CN114812940A - High-temperature air tightness test system and method for W-shaped metal sealing ring for space flight aircraft - Google Patents
High-temperature air tightness test system and method for W-shaped metal sealing ring for space flight aircraft Download PDFInfo
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- 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
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- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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- B64F5/60—Testing or inspecting aircraft components or systems
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- 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
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Abstract
The invention discloses a test system and a test method for high-temperature air tightness test of a W-shaped metal sealing ring for an aerospace craft. The device disclosed by the invention is mainly designed for research and development aiming at the leakage test of the W-shaped metal sealing ring, and the principle verification test of the sealing performance of the W-shaped metal sealing ring is realized. The testing scheme has contrastability aiming at the metal sealing rings with different specifications, the testing method has repeatability, the testing result is accurate and reliable, the research and development period of the metal sealing ring can be greatly shortened, the development cost is reduced, and the design and development of various metal sealing rings suitable for aerospace vehicles are facilitated.
Description
Technical Field
The invention relates to a test system and a method for realizing high-temperature air tightness test of a W-shaped metal sealing ring for an aerospace craft, in particular to the field of sealing performance test, and is particularly suitable for high-temperature air tightness test of the metal sealing ring. The invention relates to an automatic air tightness testing system with adjustable temperature and adjustable air pressure.
Background information
With the development of modern aviation industry technology, the working environment of aerospace vehicles becomes more severe, and a sealing device is indispensable as a device for preventing leakage, which has a profound influence on the service life, the working efficiency and the like of aerospace vehicles. In 1986, the space ship 'challenger' exploded and disintegrated 73 seconds after being launched due to the failure of the sealing ring, and 7 astronauts all suffered from the trouble. Therefore, high temperature heat sealing performance testing is critical.
The metal sealing ring is an axial self-tightening structure with a novel sealing form, has the advantages of strong vibration absorption capacity, large deformation range, good high vibration following performance, high vibration absorption capacity, long service life, good wear resistance and the like, is particularly suitable for working under severe environments such as high temperature, high pressure, vibration, strong corrosive media and the like in the fields of aviation, aerospace and nuclear power, and is applied to O-shaped, C-shaped, W-shaped and other metal sealing rings at present. The O-shaped metal sealing ring has good sealing performance under a small load, but is easy to break due to a small bearing range of the compression rate, and the sealing structure is damaged; the C-shaped metal sealing ring is generally applied to a high-pressure environment, but has poor resilience performance, is easy to generate plastic deformation, and is easy to cause fatigue failure when the compression ratio is larger; compared with the W-shaped metal sealing ring, the W-shaped metal sealing ring can be used at high temperature and high pressure, and has better rebound resilience.
In order to better verify and test the sealing performance of the W-shaped metal sealing ring at normal temperature and high temperature, an air tightness test is required. The test method is characterized in that comparative analysis is carried out on different working conditions of the metal sealing ring, different levels of test compression ratios are designed according to actual assembling and working conditions of the aerospace vehicle, the air tightness of the sealing element is comprehensively tested and analyzed, and a test basis is provided for application research of high-temperature sealing on the aerospace vehicle.
At present, a professional testing device for a high-temperature air tightness test of a metal elastic sealing ring is lacked in China, a simple testing tool is generally adopted to carry out a normal-temperature sealing test, and the air tightness under a high-temperature working condition cannot be reflected. In foreign countries, research institutions such as NASA in the united states specially customize a test device to perform performance tests on metal elastic sealing elements, but high-temperature tests can only be performed in an environmental control test box, and test tools and test elements are deformed under high-temperature conditions, so that the compression amount of metal elastic sealing rings under the high-temperature conditions cannot be accurately guaranteed, and the accuracy of test results is difficult to guarantee.
The invention provides a test system and a method for realizing high-temperature air tightness test of a W-shaped metal sealing ring for an aerospace craft, aiming at a given test piece and test parameter requirements thereof, and carrying out automatic sealing performance test. The sealing performance test of the W-shaped metal sealing ring at high temperature is realized by the test measurement and control integrated device which is jointly composed of the tester body, the upper back plate heating control system, the lower back plate heating control system, the external air supply regulation and control system and the automatic measurement and control system based on the PLC and the human-computer interface, the test scheme has contrastability for different types of metal sealing rings, the test method has repeatability, and the accuracy and reliability of test results are further ensured.
2012, patent CN202402649U discloses a novel high-temperature sealing device, which realizes the combination of mechanical seal and gas seal, and has simple and compact structure and cost saving. The sealing device is mainly used for a sealing device of a material pushing device at the front end part of a grate cooler and belongs to dynamic sealing, while the sealing device is mainly used for testing the air tightness of a W-shaped metal sealing ring for an aerospace aircraft and belongs to static sealing.
In 2016, patent CN205482319U discloses a sintering furnace high temperature resistant sealing device, and its inner structure realizes once and secondary seal, uses sealed magnetic ring to realize the tertiary sealed effect. This patent is sealed through bolt pretension, and seal structure is different, and what adopted is W type metal seal circle.
In 2020, patent CN110932204A discloses a high temperature resistant lead sealing device, which is characterized in that a high temperature insulating sleeve is installed at the joint of the lead and the heat accumulator to form an insulating sealing structure, so that the device can stably work at a higher ambient temperature, and has a simple structure and higher stability. But it lacks automatic test components and parts, and this patent can realize the effective monitoring to relevant parameter to adjust the parameter to multiple complex operating mode and test.
Other related patents are: patent No. CN103867712A, a metal foil high temperature sealing method; patent No. CN211175611U, a valve stem high temperature sealing device; patent No. CN111156222A, an ultra high temperature sealing device applied to a hydraulic cylinder, and a hydraulic cylinder. Through research and analysis on the existing patents, most of high-temperature sealing devices have common principles and design ideas and have respective characteristics. Most of the existing sealing structure patents adopt the basic mechanical structure of a sealing gland, a sealing medium, a base and a cavity, and only design different functional compositions according to different target conditions and implementation modes. The test system and the method for realizing the high-temperature air tightness test of the metal sealing ring can realize the test of various sealing rings with different sizes in the same system, can finish the comprehensive evaluation of the sealing property and the anti-leakage capability of the metal sealing ring at high temperature by the cooperation of a hardware device and an automatic measurement and control system, can carry out the test under various working conditions by changing program parameters, can greatly shorten the research and development period of the metal sealing ring, reduce the research and development cost and are beneficial to designing and developing various metal sealing rings suitable for aerospace vehicles.
Disclosure of Invention
The invention aims to provide a test system and a method for realizing high-temperature air tightness test of a W-shaped metal sealing ring for an aerospace aircraft, so as to realize test research on the sealing performance of the W-shaped metal sealing ring with different sealing modes at different temperatures and different pressures.
The technical scheme adopted by the invention is a high-temperature air tightness test system for a W-shaped metal sealing ring for an aerospace craft, which comprises a tester body, an upper back plate heating control system, a lower back plate heating control system, an external air supply regulation and control system and an automatic measurement and control system based on a PLC and a human-computer interface; an external air supply regulation and control system controls an air supply source and sends compressed air to the tester body, an upper back plate heater and a lower back plate heater are respectively installed at the top of the tester upper cover 2 and the bottom of the tester base 1, and a temperature sensor, a pressure sensor and the like are installed in the tester and are connected into a PLC (programmable logic controller) to realize automatic measurement and control.
