CN109506862B - Flexible beam tail paddle rigidity test device - Google Patents
Flexible beam tail paddle rigidity test device Download PDFInfo
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- CN109506862B CN109506862B CN201811340618.7A CN201811340618A CN109506862B CN 109506862 B CN109506862 B CN 109506862B CN 201811340618 A CN201811340618 A CN 201811340618A CN 109506862 B CN109506862 B CN 109506862B
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- bushing
- supporting
- plate
- clamping
- flexible beam
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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
Abstract
The application belongs to the technical field of helicopter tail blade rigidity tests, and particularly relates to a flexible beam tail blade rigidity test device, which comprises: a turntable; one end of the supporting plate is a connecting end, the other end of the supporting plate is a supporting end, and the connecting end is connected with the rotary table; the general supporting assembly is used for fixing the flexible beam tail blade so as to carry out a general rigidity test of the flexible beam tail blade; the integral supporting assembly is used for fixing the flexible beam tail blade so as to carry out an integral rigidity test of the flexible beam tail blade; wherein, the test device has: in a general test state, the general supporting component is fixedly connected with the supporting end in a detachable mode; and in the integral test state, the integral supporting component is fixedly connected with the supporting end in a detachable mode.
Description
Technical Field
The application belongs to the technical field of helicopter tail blade rigidity tests, and particularly relates to a tail blade rigidity test device.
Background
The bearingless rotor wing is an important mark of a fourth generation helicopter, the bearingless tail rotor is a pilot technology developed by the bearingless rotor wing, the blades of the bearingless tail rotor wing mainly adopt flexible beams, the flexible beam tail blades are made of composite materials, and the flapping, the shimmy and the pitch-variable motion of the tail rotor wing are realized through the elastic deformation of the flexible beams.
The forming process of the composite material has certain influence on the quality of the flexible beam tail blade, and a rigidity test needs to be carried out on the flexible beam tail blade for evaluating the condition that the section characteristics of the flexible beam tail blade are in accordance with the theoretical calculated value and providing reliable data for the aspects of dynamic calculation, load calculation, strength check and the like of the flexible beam tail blade.
At present, with the continuous improvement of the performance requirements of the flexible beam tail blade, the rigidity test is not only required to be carried out on a common rigidity test, but also the flapping, the shimmy and the torsional rigidity of the section of the flexible beam tail blade are tested; and the test of integral rigidity is also required to be carried out, and the integral swinging, shimmy and torsional rigidity of the test piece is tested. The general rigidity test and the integral rigidity test are different in fixing position of the flexible beam tail blade, and at present, no test device can conveniently and rapidly complete the general rigidity test and the integral rigidity test of the flexible beam tail blade by technicians in the field.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a flexible beam tail blade rigidity testing device to overcome or alleviate at least one defect of the above aspects.
The technical scheme of the application is as follows:
a kind of flexible beam tail paddle rigidity test device, including:
a turntable;
one end of the supporting plate is a connecting end, the other end of the supporting plate is a supporting end, and the connecting end is connected with the rotary table;
the general supporting assembly is used for fixing the flexible beam tail blade so as to carry out a general rigidity test of the flexible beam tail blade;
the integral supporting assembly is used for fixing the flexible beam tail blade so as to carry out an integral rigidity test of the flexible beam tail blade; wherein the content of the first and second substances,
the test apparatus comprises:
in a general test state, the general supporting component is fixedly connected with the supporting end in a detachable mode;
and in the integral test state, the integral supporting component is fixedly connected with the supporting end in a detachable mode.
According to at least one embodiment of the application, the test device further comprises a support ring which is coaxially arranged with the rotary table and is abutted against the rotary table, and the outer ring wall surface of the support ring is fixedly connected with the end face of the connecting end.
According to at least one embodiment of the application, a plurality of mounting grooves are formed in the mounting surface of the rotary table along the radial direction, and one end of each mounting groove extends to the outer edge of the rotary table;
the support ring has radially seted up a plurality of installation notches, and every installation notch forms a mounting hole with a mounting groove intercommunication, sets up a supporting bolt in every mounting hole.
According to at least one embodiment of the present application, a general support assembly includes:
a first fixing plate;
two first supporting clamping plates which are oppositely arranged on one side of the first fixing plate and are respectively fixedly connected with the side wall surface of the first fixing plate;
the test device is in a general test state, and the support end is arranged between the two first support clamping plates and is fixedly connected with the two first support clamping plates in a detachable mode.
According to at least one embodiment of the present application, the general supporting assembly further includes two cuff clamps, which are oppositely disposed on a side of the first fixing plate away from the two first supporting clamps and are respectively fixedly connected to the side wall surfaces of the first fixing plate, and the two cuff clamps are perpendicular to the two first supporting clamps;
the two-sleeve clamping plate is used for fixing a sleeve of the flexible beam tail blade.
According to at least one embodiment of the present application, when one cuff is secured by the two cuff clamps,
the oversleeve is arranged between the two oversleeve clamping plates and is connected with the two oversleeve clamping plates through a plurality of oversleeve bolts, and each oversleeve bolt penetrates through an oversleeve connecting hole on the side wall surface of the oversleeve.
According to at least one embodiment of the present application, a unitary support assembly comprises:
a second fixing plate;
two second supporting clamping plates which are oppositely arranged on one side of the second fixing plate and are respectively fixedly connected with the side wall surface of the second fixing plate;
the testing device is in an integral testing state, and the supporting end is arranged between the two second supporting clamping plates and is fixedly connected with the two second supporting clamping plates in a detachable mode.
According to at least one embodiment of the present application, the integral support assembly further comprises:
one side wall surface of the first lining clamp plate is abutted with one side wall surface of the second fixing plate far away from the two second supporting clamp plates;
and the second bushing clamping plate is arranged opposite to the first bushing clamping plate and is used for being matched with the first bushing clamping plate to fix the flexible beam tail blade.
According to at least one embodiment of the application, a first bushing clamping groove is formed in one side wall surface, close to the second bushing clamping plate, of the first bushing clamping plate, and two ends of the first bushing clamping groove extend to the outer wall surface of the first bushing clamping plate;
a second bushing clamping groove is formed in the wall surface, close to the first bushing clamping plate, of the second bushing clamping plate, two ends of the second bushing clamping groove extend to the outer wall surface of the second bushing clamping plate, a bushing clamping channel is formed between the first bushing clamping groove and the second bushing clamping groove, and the axis of the clamping channel is perpendicular to the two second supporting clamping plates;
the first bushing clamping plate and the second bushing clamping plate are screwed to the second fixing plate through a plurality of bushing bolts;
when the first bush splint and the second bush splint are matched with each other to fix the flexible beam tail blade,
the center bushing of the flexible beam tail blade is arranged in the clamping channel, the first bushing clamp plate is connected with the second bushing clamp plate through a center bolt, the center bolt penetrates through the center hole of the flexible beam tail blade, and the wall surface of the clamping channel clamps the center bushing.
According to at least one embodiment of the application, the flexible beam tail blade rigidity testing device further comprises an installation platform, and the rotary table is fixed on the installation platform.
The application has at least the following beneficial technical effects: the flexible beam type tail paddle rigidity testing device has a general testing state and an integral testing state, and can be conveniently switched between the two states, under the general testing state, the flexible beam type tail paddle rigidity testing device can be used for carrying out a general rigidity testing test on the flexible beam tail paddle, under the integral testing state, the flexible beam type tail paddle rigidity testing device is used for carrying out an integral rigidity testing test on the flexible beam tail paddle, and a person skilled in the art can accurately and efficiently finish general and integral rigidity tests on the flexible beam type tail paddle by using the device.
Drawings
Fig. 1 is a schematic structural diagram of a flexible beam tail rotor blade stiffness test device provided by an embodiment of the present application, which works in a general test state;
FIG. 2 is a schematic structural diagram of a flexible beam tail rotor blade stiffness testing device provided by the embodiment of the application working in an overall testing state;
FIG. 3 is a schematic structural diagram of a support ring and a support plate provided in an embodiment of the present application;
FIG. 4 is a schematic structural diagram of a general support assembly provided by embodiments of the present application;
fig. 5 is a schematic structural diagram of a partial assembly of an integral support assembly provided in an embodiment of the present application.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
The present application is described in further detail below with reference to fig. 1 to 5.
A kind of flexible beam tail paddle rigidity test device, including:
a rotary table 1;
one end of the supporting plate 2 is a connecting end, the other end of the supporting plate is a supporting end, and the connecting end is connected with the rotary table 1;
the general supporting assembly is used for fixing the flexible beam tail blade so as to carry out a general rigidity test of the flexible beam tail blade;
the integral supporting assembly is used for fixing the flexible beam tail blade so as to carry out an integral rigidity test of the flexible beam tail blade; wherein the content of the first and second substances,
the test apparatus comprises:
in a general test state, the general supporting component is fixedly connected with the supporting end in a detachable mode;
and in the integral test state, the integral supporting component is fixedly connected with the supporting end in a detachable mode.
In some optional embodiments, the support ring 3 is arranged coaxially with the rotary table 1 and is abutted against the rotary table, and the outer ring wall surface of the support ring is fixedly connected with the end surface of the connecting end.
In some optional embodiments, a plurality of mounting grooves are radially formed in the mounting surface of the rotary table 1, and one end of each mounting groove extends to the outer edge of the rotary table 1; the support ring 3 has radially seted up a plurality of installation notches, and every installation notch forms a mounting hole with a mounting groove intercommunication, sets up a supporting bolt 4 in every mounting hole.
In some alternative embodiments, the general support assembly comprises: a first fixing plate 5;
two first supporting splints 6, which are oppositely arranged on one side of the first fixing plate 5 and are respectively fixedly connected with the side wall surface of the first fixing plate 5; the test device is in a general test state, and the supporting end is arranged between the two first supporting splints 6 and is fixedly connected with the two first supporting splints 6 in a detachable mode.
For the above-mentioned fixed connection of the support ends to the two first support jaws 6 in a detachable manner, it is easily conceivable and adopted by the person skilled in the art to fixedly connect them by means of bolts.
In some optional embodiments, the general supporting assembly further includes two sleeve clamping plates 7, which are oppositely disposed on the side of the first fixing plate 5 away from the two first supporting clamping plates 6 and are fixedly connected to the side wall surfaces of the first fixing plate 5, respectively, and the two sleeve clamping plates 7 are perpendicular to the two first supporting clamping plates 6; the two oversleeve splints 7 are used for fixing an oversleeve 8 of the flexible beam tail blade.
In some alternative embodiments, when the two sleeve clamping plates 7 fix a sleeve 8, the sleeve 8 is arranged between the two sleeve clamping plates 7 and connected with the two sleeve clamping plates 7 through a plurality of sleeve bolts, and each sleeve bolt passes through a sleeve connecting hole 9 on the side wall surface of one sleeve 8.
In some alternative embodiments, the integral support assembly comprises: a second fixing plate 10;
two second supporting splints 11, which are oppositely arranged on one side of the second fixing plate 10 and are respectively fixedly connected with the side wall surface of the second fixing plate 10; the testing device is in an integral testing state, and the supporting end is arranged between the two second supporting clamping plates 11 and is fixedly connected with the two second supporting clamping plates 11 in a detachable mode.
In some alternative embodiments, the integral support assembly further comprises: a first bush holding plate 12, one side wall surface of which is abutted against one side wall surface of the second fixing plate 10 away from the two second support holding plates 11; and the second bushing clamping plate 13 is arranged opposite to the first bushing clamping plate 12 and is matched with the first bushing clamping plate 12 to fix the flexible beam tail blade.
In some alternative embodiments, a first bushing clamping groove is formed in a side wall surface of the first bushing clamping plate 12 close to the second bushing clamping plate 13, and two ends of the first bushing clamping groove extend to an outer wall surface of the first bushing clamping plate 12; a second bushing clamping groove is formed in the wall surface, close to the first bushing clamping plate 12, of the second bushing clamping plate 13, two ends of the second bushing clamping groove extend to the outer wall surface of the second bushing clamping plate 13, a bushing clamping channel is formed between the first bushing clamping groove and the second bushing clamping groove, and the axis of the clamping channel is perpendicular to the two second supporting clamping plates 11; the first and second bushing clamps 12 and 13 are screwed to the second fixing plate 10 by a plurality of bushing bolts 14; when the first bushing clamp plate 12 and the second bushing clamp plate 13 are matched to fix the flexible beam tail blade, the central bushing 15 of the flexible beam tail blade is arranged in the clamping channel, the first bushing clamp plate 12 and the second bushing clamp plate 13 are connected through the central bolt 16, the central bolt 16 penetrates through the central hole 17 of the flexible beam tail blade, and the wall surface of the clamping channel clamps the central bushing 15.
In some optional embodiments, the testing apparatus further comprises a mounting platform 18, and the turntable 1 is fixed on the mounting platform.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (3)
1. The utility model provides a flexible beam tail paddle rigidity test device which characterized in that includes:
a rotary table (1);
one end of the supporting plate (2) is a connecting end, the other end of the supporting plate is a supporting end, and the connecting end is connected with the rotary table (1);
the general support assembly is used for fixing the flexible beam tail blade so as to carry out a general rigidity test of the flexible beam tail blade;
the integral supporting assembly is used for fixing the flexible beam tail blade so as to carry out an integral rigidity test of the flexible beam tail blade; wherein the content of the first and second substances,
the test device comprises:
in a general test state, the general support assembly is fixedly connected with the support end in a detachable mode;
in the integral test state, the integral support assembly is fixedly connected with the support end in a detachable mode;
the general support assembly includes:
a first fixing plate (5);
two first supporting splints (6) which are oppositely arranged on one side of the first fixing plate (5) and are respectively fixedly connected with the side wall surface of the first fixing plate (5);
the testing device is in a general testing state, and the supporting end is arranged between the two first supporting splints (6) and is fixedly connected with the two first supporting splints (6) in a detachable mode;
the general supporting component also comprises two oversleeve clamping plates (7), one side of the first fixing plate (5) far away from the two first supporting clamping plates (6) is oppositely arranged and is respectively fixedly connected with the side wall surface of the first fixing plate (5), and the two oversleeve clamping plates (7) are vertical to the two first supporting clamping plates (6);
the two oversleeve clamping plates (7) are used for fixing an oversleeve (8) of the flexible beam tail blade; when the two oversleeve splints (7) fix one oversleeve (8),
the oversleeve (8) is arranged between the two oversleeve clamping plates (7) and is connected with the two oversleeve clamping plates (7) through a plurality of oversleeve bolts, and each oversleeve bolt passes through an oversleeve connecting hole (9) on the side wall surface of the oversleeve (8);
the integral support assembly comprises:
a second fixing plate (10);
two second supporting splints (11) which are oppositely arranged on one side of the second fixing plate (10) and are respectively fixedly connected with the side wall surface of the second fixing plate (10);
the testing device is in an integral testing state, and the supporting end is arranged between the two second supporting splints (11) and is fixedly connected with the two second supporting splints (11) in a detachable mode;
the integral support assembly further comprises:
a first bushing clamp plate (12) having one side wall surface abutting against one side wall surface of the second fixing plate (10) away from the two second support clamp plates (11);
a second bushing clamp plate (13) arranged opposite to the first bushing clamp plate (12) for cooperating with the first bushing clamp plate (12) for fixing the flexible beam tail blade;
a first lining clamping groove is formed in the wall surface of one side, close to the second lining clamping plate (13), of the first lining clamping plate (12), and two ends of the first lining clamping groove extend to the outer wall surface of the first lining clamping plate (12);
a second bushing clamping groove is formed in the wall surface, close to the first bushing clamping plate (12), of the second bushing clamping plate (13), two ends of the second bushing clamping groove extend to the outer wall surface of the second bushing clamping plate (13), a bushing clamping channel is formed between the first bushing clamping groove and the second bushing clamping groove, and the axis of the clamping channel is perpendicular to the two second supporting clamping plates (11);
the first bushing clamping plate (12) and the second bushing clamping plate (13) are screwed to the second fixing plate (10) by a plurality of bushing bolts (14);
when the first bushing clamp plate (12) and the second bushing clamp plate (13) are matched and fixed with the flexible beam tail blade,
a central bushing (15) of the flexible beam tail blade is arranged in the clamping channel, the first bushing clamp plate (12) and the second bushing clamp plate (13) are connected through a central bolt (16), the central bolt (16) penetrates through a central hole (17) of the flexible beam tail blade, and the wall surface of the clamping channel clamps the central bushing (15);
the rotary table is characterized by further comprising an installation platform (18), and the rotary table (1) is fixed on the installation platform.
2. The test device according to claim 1, further comprising a support ring (3) coaxially disposed with the turntable (1) and abutting against the turntable, wherein an outer ring wall surface of the support ring is fixedly connected with the connecting end face of the support plate (2).
3. Testing device according to claim 2,
a plurality of mounting grooves are formed in the mounting surface of the rotary table (1) along the radial direction, and one end of each mounting groove extends to the outer edge of the rotary table (1);
the support ring (3) is radially provided with a plurality of mounting notches, each mounting notch is communicated with one mounting groove to form a mounting hole, and each mounting hole is internally provided with a supporting bolt (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811340618.7A CN109506862B (en) | 2018-11-12 | 2018-11-12 | Flexible beam tail paddle rigidity test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811340618.7A CN109506862B (en) | 2018-11-12 | 2018-11-12 | Flexible beam tail paddle rigidity test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109506862A CN109506862A (en) | 2019-03-22 |
| CN109506862B true CN109506862B (en) | 2020-10-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811340618.7A Active CN109506862B (en) | 2018-11-12 | 2018-11-12 | Flexible beam tail paddle rigidity test device |
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| Country | Link |
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| CN (1) | CN109506862B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112224404A (en) * | 2020-10-16 | 2021-01-15 | 中国直升机设计研究所 | Oversleeve structure for foldable bearingless rotor wing |
| CN113148225B (en) * | 2021-04-20 | 2022-11-22 | 中国直升机设计研究所 | Testing device and testing method for fixing and rotating helicopter blades |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100575841B1 (en) * | 2004-07-14 | 2006-05-02 | 한국항공우주연구원 | Cross-shaped Composite Flexbeam for Bearingless Rotor System with Convenient Natural Frequncy Tuning Capacity |
| US8578753B2 (en) * | 2009-12-17 | 2013-11-12 | Sikorsky Aircraft Corporation | Impact test fixture with simulated centrifugal force |
| EP2883790B1 (en) * | 2013-12-10 | 2017-11-22 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Beam for a rotorcraft rotor and rotorcraft rotor |
| CN204495552U (en) * | 2015-04-07 | 2015-07-22 | 中国直升机设计研究所 | A kind of aerofoil profile clamping device for measuring blade twist rigidity |
| 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 |
| CN108225692B (en) * | 2017-12-01 | 2020-02-21 | 中国直升机设计研究所 | Test method for measuring overall torsional rigidity of blade |
| CN207717311U (en) * | 2017-12-01 | 2018-08-10 | 中国直升机设计研究所 | A kind of helicopter blade torsion rigidity measurer |
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