CN209069581U - SIL silicone rubber O-ring performance aircraft - Google Patents
SIL silicone rubber O-ring performance aircraft Download PDFInfo
- Publication number
- CN209069581U CN209069581U CN201822219921.3U CN201822219921U CN209069581U CN 209069581 U CN209069581 U CN 209069581U CN 201822219921 U CN201822219921 U CN 201822219921U CN 209069581 U CN209069581 U CN 209069581U
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- CN
- China
- Prior art keywords
- silicone rubber
- assembly
- ring
- welded plate
- sil silicone
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model discloses SIL silicone rubber O-ring performance aircrafts, including main body, console assembly, servo-hydraulic work station；It is characterized by: being provided with welded plate in the main body, briquetting, miniature thrust meter assembly, test fixture assembly, steering cylinder, incubator are installed on the welded plate, console assembly upper end is provided with human-computer dialogue screen, is additionally provided with gland and SIL silicone rubber O-ring on the test fixture assembly；Temp controlled meter and pressure gauge are provided on the servo-hydraulic work station.The utility model has the features such as easy to operate, temperature and pressure is controllable, and accurate speed is fast, has a vast market economic value.
Description
Technical field
The utility model relates to detecting instrument technical fields, in particular to SIL silicone rubber O-ring performance aircraft.
Background technique
Sealing ring performance aircraft is by main shaft band dynamic test axis high speed rotation, and seal cavity is fixed, and to examination
The certain eccentricity of axis is tested, the permeability phenomenon of sealing ring, but existing sealing ring performance aircraft are observed after spin for some time
Structure is complicated, inconvenient for operation, and during the work time, bearing can generate high temperature to main shaft when rotating at high speed with rotary shaft, and
Traditional experiment machine is uncontrollable for temperature and pressure, to will affect test effect and service life, and existing sealing
Circle performance aircraft be essentially all one by one test, working efficiency is low.The utility model is detection SIL silicon rubber
Glue sealing ring material in 200 degree of high pressure 21Kpa high temperature, 4 meters of speed it is per minute when, 0.1 Kpa of low pressure, when low temperature -40 is spent, speed
When 1 meter per minute；The special testing instrument of the analog equipment variation of material capability in the actual environment.
Utility model content
To solve this technical problem, the utility model takes following scheme: SIL silicone rubber O-ring performance aircraft, packet
Include main body, console assembly, servo-hydraulic work station；It is characterized by: welded plate is provided in the main body, the welded plate
On briquetting, miniature thrust meter assembly, test fixture assembly, steering cylinder, incubator are installed, console assembly upper end is set
It is equipped with human-computer dialogue screen, is additionally provided with gland and SIL silicone rubber O-ring on the test fixture assembly；The servo-hydraulic work
Temp controlled meter and pressure gauge are provided on standing.
It is further improved to be: refrigeration unit, evaporator and low temperature water tank are provided on the welded plate.
By using preceding solution, the beneficial effects of the utility model are: the present apparatus is easy to operate, and have with
Lower advantage (1) high-temperature cabinet is heated using electrothermal tube, cooperates temp controlled meter module, temperature-controllable；(2) high pressure takes hydraulic work using private
It stands, high pressure 21Kpa pressure controllable, precisely, speed is fast.Oil cylinder outside, drives the tooling piston rod of high-temperature cabinet.Outside is not injured
Piston rod, securely and reliably；(3) miniature thrust meter is designed, designed device, and using servo motor, torsion is controllable, minimum
Pressure is that 0.05Kpa. pressure gauge uses electronic contact formula pressure gauge.Refrigeration compressor uses double-compressor, second level refrigeration mould
Formula.Insulating layer is installed additional on the outside of the ultralow compression refrigerant R600. of refrigerant；(4) human-computer dialogue screen, the parameter of settable needs, back and forth
Speed, reciprocal time, height pressure pressure, high/low temperature temperature.In conclusion the utility model has easy to operate, temperature and pressure
The features such as power is controllable, and accurate speed is fast, has a vast market economic value.
Detailed description of the invention
Fig. 1 is the structural schematic diagram A of the utility model.
Fig. 2 is the structural schematic diagram B of the utility model.
Fig. 3 is the structural schematic diagram C of the utility model.
Specific embodiment
Now in conjunction with the drawings and specific embodiments, the present invention will be further described.
Various structure members involved in the utility model are all well known to those skilled in the art and grasp uses
Technology, materials are convenient, can easily buy on the market.
