CN110361187A - A kind of flexible structure test pneumatic load test device - Google Patents
A kind of flexible structure test pneumatic load test device Download PDFInfo
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- CN110361187A CN110361187A CN201910774793.5A CN201910774793A CN110361187A CN 110361187 A CN110361187 A CN 110361187A CN 201910774793 A CN201910774793 A CN 201910774793A CN 110361187 A CN110361187 A CN 110361187A
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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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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
- G01M3/32—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors for containers, e.g. radiators
- G01M3/3281—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors for containers, e.g. radiators removably mounted in a test cell
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Abstract
The invention discloses a kind of flexible structures to test pneumatic load test device, including main body rack, an opposed middle side part is connected with servo electric cylinders vertically at the top and bottom of the main body rack, the two sides of the bottom of the main body rack are respectively connected with servo electric cylinders, and are inclined to set inwardly at the top of the servo electric cylinders of two sides of the bottom.By the circumferentially stripping and slicing of aerostatics hull, and experimental rig is included in stripping and slicing and carries out load test, by controlling servo electric cylinders in experimental rig, and then simulate aerostatics hull institute in the sky locating for complex environment, meet test requirements document, loading result is made more to be distributed actual conditions close to aerodynamic loading.By the contracting of aerostatics hull than simultaneously stripping and slicing, load test is carried out to representative stripping and slicing, substantially saves space, short form test platform structure.User's brief note and flexible supporting plate are used as test fixture, and uniform load is made to be distributed in testpieces surface, and tally with the actual situation middle aerodynamic loading distribution form, and test accuracy is high.
Description
Technical field
The present invention relates to a kind of experimental rigs, and in particular to a kind of flexible structure test pneumatic load test device belongs to
Floating air bag leak detection application field.
Background technique
Aerostatics generally refers to aircraft that specific gravity is lighter than air, going up to the air by atmospheric buoyancy force.In electronics and the military people
With field, fire balloon is not drawn within the scope of aerostatics generally.In addition, space dirigible not necessarily relies on buoyancy.Other than military,
Large-scale civilian aerostatics can be also used for traffic, transport, entertain, relieves the people in stricken areas, movies-making, scientific experiment etc..Aerostatics is general
Captive balloon and dirigible can be divided into.The typically no dynamical system of captive balloon, by tether cable and ground installation or website
It is connected；Dirigible is dynamic, can under remote control or automatic control autonomous flight.According to structure, dirigible can be divided into blimp, hard
Formula dirigible and mixed structure dirigible.According to flying height, dirigible can be divided into general dirigible, stratospheric airship, Near Space Airship and
Space dirigible.
Floating air bag needs to detect it during fabrication, its quality is made to reach the standard used, will not be in use
It leaks, common aerodynamic loading load detects it.Currently, common aerodynamic loading load test is mainly that full machine is quiet
Power test, loads to object Integral synchronous is loaded.But this loading method occupied space is very big, load step is numerous
Trivial, loading structure is complicated, and flexible structure aerostatics is loaded ineffective.
Summary of the invention
The purpose of the present invention is to provide a kind of flexible structures to test pneumatic load test device, can solve existing gas
Dynamic loading load test is mainly full machine slow test, is loaded to object Integral synchronous is loaded.But this load side
Method occupied space is very big, and load step is cumbersome, and loading structure is complicated, and flexible structure aerostatics is loaded ineffective
Technical problem.
The purpose of the present invention can be achieved through the following technical solutions:
A kind of flexible structure test pneumatic load test device, including main body rack, the main body rack top and bottom
An opposed middle side part is connected with servo electric cylinders vertically, and the two sides of the bottom of the main body rack are respectively connected with servo electric cylinders,
And it is inclined to set inwardly at the top of the servo electric cylinders of two sides of the bottom.
The inside of the main body rack is equipped with testpieces, and the bottom of the testpieces is connected with three groups of flexibility supporting plates, bottom
The servo electric cylinders in portion and the top of two sides servo electric cylinders are connect with flexible supporting plate, and the flexible supporting plate and servo electric cylinders it
Between tensile stress sensor is installed, the outside of the testpieces is equipped with several foil gauges.
Several herringbone items are connected at the top of the testpieces, the bottom of top servo electric cylinders passes through rope connection second
The middle part of homogeneous stick, and the both ends bottom of the second homogeneous stick passes through rope and is connected with the first homogeneous stick, and rope is connected to
Herringbone item of the bottom of the middle part of one homogeneous stick, the first homogeneous stick and the second homogeneous stick by rope connection below.
