CN115144128A - Measurement and control system and method for leakage characteristic evaluation of spacecraft porous sealing material - Google Patents
Measurement and control system and method for leakage characteristic evaluation of spacecraft porous sealing material Download PDFInfo
- Publication number
- CN115144128A CN115144128A CN202210660208.0A CN202210660208A CN115144128A CN 115144128 A CN115144128 A CN 115144128A CN 202210660208 A CN202210660208 A CN 202210660208A CN 115144128 A CN115144128 A CN 115144128A
- Authority
- CN
- China
- Prior art keywords
- temperature
- test
- sealing
- tool
- leakage
- 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.)
- Pending
Links
Images
Classifications
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Examining Or Testing Airtightness (AREA)
Abstract
The invention discloses a measurement and control system and a measurement and control method for evaluating leakage characteristics of a porous sealing material of a spacecraft, wherein the measurement and control system comprises an external gas source device, a pressure reducing valve, an ultrahigh temperature electric heating system, an instantaneous switching pipeline, a sealing test tester tool body, a high temperature gas cooler, an intelligent active measurement and control system with a PLC (programmable logic controller) as a main controller, a transmitter and a leakage detection instrument; according to the operation condition and the installation structure characteristics of the actual porous sealing material, the test system platform is relied on to carry out the penetration and leakage test of the porous sealing material in a targeted manner, and the leakage amount is evaluated to obtain the flow penetration and heat transfer characteristics of the sealing material in a typical state. In the test process, a new test means and method aiming at the leakage monitoring and detection of the sealing element and the sealing structure are provided. The measurement and control system mainly aims at the porous sealing material to develop control software and design the structure of the tester body, and creates conditions for carrying out a multi-working-condition sealing leakage principle verification test subsequently.
Description
Technical Field
The invention provides a measurement and control system and a measurement and control method for evaluating leakage characteristics of a porous sealing material of a spacecraft, particularly belongs to the field of testing and evaluating of the sealing material, and is particularly suitable for testing the flow leakage and heat transfer characteristics of a porous sealing medium in an ultrahigh-temperature environment. The invention relates to a porous sealing material leakage characteristic evaluation and measurement and control system which can simultaneously meet the requirements of multiple working conditions (different temperatures, pressure differences and compression ratios).
Background
With the rapid rise and development of the modern aviation industry, aerospace vehicles are operating at increasingly faster speeds, thereby presenting a series of problems. Among them, the most typical is the sealing and heat insulation problem of the sensitive part of the aircraft body, and the structural sealing under the severe environment of high temperature, high pressure and high load has been considered as the key technology of the future development of the aerospace aircraft. Particularly in the field of hypersonic aircrafts, on one hand, the comprehensive performance of the aerospace aircraft is greatly improved, and on the other hand, higher requirements are placed on the structural design level and the material performance of the aircraft. This requires that the aircraft body structure can withstand the complex working environment faced by hypersonic aircraft, including mainly higher temperature environmental conditions, local heating of the overall steady and transient shock waves of the aircraft, stronger aerodynamic loads, and possibly severe structural vibration and environmental erosion. When the hypersonic aircraft is re-entered, high-temperature and high-pressure airflow leaks into the gap position of the aircraft body, so that gap inflow heat and temperature increase caused by high-speed aerodynamics are generated. Therefore, no matter the space vehicles such as manned spacecraft, gliding and cruising aircraft, reentry warhead and the like, the gaps at the openings of the fairing and the fuselage of the space vehicles need to be protected by high-temperature heat sealing.
The high-temperature heat sealing technology is developed rapidly in the modern industrial field and is widely applied, is a more key technical means, plays an important role in the aerospace field, and the related high-temperature heat sealing structure and sealing material are also one of the key technical components of various spacecrafts. In addition to the fact that the earliest Apollo spacecraft in the United states began to employ a significant amount of high temperature heat sealing technology to ensure proper operation of the aircraft, the United states' best-minded intercontinental missiles also designed and utilized as many as 340 and 900 seal structures and seals in sensitive critical areas. The space shuttle and the X-38 project aircraft in the United states also provide a plurality of sealing schemes, and theoretical support and reference are provided for the sealing development research of the hypersonic aircraft in the future.