The SIL silicone rubber O-ring performance aircraft with reference to disclosed in Fig. 1-Fig. 3, including main body 1, console assembly 4, watch
Take hydraulic workstation 13；It is characterized by: be provided with welded plate 2 in the main body 1, be equipped on the welded plate 2 briquetting 3,
Someone is arranged in miniature thrust meter assembly 8, test fixture assembly 9, steering cylinder 11, incubator 14,4 upper end of console assembly
Machine dialogue screen 12 is additionally provided with gland 16 and SIL silicone rubber O-ring 17 on the test fixture assembly 9；The servo-hydraulic
Temp controlled meter 7 and pressure gauge 15 are provided on work station 13.
It is further improved to be: refrigeration unit 5, evaporator 6 and low temperature water tank 10 are provided on the welded plate 2.
Embodiment:
The design needs following processing step in actual application:
First is placed in SIL silicone rubber O-ring 17 in test fixture assembly 9,
Second incubator, 14 temperature rises to 200 degree, keeps thermostatic in+- 2 degree ranges,
Start servo-hydraulic work station 13, pressure is per minute at 4 meters in 21Kpa speed, does the number set and moves back and forth.
Third takes out SIL silicone rubber O-ring 17, and high temperature and pressure is completed
4th, SIL silicone rubber O-ring 17 is placed in test fixture assembly 9,
5th, 14 temperature of incubator rises to -40 degree constant temperature in+- 2 degree ranges,
Start miniature thrust meter assembly 8, pressure does the reciprocating motion set at 1 meter per minute in 0.1Kpa, speed.
6th takes out SIL silicone rubber O-ring 17, and experiment is completed.Etc. to be detected.
By using preceding solution, the beneficial effects of the utility model are: the present apparatus is easy to operate, and have with
Lower advantage (1) high-temperature cabinet is heated using electrothermal tube, cooperates temp controlled meter module, temperature-controllable；(2) high pressure takes hydraulic work using private
It stands, high pressure 21Kpa pressure controllable, precisely, speed is fast.Oil cylinder outside, drives the tooling piston rod of high-temperature cabinet.Outside is not injured
Piston rod, securely and reliably；(3) miniature thrust meter is designed, designed device, and using servo motor, torsion is controllable, minimum
Pressure is that 0.05Kpa. pressure gauge uses electronic contact formula pressure gauge.Refrigeration compressor uses double-compressor, second level refrigeration mould
Formula.Insulating layer is installed additional on the outside of the ultralow compression refrigerant R600. of refrigerant；(4) human-computer dialogue screen, the parameter of settable needs, back and forth
Speed, reciprocal time, height pressure pressure, high/low temperature temperature.In conclusion the utility model has easy to operate, temperature and pressure
The features such as power is controllable, and accurate speed is fast, has a vast market economic value.
The foregoing descriptions are merely the embodiment using this origination techniques content, any those skilled in the art use this wound
Make done modifications and changes, all belong to the scope of the patents of this creation opinion, and is not limited to those disclosed embodiments.
Claims (2)
1.SIL silicone rubber O-ring performance aircraft, including main body (1), console assembly (4), servo-hydraulic work station (13)；
It is characterized by: being provided with welded plate (2) on the main body (1), briquetting (3), miniature thrust are installed on the welded plate (2)
Instrument assembly (8), test fixture assembly (9), steering cylinder (11), incubator (14), console assembly (4) upper end are provided with
Human-computer dialogue screen (12) is additionally provided with gland (16) and SIL silicone rubber O-ring (17) on the test fixture assembly (9)；Institute
It states and is provided with temp controlled meter (7) and pressure gauge (15) on servo-hydraulic work station (13).
2. SIL silicone rubber O-ring performance aircraft according to claim 1, it is characterised in that: on the welded plate (2)
It is provided with refrigeration unit (5), evaporator (6) and low temperature water tank (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822219921.3U CN209069581U (en) | 2018-12-27 | 2018-12-27 | SIL silicone rubber O-ring performance aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822219921.3U CN209069581U (en) | 2018-12-27 | 2018-12-27 | SIL silicone rubber O-ring performance aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209069581U true CN209069581U (en) | 2019-07-05 |
Family
ID=67102244
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822219921.3U Expired - Fee Related CN209069581U (en) | 2018-12-27 | 2018-12-27 | SIL silicone rubber O-ring performance aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209069581U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111238802A (en) * | 2020-01-19 | 2020-06-05 | 湖北三江航天红峰控制有限公司 | High low temperature pressurization environment O shape circle compression ratio test device |
-
2018
- 2018-12-27 CN CN201822219921.3U patent/CN209069581U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111238802A (en) * | 2020-01-19 | 2020-06-05 | 湖北三江航天红峰控制有限公司 | High low temperature pressurization environment O shape circle compression ratio test device |
| CN111238802B (en) * | 2020-01-19 | 2021-11-12 | 湖北三江航天红峰控制有限公司 | High low temperature pressurization environment O shape circle compression ratio test device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190705 Termination date: 20211227 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |