CN105181900B - High-temperature thermal radiation testing device and method capable of synchronously and continuously adjusting large-volume temperature and pressure - Google Patents
High-temperature thermal radiation testing device and method capable of synchronously and continuously adjusting large-volume temperature and pressure Download PDFInfo
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- CN105181900B CN105181900B CN201510604654.XA CN201510604654A CN105181900B CN 105181900 B CN105181900 B CN 105181900B CN 201510604654 A CN201510604654 A CN 201510604654A CN 105181900 B CN105181900 B CN 105181900B
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Abstract
The invention relates to a high-temperature thermal radiation testing device and method capable of synchronously and continuously adjusting the large-volume temperature and pressure, and belongs to the technical field of thermal vacuum testing. The device and method are used for vacuum pneumatic thermal loads stressed by an outer layer heat prevention/isolation material and structure of a ground-based simulation aircraft in the flight process from the space environment to the atmospheric layer, and the vacuum environment. Through linkage control over an electromagnetic valve A, an electromagnetic valve B and an electromagnetic valve C capable of being opened and closed quickly on three exhaust pipelines of the exhaust pipeline a, the exhaust pipeline b and the exhaust pipeline c which are connected on the downstream of an exhaust system vacuum pipeline A in parallel and have different calibers and an air supply ball valve on an air supply system vacuum pipeline, the real-time dynamic adjusting function on the cabin pressure of a vacuum testing cabin is achieved successfully, the problem of continuously and dynamically adjusting the pressure environment during orbit change of different heights in the in-orbit and orbit-transfer maneuvering flight process of the aircraft is solved, the vacuum degree of the testing cabin can be adjusted continuously and precisely within a certain vacuum degree range, and the flight environment of an aircraft of a new generation in the process of entering the atmospheric layer again can be simulated more realistically.
Description
Technical field
The present invention relates to big bulk temperature and pressure can synchronize the high temperature heat radiation assay device and the side that continuously adjust
Method, belongs to thermal vacuum test technical field, flies by space environment atmospheric reentry for ground based flight device
During row outer layer anti-/ the true aerothermal load that stood of heat-barrier material and structure and vacuum environment.Described
It is 100-130m that big volume refers to accommodate overall or partial structurtes the volume of 1:1 scale aircraft3Vacuum
Experimental cabin.
Background technology
It is research Aerodynamic Heating and the important hands of anti-/ heat-insulating problem that aircraft reenters thermal environment ground simulation test
One of section, for relative flight test, ground experiment has low cost, high reliability.On the one hand,
Aircraft has to pass through the examination of ground experiment before flight test, and using the result of appraisal as whether opening
The criterion of exhibition flight test.On the other hand, for setting up correct mathematics physics model, need with test as base
Plinth, the accuracy calculated with result of the test inspection and proof theory, provide foundation for designer.Meanwhile, ground
Interview test also be screening anti-/ heat-barrier material kind, determine that anti-/ heat-barrier material and structural behaviour and inspection are anti-/ heat insulation
The important means of product quality, is inspecting pneumatic heating and solar heat protection designed reliability and rational important channel.
In recent years, along with aircraft flight Mach number, orbit maneuver and the improving constantly of flight time in-orbit,
Each Aero-Space big country of the world, in order to improve the anti-/ heat-proof quality of thermally protective materials and assembly, is all evolving
With raising ground simulation test technology and ability, in order to evaluating system for course of new aircraft thermal protection provides more
Effective and reliable technical support.
From the sixties in last century, it is anti-/ heat insulation that external many test chambers all start to develop ground hyperthermia radiation formula
Pilot system, the heater size that this period is developed is less, mostly is " material level " (length × wide overall dimensions
100mm × 100mm), typically it is only used for carrying out the screening of material, aircraft partial structurtes are being carried out
When heat seal performance and heat structure Performance Assessment, by causing, Flight Vehicle Structure is internal produces bigger thermograde,
Temperature data accurately cannot be obtained, especially the aircraft local heat structure of junction, heat seal performance are examined
The error of nuclear test is bigger.
The nineties in last century so far, along with aircraft flight Mach number improve constantly and outer layer anti-/ heat insulation material
Material and the continuous renewal of structure, each Aero-Space big country of the world including China starts to be conceived to build newly
Type ground experiment platform, increases to " contracting is than structural level " (length × wide profile by testpieces size from " material level "
Size 1000mm × 1000mm or Φ 500mm × 1500mm), so as to test flight general ability portion
The heat structure of junction, heat seal performance, along with aerodynamic development, the gas of existing aircraft
Dynamic profile is constantly updated so that the overall dimensions of aircraft constantly increases, in order to obtain more authentic and valid examination
Test data, have experimenter to start to develop aircraft entirety or the experimental condition of partial structurtes of 1:1 size.
Reentry vehicle in early days mostly is inertia reentry trajectory condition, and it is mainly characterized in that the angle of incidence is short again, flies
Row device outer layer is anti-/ and heat-barrier material and structure do not affected by the Thermal incubation effect always adding heat, it is not necessary to it was reentered
Air pressure conditions in journey is accurately simulated, and therefore existing equipment does not possess the most accurately regulation of experimental cabin cabin pressure
Ability.And the change of ballistic conditions during reentering along with a new generation's aircraft, need to do to fly in-orbit for a long time
Row and change rail maneuvering flight.Being continually changing of flight track height so that the vacuum of aircraft local environment
Also at consecutive variations, ultimately result in aircraft outer layer anti-/ thermal physical property parameter of heat-barrier material and anti-/ heat insulation structural
Heat-conductive characteristic also changes in real time with the change of vacuum.Therefore want in ground hyperthermia radiation formula anti-/ heat insulation
On the basis of pilot system, more precisely simulation ground is to rails different in the 100km near space of ground
Steric effect under the conditions of road height, it is necessary to realize experimental cabin cabin pressure and lift with aircraft flight orbit altitude
Time load continuously accurately and regulatory function.
Due to being continuously increased of atmospheric density in ground 100km to ground space, aircraft outer layer is anti-/ every
Hot material and structure become aerothermal load size that rail flight course born by with the lifting of orbit altitude in
Positive correlation trend.And affected by the Thermal incubation effect always adding heat when long-time flight in-orbit, it is desirable to more
For simulate truly reenter for a long time during thermal environment condition residing for aircraft, it is necessary to thermal environment (temperature
Degree) carry out the accurate regulation under vacuum environment.
Therefore, high-quality to complete aircraft and reenter thermal environment ground simulation test, it is necessary to complete vacuum simultaneously
Degree (cabin pressure) and the most accurate of thermal force (temperature) load and regulation, the most time dependent same step
Joint.Aircraft outer layer that especially composite makes is anti-/ insulation product in thermal histories inside stuffing with
Gas form volatilize from matrix the discharge quantity caused bigger time, will to vacuum accurately control produce bigger
Impact.In must ensureing the big volume test cabin under the conditions of certain discharge quantity by technological innovation, thermal force is (warm
Degree) and the synchronization of vacuum (pressure) continuously adjust effect, reenter hot ring with more real simulated flight device
Border.
Summary of the invention
The technology of the present invention solves problem: overcomes the deficiencies in the prior art, proposes big bulk temperature and pressure
Can synchronize high temperature heat radiation assay device and the method continuously adjusted, this system can be to 1:1 scale aircraft
High-temperature hot load under the overall or experimental cabin cabins pressure of partial structurtes (containing material) and vacuum environment (1000 DEG C with
On) the most accurately loading and adjusted in concert when lifting with aircraft flight orbit altitude.
To achieve these goals, the technical solution of the present invention is:
Big bulk temperature and pressure can synchronize the high temperature heat radiation assay device continuously adjusted, this assay device bag
Include control system, vacuum-pumping system, heating system, cooling system, air compensating system, measurement system and true
Empty experimental cabin, heating system and cooling system be respectively positioned in vacuum test cabin, control system, air compensating system,
Vacuum-pumping system and measurement system are positioned at vacuum test out of my cabin；
Described vacuum test cabin is the experimental enviroment needed for testpieces offer, and downstream, vacuum test cabin is by true
Blank pipe road A and valve are connected with vacuum-pumping system, and vacuum line D and valve are passed through in the upstream in vacuum test cabin
Door is connected with air compensating system；
Described control system is connected by cable with vacuum-pumping system, air compensating system, is used for controlling vacuum
Pressure in vacuum test cabin is regulated by extract system and air compensating system, the pressure in needing vacuum test cabin
During reduction, the air compensation simultaneously being reduced air compensating system by the rate of air sucked in required increasing vacuum-pumping system is regulated,
When needing the pressure in vacuum test cabin to increase, increased by the rate of air sucked in required reducing vacuum-pumping system simultaneously
The air compensation of air compensating system regulates；
Described control system is connected by cable with heating system, cooling system, is used for controlling heating system
With cooling system, the temperature in vacuum test cabin is regulated；
Described air compensating system includes QI invigorating main valve, QI invigorating ball valve and air relief valve, and one end of QI invigorating main valve is with true
Being connected by vacuum line between empty experimental cabin, the other end of QI invigorating main valve and one end of QI invigorating ball valve are by true
Blank pipe road connects, and the other end of QI invigorating ball valve is connected by vacuum line with one end of air relief valve, air relief valve
The other end is connected by vacuum line with the input of extraneous high-pressure air source；
Described vacuum-pumping system includes slide valve A, slide valve B, heat exchanger, electromagnetic valve A, electromagnetism
Valve B, electromagnetic valve C, master take out valve A, lead and take out valve B, thick pump group and molecular pump group；Thick pump group includes
Two lobe pumps；Molecular pump group includes a molecular pump and a backing pump；
One end of slide valve A is connected by vacuum line A with vacuum test cabin, the other end of slide valve A
Being connected by vacuum line A with one end of heat exchanger, the other end of heat exchanger passes through with one end of electromagnetic valve A
The vacuum line of a diameter of a connects, and the other end of heat exchanger passes through a diameter of with one end of electromagnetic valve B simultaneously
The vacuum line of b connects, and the other end of heat exchanger the most also passes through a diameter of c's with one end of electromagnetic valve C
Vacuum line connects, a ＞ b ＞ c；The other end of electromagnetic valve A and master take out one end of valve A, master smokes valve B's
One end is connected by vacuum line B, and the other end of electromagnetic valve B and master take out one end of valve A, master takes out valve B
One end connected by vacuum line B, the other end of electromagnetic valve C with main take out one end of valve A, main take out valve B
One end connected by vacuum line B；The diameter of vacuum line A is identical with the diameter of vacuum line B,
Caliber a, b, c be three's and not less than the value of vacuum line A；Master takes out valve A and the main downstream taking out valve B
One lobe pump of each connection；
One end of slide valve B is connected by vacuum line C with vacuum test cabin, the other end of slide valve B
Being connected by vacuum line C with one end of molecular pump, the other end of molecular pump and backing pump pass through vacuum line
C connects；
Described heating system includes Power Regulation equipment and heater, the control that Power Regulation equipment sends according to control system
Output power signal processed heats to testpieces to heater, the power that heater inputs according to Power Regulation equipment；
Cooling system is for cooling down vacuum test cabin；
Described measurement system is connected with heating system by temperature sensor, cable, and measurement system passes through liquid
Body flow transducer, cable are connected with cooling system, and measurement system is used for measuring and recording in vacuum test cabin
Temperature and cooling system in cool down the flow of water；
Described measurement system is connected with vacuum-pumping system by pressure transducer, cable, and system of measuring is led to
Cross gas flow sensor, cable is connected with air compensating system, for measuring and record the pressure in vacuum test cabin
Power, the rate of air sucked in required of vacuum-pumping system and the air compensation of air compensating system；
Described measurement system is connected with control system by cable, in real time by the temperature in vacuum test cabin
The air compensation of degree, pressure, cooling water flow, the rate of air sucked in required of vacuum-pumping system and air compensating system feeds back to control
System processed.
This assay device also includes leak test plant and monitoring system, and monitoring system is positioned at vacuum test cabin, inspection
Leakage equipment is positioned at vacuum test out of my cabin；Described leak test plant is connected with vacuum test cabin by pipeline, is used for
The slip in detection vacuum test cabin and the leakage point position found on vacuum test cabin and vacuum line；Described
Monitoring system by cable with measure system be connected, be used for record the trystate in vacuum test cabin and mistake
Journey.
The diameter of the vacuum line of a diameter of c is according in the anti-heat-barrier material thermal histories on aircraft outer surface
Discharge quantity determine, owing to discharge quantity when anti-heat-barrier material is tested is not more than 100g/s,
Wherein, c is the diameter of vacuum line, and ω is the volume flow of the medium in the vacuum line of a diameter of c, and v is
The flow velocity of the medium in the vacuum line of a diameter of c.
By the vacuum tube with KF25 type snap joint in the middle of the vacuum line connecting molecular pump and backing pump
Road E connects leak detector.
The described heater in heating system include heating element heater and cooled plate, Power Regulation equipment be 10 can
Control silicon class power supply, separate unit 100kW, every corresponding heater of Power Regulation equipment；Heating unit in heater
Part uses 3000W quartz lamp, is formed flat heated by 33 quartz lamps in each heater；Cooled plate position
Both sides in the flat heated that heating element heater is formed；
Cooled plate is sandwich, including metallic plate and the snakelike water-cooled being positioned in the middle of two metallic plates at two ends
Passage, water-cooling channel is with the fin of material with metallic plate；Testpieces is fixed on the water that heating element heater is irradiated
On cold drawing；Control system receives the measurement temperature of the testpieces that temperature sensor is passed back, and control system will be measured
After the design temperature on temperature and testpieces surface compares, obtaining control signal, control is believed by control system
Number sending Power Regulation equipment to, Power Regulation equipment power needed for heating element heater exports, heating element heater is to testpieces
Radiant heat energy is provided, forms the closed loop control of testpieces surface temperature.