The method is characterized in that the method tracks relevant high-temperature heat sealing research data at home and abroad, finds that the existing research mainly aims at the heat sealing material, obtains relevant mechanical properties and thermal properties of the sealing material by developing various normal-temperature and high-temperature test tests and numerical simulation calculation, and carries out comprehensive evaluation and reliability analysis on the sealing leakage effect according to the behavior and the test data. The typical sealing structure and the sealing element mainly comprise a reciprocating dynamic sealing structure consisting of a rubber ring and a slip ring, a rubber sealing ring made of heat-resistant fluororubber, a hollow pipe O-shaped sealing ring made of metal materials and a fiber woven sealing rope embedded with a metal spring pipe, and the characteristics of the various structures and materials and the application working conditions are different. Therefore, the high-temperature heat sealing technology for the aerospace craft is more critical and important, and the development of the high-temperature heat sealing technology becomes an important problem to be solved at present.
The invention provides a measurement and control system and a measurement and control method for evaluating leakage characteristics of a porous sealing material of a spacecraft. The method is characterized in that point-to-point test tool design and measurement and control program development are carried out aiming at the existing porous sealing material to be tested and target test parameters, and hardware equipment and a software system are debugged to provide technical support for subsequent development of sealing material leakage test and evaluation. The automatic intelligent sealing leakage measurement and control system which integrates state monitoring, parameter control and data recording and is composed of a high-pressure inflator pump, a high-pressure stabilizing tank, a high-power air compressor, a pressure reducing valve, an ultrahigh-temperature electric heating system, an instantaneous switching pipeline, a sealing test tester tool, a high-temperature gas cooler, test software, a control cabinet, a temperature pressure transmitter, a high-precision mass flowmeter and the like can verify and evaluate the principle of the sealing characteristic of the aerospace porous sealing material under the condition of combined working conditions (temperature, pressure difference and compression ratio). The test scheme is drawn up to different porous materials and has certain reference and transportability, and the test method and the test process can be reproduced to ensure the reliability and consistency of the test result.
In 2014, patent CN103867712A discloses a high-temperature sealing method for metal foil. The sealing method of the patent technology belongs to the field of structural heat strength tests, and reduces the influence of high temperature on a target part through active and passive cooling modes. By using the technology, sealing of a positive pressure environment and a negative pressure environment at 1000 ℃ can be realized, and the realization of a stamping loading mode of a hot strength test target part is facilitated. Compared with the patent, the difference lies in that: this patent realizes the target temperature that awaits measuring through phlogopite electric heating wire to the cooling method adopts passive air cooling, and the cool time is longer. In addition, the purpose of this patent is to realize the high temperature leakage test of the target object to be measured, and there is a certain difference with the thermal insulation cooling target object of the reference patent.
In 2019, patent CN110043665A discloses a heat sealing structure suitable for high temperature environment and an assembling method thereof. The device mainly comprises an elastic element, an inner thermal insulation layer, an outer thermal insulation layer and an outer coating layer, and through reasonable design and combination of all parts of the device, the device can effectively carry out thermal protection on aircraft body opening parts such as aircraft control wing gaps, cabin doors and the like, and avoids failure and damage of aircraft sensitive structures and parts due to overheating. Compared with the patent, the difference lies in that: the patent mainly aims at one or more typical sealing materials to carry out sealing leakage test and evaluation, and the test system comprises a plurality of components with complete functions, and focuses on principle verification and test. The referenced patent is mainly a specific heat seal structure and its assembly method, with emphasis on practical application and functional attributes.
In 2021, patent CN213064611U discloses an aircraft cowling heat sealing device. This patent drives the feeding post through screw-thread fit's precession ring, makes the sealing connection material conveniently controllable outwards supply from pressing the feed bin, and certain degree has improved to the sealed quality of convector shield clearance line heating. Meanwhile, the illuminating lamp is arranged at the lower end of the device frame, so that an operator can observe the lines of the fairing needing to be sealed conveniently, and the working efficiency of heating sealing is improved. Compared with the patent, the difference lies in that: the sealing material tested by the patent is a loose porous material and has certain compressibility, and the reference patent mainly aims at the thread lines of the gaps of the fairing structure to implement heating sealing; the software measurement and control aspect of the patent technology is comprehensive, real-time monitoring recording and active control of process multi-parameters can be achieved, and the degree of automation is good.
Other related patents are: patent No. CN110095364A, a high temperature thermal seal high temperature performance thermal coupling test platform; patent No. CN111156222A, an ultra-high temperature sealing device applied to a hydraulic cylinder and the hydraulic cylinder; patent No. CN112963547A, magnetic liquid heat-insulating sealing device, etc. Through the analysis and research of the patent information in the existing high-temperature heat sealing field, different heat sealing devices and test methods have respective advantages and innovation points. In the aspect of the heat protection of the target object, some existing patent technologies are designed to develop innovative designs, and some existing patent technologies are designed to reduce heat loss. The invention provides a measurement and control system and a measurement and control method for evaluating leakage characteristics of a porous sealing material of a spacecraft, and aims to finish leakage detection and characteristic evaluation of the porous sealing material of the spacecraft under various working conditions through a self-built high-temperature principle test verification platform (software and hardware). The upper computer control program can change the test parameters in real time and optimally match hardware equipment so as to simulate the actual working environment of the sealing element to be tested to the maximum extent and enable the test data to have certain authenticity and reference value. The high-temperature sealing test method and the test device provided and designed by the invention provide ideas and technical reserves for the research and development of the high-temperature sealing medium from the practical engineering, simultaneously shorten the research and development period of the material, reduce the use and production cost and fill the technical blank of the test evaluation of the heat sealing material at the sensitive part of the spacecraft structure in the test stage.
Disclosure of Invention
The invention aims to provide a measurement and control system and a measurement and control method for evaluating leakage characteristics of a porous sealing material of a spacecraft, so as to test, evaluate and research the leakage characteristics of the porous sealing material under complex working conditions of different temperatures, pressure differences, compression ratios and the like.
The invention adopts the technical scheme that the measurement and control system for evaluating the leakage characteristic of the porous sealing material of the spacecraft comprises an external air source device, a pressure reducing valve, an ultrahigh temperature electric heating system, an instantaneous switching pipeline, a sealing test tester tool body, a high temperature gas cooler, an intelligent active measurement and control system with PLC as a main controller, a transmitter and a leakage detection instrument. The external air source device is connected with the air inlet of the pressure reducing valve through the high-pressure air pipe, and the air outlet of the pressure reducing valve is connected with the ultrahigh-temperature electric heating system. The far end of the electric heating system is connected with the instantaneous switching pipeline through a bolt flange, the outlet end of the switching pipeline is connected with the sealing test tester tool body, and various sensors and transmitter elements are installed on the test tester tool. In addition, a leakage outlet at the bottom of the tester tool is connected with a high-temperature gas cooler and finally connected to a leakage detection instrument. And a transmitter element arranged on the tester test tool is connected into an intelligent active measurement and control system which takes the PLC as a main controller to realize active control monitoring and data real-time reading of the whole sealing test process. Finite element simulation is used for carrying out steady-state thermal analysis on a tester test tool temperature field (the actual measured temperature of a measurement and control system temperature transmitter is compared with the temperature rise data of a software simulation tester temperature field), and a simulation and test mutual verification method is adopted to improve the design efficiency and the test accuracy.
The comprehensive test system for the leakage characteristic of the aerospace porous sealing material is characterized in that a built test flow platform mainly comprises an external air source device (a high-pressure inflating pump and a high-power air compressor) for providing fluid required by the test and outputting controllable parameters of fluid pressure and volume flow; the pressure reducing valve plays a role of turning, and controls the pressure at the upstream of the gas circuit to match the actual test pressure at the downstream; the independently designed high-temperature electric heater is used for heating the target gas to meet the temperature requirement of the test, and the design temperature is up to 1200 ℃; the tester testing tool part is a core device of the invention and is used for bearing and installing a sealing element to be tested and providing a testing space; the high-temperature cooler is designed for cooling high-temperature leakage gas so as to prevent damage to a leakage test instrument; a core control center taking a PLC (programmable logic controller) as a main body is carried in the main control cabinet, and a comprehensive measurement and control system integrating control, monitoring, data recording, screen display and man-machine interaction is provided, wherein the specific test process is shown in figure 2, and the system entity is shown in figure 1. The device comprises a tester tool body 1, an ultrahigh-temperature electric heater 3, an electric heater outlet temperature transmitter 5, a high-power air compressor 6, human-computer interaction upper computer test software 7, a main control cabinet 8, high-temperature-resistant heat-insulating gloves 9 and a fire extinguisher 10 for test safety. The high-power air compressor is connected with the ultrahigh-temperature electric heater through the high-pressure air pipe, the electric heater outlet temperature transmitter is installed on the ultrahigh-temperature electric heater and used for monitoring outlet temperature, and test software of the human-computer interaction upper computer is embedded into the main control cabinet to realize active control of a test process. Finally, the high-temperature-resistant heat-insulating gloves and the fire extinguisher for test safety are used for ensuring the safety of test personnel.