Preferably, the two sides of the bottom of the main body rack are welded with frame, and the servo electric cylinders bottom of two sides passes through bolt
The top of connection framework.
Preferably, the bottom of the testpieces is connected with three blocks of flexible supporting plates, and the bottom of three blocks of flexible supporting plates and testpieces
The cementing fixation in portion, and the lower half to be arranged in testpieces in a manner of 60 °.
Preferably, the both ends of the tensile stress sensor pass through screw thread and connect with flexible supporting plate and servo electric cylinders, and on
Main body rack is bolted in the bottom of lower both ends servo electric cylinders.
Preferably, the tensile stress sensor is electrically connected data acquisition module, and foil gauge is electrically connected static resistance and answers
Become instrument.
Preferably, the upper half of the testpieces is cementing five groups of herringbone items, herringbone item by two long 260mm, wide 5mm's
Thick cloth is relatively viscous and forms, and herringbone item is provided with three pieces of radiuses in the viscous region with together in top as the fixation hole of 5mm, and five
Group herringbone item is uniformly fixed on testpieces in a manner of being separated by 25 °.
Preferably, at the top of the testpieces middle-end herringbone item, connect the bottom of the second homogeneous stick by three ropes, two
The herringbone item of side passes through three ropes and connects the first homogeneous stick, and the bottom of rope is connected to the inside of fixation hole, and rope is in
It is vertically arranged.
The specific steps that the pneumatic load test device uses include:
Step 1: aerostatics hull is scaled, and the model of diminution is circumferentially subjected to stripping and slicing, the ring-type being cut into
As testpieces, testpieces is placed on to the inside of main body rack, and 100 foil gauges are installed in the external of testpieces, is being tested
The upper half of part connects 5 groups of herringbone items, and herringbone item connects the homogeneous stick on top by rope；And it is installed in the lower half of testpieces
Three groups of flexibility supporting plates, and the servo electric cylinders of flexible supporting plate and lower section are connected；
Step 2: the flexible stroke by controlling servo electric cylinders, the data 0 for acquiring the tensile stress sensor on top,
The quality for offsetting testpieces influences；The servo electric cylinders for controlling top again are shunk upwards, and testpieces is pulled to move up, and then outward
Deformation, the testpieces upper half is in tensional state at this time, completes the tensile load load test to it；
Step 3: the flexible stroke of control servo electric cylinders, the data 0 for acquiring the tensile stress sensor of bottom are offset
Influence of the gravity to testpieces lower half；The servo electric cylinders of control bottom move upwards, and the lower half of testpieces is pushed inwardly to become
Shape, the lower half of testpieces is in compressive state at this time, completes the compressive load load test to it；The servo of bottom is controlled again
Electric cylinders retracted downward pulls testpieces lower half to deform outward, and testpieces lower half be in tensional state at this time, completion to its
Tensile load load test；
Step 4: the flexible structure strain data that the load of flexible structure aerodynamic loading obtains is received by information acquisition system
Collection；Dependent variable is acquired by foil gauge, is summarized to static resistance deformeter, imports computer via serial ports；Load capacity passes through
The acquisition of tensile stress sensor summarizes to digital collection module, imports computer via serial ports.
Beneficial effects of the present invention:
1, by moving back and forth servo electric cylinders are flexible, testpieces is driven to stretch and compression, reach load tensile load with
The purpose of compressive load.The stroke that can be controlled separately each servo electric cylinders in test, applies different load to testpieces, very
The distribution of circumferential aerodynamic loading under the real simulation each operating condition of aerostatics.Herringbone item is connect with homogeneous stick by rope and tensile stress passes
Sensor applies load to the testpieces upper half using servo electric cylinders.The load applied by tensile stress sensor measurement, according to
The stroke of the load adjustment servo electric cylinders of measurement, to achieve the purpose that Simulated Aerodynamic Loads load.
2, the flexible structure strain data that the load of flexible structure aerodynamic loading obtains is collected by information acquisition system.Strain
Amount is acquired by foil gauge, is summarized to static resistance deformeter, imports computer via serial ports.Load capacity is passed by tensile stress
Sensor acquisition summarizes to digital collection module, imports computer via serial ports.The processing of data is completed by computer.Tensile stress
Sensor and the data summarization of foil gauge acquisition import computer, and computer carries out summary record to data first, facilitates subsequent
Data preparation.Again with the reciprocating stroke that data are according to feedback regulation servo electric cylinders, precision and the test behaviour of test data are improved
The degree of automation of work.
3, by the circumferentially stripping and slicing of aerostatics hull, and experimental rig is included in stripping and slicing and carries out load test, by test
Servo electric cylinders are controlled in device, so simulate aerostatics hull locating complex environment in the sky, meet test and want
It asks, loading result is made more to be distributed actual conditions close to aerodynamic loading.By the contracting of aerostatics hull than simultaneously stripping and slicing, to representative stripping and slicing
Load test is carried out, space, short form test platform structure are substantially saved.User's brief note and flexible supporting plate are used as test fixture, make
Uniform load is distributed in testpieces surface, and tally with the actual situation middle aerodynamic loading distribution form, and test accuracy is high.Use servo electricity
Cylinder, which moves back and forth, provides power, easy to operate, low in cost, is easy installation, simple for structure.It is arranged on testpieces surface and strains
Piece is arranged pull pressure sensor in servo electric cylinders and fixture junction, servo electric cylinders row is further controlled according to sensor signal
Journey realizes test procedure automation, further increases test accuracy to control the load being applied on testpieces.
Detailed description of the invention
In order to facilitate the understanding of those skilled in the art, the present invention will be further described below with reference to the drawings.
Fig. 1 is overall structure of the present invention.
Fig. 2 is the isometric structural schematic diagram of invention figure 1.
Fig. 3 is invention servo electric cylinders and frame mounting structure schematic diagram.
Fig. 4 is details enlarged structure schematic diagram at A in invention figure 3.
Fig. 5 is the main view of invention figure 1.
Fig. 6 is invention foil gauge and static resistance deformeter attachment structure schematic diagram.
In figure: 1, main body rack；2, flexible supporting plate；3, servo electric cylinders；4, testpieces；5, herringbone item；6, rope；7, first
Homogeneous stick；8, the second homogeneous stick；9, tensile stress sensor；10, foil gauge；11, static resistance deformeter；12, data acquisition module
Block；13, frame；14, fixation hole.
Specific embodiment
Technical solution of the present invention is clearly and completely described below in conjunction with embodiment, it is clear that described reality
Applying example is only a part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, this field is general
Logical technical staff all other embodiment obtained without creative efforts belongs to what the present invention protected
Range.
It please refers to shown in Fig. 1-6, a kind of flexible structure test pneumatic load test device, including main body rack 1, main body branch
The 1 opposed middle side part in top and bottom of frame is connected with servo electric cylinders 3 vertically, and the two sides of the bottom of main body rack 1 are all connected with
There are servo electric cylinders 3, and 3 top of servo electric cylinders of two sides of the bottom is inclined to set inwardly；
The inside of main body rack 1 is equipped with testpieces 4, and the bottom of testpieces 4 is connected with three groups of flexibility supporting plates 2, bottom
The top of servo electric cylinders 3 and two sides servo electric cylinders 3 is connect with flexible supporting plate 2, and between flexible supporting plate 2 and servo electric cylinders 3
Tensile stress sensor 9 is installed, the outside of testpieces 4 is equipped with several foil gauges 10；
The top of testpieces 4 is connected with several herringbone items 5, and the bottom of top servo electric cylinders 3 passes through the connection of rope 6 second
The middle part of homogeneous stick 8, and the both ends bottom of the second homogeneous stick 8 passes through rope 6 and is connected with the first homogeneous stick 7, and rope 6 connects
At the middle part of the first homogeneous stick 7, the bottom of the first homogeneous stick 7 and the second homogeneous stick 8 passes through the herringbone of the connection of rope 6 below
Item 5.
The two sides of the bottom of main body rack 1 are welded with frame 13, and frame is bolted in 3 bottom of servo electric cylinders of two sides
13 top, bolt facilitate servo electric cylinders 3 to be connected and fixed with frame 13.
The bottom of testpieces 4 is connected with three blocks of flexible supporting plates 2, and three blocks of flexible supporting plates 2 and the bottom of testpieces 4 are cementing solid
Determine, and be arranged in the lower half of testpieces 4 in a manner of apart 60 °, three blocks of flexible supporting plates 2 can carry out testpieces 4 stable
Support, so that the uniform force in testing of testpieces 4.
The both ends of tensile stress sensor 9 pass through screw thread and connect with flexible supporting plate 2 and servo electric cylinders 3, and upper and lower ends are watched
Main body rack 1 is bolted in the bottom for taking electric cylinders 3, and tensile stress sensor 9 is capable of measuring the load in test.
Tensile stress sensor 9 is electrically connected data acquisition module 12, and foil gauge 10 is electrically connected static resistance deformeter 11,
Dependent variable is acquired by foil gauge 10, is summarized to static resistance deformeter 11, imports computer via serial ports.Load capacity passes through
The acquisition of tensile stress sensor 9 summarizes to digital collection module 12, imports computer via serial ports.
The upper half of testpieces 4 is cementing five groups of herringbone items 5, and herringbone item 5 is by two long 260mm, the thick cloth phase of wide 5mm
To gluing and forming, herringbone item 5 is provided with the fixation hole 14 that three pieces of radiuses are 5mm, five groups of people in the viscous region together in top
Brief note 5 is uniformly fixed on testpieces 4 in a manner of being separated by 25 °, and herringbone item 5 both facilitates on top to be fixedly connected with testpieces 4,
It can conveniently be connect again by rope 6 with the homogeneous stick on top.
The herringbone item 5 of 4 top middle-end of testpieces connects the bottom of the second homogeneous stick 8, the people of two sides by three ropes 6
Brief note 5 connects the first homogeneous stick 7 by three ropes 6, and the bottom of rope 6 is connected to the inside of fixation hole 14, and rope 6 is in
It is vertically arranged.It is more accurate in measurement so that the homogeneous stick uniform force on top.
The specific steps that the pneumatic load test device uses include:
Step 1: aerostatics hull is scaled, and the model of diminution is circumferentially subjected to stripping and slicing, the ring-type being cut into
As testpieces 4, testpieces 4 is placed on to the inside of main body rack 1, and 100 foil gauges 10 are installed in the external of testpieces 4,
5 groups of herringbone items 5 are connected in the upper half of testpieces 4, herringbone item 5 connects the homogeneous stick on top by rope 6；And in testpieces 4
Lower half three groups of flexibility supporting plates 2 are installed, and flexible supporting plate 2 is connect with the servo electric cylinders 3 of lower section；
Step 2: the flexible stroke by controlling servo electric cylinders 3, the data for acquiring the tensile stress sensor 9 on top
0, the quality for offsetting testpieces 4 influences；The servo electric cylinders 3 for controlling top again are shunk upwards, and testpieces 4 is pulled to move up, into
And deform outward, 4 upper half of testpieces is in tensional state at this time, completes the tensile load load test to it；
Step 3: the flexible stroke of control servo electric cylinders 3, the data 0 for acquiring the tensile stress sensor 9 of bottom are supported
Disappear influence of the gravity to 4 lower half of testpieces；Control bottom servo electric cylinders 3 move upwards, push testpieces 4 lower half to
Interior deformation, the lower half of testpieces 4 is in compressive state at this time, completes the compressive load load test to it；Bottom is controlled again
3 retracted downward of servo electric cylinders, pull 4 lower half of testpieces deform outward, 4 lower half of testpieces is in tensional state at this time,
Complete the tensile load load test to it；
Step 4: the flexible structure strain data that the load of flexible structure aerodynamic loading obtains is received by information acquisition system
Collection；Dependent variable is acquired by foil gauge 10, is summarized to static resistance deformeter 11, imports computer via serial ports；Load capacity
Summarized by the acquisition of tensile stress sensor 9 to digital collection module 12, imports computer via serial ports.
It is moved back and forth in the use of the present invention, servo electric cylinders 3 are flexible, drives the stretching of testpieces 4 and compression, reached load and draw
Stretch the purpose of load and compressive load.The stroke that can be controlled separately each servo electric cylinders 3 in test applies not testpieces 4
With load, the distribution of circumferential aerodynamic loading under each operating condition of real simulation aerostatics.Herringbone is connect with homogeneous stick by rope 6
Item 5 and tensile stress sensor 9 apply load to 4 upper half of testpieces using servo electric cylinders 3.It is measured by tensile stress sensor 9
The load applied, the stroke of servo electric cylinders 3 is adjusted according to the load of measurement, to reach the mesh of Simulated Aerodynamic Loads load
's.
