CN108760512A - A kind of air pressure static test system of aero-engine Middle casing support plate covering - Google Patents
A kind of air pressure static test system of aero-engine Middle casing support plate covering Download PDFInfo
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- CN108760512A CN108760512A CN201810237488.8A CN201810237488A CN108760512A CN 108760512 A CN108760512 A CN 108760512A CN 201810237488 A CN201810237488 A CN 201810237488A CN 108760512 A CN108760512 A CN 108760512A
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- main body
- middle casing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/10—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by pneumatic or hydraulic pressure
- G01N3/12—Pressure testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/003—Generation of the force
- G01N2203/0042—Pneumatic or hydraulic means
- G01N2203/0044—Pneumatic means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0075—Strain-stress relations or elastic constants
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/026—Specifications of the specimen
- G01N2203/0262—Shape of the specimen
- G01N2203/0278—Thin specimens
- G01N2203/0282—Two dimensional, e.g. tapes, webs, sheets, strips, disks or membranes
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0682—Spatial dimension, e.g. length, area, angle
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- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a kind of air pressure static test systems of aero-engine Middle casing support plate covering, including sealing box main body (6), Middle casing support plate skin product (14) is vertically fixedly installed in the sealing box main body (6)；The sealing box main body (6) is connected with the gas supply output end of an air pressure supply device；It is provided with pressure sensor (3) at the top of the sealing box main body (6)；The Middle casing support plate skin product (14) is pasted with foil gauge (7)；There are one displacement sensors (8) for the right side inner wall fixed setting of the sealing box main body (6)；Signal is connect between data collecting instrument (1) respectively for the foil gauge (7), displacement sensor (8) and pressure sensor (3).The present invention can measure the deformation displacement amount and strain data of aero-engine Middle casing support plate skin-surface, the structural strength for examining Middle casing support plate covering under defined gas pressure loads.
Description
Technical field
The present invention relates to experimental technique fields, more particularly to a kind of air pressure of aero-engine Middle casing support plate covering
Static test system.
Background technology
Currently, for aero-engine, aero-engine Middle casing is the important load-carrying construction of engine.It is sending out
In the operational process of motivation, Middle casing support plate covering can be acted on by gas pressure loads.Since Middle casing support plate covering is
The cavity body structure of thin-walled, when it is by larger pressure loading, it is possible that the phenomenon that unstability so that its structural strength without
Method meets the use demand of aero-engine.
The lightweight of product design is increasingly paid close attention in modern structure design, however the light-weight design of product is often brought
Structural strength cannot be satisfied the risk of requirement.In the design process of Middle casing support plate covering, equally exist such
Problem.Therefore, in the design process, it is necessary first to by the method for finite element analysis come its structural strength properties of preanalysis.
In order to ensure the reliability of the structural strength of Middle casing support plate covering used in aero-engine, centering is needed
Jie's casing support plate covering carries out corresponding structural strength test, measures it under defined gas pressure loads, the deformation of skin-surface
Displacement and strain data examine its structural strength properties, so as to allow people further by test data and finite element fraction
Analysis result is compared, and is modified to finite element model.
But there is presently no a kind of technologies, it can be to the deformation of aero-engine Middle casing support plate skin-surface
Displacement and strain data measure, the structural strength for examining Middle casing support plate covering, so as to ensure aviation
The reliability of the structural strength of Middle casing support plate covering used in engine.
Invention content
In view of this, the object of the present invention is to provide a kind of examinations of the air pressure static load of aero-engine Middle casing support plate covering
Check system, can be under defined gas pressure loads, to the deformation displacement amount of aero-engine Middle casing support plate skin-surface
And strain data measures, the structural strength for examining Middle casing support plate covering, so as to ensure aero-engine
The reliability of the structural strength of used Middle casing support plate covering is conducive to widely promote and apply, and has great life
Produce practice significance.
For this purpose, the present invention provides a kind of air pressure static test system of aero-engine Middle casing support plate covering, packet
Sealing box main body is included, Middle casing support plate skin product is vertically fixedly installed in the sealing box main body；
The sealing box main body is connected with the gas supply output end of an air pressure supply device, and the air pressure supply device is used
In providing compressed air for the seal box body interior；
There are one pressure sensors for the seal box body top setting；
There are one foil gauges for the Middle casing support plate skin product stickup；
The right side inner wall of the sealing box main body is fixedly installed there are one displacement sensor, institute's displacement sensors left end
Thimble withstands on the outer right wall of the Middle casing support plate skin product；
Signal is connect between a data collecting instrument respectively for the foil gauge, displacement sensor and pressure sensor.
