said test piece holding device is mounted on an arc profile of a middle portion of said main blade airfoil section, and said test piece holding device is movable in a chord line direction of said main blade airfoil section.
4. The main blade airfoil section calibration apparatus of claim 1, wherein the first fixture comprises:
the ground fixing device is arranged on the ground;
and the clamping assembly is arranged on the ground fixing device.
5. The main blade airfoil section calibration apparatus of claim 4, wherein said first fixture further comprises:
the rotary fixing device is arranged in the clamping assembly and used for fixing one end of the main blade airfoil section;
and one end of the main blade airfoil section is connected with the rotary fixing device through the first pin shaft.
6. The main blade airfoil section calibration device according to claim 5, wherein the rotation fixing device can drive the main blade airfoil section to realize 360-degree rotation along the installation central axis of the main blade airfoil section in the length direction.
7. The main blade airfoil section calibration apparatus of claim 1, further comprising:
the loading rod is arranged at the other end of the test piece;
and the load applying device is arranged at the end part of the loading rod and is used for applying load.
8. The main blade airfoil section calibration device according to claim 7, wherein the loading rod is connected with the other end of the test piece through a second pin shaft; the load applying means comprises an actuator or a standard weight applying means.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111382130.2A CN114112351A (en) | 2021-11-19 | 2021-11-19 | Main blade airfoil section calibration device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111382130.2A CN114112351A (en) | 2021-11-19 | 2021-11-19 | Main blade airfoil section calibration device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114112351A true CN114112351A (en) | 2022-03-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111382130.2A Pending CN114112351A (en) | 2021-11-19 | 2021-11-19 | Main blade airfoil section calibration device |
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| Country | Link |
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| CN (1) | CN114112351A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4146967A (en) * | 1977-08-15 | 1979-04-03 | The Boeing Company | Rotor blade inspection fixture |
| 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 |
| CN105806602A (en) * | 2016-03-16 | 2016-07-27 | 中国直升机设计研究所 | Anti-icing and deicing main blade fatigue test device |
| CN107389973A (en) * | 2017-08-22 | 2017-11-24 | 哈尔滨工程大学 | A kind of underwater PIV measuring tables for obtaining catheter propeller interior flow field |
| CN112525737A (en) * | 2020-11-20 | 2021-03-19 | 中国直升机设计研究所 | Test device and test method for measuring flapping rigidity of helicopter blade |
-
2021
- 2021-11-19 CN CN202111382130.2A patent/CN114112351A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4146967A (en) * | 1977-08-15 | 1979-04-03 | The Boeing Company | Rotor blade inspection fixture |
| 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 |
| CN105806602A (en) * | 2016-03-16 | 2016-07-27 | 中国直升机设计研究所 | Anti-icing and deicing main blade fatigue test device |
| CN107389973A (en) * | 2017-08-22 | 2017-11-24 | 哈尔滨工程大学 | A kind of underwater PIV measuring tables for obtaining catheter propeller interior flow field |
| CN112525737A (en) * | 2020-11-20 | 2021-03-19 | 中国直升机设计研究所 | Test device and test method for measuring flapping rigidity of helicopter blade |
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