The seal test tester tool mainly comprises the following components: the device comprises an inlet chamber pressure transmitter 12, porous sealing materials (3 types) to be tested 18, a bottom plate positioning block (with various thicknesses) 19, an inlet chamber air outlet pipeline 20, an upper heater gland 21, a phlogopite electric heater 22, a sealing tool upper cover 23, two side positioning blocks 24, a sealing tool box base 25, a tool bottom surface heat insulation felt 26 and a bottom leakage pipeline 27. Firstly, a sealed tooling box base 25 is placed on a tooling bottom surface heat insulation felt 26, a bottom leakage pipeline 27 is connected to the lower end of the box base through threads, an inlet chamber pressure transmitter and an inlet chamber air outlet pipeline are in threaded connection to the side surface and the rear end surface of the box base in the same way, positioning blocks on two sides are installed at the upper end and the lower end of a bottom plate positioning block after the mounting bottom plate positioning block is arranged inside the box base, a phlogopite electric heater is installed between an upper heater gland and a sealed tooling upper cover, and finally the upper cover is integrally connected to the tooling box base through thread pre-tightening, which is detailed as shown in figure 5. The main structure of the test tool is made of No. 45 carbon steel by design and processing, and a two-dimensional design drawing is shown in figure 3. The method comprises the steps of firstly placing a box base of a test tool, selecting a bottom plate positioning block and two side positioning blocks according to different types of sealing elements to be tested in a matched mode, and mounting and fixing the bottom plate positioning block and the two side positioning blocks in the box base through thread pretension. All designs on bottom plate locating piece and the both sides locating piece have sealed recess, pastes high temperature resistant rubber sealing strip in sealed recess, realizes that the inside circumference of testing arrangement is sealed, installs the sealing member that awaits measuring this moment between the locating piece of both sides. And finally, installing an upper cover of the sealing tool and pre-tightening the upper cover to a circle of threads, wherein the installation of the tester tool is finished.
The instantaneous switching pipeline mainly comprises the following parts: the installation position in the whole test process is shown as a guide wire 2 in fig. 3, and the high-temperature electric heating system is installed in the area between the air outlet end of the ultra-high-temperature electric heating system and the sealing test tester tool, so that the high-temperature air flow can be instantly switched to flow direction after reaching the target test temperature, and the high-temperature air flow is introduced into the sealing test tool to complete the subsequent leakage detection. The concrete components are as follows: a long pipe 11 for discharging hot air, a heat insulation pad 13, a flange 14 with an internal thread, a short pair of threads 15, a high temperature resistant combined tee joint 16 and a long pair of threads 17. Use high temperature resistant combination tee bend as installation center, both ends are connected and are short to silk and long to the silk about the tee bend, and the silk flange is connected in another free end connecting band of long pair silk, and the same reason is short to a silk free end and connect an interior silk flange equally, and whole switching pipeline passes through heat insulating mattress flange joint in sealed test fixture body. High-temperature fluid enters from the inner thread flange 14 and continuously flows out through the long pipe 11 for discharging hot air, the temperature of the air outlet is monitored in real time in the process, the high-temperature hot air is reversed through the high-temperature-resistant combined tee joint 16 when the air outlet temperature reaches the target test temperature, the end of the long pipe 11 for discharging hot air is closed, and the end of the long paired wires 17 is opened, so that the prepared high-temperature hot air is switched instantly and introduced into the sealing test tool main body, and the subsequent test of the sealing element to be tested is completed. The design of the switching mechanism avoids the situation that the sealing element to be tested is heated continuously to cause heat loss, and removes uncontrollable factors irrelevant to the test.
The electric heater of the phlogopite (mica sheet and heating wire) and the electronic component transmitter are designed and calculated independently and an electric heating temperature control system based on the mica heating wire is built in order to meet the heat preservation requirement of the device in the whole testing process. The electric heating control program is started through a general instruction sent by the control cabinet, the temperature value is recorded and transmitted in real time through the temperature transmitter, the target heat preservation temperature of 200 ℃ can be reached by the sealing test tool after 15 minutes under the continuous operation of electric heating, and the whole temperature control process adopts a proportional-integral-derivative closed-loop control mode, so that the temperature of 200 ℃ can be stably kept unchanged as long as the temperature set value is unchanged. Furthermore, in order to match the intelligent property of the measurement and control system, various electronic transmitters are preferably selected to achieve real-time and accurate monitoring of the test state parameters. High-precision electronic pressure gauges are used for monitoring pressure in the testing process, high-precision thermal mass flow controllers are used for leakage detection, and wide-range thermocouple components are used for temperature monitoring. All output signals of the various transmitter elements are connected to a PLC of the control cabinet, and the state parameters are displayed in real time through an upper computer human-computer interaction interface on the basis of the stability and robustness of the control system. And finally, automatically recording the test data by a test finishing program, storing the test data as a text file, and preparing for post data processing and analysis.
According to the finite element-based temperature field thermal analysis method, the temperature distribution and deformation conditions of the whole tool and the base of the box body are analyzed and calculated by means of simulation before the sealing test tool is processed and manufactured, and particularly, the temperature distribution and deformation conditions are shown in fig. 6. The structural detail design of the tester tool is optimized through a simulation result, the thermal deformation and the loaded deformation of the device are reasonably considered, and the size compensation is carried out, so that the tightness of each assembling contact surface of the sealing tool in the processes of installation, continuous heating, heat preservation and high-temperature test is ensured, and the problem of leakage caused by the sealing failure of the device is avoided. Due to the introduction of a finite element simulation technical means, the design pressure is relieved to a great extent, the production progress of the sealing test tool is accelerated, the investment of production equipment is reduced, and the utilization rate of the equipment is improved.
Compared with the prior art, the measurement and control system and the measurement and control method for evaluating the leakage characteristics of the porous sealing material of the spacecraft, provided by the invention, have the following beneficial effects:
1. the high-temperature heat seal leakage test and evaluation comprehensive test system built by adopting autonomous design can meet the requirement of a full-period sealing performance test applicable to typical heat seal materials of spacecrafts. Hardware and software, data acquisition instruments and equipment, test schemes and procedures are mature, and a set of complete sealing material performance detection method is developed and independently mastered.
2. The tool is designed and researched autonomously to meet the target test requirement, the tool can realize the leakage characteristic test of three porous sealing materials, two rectangular porous sealing elements and a long and thin sealing rope are installed in a matching mode by replacing different two side positioning blocks, the function of continuously testing different sealing elements by the same test tool is realized, and the test tool has strong interchangeability.
3. The matching combination design of the bottom plate positioning block and the positioning blocks at the two sides meets the test requirements of different compression ratios of the sealing material to be tested. The compression ratio can be continuously changed from 5%, 15% and 30% by selecting the bottom plate positioning blocks with different thicknesses, the thicker the bottom plate positioning blocks are, the larger the compression ratio is, the positioning blocks on the two sides are used for limiting the freedom degrees of the front and back surfaces of the sealing material, and the compression ratio of a test target is finally accurately set by matching with the pre-tightening of the upper cover bolt of the sealing tool.
4. The design of the high-temperature fluid air inlet section instantaneous switching pipeline can effectively relieve the heat loss of the sealing material to be tested in a long-time high-temperature environment, the sealing tool is instantly introduced to start testing after the temperature reaches the target testing temperature, and high-temperature hot air is exhausted to air when the temperature does not reach the target temperature. The design not only meets the test requirement, but also protects the sample to be tested, and simultaneously improves the accuracy of test data.
5. The processing mode of innovatively combining finite element simulation and test testing, simulating prediction, guiding test and testing verification simulation, wherein the finite element simulation and the test testing are combined in parallel is an innovative idea in the field of high-temperature heat seal testing.
Drawings
FIG. 1 is a schematic diagram of a high-temperature heat-seal measurement and control system;
FIG. 2 is a schematic flow chart of a test measurement and control system;
FIG. 3 is a simulation diagram of a typical equipment design of a measurement and control system;
FIG. 4 is a schematic view of a leak path for a seal test of a porous sealing material;
FIG. 5 is a schematic view of a machining and assembling structure of a sealing tool of the tester;
FIG. 6 is a finite element temperature field simulation map.
Wherein: p1, outlet pressure of a high-pressure gas source; q v1 The volume flow of the high-pressure gas source outlet; temperature in T1, super high temperature electric heater cavity(ii) a T2, the outlet temperature of the ultrahigh-temperature electric heater; t3, the temperature of the electric heater back plate of the sealing test tool is measured; p2, testing pressure inside the seal tester tool; t4, cooling the leaked gas; q v2 And the volume flow of the leaked gas is accumulated.
Note: in FIG. 6, 28-seal test tool finite element meshing, 29-seal tool integral steady state thermal analysis temperature distribution cloud chart under 200 ℃ thermal load working condition, 30-seal tool box base temperature distribution cloud chart under 200 ℃ heat source preloading, 31-test tool actual installation schematic diagram, 32-test tool to-be-tested seal element installation schematic diagram, and 33-seal tool box base heating schematic diagram.