The tester body mainly comprises a tester base 1, a tester upper cover 2, an upper heater gland 3, an upper heater 4, a lower heater 5 and a lower heater gland 6. The tester base 1 is arranged on a high-temperature-resistant resin heat-insulating base 10, a required high-precision positioning block 18 is installed according to test requirements, a tester upper cover 2 is installed on the tester base 1 in a centering mode, an upper heater 4 is installed at the center of the top of the tester upper cover 2, a heater gland 3 is installed, a lower heater 5 is installed at the center of the bottom of the tester base 1, a lower heater gland 6 is installed, and the installation is achieved through bolt connection. Three-layer stepped structure is processed in the tester base 1 by taking a geometric center as a standard, three-layer boss structure is processed below the tester upper cover 2 correspondingly, the W-shaped metal sealing ring is arranged on the left sealing surface and the right sealing surface of the W-shaped metal sealing ring which can be tested by the boss structure of the tester upper cover 2, the W-shaped metal sealing ring is arranged on the upper sealing surface and the lower sealing surface of the W-shaped metal sealing ring which can be tested by the stepped structure of the tester base 1, and the sealing effect of two sealing modes of end face sealing and thin wall sealing of the W-shaped metal sealing ring can be tested by the cooperation of the stepped structure and the boss structure. The high-precision positioning block 18 arranged in the tester body can realize accurate compression ratio test, different positioning blocks are adopted for different compression ratios, test is started after the W-shaped metal sealing ring is installed, compressed air is introduced, the compressed air is leaked along the outer side of the annular sealing sample in an inward measuring way and is leaked in an annular way, leaked gas is introduced into the coil type heat exchanger along the leakage pipeline 14 and is cooled to be lower than 50 ℃, then the high-precision thermal flowmeter is introduced, the leakage flow and the leakage temperature are measured in real time, the leakage parameter measurement of the same measurement position is realized, and the high-temperature sealing performance of the sealing element is measured.
The upper and lower back plate heating control system comprises an upper heater 4, a lower heater 5, temperature sensors 15 and 16 and temperature control meters 20 and 21. The temperature sensor 15 is installed on the upper heater 4 and connected to the temperature control meter 20, the temperature sensor 16 is installed on the lower heater 5 and connected to the temperature control meter 21, the temperature is automatically sampled and transmitted to the temperature control meters 20 and 21 to be monitored in real time, the target temperature set in the temperature control meters 20 and 21 is compared, the closed-loop control of the temperatures of the upper heater 4 and the lower heater 5 is realized through a PID (proportion integration differentiation) adjusting mode, and the air in the hot air cavity 11 of the tester is heated to raise the temperature, so that the high-temperature working environment of the sealing element is simulated. The bottom surface of the tester upper cover 2 is directly contacted with the sealing element, the temperature sensor is placed right above the contact position and is fastened by using bolts, and the temperature of the measuring point position can reflect the actual temperature of the heater and the sealing element due to good heat-conducting property of metal and the heater.
The external air supply regulation and control system comprises a high-pressure pump, a high-pressure air storage tank, a pressure regulating valve and a pressure sensor 9, wherein the high-pressure pump is used as an air source of the test system before the high-pressure air storage tank is installed, the high-pressure air storage tank provides air under pressure, stable pressure input is provided for a test device, the pressure sensor 9 is installed at a corresponding position of a tester base 1, actual hot air pressure in the tester is measured, the air pressure is accurately regulated through the pressure regulating valve, and the flowing air pressure in the tester can be ensured to reach the set target pressure.
The automatic measurement and control system based on the PLC and the human-computer interface and the leakage parameter measurement system are composed of temperature sensors, temperature display instruments 19 and 22, a pressure sensor 9, a thermal type flowmeter, a PLC main controller and upper computer measurement and control software. The PLC is the core equipment of the system, all the instruments are connected with the PLC, the sensor transmits analog signals into the PLC through the transmitter, and then the PLC outputs control instructions. The high-pressure pump and the pressure sensor in the external air supply regulation and control system are connected into the automatic measurement and control system so as to control the starting and stopping of the high-pressure pump and monitor the air pressure change in the high-pressure air storage tank and the tester body in real time; the upper back plate heating system and the lower back plate heating system are connected with the automatic measurement and control system, the heating system is manually controlled to be started and stopped based on a human-computer interface, the temperature of the heater is accurately and stably controlled based on the negative feedback closed-loop control of a PID algorithm, and the temperature of air in a cavity of the tester and the temperature of leaked air can be visually displayed by combining a temperature sensor and a display instrument so as to provide a simulation environment which accords with the actual working condition; the leakage gas outlet is connected with a coil heat exchanger for cooling high-temperature gas to ensure safety, and the thermal type flowmeters with different measuring ranges are connected through a three-way valve and can be switched to use in real time according to test requirements. The upper computer measurement and control software is independently developed monitoring software, can calculate a measurement result in real time, and displays and records leakage parameters such as temperature, pressure, flow and the like. The measurement and control system can realize regulation and control and detection of test parameters such as temperature and the like in the test process, has higher automation and intelligence degree, can read data with the precision reaching ten deciles, can continuously sample for a long time, and has better accuracy of data reading.
The simulation design method and the test method based on Ansys are realized based on the test system, and the leakage test method needs to firstly carry out temperature field simulation and strength check to ensure that the system meets the required working condition; basic test method step 1: the high-pressure pump is used as an air source to charge the high-pressure air storage tank to a set pressure; step 2: inputting compressed air required by testing into the tester through a pressure regulating valve, and heating the compressed air in a hot air cavity 11 of the tester; and step 3: and (3) starting a heat seal air tightness test, measuring leakage of compressed air inwards along the outer side of the annular seal sample in an annular way, introducing the leakage gas into the coil type heat exchanger along the leakage pipeline 14, cooling to a temperature lower than 50 ℃, introducing the leakage gas into the high-precision thermal flowmeter, measuring the leakage flow and the leakage temperature in real time, and realizing the measurement of the leakage parameters at the same measurement position. The simulation design method based on Ansys comprises the following steps of temperature field simulation design and strength check: the tester structure is designed through temperature field simulation, the heating state of the sealing element in the tester is verified, the sealing element conforms to the actual working condition to the maximum extent, and the power required by the heater is obtained through analysis, so that the sealing element reaches the temperature required by the test within a fixed time; the strength of the hexagon socket head cap bolts for connecting the upper cover and the base of the tester is checked, so that the tester can bear at least 2Mpa of internal pressure, and the test is ensured to be safely carried out.
Compared with the prior art, the high-temperature air tightness test system and method for the W-shaped metal sealing ring for the space aircraft have the following beneficial effects:
1. the air tightness test of three sealing samples with different sealing surfaces and different diameters can be completed in the same set of tester. The structural positioning of two sealing surfaces is realized by utilizing a back plate and a base, the upper and lower sealing and the left and right sealing positioning are realized by a stepped structure, and positioning surfaces with different diameters are designed to match the air tightness test of three W-shaped metal sealing rings;
2. when in leakage test, the gas leaks along an annular leakage path from outside to inside, so that whether the gas at the outer side of the ring leaks or not is not required to be worried about, the leaked gas is completely collected, and the accurate measurement of the leakage rate is ensured;
3. the accurate compression ratio test is realized by adopting the positioning block processed with high precision, and different positioning blocks are adopted for different compression ratios, so that the test parameters are accurately controlled, and the accurate measurement of the leakage rate is ensured;
4. the continuous three-range intelligent high-precision thermal flowmeter is used for realizing the wide-range leakage test of 0-450L/min. The three ranges are respectively 0.025-0.6L/min, 0.6-60L/min and 60-450L/min, the precision of each flowmeter is +/-0.3% of the full range, the flowmeters are connected by a tee joint and switched to be used in real time according to test requirements;
5. the mode that adopts high-pressure pump cooperation high pressure gas holder provides stable pressure input for testing arrangement, and the pressure fluctuation that repeated start caused when avoiding directly using the air compressor machine air feed improves test stability greatly.
6. The upper and lower back plate heating control systems for high-temperature test are based on simulation, the temperature field distribution and the required heating time of the test bed in different heating states are simulated through modeling simulation, and the simulation result is used for designing the heater power and the heating system distribution mode of the back plate heating system, so that the system can be heated to the required high-temperature environment within the specified time. Meanwhile, checking the structural strength to ensure the safe performance of the test;
7. the automatic measurement and control system based on the PLC and the human-computer interface is completely and autonomously designed, changes of process parameters such as temperature, pressure and flow in the test can be monitored and recorded in real time, stored data can be analyzed, the leakage state of a test piece can be effectively captured, a tester can issue instructions such as starting and stopping of a heater, opening and closing of a valve and the like through the operation of the human-computer interface, and the automation degree of the test system is improved.
Drawings
FIG. 1 is a schematic view of a gas leakage path of a test seal.
FIG. 2 is a schematic diagram of a seal air tightness test system.
Fig. 3 is a schematic diagram of the serial operation of a thermal flow meter.
Fig. 4 is a sample mounting diagram of the tester.
FIG. 5 is a simulation analysis design.
Wherein 1-a tester base, 2-a tester upper cover, 3-an upper heater gland, 4-an upper heater, 5-a lower heater, 6-a lower heater gland, 7-W1 type metal seal ring, 8-graphite pad, 9-a pressure sensor interface, 10-a high temperature resistant resin heat insulation base, 11-a hot air cavity, 12-W3 type metal seal ring, 13-W2 type metal seal ring, 14-a leakage pipeline, 15-an upper heating sensor interface, 16-a lower heating sensor interface, 17-an air inlet, 18-a high precision positioning block, 19-a hot air thermometer, 20-an upper heater temperature control meter, 21-a lower heater temperature control meter and 22-a leakage gas thermometer, and the leakage path is marked by arrows in figure 1;
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings.
Example 1: taking the test of W1 type metal sealing ring as an example, the maximum test temperature is 740 ℃, and the power density (heat generation) of the upper heater body is 45W/m through the simulation of temperature field 3 The lower heater body power density (heat generation) was 36W/m 3 The average temperature of the air in the cavity can reach 740 ℃ after heating for 75 min. The left and right sealing surfaces of the W1 type metal sealing ring are required to be tested, so the W1 type metal sealing ring is installed at a boss of an upper cover of a tester, the upper cover 2 of the tester, an upper heater gland 3, a lower heater gland 6 and a test piece are installed, the W1 type metal sealing ring 7 to be tested is placed in a base 1 of the tester, a positioning block 18 is installed, a graphite pad 8 with proper thickness is selected, the upper cover 2 of the tester is installed, a bolt is screwed down, a bottom leakage pipeline 14 is connected, an outlet of the leakage pipeline 14 is connected with a coil pipe heat exchanger and then connected with a three-way valve, and a thermal flowmeter is installed on the valve to connect and check the lines of each testing instrument. And then powering on, checking whether the device is normal, and opening an upper computer program interface to start testing if all the devices are normal. Closing the outlet valve of the device, opening the high-pressure air storage tank to output air,carrying out normal-temperature air tightness test; the pressure is adjusted to the respective pressure using a pressure regulating valve for measurement. After an aluminum silicate cotton heat insulation material is added to a tester, heating is started, an upper back plate heater and a lower back plate heater are heated to the temperature to be tested at the same time, the heating time is recorded and the state is stabilized for 10min, pressurized air is introduced, the temperature and pressure change in a hot air cavity 11 of a process real-time monitoring device are monitored, when the target test pressure is stable and does not fluctuate, formal test is started after the stable state is kept, the temperature of the upper heater and the lower heater at the moment, the real-time leakage quantity and the accumulated leakage quantity of a test piece under the pressure are recorded, the pressure is increased step by step and the test is carried out according to the test pressure, the back plate heaters are turned on again for electric heating, the temperature is increased step by step to the target test temperature, the test is carried out respectively according to different pressures until all the pressure working conditions of all temperatures are completely tested, the electric heating is turned off, and the high-temperature test is finished. And after the temperature of the tester is cooled to the room temperature, carrying out the normal-temperature air tightness test again, comparing with the normal-temperature test before heating, and finally unifying and summarizing data records to analyze to obtain the high-temperature sealing performance of the test piece.
Example 2: taking the test of W3 type metal sealing ring as an example, the maximum test temperature is 650 ℃, and the power density (heat generation) of the upper heater body is 45W/m through the simulation of temperature field 3 The lower heater body power density (heat generation) was 36W/m 3 The average temperature of the air in the cavity can reach 650 ℃ after heating for 65 min. The upper and lower sealing surfaces of the W1 type metal sealing ring are required to be tested, so that the sealing ring is arranged at the step of the tester base 1, and a corresponding high-precision positioning block 18 is arranged to ensure the required compression ratio. And after the assembly is finished, the testing is started, the outlet valve of the device is closed, the high-pressure air storage tank is opened to output air, the normal-temperature air tightness test is carried out, then the thermal insulation material is additionally arranged to carry out the high-temperature air tightness test, after the temperature of the tester is cooled to the room temperature, the normal-temperature air tightness test is carried out again, the normal-temperature air tightness test is compared with the normal-temperature test before heating, finally, the data records are summarized in a unified mode, and the high-temperature sealing performance of the test piece is obtained through analysis.
Claims (8)
1. High-temperature air tightness test system of W-shaped metal seal ring for space flight vehicle, its characterized in that: the tester comprises a tester body, an upper back plate heating control system, a lower back plate heating control system, an external air supply regulation and control system and an automatic measurement and control system based on a PLC and a human-computer interface; an external air supply regulation and control system controls an air supply source and sends compressed air to the tester body, an upper back plate heater and a lower back plate heater are respectively installed at the top of an upper cover of the tester and the bottom of a base of the tester, and temperature and pressure sensors are installed in the tester and are connected into a PLC to realize automatic measurement and control.
2. The high-temperature air tightness testing system for the W-shaped metal sealing ring for the spacecraft of claim 1, characterized in that: the tester body comprises a tester base, a tester upper cover, an upper heater gland, an upper heater, a lower heater and a lower heater gland; the tester base is arranged on the high-temperature-resistant resin heat-insulating base, a required high-precision positioning block is installed according to the test requirement, the tester upper cover is installed on the tester base in a centering mode, the upper heater is installed at the center of the top of the tester upper cover, the upper heater gland is installed, the lower heater is installed at the center of the bottom of the tester base, and the lower heater gland is installed; the three-layer stepped structure is processed in the tester base by taking the geometric center as a standard, the three-layer boss structure is processed below the tester upper cover correspondingly, the W-shaped metal sealing ring is arranged on the boss structure of the tester upper cover to test the left sealing surface and the right sealing surface of the W-shaped metal sealing ring, the W-shaped metal sealing ring is arranged on the stepped structure of the tester base to test the upper sealing surface and the lower sealing surface of the W-shaped metal sealing ring, the stepped structure is matched with the boss structure, and the sealing effects of two sealing modes of end face sealing and thin wall sealing of the W-shaped metal sealing ring are tested.
3. The high-temperature air tightness testing system for the W-shaped metal sealing ring for the spacecraft of claim 2, characterized in that: the high-precision positioning block is arranged in the tester body, accurate compression ratio testing is achieved, different positioning blocks are adopted for different compression ratios, testing is started after the W-shaped metal sealing ring is installed, compressed air is introduced, the compressed air is leaked along the outer side of the annular sealing sample in an inward measuring mode and is leaked in an annular way, leaked gas is introduced into the coil type heat exchanger along a leakage pipeline and is cooled to be lower than 50 ℃, then the high-precision thermal flowmeter is introduced, leakage flow and leakage temperature are measured in real time, leakage parameter measurement of the same measurement position is achieved, and high-temperature sealing performance of the sealing element is measured.
4. The high-temperature air tightness testing system for the W-shaped metal sealing ring for the spacecraft of claim 1, characterized in that: the upper back plate and the lower back plate heating control system comprise an upper heater, a lower heater, a temperature sensor I, a temperature sensor II, a temperature control meter I and a temperature control meter II; the temperature sensor I is arranged on the upper heater and connected to the temperature control meter I, the temperature sensor II is arranged on the lower heater and connected to the temperature control meter II, the temperature is automatically sampled and transmitted to the temperature control meter I and the temperature control meter II for real-time monitoring, the temperature is compared with target temperatures set in the temperature control meter I and the temperature control meter II, the closed-loop control of the temperatures of the upper heater and the lower heater is realized through a PID (proportion integration differentiation) regulation mode, and the air in a hot air cavity of the tester is heated and heated, so that the high-temperature working environment of the sealing element is simulated; the bottom surface of the upper cover of the tester is in direct contact with the sealing element, the temperature sensor is placed right above the contact position and is fastened by using bolts, and the temperature of the measuring point position reflects the actual temperature of the heater and the sealing element.
