CN108982041B - Air rudder core excitation testing device - Google Patents
Air rudder core excitation testing device Download PDFInfo
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- CN108982041B CN108982041B CN201811099685.4A CN201811099685A CN108982041B CN 108982041 B CN108982041 B CN 108982041B CN 201811099685 A CN201811099685 A CN 201811099685A CN 108982041 B CN108982041 B CN 108982041B
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- 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
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Abstract
The invention provides an excitation test device for an air rudder core, which adopts a special test tool for the air rudder core, the air rudder core is arranged on a test workbench, strain gauges and displacement sensors are arranged on or around the air rudder core, when a vibration exciter on the test workbench exerts an excitation effect on the air rudder core, the strain gauges and the displacement sensors arranged around the air rudder core are arranged on the air rudder to test the strain and the integral deformation of the air rudder core, and reliable support is provided for the design and subsequent processes of the air rudder core.
Description
Technical Field
The invention relates to an air rudder core excitation test device, in particular to an air rudder core excitation test device capable of changing excitation force application positions, and belongs to the technical field of mechanical part testing.
Background
The air rudder is a control and execution mechanism of the flight path of the aircraft, and the lifting, pitching or yawing flight of the aircraft can be realized by changing the angle of the air rudder in the flight process. The aerodynamic shape of the air rudder directly affects the control accuracy of the aircraft and is an important part of the aircraft.
The rudder core of the air rudder is generally formed by welding a rudder core framework and a rudder core skin, and the rudder core is generally made of titanium alloy; when an aircraft flies in the atmosphere, the temperature of the air rudder is very high under the influence of pneumatic heating, so that a heat-proof jacket layer is coated outside the metal rudder core, the heat-proof jacket layer is generally made of a composite material with the characteristics of high temperature resistance, ablation resistance, scouring resistance, thermal shock resistance and the like, and the composite material is relatively brittle, so that before the air rudder heat-proof jacket is prepared, the test on the excited structural strength and the deformation condition of the air rudder core is very necessary, unnecessary damage to the heat-proof jacket layer caused by the air rudder core in the air rudder flying shock excitation state is avoided, and the problem is less concerned by the prior art.
Disclosure of Invention
The present invention has been made to solve the above-mentioned problems occurring in the related art to a certain extent.
The invention relates to an air rudder core excitation test device which is used for testing the strain condition and the appearance change condition of an air rudder core under the condition that the air rudder core is subjected to an excitation force.
The invention is realized by adopting the following technical means:
air rudder core excitation testing arrangement includes: the test bench and the tool for clamping the air rudder shaft are characterized in that the tool comprises two clamping components with the same structure, a stud and 6 bolts, the clamping components are of a cuboid structure with a through groove on one side surface, the two clamping components form a cuboid when combined together, the two through grooves on the side surfaces of the two clamping components form a cylindrical or conical hole (the rudder shaft can be in a cylindrical or conical shape) which is completely matched with the air rudder shaft in size, the axis of the cylindrical or conical hole formed by combining the through grooves of the two clamping components is vertical to the test bench, four corners of the upper surface of the cuboid formed by combining the two clamping components are respectively provided with a first countersunk hole, 4 bolts fixedly connect the tool and the test bench through the first countersunk holes, and the left side surface and the right side surface of the cuboid formed by the two clamping components are respectively provided with two second countersunk holes with corresponding positions, the positions of the two second countersunk holes on the same side surface are symmetrical relative to the symmetrical center of the side surface, 2 bolts penetrate through the two symmetrically arranged side surface second countersunk holes, the other end of the two clamping components are fastened and connected through nuts, a third countersunk hole is formed in the center position of the left side surface and the right side surface of a cuboid formed by the two clamping components, and the third countersunk hole is used for a stud to penetrate through;
a rudder shaft is arranged below the air rudder core, the rudder shaft and the rudder core are connected together by welding, a through hole is processed at the position where the height of the third countersunk hole of the tooling is the same as that of the rudder shaft, the air rudder core is inserted into the tooling for clamping the air rudder shaft, the lower surface of the air rudder core falls on the upper surface of the tooling, and the through hole on the rudder shaft corresponds to the third countersunk hole arranged at the central position of the left side surface and the right side surface of a cuboid formed by two clamping components and has the same aperture; the stud penetrates through the two clamping assemblies and the air rudder shaft, the air rudder is fixed on a tool through the rudder shaft, two ends of the stud are fastened through nuts, and the middle section of the stud is the same as the size of the through hole of the rudder shaft;
the tool is a cuboid formed by combining two clamping components together, in order to adapt to the fixed requirements of different models and sizes, tools with various specifications are manufactured, the external size of the tool is unchanged, the tool is only adapted to the shape and size of different air rudder shafts, the size of a cylindrical or conical table hole in the center of the tool is changed, and when air rudder tests of different models are carried out, the tool and an air rudder core are installed by only using the tool corresponding to the tool, and the test can be started by installing the tool and the air rudder core on a test workbench;
the middle position of the test workbench is provided with a cuboid space for installing a tool for clamping an air rudder shaft, the size of the cuboid space is the same as that of a cuboid formed by combining two clamping components, the left side and the right side of the cuboid space are respectively provided with a strip-shaped groove, a vibration exciter is arranged in each strip-shaped groove and used for providing exciting force for an air rudder core, and the vibration exciter can change the installation position in each groove so as to change the exciting position applied to the air rudder core;
furthermore, guide rails are arranged in the two strip-shaped grooves, and the vibration exciter can slide on the guide rails and is locked at the current position after sliding to the specified position.
The surface of the air rudder core is provided with strain gauges which are mainly arranged on two symmetrical aerodynamic force acting surfaces of the rudder core and used for detecting strain values of the surface of the rudder core, and electric signals of the strain gauges are transmitted to an upper computer through a signal acquisition device for data processing and analysis; meanwhile, a laser displacement sensor is arranged near the surface of the air rudder core and used for detecting the deformation condition of the air rudder core in the excitation process, an electric signal of the laser displacement sensor is also transmitted to an upper computer through a signal acquisition device for data processing and analysis, and the stress-strain condition and the appearance change condition of the air rudder core under various excitation conditions are comprehensively analyzed through a strain value and a displacement value.
The air rudder core excitation test method comprises the following steps:
(1) assembling the tool, wherein a cuboid tool is formed when two same clamping components are combined together, a through groove arranged on one side surface of each of the two clamping components forms a cylindrical or conical table hole which is completely matched with the air rudder shaft in size, two second countersunk holes corresponding to two positions are respectively arranged on the left side surface and the right side surface of the cuboid formed by the two clamping components, the two second countersunk holes on the same side surface are symmetrical relative to the symmetrical center of the side surface, 2 bolts penetrate through the two symmetrically arranged second countersunk holes on the same side surface, the two clamping components are connected in series, and the two clamping components are fastened and connected together at the other end through nuts;
(2) installing an air rudder core to be tested, arranging a rudder shaft below the air rudder core, inserting the air rudder shaft into a cylindrical or conical table hole in the vertical direction of a tool, processing a through hole with the same size at the position where the height of the rudder shaft is the same as that of a third countersunk hole of the tool, penetrating a stud through the third countersunk holes of the two clamping components and the hole on the air rudder core, fixing the air rudder on the tool through the rudder shaft, and fastening two ends of the stud through nuts;
(3) the tool is placed in a cuboid space arranged in the middle of a test workbench, four corners of the upper surface of a cuboid formed by combining two clamping assemblies are respectively provided with a first counter bore, and the tool and the test workbench are fixedly connected through the first counter bores by 4 bolts, so that the clamping and mounting work of the air rudder core is completed;
(4) the surface of the air rudder core is provided with a strain gauge for detecting a strain value on the surface of the rudder core, the strain gauge is connected with a signal acquisition device, and the signal acquisition device is connected with an upper computer; a laser displacement sensor is arranged near the surface of the rudder core of the air rudder and is connected with a signal acquisition device, and the signal acquisition device is connected with an upper computer;
(5) adjusting the positions of vibration exciters in the two strip-shaped grooves of the test workbench, and starting the test at the locked position after the adjustment;
(6) acquiring strain values and displacement values of the air rudder core under various excitation conditions, and comprehensively analyzing stress strain conditions and appearance change conditions of the air rudder core under various excitation conditions through the strain values and the displacement values;
(7) after the excitation test of the air rudder core of one model is finished, the steps (1) - (5) can be repeated by replacing different tools of the air rudder cores of different models, and then the test of the air rudder cores of other models can be carried out.
The invention has the following advantages
(1) The problem that the design and analysis of the rudder core of the conventional air rudder only has a theoretical analysis value and no actual test data support is solved
(2) The testing device is reasonable in design, can adapt to air rudder core tests of various different models, does not need complex mechanical structure design, realizes clamping of different models only by changing one tool, and greatly improves the working efficiency.
Drawings
Fig. 1 shows a rudder core frame, a rudder core skin and a rudder core with a rudder shaft of an air rudder
FIG. 2 shows an excitation test device for an air rudder core of the present invention
1. Test workbench, 11, cuboid space, 12, vibration exciter, 13, elongated groove, 2, tooling, 21, cylindrical or conical table hole, 22, third counter sink, 23, stud, 24, second counter sink, 25, first counter sink, 26, clamping assembly, 3, air rudder core, 31, through hole, 32, rudder core framework, 33, rudder core skin, 34 and rudder shaft.
DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be noted that, for the convenience of description, only some but not all of the elements related to the present invention are shown in the drawings.
Example one
Fig. 1 shows a rudder core frame 32, a rudder core skin 33 and a rudder core with a rudder shaft 34 of an air rudder. Fig. 2 is an air rudder core excitation test device of the present invention.
The invention is realized by adopting the following technical means:
air rudder core excitation testing arrangement includes: the test bench 1 and the tool 2 used for clamping the air rudder shaft 34, the tool 2 is composed of two clamping components 26 with the same structure, a stud 23 and 6 bolts, the clamping component 26 is a cuboid structure with a through groove on one side surface, the two clamping components 26 are combined together to form a cuboid, the two through grooves on the side surfaces of the two clamping components 26 are combined to form a cylindrical or conical hole 21 (the rudder shaft 34 can be in a cylindrical or conical shape) which is completely matched with the air rudder shaft in size, the axis of the cylindrical or conical hole 21 formed by the combination of the through grooves of the two clamping components 26 is vertical to the test bench, the upper surface of the cuboid formed by the combination of the two clamping components 26 is respectively provided with a first countersunk hole 25, 4 bolts fixedly connect the tool 2 and the test bench 1 through the first countersunk holes 25, the left and right side surfaces of the cuboid formed by the two clamping assemblies 26 are respectively provided with two second counter bores 24 corresponding in position, the positions of the two second counter bores 24 on the same side surface are symmetrical relative to the symmetrical center of the side surface, 2 bolts penetrate through the two symmetrically arranged side surface second counter bores 24, the other end of the two clamping assemblies 26 are fixedly connected through nuts, the center positions of the left and right side surfaces of the cuboid formed by the two clamping assemblies 26 are provided with a third counter bore 22, and the third counter bore 22 is used for the stud 23 to penetrate through;
a rudder shaft 34 is arranged below the air rudder core 3, the rudder shaft 34 and the rudder core are connected together by welding, a through hole 31 is processed at the position where the height of the rudder shaft 34 is the same as that of the third countersunk hole 22 of the tool 2, the air rudder core 34 is inserted into the tool 2 for clamping the air rudder shaft 34, the lower surface of the air rudder core falls on the upper surface of the tool, the through hole 31 on the rudder shaft 34 corresponds to the third countersunk hole 22 arranged at the central position of the left side surface and the right side surface of the cuboid formed by the two clamping components 26, and the aperture is the same; the stud 26 penetrates through the two clamping assemblies 26 and the air rudder shaft 34, the air rudder is fixed on the tool 2 through the rudder shaft 34, two ends of the stud 26 are fastened through nuts, and the middle section of the stud 26 is the same as the through hole 31 of the rudder shaft 34 in size;
the tool is a cuboid formed by combining two clamping components 26 together, in order to meet the fixed requirements of different models and sizes, the tools 2 with various specifications are manufactured, the external size of the tool 2 is not changed, the tool is only suitable for the shapes and sizes of different air rudder shafts 34, and the size of a cylindrical or conical platform hole 21 in the center of the tool 2 is changed; when air rudders of different models are tested, only the corresponding tool 2 is needed to be used, the tool 2 and the air rudder core are installed, and the test can be started by installing the tool 2 and the air rudder core on the test workbench 1;
a rectangular space 11 for installing the tool 2 for clamping the air rudder shaft 34 is arranged in the middle of the test workbench 1, the size of the rectangular space is the same as that of a rectangular structure formed by combining the two clamping assemblies 26, strip-shaped grooves 13 are respectively arranged on the left side and the right side of the rectangular space 11, vibration exciters 12 are arranged in the strip-shaped grooves 13 and used for providing exciting force for the air rudder core, and the installation positions of the vibration exciters 12 in the strip-shaped grooves 13 can be changed, so that the exciting positions applied to the air rudder core are changed;
further, guide rails are arranged in the two strip-shaped grooves, and the vibration exciter 12 can slide on the guide rails and is locked at the current position after sliding to the specified position.
The surface of the air rudder core is provided with strain gauges which are mainly arranged on two symmetrical aerodynamic force acting surfaces of the rudder core and used for detecting strain values of the surface of the rudder core, and electric signals of the strain gauges are transmitted to an upper computer through a signal acquisition device for data processing and analysis; meanwhile, a laser displacement sensor is arranged near the surface of the air rudder core and used for detecting the deformation condition of the air rudder core in the excitation process, an electric signal of the laser displacement sensor is also transmitted to an upper computer through a signal acquisition device for data processing and analysis, and the stress-strain condition and the appearance change condition of the air rudder core under various excitation conditions are comprehensively analyzed through a strain value and a displacement value.
The air rudder core excitation test method comprises the following steps:
(1) assembling the tool 2, wherein two identical clamping assemblies 26 are combined together to form a rectangular tool 2, a through groove arranged on one side surface of each of the two clamping assemblies 26 forms a cylindrical or conical frustum hole 21 which is completely matched with the air rudder shaft 34 in size, two second counter sink holes 24 corresponding to the left and right side surfaces of a rectangular body formed by the two clamping assemblies 26 are respectively arranged, the positions of the two second counter sink holes 24 on the same side surface are symmetrical relative to the symmetrical center of the side surface, 2 bolts penetrate through the two symmetrically arranged second counter sink holes 24 on the same side surface to connect the two clamping assemblies 26 in series, and the two clamping assemblies 26 are fastened together at the other end through nuts;
(2) installing an air rudder core to be tested, arranging a rudder shaft 34 below the air rudder core, inserting the air rudder shaft 34 into a cylindrical or conical table hole 21 in the vertical direction of a tool 2, processing a through hole 31 with the same size at the position where the height of the rudder shaft 34 is the same as that of a third countersunk hole 22 of the tool 2, passing a stud 23 through the third countersunk holes 22 of two clamping components 26 and the through hole 31 on the air rudder shaft 34, fixing the air rudder core on the tool 2 through the rudder shaft 34, and fastening two ends of the stud 23 through nuts;
(3) the tool 2 is placed in a cuboid space 11 arranged in the middle of the test workbench 1, four corners of the upper surface of a cuboid formed by combining two clamping assemblies 26 are respectively provided with a first counter bore 25, 4 bolts fixedly connect the tool 2 and the test workbench 1 through the first counter bores 25, and thus the clamping and mounting work of the air rudder core is completed;
(4) the surface of the air rudder core is provided with a strain gauge for detecting a strain value on the surface of the rudder core, the strain gauge is connected with a signal acquisition device, and the signal acquisition device is connected with an upper computer; a laser displacement sensor is arranged near the surface of the rudder core of the air rudder and is connected with a signal acquisition device, and the signal acquisition device is connected with an upper computer;
(5) adjusting the positions of the vibration exciters 12 in the two strip-shaped grooves of the test workbench, and starting the test at the locked position after the adjustment;
(6) acquiring strain values and displacement values of the air rudder core under various excitation conditions, and comprehensively analyzing stress strain conditions and appearance change conditions of the air rudder core under various excitation conditions through the strain values and the displacement values;
(7) after the excitation test of the air rudder core of one model is finished, the steps (1) - (5) can be repeated by replacing different tools of the air rudder cores of different models, and then the test of the air rudder cores of other models can be carried out.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing embodiments, or that certain features may be substituted in equivalent manner. Any modification and equivalent replacement within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. An excitation test device for an air rudder core comprises a test workbench, a tool for clamping an air rudder shaft, a vibration exciter, a strain gauge and a laser displacement sensor; the method is characterized in that: the tool consists of two clamping assemblies with the same structure, a stud and 6 bolts; the clamping component is a cuboid structure with a through groove on one side surface, the two clamping components form a cuboid when combined together, the two through grooves arranged on the side surfaces of the two clamping components form a cylinder or a cone platform hole which is completely matched with the size of an air rudder shaft, the axis of the cylinder or the cone platform formed by the through grooves of the two clamping components is vertical to the test workbench, four corners of the upper surface of the cuboid formed by the combination of the two clamping components are respectively provided with a first countersunk hole, 4 bolts fixedly connect the tool with the test workbench through the first countersunk holes, the left side surface and the right side surface of the cuboid formed by the two clamping components are respectively provided with two second countersunk holes with corresponding positions, the positions of the two second countersunk holes on the same side surface are symmetrical relative to the symmetrical center of the side surface, and 2 bolts pass through the two symmetrically arranged side surface second countersunk holes, the other end of the clamping component is fixedly connected with the two clamping components through nuts, a third counter sink hole is formed in the center of the left side surface and the right side surface of the cuboid formed by the two clamping components, and the third counter sink hole is used for the stud to pass through;
a rudder shaft is arranged below the air rudder core, the rudder shaft and the rudder core are connected together by welding, a through hole is processed at the position where the height of the third countersunk hole of the tooling is the same as that of the rudder shaft, the air rudder core is inserted into the tooling for clamping the air rudder shaft, the lower surface of the air rudder core falls on the upper surface of the tooling, and the through hole on the rudder shaft corresponds to the third countersunk hole arranged at the central position of the left side surface and the right side surface of a cuboid formed by two clamping components and has the same aperture; the stud penetrates through the two clamping assemblies and the air rudder shaft, the air rudder is fixed on a tool through the rudder shaft, two ends of the stud are fastened through nuts, and the diameter of the middle section of the stud is the same as that of the through hole of the rudder shaft;
a rectangular space for accommodating a tool for clamping the air rudder shaft is arranged in the middle of the test workbench, the size of the rectangular space is the same as that of a rectangular body formed by combining two clamping components, the left side and the right side of the rectangular space are respectively provided with a strip-shaped groove, and a vibration exciter is arranged in each strip-shaped groove and used for providing an exciting force for an air rudder core;
the surface of the air rudder core is provided with strain gauges, the strain gauges are arranged on two symmetrical aerodynamic force action surfaces of the rudder core and used for detecting strain values of the surface of the rudder core, and electric signals of the strain gauges are transmitted to an upper computer through a signal acquisition device to be subjected to data processing analysis; the laser displacement sensor is arranged near the surface of the air rudder core and used for detecting the deformation condition of the air rudder core in the excitation process, the electric signal of the laser displacement sensor is also transmitted to the upper computer through the signal acquisition device for data processing and analysis, and the stress-strain condition and the appearance change condition of the air rudder core under various excitation conditions are comprehensively analyzed through the strain value and the displacement value.
2. The air-rudder core excitation testing device of claim 1, wherein the exciter is capable of changing an installation position in the elongated groove, thereby changing an excitation position applied to the air-rudder core.
3. The excitation test device for the air rudder core according to claim 2, wherein guide rails are arranged in the two elongated grooves, and the exciter can slide on the guide rails and be locked at a current position after sliding to a specified position.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811099685.4A CN108982041B (en) | 2018-09-20 | 2018-09-20 | Air rudder core excitation testing device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811099685.4A CN108982041B (en) | 2018-09-20 | 2018-09-20 | Air rudder core excitation testing device |
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| CN108982041A CN108982041A (en) | 2018-12-11 |
| CN108982041B true CN108982041B (en) | 2020-04-24 |
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| CN114011665B (en) * | 2021-11-09 | 2022-10-21 | 山西钢科碳材料有限公司 | Clamp for air rudder |
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| JP3821978B2 (en) * | 1999-02-22 | 2006-09-13 | アルプス電気株式会社 | Rudder angle sensor unit |
| CN107243832B (en) * | 2017-07-06 | 2023-04-14 | 南华大学 | Automatic clamping fixture for grinding air vane |
| CN107345844A (en) * | 2017-08-07 | 2017-11-14 | 北京工业大学 | A kind of round cross-section rod vibration experiment clamping device |
| CN108168812B (en) * | 2017-12-12 | 2019-09-17 | 北京自动化控制设备研究所 | A kind of steering gear flat vibration load combination unit |
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Effective date of registration: 20200402 Address after: 318010 No.4, building 17, xiayangpan community, Jiaojiang District, Taizhou City, Zhejiang Province Applicant after: Hu Fangjuan Address before: 453400 No. 18 Qinzhuang Village, Fanxiang Town, Changyuan County, Xinxiang City, Henan Province Applicant before: Wang Ruifang |
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Effective date of registration: 20221208 Address after: 276000 south of the intersection of Wenhua Road and Pingwang Road, Pingyi Economic Development Zone, Pingyi County, Linyi City, Shandong Province Patentee after: Pingyi ren'an traditional Chinese Medicine Industry Development Co.,Ltd. Address before: No. 4, Building 17, Xiayangpan Community, Jiaojiang District, Taizhou, Zhejiang 318010 Patentee before: Hu Fangjuan |