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 a leakage characteristic test of the square aerospace porous sealing material as an example, a sealing test tool, a sealing element installation mode, a measurement and control system function, a test process and a method are specifically explained. Assembling a tester tool and a to-be-tested porous sealing element on each structural unit shown in figure 5, pasting a high-temperature-resistant sealing rubber strip at the position of a sealing groove of a tool main body, installing an upper cover pre-tightening bolt, checking a leakage pipeline at the bottom of the tool and the wiring condition of a test instrument, opening a high-power air compressor to be connected with an air pipeline, supplying power to a main control cabinet, a high-temperature electric heater and a PC (personal computer) upper computer, finally opening an upper computer program measurement and control panel, and completing preparation before testing software and hardware. And (3) normal temperature test: and installing a sealing element to be tested, and selecting a proper bottom plate positioning block and positioning blocks on two sides to realize the setting of the compression rate. And opening an air outlet valve of the air compressor, regulating pressure through a pressure reduction valve, introducing into the sealing test tool, maintaining for 1min after the test state is stable, testing for 2min for each test pressure, continuously boosting and keeping the same test time until the normal-temperature test is finished. And (3) high-temperature testing: before formal testing, firstly, opening a phlogopite electric heater positioned on an upper cover of a sealing tool through a main control cabinet to continuously raise the temperature to 200 ℃, keeping the temperature unchanged, opening an ultrahigh-temperature electric heating system, as shown in a reference numeral 3 in figure 3, opening an air compressor valve to continuously introduce air flow when the temperature reaches a target testing temperature, opening an instantaneous switching pipeline to instantaneously guide high-temperature hot air flow originally exhausted to air to the sealing tool to start testing when the temperature of outlet air reaches a final testing temperature, ending the test after 2min of testing, closing an air circuit and the electric heating system, cutting off all power supplies, and recording and storing test data.
Example 2: the leakage characteristic test of the long-strip-shaped spaceflight porous sealing rope is taken as an example, and the sealing test tool, the installation mode of the sealing element, the function of the measurement and control system, the test process and the method are concretely explained. The test process is the same as that of the embodiment 1, and is divided into normal temperature test and high temperature test, and the software and hardware installation and debugging process and the method are similar to those of the embodiment 1. The difference lies in the selection of the positioning blocks at two sides. Need select and install the side locating piece with rectangular sealing rope adaptation in this embodiment, this locating piece bottom is opened has square groove and is used for fixing the sealing material that awaits measuring, with rectangular sealing rope left and right sides both ends card in the square groove of both sides locating piece, all the other mounting means remain unchanged, and the assembly is accomplished and is started the test, preserves and takes notes experimental data at last.
Claims (6)
1. A measurement and control system for evaluating leakage characteristics of a porous sealing material of a spacecraft is characterized in that: the device comprises an external air source device, a pressure reducing valve, an ultrahigh temperature electric heating system, an instantaneous switching pipeline, a seal test tester tool body, a high temperature gas cooler, an intelligent active measurement and control system with a PLC as a main controller, a transmitter and a leakage detection instrument; the external air source device is connected with an air inlet of the pressure reducing valve through a high-pressure air pipe, and an air outlet of the pressure reducing valve is connected with the ultrahigh-temperature electric heating system; the far end of the electric heating system is connected with the instantaneous switching pipeline through a bolt flange, the outlet end of the switching pipeline is connected with the seal test tester tool body, and each sensor and the transmitter element are installed on the test tester tool; a leakage outlet at the bottom of the tester tool is connected with a high-temperature gas cooler and connected to a leakage detection instrument; a transmitter element arranged on a tester test tool is accessed into an intelligent active measurement and control system which takes a PLC as a main controller to realize active control monitoring and data real-time reading of the whole sealing test process; finite element simulation is used for carrying out steady-state thermal analysis of the temperature field of the tester testing tool, and a simulation and test testing mutual verification method is adopted to improve the design efficiency and the test accuracy.