Wherein, be respectively provided with upper end flange and lower end flange at the top and bottom of the sealing box main body, it is described on
End flange is sealed connected together with a sealing upper flange, and the lower end flange and a sealing lower flange are tightly connected
Together.
Wherein, there are one sealing rubber pad, the upper ends for setting between the upper end flange and the sealing upper flange
Portion's flange, sealing rubber pad and the sealing upper flange are bolted to connection together；
The sealing rubber pad there are one being also provided between the lower end flange and the sealing lower flange, the lower end
Portion's flange, sealing rubber pad and the lower flange are bolted to connection together.
Wherein, there is blow vent, on the venthole and the Middle casing support plate skin product on the sealing upper flange
The air inlet at end is connected by a tracheae.
Wherein, there are two vacuum sealing aerospace connectors for setting on the sealing upper flange；
The lower end of described two vacuum sealing aerospace connectors passes through signal with the foil gauge and displacement sensor respectively
Line is connected；
It is connected by signal wire between the upper end of described two vacuum sealing aerospace connectors and the data collecting instrument.
Wherein, there are one stationary fixtures for the bottom interior surface fixed setting of the sealing lower flange；
The Middle casing support plate skin product is fixedly connected at the top of the stationary fixture.
Wherein, the air pressure supply device includes at least one gas cylinder.
Wherein, the gas supply output end of the air pressure supply device passes through a pressure regulator valve and the seal box body interior phase
Connection.
Wherein, further include a pressure control unit, the pressure control unit respectively with data collecting instrument and pressure regulator valve
It is connected by signal wire, the sealing measured for reading the pressure sensor that the data collecting instrument is acquired, described in real time
Pressure value in box main body exports control signal to the pressure regulator valve, described in control then according to control instruction input by user
The pressure in the sealing box main body is adjusted in pressure regulator valve, as defined in the satisfaction until pressure loading.
By the above technical solution provided by the invention as it can be seen that compared with prior art, the present invention proposes a kind of aviation
The air pressure static test system of engine Middle casing support plate covering, can be under defined gas pressure loads, to aeroplane engine
The deformation displacement amount and strain data of machine Middle casing support plate skin-surface measure, for examining Middle casing support plate covering
Structural strength, so as to ensure the reliability of the structural strength of Middle casing support plate covering used in aero-engine,
Be conducive to widely promote and apply, be of great practical significance.
For a kind of air pressure static test system of aero-engine Middle casing support plate covering provided by the invention, lead to
The gas pressure loads experiment for realizing Middle casing support plate covering is crossed, product structure intensity is verified, can be the optimization of finite element model
Data supporting is provided.
Description of the drawings
Fig. 1 is a kind of air pressure static test system of aero-engine Middle casing support plate covering provided by the invention right
Connection status schematic diagram when Middle casing support plate skin product is tested；
Fig. 2 is a kind of bowing for air pressure static test system of aero-engine Middle casing support plate covering provided by the invention
View；
In figure, 1 is data collecting instrument, and 2 be vacuum sealing aerospace connectors, and 3 be pressure sensor, and 4 be sealing upper flange,
5 be sealing rubber pad, and 6 be sealing box main body, and 7 be foil gauge, and 8 be displacement sensor, and 9 be stationary fixture, and 10 be sealing laxative remedy
Orchid, 11 be pressure control unit, and 12 be pressure regulator valve, and 13 be air pressure supply device, and 14 be Middle casing support plate skin product.
Specific implementation mode
In order to enable those skilled in the art to better understand the solution of the present invention, below in conjunction with the accompanying drawings with embodiment to this
Invention is described in further detail.