5. The high-temperature air tightness testing system for the W-shaped metal sealing ring for the spacecraft of claim 1, characterized in that: the external air supply regulation and control system comprises a high-pressure pump, a high-pressure air storage tank, a pressure regulating valve and a pressure sensor, wherein the high-pressure pump is used as an air source of the test system before the high-pressure air storage tank is installed, the high-pressure air storage tank provides air under pressure, stable pressure input is provided for a test device, the pressure sensor is installed at a corresponding position of a base of the tester, actual hot air pressure in the tester is measured, and the pressure is accurately regulated through the pressure regulating valve so as to ensure that the flowing air pressure in the tester can reach the set target pressure.
6. The high-temperature air tightness testing system for the W-shaped metal sealing ring for the spacecraft of claim 1, characterized in that: the automatic measurement and control system based on the PLC and the human-computer interface and the leakage parameter measurement system are composed of a temperature sensor, a temperature display instrument, a pressure sensor, a thermal flowmeter, a PLC main controller and upper computer measurement and control software; the temperature sensor, the temperature display instrument, the pressure sensor and the thermal flowmeter are all connected with the PLC, the pressure sensor transmits an analog signal into the PLC main controller through the transmitter, and then the PLC main controller outputs a control instruction; the high-pressure pump and the pressure sensor in the external air supply regulation and control system are connected into the automatic measurement and control system so as to control the starting and stopping of the high-pressure pump and monitor the air pressure change in the high-pressure air storage tank and the tester body in real time; the upper back plate heating system and the lower back plate heating system are connected with the automatic measurement and control system, the heating system is manually controlled to be started and stopped based on a human-computer interface, the temperature of the heater is accurately and stably controlled based on the negative feedback closed-loop control of a PID algorithm, and the temperature of air in a cavity of the tester and the temperature of leaked air can be visually displayed by combining a temperature sensor and a display instrument so as to provide a simulation environment which accords with the actual working condition; the leakage gas outlet is connected with a coil heat exchanger for cooling high-temperature gas to ensure safety, and the thermal type flowmeters with different measuring ranges are connected through a three-way valve and switched to use in real time according to test requirements; the upper computer measurement and control software can calculate the measurement result in real time and display and record the temperature, pressure and flow leakage parameters.
7. The testing method by using the high-temperature air tightness testing system for the W-shaped metal sealing ring for the space aircraft as claimed in any one of claims 1 to 6 is characterized in that: firstly, temperature field simulation and strength check are required to be carried out, and the system is ensured to meet the required working condition;
the test method comprises the following steps:
step 1: the high-pressure pump is used as an air source to charge the high-pressure air storage tank to a set pressure;
step 2: inputting compressed air required by testing into the tester through a pressure regulating valve, and heating the compressed air in a hot air cavity of the tester;
and step 3: and (3) starting a heat seal air tightness test, measuring leakage of compressed air inwards along the outer side of the annular seal sample in an annular way, introducing the leakage gas into the coil type heat exchanger along a leakage pipeline, cooling to a temperature lower than 50 ℃, introducing the leakage gas into the high-precision thermal flowmeter, measuring the leakage flow and the leakage temperature in real time, and realizing the measurement of the leakage parameters at the same measurement position.
8. The high-temperature air tightness test method of the W-shaped metal sealing ring for the spacecraft of claim 7, characterized in that: the simulation design method based on Ansys comprises the following steps of temperature field simulation design and strength check: the tester structure is designed through temperature field simulation, the heating state of the sealing element in the tester is verified to meet the actual working condition, the power required by the heater is obtained through analysis, and the temperature required by the test is reached within a fixed time; the strength of the hexagon socket head cap bolts for connecting the upper cover and the base of the tester is checked, so that the tester can bear at least 2Mpa of internal pressure, and the test is ensured to be safely carried out.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210425942.9A CN114812940B (en) | 2022-04-21 | 2022-04-21 | High-temperature air tightness testing system and method for W-shaped metal sealing ring for aerospace aircraft |
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| CN202210425942.9A CN114812940B (en) | 2022-04-21 | 2022-04-21 | High-temperature air tightness testing system and method for W-shaped metal sealing ring for aerospace aircraft |
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