By controlling the flexible stroke of servo electric cylinders 3, the data 0 for acquiring the tensile stress sensor 9 on top offset examination
The quality for testing part 4 influences.The servo electric cylinders 3 for controlling top again are shunk upwards, pull testpieces 4 to move up, and then become outward
Shape, 4 upper half of testpieces is in tensional state at this time, completes to load its tensile load.
The flexible stroke of servo electric cylinders 3 is controlled, the data 0 for acquiring the tensile stress sensor 9 of bottom offset gravity pair
The influence of 4 lower half of testpieces.The servo electric cylinders 3 of control bottom move upwards, and the lower half of testpieces 4 is pushed to be deformed inward,
The lower half of testpieces 4 is in compressive state at this time, completes to load its compressive load.Control bottom servo electric cylinders 3 to
Lower contraction pulls 4 lower half of testpieces to deform outward, and 4 lower half of testpieces is in tensional state at this time, completes the stretching to it
Load load.
The flexible structure strain data that the load of flexible structure aerodynamic loading obtains is collected by information acquisition system.Foil gauge
10 are bonded in the outside of testpieces, and dependent variable is acquired by model BX120-3AA resistance strain plate 10, summarized to model
After the static resistance deformeter 11 of AFT-CM-10, computer is imported via serial ports.Load capacity passes through the drawing of model DYMH-103
The acquisition of strain gauge 9 summarizes to the digital collection module 12 of model I-7017, imports computer via serial ports.Pass through calculating
The processing of machine completion data.The data summarization that tensile stress sensor 9 and foil gauge 10 acquire imports computer, and computer is right first
Data carry out summary record, and follow-up data is facilitated to arrange.It is again the reciprocating stroke of foundation feedback regulation servo electric cylinders 3 with data,
Improve the precision of test data and the degree of automation of test operation.Computer passes through control matched with digital collection module 12
System summarizes data from serial acquisition, is recorded in control system；Servo electricity is adjusted according to the data that tensile stress sensor 9 is fed back
The stroke of cylinder 2, the value for feeding back tensile stress sensor 9 are equal with the load that requirement of experiment applies.
Present invention disclosed above preferred embodiment is only intended to help to illustrate the present invention.There is no detailed for preferred embodiment
All details are described, are not limited the invention to the specific embodiments described.Obviously, according to the content of this specification,
It can make many modifications and variations.These embodiments are chosen and specifically described to this specification, is in order to better explain the present invention
Principle and practical application, so that skilled artisan be enable to better understand and utilize the present invention.The present invention is only
It is limited by claims and its full scope and equivalent.
Claims (8)
1. a kind of flexible structure tests pneumatic load test device, which is characterized in that including main body rack (1), the main body branch
An opposed middle side part is connected with servo electric cylinders (3) vertically at the top and bottom of frame (1), the bottom of the main body rack (1)
Two sides are respectively connected with servo electric cylinders (3), and are inclined to set inwardly at the top of the servo electric cylinders (3) of two sides of the bottom；
The inside of the main body rack (1) is equipped with testpieces (4), and the bottom of the testpieces (4) is connected with three groups of flexibility supports
Plate (2), the servo electric cylinders (3) of bottom and the top of two sides servo electric cylinders (3) are connect with flexible supporting plate (2), and described soft
Tensile stress sensor (9) are installed between property supporting plate (2) and servo electric cylinders (3), the outside of the testpieces (4) is equipped with several
A foil gauge (10)；
Several herringbone items (5) are connected at the top of the testpieces (4), the bottom of top servo electric cylinders (3) passes through rope (6)
The middle part of the second homogeneous stick (8) is connected, and the both ends bottom of the second homogeneous stick (8) passes through rope (6) and is connected with the first homogeneous
Stick (7), and rope (6) is connected to the middle part of the first homogeneous stick (7), the bottom of the first homogeneous stick (7) and the second homogeneous stick (8)
Portion passes through the herringbone item (5) of rope (6) connection below.
2. a kind of flexible structure according to claim 1 tests pneumatic load test device, which is characterized in that the main body
The two sides of the bottom of bracket (1) are welded with frame (13), and frame (13) is bolted in servo electric cylinders (3) bottom of two sides
Top.
3. a kind of flexible structure according to claim 1 tests pneumatic load test device, which is characterized in that the test
The bottom of part (4) is connected with three pieces of flexible supporting plates (2), and the cementing fixation in bottom of three pieces of flexible supporting plates (2) and testpieces (4),
And the lower half of testpieces (4) is arranged in a manner of apart 60 °.
4. a kind of flexible structure according to claim 1 tests pneumatic load test device, which is characterized in that the drawing is answered
The both ends of force snesor (9) pass through screw thread and connect with flexible supporting plate (2) and servo electric cylinders (3), and upper and lower ends servo electric cylinders
(3) main body rack (1) is bolted in bottom.
5. a kind of flexible structure according to claim 1 tests pneumatic load test device, which is characterized in that the drawing is answered
Force snesor (9) is electrically connected data acquisition module (12), and foil gauge (10) is electrically connected static resistance deformeter (11).
6. a kind of flexible structure according to claim 1 tests pneumatic load test device, which is characterized in that the test
The upper half of part (4) is cementing five groups of herringbone items (5), herringbone item (5) by two long 260mm, the thick cloth of wide 5mm it is relatively viscous and
It forms, herringbone item (5) is provided with the fixation hole (14) that three pieces of radiuses are 5mm, five groups of herringbones in the viscous region together in top
Item (5) is uniformly fixed on testpieces (4) in a manner of being separated by 25 °.
7. a kind of flexible structure according to claim 1 tests pneumatic load test device, which is characterized in that the test
The herringbone item (5) of middle-end at the top of part (4), the bottom of the second homogeneous stick (8), the herringbone item of two sides are connected by three ropes (6)
(5) the first homogeneous stick (7) being connected by three ropes (6), the bottom of rope (6) is connected to the inside of fixation hole (14), and
Rope (6) is vertical setting.
8. a kind of flexible structure according to claim 1 tests pneumatic load test device, which is characterized in that the pneumatic load
The specific steps that lotus experimental rig uses include:
Step 1: aerostatics hull is scaled, and the model of diminution is circumferentially subjected to stripping and slicing, the ring-type being cut into becomes
Testpieces (4) is placed on the inside of main body rack (1), and installs 100 foil gauges in the external of testpieces (4) by testpieces (4)
(10), 5 groups of herringbone items (5) are connected in the upper half of testpieces (4), herringbone item (5) connects the homogeneous on top by rope (6)
Stick；And three groups of flexibility supporting plates (2) are installed in the lower half of testpieces (4), and by the servo electric cylinders of flexible supporting plate (2) and lower section
(3) it connects；
Step 2: the flexible stroke by controlling servo electric cylinders (3), the data for acquiring the tensile stress sensor (9) on top
0, the quality for offsetting testpieces (4) influences；The servo electric cylinders (3) for controlling top again are shunk upwards, pull testpieces (4) Xiang Shangyi
It is dynamic, and then deform outward, testpieces (4) upper half is in tensional state at this time, completes the tensile load load test to it；
Step 3: the flexible stroke of control servo electric cylinders (3), the data 0 for acquiring the tensile stress sensor (9) of bottom are supported
Disappear influence of the gravity to testpieces (4) lower half；The servo electric cylinders (3) of control bottom move upwards, and push under testpieces (4)
Half portion is deformed inward, and the lower half of testpieces (4) is in compressive state at this time, completes the compressive load load test to it；Again
Servo electric cylinders (3) retracted downward of bottom is controlled, pulls testpieces (4) lower half to deform outward, at this time testpieces (4) lower half
In tensional state, the tensile load load test to it is completed；
Step 4: the flexible structure strain data that the load of flexible structure aerodynamic loading obtains is collected by information acquisition system；It answers
Variable is acquired by foil gauge (10), is summarized to after static resistance deformeter (11), imports computer via serial ports；Load capacity is logical
It crosses tensile stress sensor (9) acquisition to summarize to digital collection module (12), imports computer via serial ports.
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| CN201910774793.5A CN110361187A (en) | 2019-08-21 | 2019-08-21 | A kind of flexible structure test pneumatic load test device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910774793.5A CN110361187A (en) | 2019-08-21 | 2019-08-21 | A kind of flexible structure test pneumatic load test device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112067332A (en) * | 2020-08-28 | 2020-12-11 | 合肥工业大学 | Experimental concentrated force loading test device of airship flexible structure |
| CN112326436A (en) * | 2020-10-29 | 2021-02-05 | 合肥工业大学 | Device and method for testing mechanical properties of inner curtain cloth assembly of airship |
| CN114166495A (en) * | 2021-12-03 | 2022-03-11 | 中国特种飞行器研究所 | Load slant follow-up loading device |
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Application publication date: 20191022 |