2. The measurement and control system for evaluating the leakage characteristic of the porous sealing material of the spacecraft according to claim 1, wherein: the comprehensive test system for the leakage characteristic of the aerospace porous sealing material is characterized in that a built test flow platform comprises an external air source device for providing fluid required by the test, and controllable parameters are output as fluid pressure and volume flow; the pressure reducing valve controls the pressure upstream of the gas circuit to match the actual test pressure downstream; the high-temperature electric heater is used for heating the target gas to meet the temperature requirement of the test; the tester testing tool part is a core device and is used for bearing and installing a sealing element to be tested and providing a testing space; the high temperature cooler is designed to cool the high temperature blow-by gases; the main control cabinet is internally provided with a core control center which takes a PLC as a main body, and a comprehensive measurement and control system which integrates control, monitoring, data recording, screen display and man-machine interaction is provided; the high-power air compressor is connected with the ultrahigh-temperature electric heater through the high-pressure air pipe, an outlet temperature transmitter of the electric heater is arranged on the ultrahigh-temperature electric heater and used for monitoring the outlet temperature, and test software of a human-computer interaction upper computer is embedded into the main control cabinet to realize active control of the test process; the high-temperature-resistant heat-insulating gloves and the fire extinguisher for test safety are used for ensuring the safety of test personnel.
3. The measurement and control system for evaluating the leakage characteristics of the porous sealing material of the spacecraft according to claim 1, wherein: seal test tester frock includes: the device comprises an inlet chamber pressure transmitter, a to-be-tested porous sealing material, a bottom plate positioning block, an inlet chamber air outlet pipeline, an upper heater gland, a phlogopite electric heater, a sealing tool upper cover, two side positioning blocks, a sealing tool box base, a tool bottom surface heat insulation felt and a bottom leakage pipeline; the sealed tooling box base is placed on a tooling bottom surface heat insulation felt, a bottom leakage pipeline is connected to the lower end of the box base through a thread, an inlet chamber pressure transmitter and an inlet chamber air outlet pipeline are in thread connection with the side surface and the rear end surface of the box base in the same way, positioning blocks at two sides are installed at the upper end and the lower end of the bottom plate positioning block after the bottom plate positioning block is installed in the box base, a phlogopite electric heater is installed between an upper heater gland and a sealed tooling upper cover, and the upper cover is integrally connected to the tooling box base through a thread in a pre-tightening way; placing a box body base of the testing tool, selecting a bottom plate positioning block and two side positioning blocks according to different types of sealing elements to be tested in a matched mode, and mounting and fixing the bottom plate positioning blocks and the two side positioning blocks in the box body base through threads in a pre-tightening mode; sealing grooves are formed in the bottom plate positioning blocks and the positioning blocks on the two sides, high-temperature-resistant rubber sealing strips are pasted in the sealing grooves, circumferential sealing inside the testing device is achieved, and the sealing elements to be tested are installed between the positioning blocks on the two sides; and installing an upper cover of the sealing tool and pre-tightening the upper cover to the annular circle of threads, wherein the installation of the tester tool is finished.
4. The measurement and control system for evaluating the leakage characteristic of the porous sealing material of the spacecraft according to claim 1, wherein: the instantaneous switching pipeline is arranged in a region between the air outlet end of the ultrahigh-temperature electric heating system and the seal test tester tool, and is used for instantaneously switching the flow direction of high-temperature air flow after the high-temperature air flow reaches a target test temperature and introducing the high-temperature air flow into the seal test tool to complete subsequent leakage detection; taking a high-temperature-resistant combined tee joint as an installation center, connecting a short pair of wires and a long pair of wires at the left end and the right end of the tee joint, connecting the other free end of the long pair of wires with an inner wire flange, similarly connecting the free ends of the short pair of wires with one inner wire flange, and connecting the whole switching pipeline to a sealing test tool body through a heat insulation pad flange; high-temperature fluid enters from the internal thread flange and continuously flows out through the long pipe for discharging hot air, the temperature of the air outlet is monitored in real time in the process, the high-temperature hot air is reversed through the high-temperature-resistant combined tee joint when the air outlet temperature reaches the target test temperature, the long pipe end for discharging hot air is closed, and meanwhile, the long wire end is opened, so that the prepared high-temperature hot air is switched and introduced into the sealing test tool main body instantly, and the subsequent test of the sealing element to be tested is completed.
5. The measurement and control system for evaluating the leakage characteristic of the porous sealing material of the spacecraft according to claim 1, wherein: the phlogopite electric heater and the electronic component transmitter start an electric heating control program through a general instruction sent by the control cabinet, record and transmit a temperature value in real time through the temperature transmitter, and the sealing test tool can reach a target heat preservation temperature of 200 ℃ after 15 minutes under the continuous operation of electric heating, and can stably keep 200 ℃ without fluctuation as long as a temperature set value is unchanged due to the fact that a proportional-integral-derivative closed-loop control mode is adopted in the whole temperature control process; the high-precision electronic pressure gauges are used for monitoring pressure in the testing process, the high-precision thermal mass flow controllers are used for leakage detection, and the large-range thermocouple elements are used for temperature monitoring; and the test finishing program automatically records the test data and stores the test data as a text file to prepare for later data processing and analysis.
6. The measurement and control system for evaluating the leakage characteristics of the porous sealing material of the spacecraft according to claim 1, wherein: according to the finite element-based temperature field thermal analysis method, the temperature distribution and deformation conditions of the whole tool and a box body base are analyzed and calculated by means of simulation means before the sealing test tool is processed and manufactured; the structural detail design of the tester tool is optimized through a simulation result, the thermal deformation and the loaded deformation of the device are considered, and the size compensation is carried out, so that the sealing tool is ensured to be tight and compact in each assembling contact surface in the processes of installation, continuous heating and heat preservation and high-temperature test.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210660208.0A CN115144128A (en) | 2022-06-13 | 2022-06-13 | Measurement and control system and method for leakage characteristic evaluation of spacecraft porous sealing material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210660208.0A CN115144128A (en) | 2022-06-13 | 2022-06-13 | Measurement and control system and method for leakage characteristic evaluation of spacecraft porous sealing material |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115144128A true CN115144128A (en) | 2022-10-04 |
Family
ID=83408073
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210660208.0A Pending CN115144128A (en) | 2022-06-13 | 2022-06-13 | Measurement and control system and method for leakage characteristic evaluation of spacecraft porous sealing material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115144128A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116678802A (en) * | 2023-08-03 | 2023-09-01 | 常州市建筑材料研究所有限公司 | Prefabricated inspection well impermeability detection device and detection method thereof |
-
2022
- 2022-06-13 CN CN202210660208.0A patent/CN115144128A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116678802A (en) * | 2023-08-03 | 2023-09-01 | 常州市建筑材料研究所有限公司 | Prefabricated inspection well impermeability detection device and detection method thereof |
| CN116678802B (en) * | 2023-08-03 | 2023-11-14 | 常州市建筑材料研究所有限公司 | Prefabricated inspection well impermeability detection device and detection method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112903208B (en) | Test system and method for realizing performance simulation test of high-temperature metal sealing ring | |
| CN103207054B (en) | High temperature structure sealing performance ground-based simulation testing device and method | |
| CN102840982B (en) | Service life verification tester for ceramic bearing | |
| CN115144128A (en) | Measurement and control system and method for leakage characteristic evaluation of spacecraft porous sealing material | |
| CN104101470A (en) | Pipeline flange test system | |
| CN105423018A (en) | Leakage detecting device of high-temperature flange connecting system | |
| CN102507164B (en) | Comprehensive quickly-disassembled clamping hoop test system | |
| CN109580228B (en) | Cold test run test system for solid rocket engine | |
| CN107328671A (en) | A kind of pilot system for being used to test the bellows fatigue life for bearing alternating pressure | |
| CN105181565A (en) | Combined type temperature, air pressure and irradiation three integrated experiment test system | |
| CN112730075B (en) | Pressure testing device and method for aviation pipeline connecting piece system | |
| CN113848065A (en) | Multi-dimensional dynamic coupling experiment system and method for supplying working medium for aerospace engine | |
| RU2286290C1 (en) | Method of manufacture of three-layer panel | |
| CN101487759A (en) | System and method for testing stress, displacement and airtight performance in ultra-low temperature surroundings | |
| CN210863158U (en) | Test device for measuring resistance loss of pipeline of starting system of aircraft engine | |
| Anthony et al. | Modifications and upgrades to the AFRL Turbine Research Facility | |
| CN115508221A (en) | High-temperature sealing performance test device for metal sealing ring | |
| CN202648938U (en) | Thermal state sealing test device of super high temperature hot valve | |
| CN109060578B (en) | Thermal fatigue testing device for cylinder cover of diesel engine | |
| Yin | High Speed Pneumatic Theory and Technology Volume I: Servo System | |
| CN106153318A (en) | Precise bushing valve couple performance test measurement apparatus | |
| CN112903276A (en) | Open turbine blade test equipment | |
| KR101109249B1 (en) | Apparatus for Regulating Concentricity of Pipe and System having the Same | |
| CN213842882U (en) | Pressure-bearing test device for cartridge receiver | |
| Tamasy et al. | Ground-Based Cryogenic Leak Test of Fittings for Cryogenic Fluid Management |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |