CN108982041A - A kind of airvane rudder core exciting test device - Google Patents
A kind of airvane rudder core exciting test device Download PDFInfo
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- CN108982041A CN108982041A CN201811099685.4A CN201811099685A CN108982041A CN 108982041 A CN108982041 A CN 108982041A CN 201811099685 A CN201811099685 A CN 201811099685A CN 108982041 A CN108982041 A CN 108982041A
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- airvane
- rudderpost
- rudder
- clamp assemblies
- tooling
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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
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention provides a kind of airvane rudder core exciting test device, it uses airvane rudder core special test tooling, airvane rudder core is installed on test table, on airvane rudder core or foil gauge and displacement sensor are arranged in periphery, when the vibration excitor on test table applies exciting effect to airvane rudder core, the strain of the displacement sensor test airvane rudder core of foil gauge and periphery arrangement and the deformation of entirety are arranged on airvane, provide reliable support for the design and subsequent technique of airvane rudder core.
Description
Technical field
The present invention relates to a kind of airvane rudder core exciting test devices, and in particular to a kind of changeable exciting force application location
Airvane rudder core exciting test device, belongs to component of machine the field of test technology.
Background technique
Airvane is the control of aircraft flight route, executing agency, by changing air rudder angles in flight course,
Lifting, pitching or the yawed flight of aircraft can be achieved.The aerodynamic configuration of airvane directly affects flying vehicles control precision, is winged
The important component of row device.
The rudder core of airvane is generally welded in the form of rudder core crab and rudder core covering, and rudder core generally uses titanium to close
Gold is made；Aircraft when flight, is influenced in atmosphere by " Aerodynamic Heating ", and rudder temperature of taking offence can be very high, therefore
Solar heat protection jacket layer is coated outside metal rudder core, solar heat protection jacket layer is generally using with spies such as high temperature resistant, anti-ablation, resistance to erosion, anti-thermal shocks
The composite material of point, and composite material is relatively crisp, therefore before the preparation of airvane heat shroud, is excited to tie to airvane rudder core
Structure intensity and deformation are tested very necessary, in order to avoid under airvane flight exciting state, airvane rudder core is to anti-
Hot jacket layer causes unnecessary damage, and the prior art pays close attention to this problem less.
Summary of the invention
The present invention is directed to solve above-mentioned technical problem in the related technology to a certain extent.
The present invention relates to a kind of airvane rudder core exciting test devices, are used to test airvane rudder core by exciting force
In the case of, the strained situation and profile variation situation of rudder core.
The present invention takes following technological means to realize:
Airvane rudder core exciting test device includes: test table and the tooling for entraining air rudder rudderpost, and tooling is by two
A completely identical in structure clamp assemblies, a studs and 6 bolt compositions, clamp assemblies are to have to pass through a side
The rectangular parallelepiped structure of through slot constitutes a cuboid, two clamp assemblies side institute bands when two clamp assemblies are combined
Two through slots having be combined into one with airvane rudderpost size exact matching cylinder or frustum of a cone hole (rudderpost may for circle
Column or truncated cone shape), the through slots of two clamp assemblies it is combined at cylinder or the frustum of a cone axis and test table
Vertically, the angle of upper surface four that two clamp assemblies combine constituted cuboid is respectively equipped with the first counter sink, 4 bolt warps
It crosses the first counter sink and is fixedly connected with tooling with test table, left and right two of the cuboid that two clamp assemblies are constituted
Side is respectively equipped with corresponding second counter sink in two positions, and two the second countersunk head hole sites of same side are relative to side
Symmetrical centre it is symmetrical, 2 bolts pass through two symmetrically arranged the second counter sinks of side, in the other end by nut by two
Clamp assemblies are fastenedly connected, and the center of the left and right side for the cuboid that two clamp assemblies are constituted is provided with a third
Counter sink, third counter sink are passed through for studs；
Rudderpost, rudderpost and rudder core is provided below by being welded together in airvane rudder core, sinks in rudderpost and tooling third
Head bore height processes a through-hole on identical position, by the tooling of airvane rudderpost insertion entraining air rudder rudderpost, airvane rudder
The lower surface of core is fallen on the upper surface of tooling, the cuboid that the through-hole on rudderpost and two clamp assemblies are constituted it is left and right
The third countersunk head hole site of the center setting of side is corresponding, and aperture is identical；Studs passes through two clamp assemblies
And airvane rudderpost, airvane is fixed in tooling by rudderpost, the both ends of studs are fastened by nut, double end spiral shell
The interlude of column is identical as the size of rudderpost through-hole；
Tooling is the cuboid that two clamp assemblies are constituted when combining, for the fixed demand for adapting to different model size,
The tooling of plurality of specifications is made, the external dimensions of tooling is constant, is only adapted, changes from the geomery of different airvane rudderposts
It exchanges work the cylinder or frustum of a cone pore size at the center that fills, when carrying out the test of different model airvane, it is only necessary to using corresponding
Tooling installs tooling and airvane rudder core, is mounted on test table that the test can be started；
The middle position of test table is provided with the rectangular parallelepiped space of a tooling for installing clamping airvane rudderpost, ruler
The very little size of cuboid that constitutes when combining with two clamp assemblies is identical, sets respectively in the left and right sides of rectangular parallelepiped space
It is equipped with strip-shaped groove, is provided with vibration excitor in strip-shaped groove, for providing exciting force for airvane rudder core, vibration excitor can be with
Change the installation site in groove, to change the Position of Vibrating for being applied to airvane rudder core；
Further, guide rail is provided in two strip-shaped grooves, vibration excitor can slide on guide rail, after sliding into designated position
Locking and current location.
The surface of airvane rudder core is provided with foil gauge, foil gauge is mainly arranged in two, rudder core symmetrical pneumatic masterpieces
With surface, for detecting the strain value of rudder wicking surface, the electric signal of foil gauge by signal pickup assembly be transmitted to host computer into
Row Data Management Analysis；Meanwhile laser displacement sensor, laser displacement sensor are provided near the surface of airvane rudder core
For detecting the deformation situation of airvane rudder core during exciting, the electric signal of laser displacement sensor is filled also by signal acquisition
It sets and is transmitted to host computer progress Data Management Analysis, by strain value and shift value comprehensive analysis airvane rudder core in various excitings
Under the conditions of ess-strain situation and profile variation situation.
Airvane rudder core exciting test method includes:
(1) assembling of tooling constitutes a cuboid tooling, two clamp assemblies when two identical clamp assemblies are combined
A side have through slot composition with airvane rudderpost size exact matching cylinder or frustum of a cone hole, two clamping groups
Left and right two sides for the cuboid that part is constituted are respectively equipped with corresponding second counter sink in two positions, same side
Two the second countersunk head hole sites are symmetrical relative to the symmetrical centre of side, and 2 bolts pass through two symmetrically arranged ipsilaterals the
Two clamp assemblies are together in series by two counter sinks, and two clamp assemblies are fastened together by nut in the other end；
(2) rudderpost is provided below in the installation of airvane rudder core to be tested, airvane rudder core, and airvane rudderpost insertion tooling is erected
Histogram to cylinder or frustum of a cone hole in, be machined with an identical ruler on rudderpost position identical with tooling third counter sink height
Very little through-hole, the third counter sink and the hole on airvane rudderpost that studs passes through two clamp assemblies, airvane is led to
It crosses rudderpost to be fixed in tooling, the both ends of studs are fastened by nut；
(3) tooling is placed in the rectangular parallelepiped space of middle position setting of test table, two clamp assemblies combine institute's structure
At the angle of upper surface four of cuboid be respectively equipped with the first counter sink, 4 bolts are by the first counter sink by tooling and test
Workbench is fixedly connected, and so far completes the clamping installment work of airvane rudder core；
(4) foil gauge is set on the surface of airvane rudder core, for detecting the strain value of rudder wicking surface, foil gauge and signal acquisition
Device connection, signal pickup assembly are connected with host computer；Laser displacement sensor is set near the surface of airvane rudder core,
Laser displacement sensor is connected with signal pickup assembly, and signal pickup assembly is connected with host computer；
(5) the vibration excitor position in two strip-shaped groove of test table is adjusted, rear latched position is adjusted and starts to test；
(6) strain value and shift value for acquiring airvane rudder core under the conditions of various excitings, pass through strain value and comprehensive point of shift value
Analyse airvane rudder core ess-strain situation and profile variation situation under the conditions of various excitings；
(7) after completing a model airvane rudder core exciter test, the difference of replacement different model airvane rudder core can be passed through
Tooling repeats the above steps (1)-(5), can carry out the test of other model airvane rudder cores.
The invention has the advantages that
(1) it solves the design analysis of previous airvane rudder core and there was only theory analysis value, the problem of without actual tests data supporting
(2) test device design rationally, is adapted to the airvane rudder core test of a variety of different models, is not required to complicated mechanical knot
Structure design is only the clamping for realizing different model by changing a tooling, greatly improves working efficiency.
Detailed description of the invention
Fig. 1 show the rudder core crab, rudder core covering and the rudder core with rudderpost of airvane
Fig. 2 show airvane rudder core exciting test device of the invention
1, test table, 11, rectangular parallelepiped space, 12, vibration excitor, 13, strip-shaped groove, 2, tooling, 21, cylinder or the frustum of a cone
Hole, 22, third counter sink, 23, studs, the 24, second counter sink, the 25, first counter sink, 26, clamp assemblies, 3, airvane
Rudder core, 31, through-hole, 32, rudder core crab, 33, rudder core covering, 34, rudderpost.
Specific embodiment
The present invention is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining the present invention rather than limiting the invention.It is further to note that for the ease of
Description, only the parts related to the present invention are shown in attached drawing and it is not all.
Embodiment one
Fig. 1 is the rudder core crab 32 of airvane, rudder core covering 33 and the rudder core with rudderpost 34.Fig. 2 is airvane of the invention
Rudder core exciting test device.
The present invention takes following technological means to realize:
Airvane rudder core exciting test device includes: test table 1 and the tooling 2 for entraining air rudder rudderpost 34, tooling 2
It is made of two completely identical in structure clamp assemblies, 26, studs 23 and 6 bolts, clamp assemblies 26 are at one
Side has the rectangular parallelepiped structure of through slot, and a cuboid, two clampings are constituted when two clamp assemblies 26 are combined
Two through slots that 26 side of component is had are combined into the cylinder or the frustum of a cone of one with the exact matching of airvane rudderpost size
Hole 21(rudderpost 34 may be cylinder or truncated cone shape), the through slot of two clamp assemblies 26 it is combined at cylinder or circular cone
The axis in platform hole 21 is vertical with test table, and two clamp assemblies 26 combine the angle of upper surface four point of constituted cuboid
Not She You 25,4 bolts of the first counter sink tooling 2 is fixedly connected with test table 1 by the first counter sink 25, two press from both sides
Left and right two sides for holding the cuboid that component 26 is constituted are respectively equipped with corresponding second counter sink 24 in two positions, together
Two 24 positions of the second counter sink of one side are symmetrical relative to the symmetrical centre of side, and 2 bolts pass through two and are symmetrical arranged
The second counter sink of side 24, two clamp assemblies 26 are fastenedly connected by nut in the other end, two 26 institutes of clamp assemblies
The center of the left and right side of the cuboid of composition is provided with a third counter sink 22, and third counter sink 22 is for studs
23 pass through；
Rudderpost 34, rudderpost 34 and rudder core is provided below by being welded together, in rudderpost 34 and tooling in airvane rudder core 3
2 third counter sink, 22 height processes a through-hole 31 on identical position, and airvane rudderpost 34 is inserted into entraining air rudder rudderpost 34
Tooling 2, the lower surface of airvane rudder core falls on the upper surface of tooling, through-hole 31 and two clamp assemblies 26 on rudderpost 34
22 position of third counter sink of the center setting of the left and right side of the cuboid constituted is corresponding, and aperture is identical；It is double
Header stud 26 passes through two clamp assemblies 26 and airvane rudderpost 34, and airvane is fixed in tooling 2 by rudderpost 34, double
The both ends of header stud 26 are fastened by nut, and the interlude of studs 26 is identical as the size of 34 through-hole 31 of rudderpost；
Tooling is the cuboid constituted when two clamp assemblies 26 are combined, is needed to adapt to the fixed of different model size
It asks, makes the tooling 2 of plurality of specifications, the external dimensions of tooling 2 is constant, only the geomery phase from different airvane rudderposts 34
It adapts to, changes 21 size of cylinder or frustum of a cone hole at 2 center of tooling；When carrying out the test of different model airvane, it is only necessary to use
Corresponding tooling 2 installs tooling 2 and airvane rudder core, is mounted on test table 1 that the test can be started；
The middle position of test table 1 is provided with the rectangular parallelepiped space of a tooling 2 for installing clamping airvane rudderpost 34
11, the composition size of cuboid is identical when size is combined with two clamp assemblies 26, on a left side for rectangular parallelepiped space 11
Right two sides are respectively arranged with strip-shaped groove 13, and vibration excitor 12 is provided in strip-shaped groove 13, for mentioning for airvane rudder core
For exciting force, vibration excitor 12 can change the installation site in strip-shaped groove 13, be applied to airvane rudder core to change
Position of Vibrating；
Further, guide rail is provided in two strip-shaped grooves, vibration excitor 12 can slide on guide rail, slide into designated position
Locking and current location afterwards.
The surface of airvane rudder core is provided with foil gauge, foil gauge is mainly arranged in two, rudder core symmetrical pneumatic masterpieces
With surface, for detecting the strain value of rudder wicking surface, the electric signal of foil gauge by signal pickup assembly be transmitted to host computer into
Row Data Management Analysis；Meanwhile laser displacement sensor, laser displacement sensor are provided near the surface of airvane rudder core
For detecting the deformation situation of airvane rudder core during exciting, the electric signal of laser displacement sensor is filled also by signal acquisition
It sets and is transmitted to host computer progress Data Management Analysis, by strain value and shift value comprehensive analysis airvane rudder core in various excitings
Under the conditions of ess-strain situation and profile variation situation.
Airvane rudder core exciting test method includes:
(1) assembling of tooling 2 constitutes a cuboid tooling 2, two clampings when two identical clamp assemblies 26 are combined
Cylinder or frustum of a cone hole 21 of the through slot composition that one side of component 26 has with the exact matching of 34 size of airvane rudderpost,
Left and right two sides for the cuboid that two clamp assemblies 26 are constituted are respectively equipped with corresponding second counter sink in two positions
24, two 24 positions of the second counter sink of same side are symmetrical relative to the symmetrical centre of side, and 2 bolts pass through two symmetrically
The second counter sink of ipsilateral 24 of setting, two clamp assemblies 26 are together in series, and are clamped two by nut in the other end
Component 26 is fastened together；
(2) rudderpost 34 is provided below in the installation of airvane rudder core to be tested, airvane rudder core, and airvane rudderpost 34 is inserted into work
It fills in the cylinder or frustum of a cone hole 21 of 2 vertical directions, adds on rudderpost 34 and the identical position of 2 third counter sink of tooling, 22 height
Work has the through-hole 31 of an identical size, and studs 23 passes through the third counter sink 22 and airvane rudder of two clamp assemblies 26
Airvane rudder core is fixed in tooling 2 by the through-hole 31 on axis 34 by rudderpost 34, and the both ends of studs 23 are tight by nut
Gu；
(3) tooling 2 is placed in the rectangular parallelepiped space 11 of middle position setting of test table 1, two 26 groups of clamp assemblies
The angle of upper surface four of the constituted cuboid of conjunction is respectively equipped with 25,4 bolts of the first counter sink will by the first counter sink 25
Tooling 2 is fixedly connected with test table 1, so far completes the clamping installment work of airvane rudder core；
(4) foil gauge is set on the surface of airvane rudder core, for detecting the strain value of rudder wicking surface, foil gauge and signal acquisition
Device connection, signal pickup assembly are connected with host computer；Laser displacement sensor is set near the surface of airvane rudder core,
Laser displacement sensor is connected with signal pickup assembly, and signal pickup assembly is connected with host computer；
(5) 12 position of vibration excitor in two strip-shaped groove of test table is adjusted, rear latched position is adjusted and starts to test；
(6) strain value and shift value for acquiring airvane rudder core under the conditions of various excitings, pass through strain value and comprehensive point of shift value
Analyse airvane rudder core ess-strain situation and profile variation situation under the conditions of various excitings；
(7) after completing a model airvane rudder core exciter test, the difference of replacement different model airvane rudder core can be passed through
Tooling repeats the above steps (1)-(5), can carry out the test of other model airvane rudder cores.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, although referring to aforementioned reality
Applying example, invention is explained in detail, to those skilled in the art, still can be to foregoing embodiments
Documented technical solution improves or equivalent replacement of some of the technical features.It is all in spirit of the invention
Within principle, made any modification, equivalent replacement be should all be included in the protection scope of the present invention.
Claims (3)
1. a kind of airvane rudder core exciting test device, it is characterised in that: including test table and be used for entraining air rudder rudder
The tooling of axis, tooling are made of two completely identical in structure clamp assemblies, a studs and 6 bolts, clamp assemblies
For the rectangular parallelepiped structure for having through slot a side, one cuboid of composition when two clamp assemblies are combined, two
Two through slots that a clamp assemblies side is had are combined into the cylinder or circle of one with the exact matching of airvane rudderpost size
Cone machine hole, the through slots of two clamp assemblies it is combined at cylinder or the frustum of a cone axis it is vertical with test table, two
The angle of upper surface four that clamp assemblies combine constituted cuboid is respectively equipped with the first counter sink, and 4 bolts are heavy by first
Tooling is fixedly connected by head bore with test table, the left and right two sides difference for the cuboid that two clamp assemblies are constituted
If there are two corresponding second counter sink in position, two the second countersunk head hole sites of same side relative to side it is symmetrical in
The heart is symmetrical, and 2 bolts pass through two symmetrically arranged the second counter sinks of side, passes through nut for two clamp assemblies in the other end
It being fastenedly connected, the center of the left and right side for the cuboid that two clamp assemblies are constituted is provided with a third counter sink, the
Three counter sinks are passed through for studs；
Rudderpost, rudderpost and rudder core is provided below by being welded together in airvane rudder core, sinks in rudderpost and tooling third
Head bore height processes a through-hole on identical position, by the tooling of airvane rudderpost insertion entraining air rudder rudderpost, airvane rudder
The lower surface of core is fallen on the upper surface of tooling, the cuboid that the through-hole on rudderpost and two clamp assemblies are constituted it is left and right
The third countersunk head hole site of the center setting of side is corresponding, and aperture is identical；Studs passes through two clamp assemblies
And airvane rudderpost, airvane is fixed in tooling by rudderpost, the both ends of studs are fastened by nut, double end spiral shell
The interlude diameter of column is identical as the diameter of rudderpost through-hole；
The middle position of test table is provided with the rectangular parallelepiped space of a tooling for disposing entraining air rudder rudderpost, ruler
The very little size of cuboid that constitutes when combining with two clamp assemblies is identical, sets respectively in the left and right sides of rectangular parallelepiped space
It is equipped with strip-shaped groove, is provided with vibration excitor in strip-shaped groove, for providing exciting force for airvane rudder core；
The surface of airvane rudder core is provided with foil gauge, foil gauge is arranged in two, rudder core symmetrical Aerodynamic force action surfaces,
For detecting the strain value of rudder wicking surface, the electric signal of foil gauge is transmitted to host computer by signal pickup assembly and carries out at data
Reason analysis；Laser displacement sensor is provided near the surface of airvane rudder core, laser displacement sensor is for detecting exciting
The deformation situation of airvane rudder core in the process, the electric signal of laser displacement sensor are transmitted to upper also by signal pickup assembly
Machine carries out Data Management Analysis, and by strain value and shift value comprehensive analysis airvane rudder core, stress under the conditions of various excitings is answered
Become situation and profile variation situation.
2. airvane rudder core exciting test device as described in claim 1, which is characterized in that vibration excitor can change in strip
Installation site in connected in star, to change the Position of Vibrating for being applied to airvane rudder core.
3. airvane rudder core exciting test device as claimed in claim 2, which is characterized in that be provided in two strip-shaped grooves
Guide rail, vibration excitor can slide on guide rail, lock onto current location after sliding into designated position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811099685.4A CN108982041B (en) | 2018-09-20 | 2018-09-20 | Air rudder core excitation testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811099685.4A CN108982041B (en) | 2018-09-20 | 2018-09-20 | Air rudder core excitation testing device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108982041A true CN108982041A (en) | 2018-12-11 |
| CN108982041B CN108982041B (en) | 2020-04-24 |
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ID=64546426
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811099685.4A Active CN108982041B (en) | 2018-09-20 | 2018-09-20 | Air rudder core excitation testing device |
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| CN (1) | CN108982041B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114011665A (en) * | 2021-11-09 | 2022-02-08 | 山西钢科碳材料有限公司 | Clamp for air rudder |
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|---|---|---|---|---|
| JP2000241144A (en) * | 1999-02-22 | 2000-09-08 | Alps Electric Co Ltd | Rudder angle sensor unit |
| CN107243832A (en) * | 2017-07-06 | 2017-10-13 | 南华大学 | Airvane grinding automatic clamping fixture |
| 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 |
| CN108168812A (en) * | 2017-12-12 | 2018-06-15 | 北京自动化控制设备研究所 | A kind of steering gear flat vibration loading combination unit |
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2018
- 2018-09-20 CN CN201811099685.4A patent/CN108982041B/en active Active
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|---|---|---|---|---|
| JP2000241144A (en) * | 1999-02-22 | 2000-09-08 | Alps Electric Co Ltd | Rudder angle sensor unit |
| CN107243832A (en) * | 2017-07-06 | 2017-10-13 | 南华大学 | Airvane grinding automatic clamping fixture |
| 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 |
| CN108168812A (en) * | 2017-12-12 | 2018-06-15 | 北京自动化控制设备研究所 | A kind of steering gear flat vibration loading combination unit |
Non-Patent Citations (1)
| Title |
|---|
| 范文洋: "空气舵系统频响特性分析及试验研究", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114011665A (en) * | 2021-11-09 | 2022-02-08 | 山西钢科碳材料有限公司 | Clamp for air rudder |
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| CN108982041B (en) | 2020-04-24 |
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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 |
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