Referring to Fig. 1, Fig. 2, a kind of air pressure static test of aero-engine Middle casing support plate covering provided by the invention
System can measure the deformation displacement amount and strain data of aero-engine Middle casing support plate skin-surface, use
In the structural strength of examination Middle casing support plate covering.The air pressure of aero-engine Middle casing support plate covering provided by the invention
Static test system specifically includes sealing box main body 6, test structure in need is vertically fixedly installed in the sealing box main body 6
The Middle casing support plate skin product 14 of intensity；
The sealing box main body 6 is connected with the gas supply output end of an air pressure supply device, the air pressure supply device
For to provide compressed air inside the sealing box main body 6；
There are one pressure sensors 3 for 6 top setting of the sealing box main body；
There are one foil gauges 7 for the stickup of Middle casing support plate skin product 14；
There are one displacement sensor 8, institute's displacement sensors 8 are left for the right side inner wall fixed setting of the sealing box main body 6
The outer right wall that the thimble at end withstands on the Middle casing support plate skin product 14 (is specially longitudinal interposition of outer right wall
It sets)；
The foil gauge 7, displacement sensor 8 and pressure sensor 3 carry out signal between a data collecting instrument 1 respectively
Connection.
It should be noted that in the present invention, the pressure sensor 3, for measuring the pressure in sealing box main body 6
Value.
In the present invention, the foil gauge 7 is to constitute element for measuring strain by sensitive grid etc., such as can be electricity
Foil gauge is hindered, the foil gauge 7 is for measuring the machinery that 14 surface of Middle casing support plate skin product generates under ordinance load
Deformation.Institute's displacement sensors 8, the normal generated under ordinance load for measuring 14 surface of Middle casing support plate skin product
The mechanically deform amount in direction.
It should be noted that the data collecting instrument 1, for acquiring and storing pressure sensor 3, foil gauge 7 and displacement
The measurement data of sensor 8.
In the present invention, in specific implementation, it is described sealing box main body 6 top and bottom be respectively provided with upper end flange and
Lower end flange, the upper end flange are sealed connected together with a sealing upper flange 4, the lower end flange and one
Sealing lower flange 10 is sealed connected together.
In specific implementation, sealing rubber pad 5 there are one settings between the upper end flange and the sealing upper flange 4,
The upper end flange, sealing rubber pad 5 and the sealing upper flange 4 are bolted to connection together.
In specific implementation, it is also provided between the lower end flange and the sealing lower flange 10 there are one the sealing rubber
Rubber cushion 5, the lower end flange, sealing rubber pad 5 and the lower flange 10 are bolted to connection together.
It should be noted that by the setting of sealing rubber pad 5, it can effectively prevent the sealing box main body 6 and occur
The problem of gas leakage.Therefore, the sealing box main body 6 is in sealing upper flange 4, sealing rubber pad 5 and the assembly for sealing lower flange 10
Under cooperation, the test space effectively sealed is may be constructed, to facilitate test under defined gas pressure loads, in aero-engine
The deformation displacement amount and strain data of Jie's casing support plate skin-surface.
In the present invention, in specific implementation, there is blow vent, the venthole and the intermediary on the sealing upper flange 4
The air inlet of 14 upper end of casing support plate skin product is connected by a tracheae.
It should be noted that the Middle casing support plate skin product 14 is the thin walled cavity structure of hollow sealing.
In the present invention, in specific implementation, vacuum sealing aerospace connectors 2 there are two settings on the sealing upper flange 4,
The vacuum sealing aerospace connectors 2 are signal transmitting apparatus；
The lower end of described two vacuum sealing aerospace connectors 2 passes through letter with the foil gauge 7 and displacement sensor 8 respectively
Number line is connected；
It is connected by signal wire between the upper end of described two vacuum sealing aerospace connectors 2 and the data collecting instrument 1
It connects.
It should be noted that the vacuum sealing aerospace connectors 2, for the foil gauge in box main body 67 and position will to be sealed
Displacement sensor 8 collected respectively, described Middle casing support plate skin product 14 strain signal and displacement signal be transferred to
The data collecting instrument 1, while the sealing performance for ensureing sealing box main body 6.
In specific implementation, the connecting terminal quantity used on the vacuum sealing aerospace connectors 2 can be according to testing requirement
It adjusts, meets the requirement of different TCH test channels.
In the present invention, in specific implementation, the bottom interior surface fixed setting of the sealing lower flange 10 (is specially spiral shell
Connect) there are one stationary fixtures 9；
The top of the stationary fixture 9 is fixedly connected with the Middle casing support plate skin product 14, especially by installation
Hole is spirally connected, so that the test mode of the Middle casing support plate skin product 14 keeps stablizing.
In the present invention, in specific implementation, the air pressure supply device 13 may include at least one gas cylinder, preferably high
High pressure dry nitrogen gas cylinder specifically may be used in air bottle.
In specific implementation, the gas supply output end of the air pressure supply device 13 passes through a pressure regulator valve 12 and the seal box
It is connected inside main body 6.
It should be noted that the gas cylinder is for providing stable high-pressure air source.The pressure regulator valve 12 is used for institute
It states after the hyperbar that pressure feedway 13 (such as gas cylinder) exports is automatically lowered to lower pressure and exports, that is, be used to adjust institute
The air pressure size that pressure feedway 13 (such as gas cylinder) exports is stated, is met under different gas pressure loads, in aero-engine
The demand that the deformation displacement amount and strain data of Jie's casing support plate skin-surface measure.
It should also be noted that, for the pressure regulator valve 12, when the pressure in sealing box main body 6 is less than authorized pressure value
When, pressure regulator valve supplements air pressure, and when sealing the pressure in box main body higher than authorized pressure value, pressure regulator valve discharges air pressure.
In the present invention, in specific implementation, for the gas of aero-engine Middle casing support plate covering provided by the invention
Press static test system, further include a pressure control unit 11, the pressure control unit 11 respectively with data collecting instrument 1
It is connected by signal wire with pressure regulator valve 7, for reading the pressure sensor that the data collecting instrument 1 is acquired, described 3 in real time
Pressure value (i.e. atmospheric pressure value) in the sealing box main body 6 of measurement, then according to control instruction input by user, output control signal
To the pressure regulator valve 7, controls the pressure regulator valve 12 and the pressure in the sealing box main body 1 is adjusted, provided until meeting
Pressure loading until.
It should be noted that for the present invention, it, can be according to the gas needed for experiment by the setting of pressure control unit 11
Compressive load size is exported to control the air pressure of the air pressure supply device by controlling pressure regulator valve, can meet different air pressures and carry
The control requirement of lotus.
In order to which the present invention is more clearly understood, below with regard to aero-engine Middle casing support plate covering provided by the invention
The specific installation and debugging step of air pressure static test system illustrates：
First, according to the technology for applying specification of foil gauge, foil gauge 7 is pasted onto 14 table of Middle casing support plate skin product
On the specifying measurement position in face, and connecting test cable；
Then, Middle casing support plate skin product 14 is securely connect with stationary fixture 9 by screw, then utilizes bolt
The bottom plate of stationary fixture 9 is fixed on sealing lower flange 10；
Then, by sealing rubber pad 5 be positioned over sealing lower flange 10 on, then with sealing box main body 6 lower end flange
Docking, and fastened using bolt；
Then, vacuum sealing aerospace connectors 2, pressure sensor 3 are fixed on sealing upper flange 4, and smear sealing
Glue；
Then, displacement sensor 8 is fixed on the inner wall of sealing box main body 6 using magnetic support, makes 8 left end of displacement sensor
Thimble withstand on the specified position on 14 surface of Middle casing support plate skin product, and adjust the direction of thimble, it made to be parallel to illiteracy
The normal direction in epidermis face；
Then, the cable of foil gauge 7, displacement sensor 8 is connected to one end of vacuum sealing aerospace connectors 2, will in
The air inlet of 1414 upper end of Jie's casing support plate skin product is connect with the blow vent on sealing upper flange 4 by tracheae, therefore, is surveyed
During examination, the pressure of 14 inside cavity of Middle casing support plate skin product is set to be consistently equal to standard atmospheric pressure, it is ensured that intermediary machine
The inside and outside differential pressure of casket support plate skin product 14 is equal to authorized pressure load；
Then, upper flange 4 will be sealed, sealing rubber pad 5 docks with the upper end flange of sealing box main body 6, and utilizes spiral shell
Bolt fastens；
Then, vacuum sealing aerospace connectors 2, pressure sensor 3 are connected on data collecting instrument 1 (tool by cable
On body is realized, the cable of foil gauge can be first coupled on the suitable tune device of strain acquirement, then be connect again with data collecting instrument)；
Then, air pressure supply device 13 is connect with the air inlet of pressure regulator valve 12 using tracheae, then with tracheae by pressure regulation
The gas outlet of valve 12 is connect with the air inlet on sealing upper flange 4；
Then, pressure control unit 11 is connected into data collecting instrument 1 and pressure regulator valve 12；
Then, the debugging of pilot system is carried out.The setting debugging load value on pressure control unit 11, opens air pressure supply
Device 13 starts ventilation pressurization, while utilizing the sealing box main body 6 measured by data collecting instrument 1 in real time record pressure sensor 3
Interior pressure value, and pressure control unit 11 is fed back to, when the pressure value that pressure sensor 3 measures reaches ordinance load value,
Pressure regulator valve 12 is closed, and so that sealing box main body 6 is kept the pressure, is checked the air-tightness of the system；
Then, in above-mentioned pressure process, the number of foil gauge 7 and displacement sensor 8 is acquired in real time using data collecting instrument 1
According to checking whether each Measurement channel data are normal；
Finally, when the air-tightness of the system is good, after each Measurement channel data are normal, according to the load pressure of regulation, into
Row formal test.
Therefore, compared with prior art, for the present invention, pressure is realized using closed box main body and pressure sensor
Monitoring, control and accurate load, while realizing the examinations such as strain, displacement using vacuum sealing aerospace connectors and data collecting instrument
Test the accurate measurement of parameter.The stable load of the present invention is controllable, and simple in structure, easy to operate, securely and reliably, Measurement channel number can
It adjusts, the Displacement-deformation amount and strain data that obtain skin-surface can be measured simultaneously, and can add by adjusting various sizes of
It carries and sets to meet the test request of products of different specifications.
The static load test system of Middle casing support plate covering air pressure provided by the invention, it is simple in structure, it is easily installed
Debugging, test method is easy to operate, and Loading Control mode is safe and reliable, and load is evenly distributed, and is not limited by product structure shape
System.In addition, larger test pressure range may be implemented in the output quantity by adjusting pressure regulator valve 12, by converting vacuum sealing boat
The connection line number of empty connector 2 can be adapted for the testing requirement of different Measurement channels, increase the versatility of pilot system.
Compared with prior art, the present invention relatively has the following advantages that：
1, test method of the invention is simple to operation, can realize to labyrinth Middle casing support plate skin product
Pressure loading, while can realize larger on-load pressure range, and load control is accurate；
2, test device of the invention is simple in structure, can product to be measured be directly fixed on seal box body interior, and can
With the volume size by adjusting seal box, to meet the test of different dimensions products；
3, closer to the actual bearer operating mode of product, load is evenly distributed load mode of the invention, while can realize production
The synchro measure of product specified position deformation quantity and strain；
4, the present invention uses vacuum sealing aerospace connectors, the key device as seal box inside and outside of the main body signal transmission.
The device has good sealing performance, ensure that the sealing state of seal box；Reliable linkage function, ensure that measuring signal
The accuracy of reliability and the data acquisition of transmission.It, can be in addition, the interface channel quantity of vacuum sealing aerospace connectors is adjustable
Meet the requirement of different measurement point quantity.
In conclusion compared with prior art, a kind of aero-engine Middle casing support plate covering provided by the invention
Air pressure static test system, can be under defined gas pressure loads, to aero-engine Middle casing support plate skin-surface
Deformation displacement amount and strain data measure, the structural strength for examining Middle casing support plate covering, so as to protect
The reliability for demonstrate,proving the structural strength of Middle casing support plate covering used in aero-engine, is conducive to widely promote and apply,
It is of great practical significance.
For a kind of air pressure static test system of aero-engine Middle casing support plate covering provided by the invention, lead to
The gas pressure loads experiment for realizing Middle casing support plate covering is crossed, product structure intensity is verified, can be the optimization of finite element model
Data supporting is provided.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
It is considered as protection scope of the present invention.
Claims (9)
1. a kind of air pressure static test system of aero-engine Middle casing support plate covering, which is characterized in that including seal box
Main body (6) is vertically fixedly installed Middle casing support plate skin product (14) in the sealing box main body (6)；
The sealing box main body (6) is connected with the gas supply output end of an air pressure supply device, and the air pressure supply device is used
In to provide compressed air inside the sealing box main body (6)；
There are one pressure sensors (3) for setting at the top of the sealing box main body (6)；
There are one foil gauges (7) for Middle casing support plate skin product (14) stickup；
There are one displacement sensor (8), institute's displacement sensors (8) for the right side inner wall fixed setting of the sealing box main body (6)
The thimble of left end withstands on the outer right wall of the Middle casing support plate skin product (14)；
The foil gauge (7), displacement sensor (8) and pressure sensor (3) signal between a data collecting instrument (1) respectively
Connection.
2. air pressure static test system as described in claim 1, which is characterized in that it is described sealing box main body (6) top and
Bottom is respectively provided with upper end flange and lower end flange, and the upper end flange and a sealing upper flange (4) are tightly connected
Together, the lower end flange is sealed connected together with a sealing lower flange (10).
3. air pressure static test system as claimed in claim 2, which is characterized in that on the upper end flange and the sealing
There are one sealing rubber pad (5), the upper end flange, sealing rubber pad (5) and methods in the sealing for setting between flange (4)
Blue (4) are bolted to connection together；
The sealing rubber pad (5) there are one being also provided between the lower end flange and the sealing lower flange (10), it is described
Lower end flange, sealing rubber pad (5) and the lower flange (10) are bolted to connection together.
4. air pressure static test system as described in claim 1, which is characterized in that have on the sealing upper flange (4) logical
Gas port, the venthole are connected with the air inlet of Middle casing support plate skin product (14) upper end by a tracheae.
5. air pressure static test system as described in claim 1, which is characterized in that be provided on the sealing upper flange (4)
Two vacuum sealing aerospace connectors (2)；
The lower end of described two vacuum sealing aerospace connectors (2) passes through with the foil gauge (7) and displacement sensor (8) respectively
Signal wire is connected；
It is connected by signal wire between the upper end of described two vacuum sealing aerospace connectors (2) and the data collecting instrument (1)
It connects.
6. air pressure static test system as described in claim 1, which is characterized in that in the bottom of the sealing lower flange (10)
There are one stationary fixtures (9) for surface fixed setting；
The Middle casing support plate skin product (14) is fixedly connected at the top of the stationary fixture (9).
7. air pressure static test system as described in claim 1, which is characterized in that the air pressure supply device (13) includes extremely
A few gas cylinder.
8. the air pressure static test system as described in any one of claim 1 to 7, which is characterized in that the air pressure supply dress
The gas supply output end of (13) is set by being connected inside a pressure regulator valve (12) and the sealing box main body (6).
9. air pressure static test system as claimed in claim 8, which is characterized in that further include a pressure control unit
(11), the pressure control unit (11) is connected with data collecting instrument (1) and pressure regulator valve (7) by signal wire respectively, is used for
The pressure in the sealing box main body (6) that the pressure sensor (3) that the data collecting instrument (1) is acquired, described measures is read in real time
Force value exports control signal to the pressure regulator valve (7), controls the pressure regulator valve then according to control instruction input by user
(12) pressure in sealing box main body (1) is adjusted, as defined in the satisfaction until pressure loading.
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| CN201810237488.8A CN108760512A (en) | 2018-03-22 | 2018-03-22 | A kind of air pressure static test system of aero-engine Middle casing support plate covering |
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| CN201810237488.8A CN108760512A (en) | 2018-03-22 | 2018-03-22 | A kind of air pressure static test system of aero-engine Middle casing support plate covering |
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| CN111717412A (en) * | 2020-06-17 | 2020-09-29 | 江西洪都航空工业集团有限责任公司 | Flexible missile wing skin deformation load testing device |
| CN111811760A (en) * | 2020-08-12 | 2020-10-23 | 中国人民解放军海军工程大学 | Plate frame model strength/rigidity test system |
| CN113879559A (en) * | 2021-10-12 | 2022-01-04 | 北京机电工程研究所 | Aircraft skin static force loading device and skin dynamic strength test method |
| CN114166408A (en) * | 2021-10-29 | 2022-03-11 | 成都凯天电子股份有限公司 | Embedded atmospheric pressure sensor with low radar scattering efficiency and mounting structure |
| CN114216787A (en) * | 2022-02-22 | 2022-03-22 | 江苏汇联活动地板股份有限公司 | Testing equipment and testing method for anti-static steel floor deformation |
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| CN111717412B (en) * | 2020-06-17 | 2022-05-06 | 江西洪都航空工业集团有限责任公司 | Flexible missile wing skin deformation load testing device |
| CN111811760A (en) * | 2020-08-12 | 2020-10-23 | 中国人民解放军海军工程大学 | Plate frame model strength/rigidity test system |
| CN113879559A (en) * | 2021-10-12 | 2022-01-04 | 北京机电工程研究所 | Aircraft skin static force loading device and skin dynamic strength test method |
| CN113879559B (en) * | 2021-10-12 | 2023-08-15 | 北京机电工程研究所 | Aircraft skin static force loading device and skin dynamic strength test method |
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