Described cooling system includes water-cooled carbon steel pipeline, regulation valve and filter, and filter is arranged on water-cooled
The upstream of carbon steel pipeline, regulation valve is arranged on the downstream of water-cooled carbon steel pipeline.
Assay device carries out the high temperature heat radiation test method that temperature and pressure synchronizes to continuously adjust, and step is:
(1) testpieces of 1:1 size is fixed in the cooled plate that heating element heater is irradiated, by testpieces
It is positioned over together with heater in vacuum test cabin；
(2) goal pressure curve and target temperature profile are input in control system；
(3) vacuum-pumping system, air compensating system, heating system, cooling system and control system are run, by
Control system completes to continuously adjust the synchronization of vacuum test cabin pressure and testpieces surface temperature；
(4) vacuum-pumping system, air compensating system, heating system, cooling system, off-test are closed.
The pressure controlled method in vacuum test cabin is by control system: control system is by vacuum test cabin
Pressure transducer measured value carries out with target pressure value after real-time operation compares, obtaining Stress control amount output letter
Number, Stress control amount output signal is delivered simultaneously to vacuum-pumping system and air compensating system by control system, its
Middle vacuum-pumping system is taken out in real time by rapidly opened and closed control of electromagnetic valve A, electromagnetic valve B and electromagnetic valve C
Tolerance, simultaneously by the real-time air compensation of opening and closing extent control of the QI invigorating ball valve on air compensating system, by bleeding
Amount and air compensation jointly controlled the most dynamically regulation of pressure in vacuum test cabin: during on-test,
In vacuum test cabin, pressure is normal pressure, now opening control, open slide valve A in vacuum-pumping system,
Heat exchanger, electromagnetic valve A, electromagnetic valve B, electromagnetic valve C, master take out valve A, lead and take out valve B and two lobe pumps
To normally open, now in vacuum test cabin, pressure will be gradually reduced；When in vacuum experimental cabin, pressure is down to not
During more than 10Pa, open slide valve B, molecular pump and backing pump in vacuum-pumping system, by vacuum test
In cabin, pressure is evacuated to set ultimate value 1Pa, opens the air relief valve in air compensating system, QI invigorating ball valve and QI invigorating master
Valve, wherein decompressor and QI invigorating main valve are full-gear, are automatically adjusted by control system according to air compensation size
The opening and closing degree of QI invigorating ball valve, in process of the test, the change according to aircraft altitude carries out the continuous of pressure
Regulation.
In process of the test, change according to aircraft altitude carries out the method that pressure continuously adjusts and is: when needing
During pressure in vacuum test cabin to be increased, by increasing the aperture of QI invigorating ball valve, raise according to pressure simultaneously
Speed closes electromagnetic valve A or electromagnetic valve B or electromagnetic valve C selectively, or simultaneously close off electromagnetic valve A and
Electromagnetic valve B or electromagnetic valve A and electromagnetic valve C or electromagnetic valve B and electromagnetic valve C or regulation three can be rapidly opened and closed
The opening/closing time of electromagnetic valve make vacuum test cabin in pressure rise；
When pressure in needs reduce vacuum test cabin, by closing or adjust and reduce the opening and closing degree of QI invigorating ball valve,
Extend rapidly opened and closed electromagnetic valve A, electromagnetic valve B, the ETAD expected time of arrival and departure of electromagnetic valve C simultaneously, make rate of air sucked in required be more than
Air compensation and realize；Concrete control algolithm is: by the actual measurement of gas pressure in acquisition vacuum test cabin in real time
Value, compares with target pressure value, and the deviation value obtained is as the input quantity of control system, for QI invigorating
For system, the opening information that output controlled quentity controlled variable is QI invigorating ball valve of control system, opening of regulation QI invigorating ball valve
Degree, thus regulate air compensation size；For vacuum-pumping system, the output control signal of control system
Electromagnetic valve A, electromagnetic valve B, the service time of electromagnetic valve C are controlled；By to air compensating system and true
Jointly controlling of empty extract system, it is achieved the most dynamically purpose of gas pressure in regulation vacuum test cabin, complete
Become a Closed loop operation, repeat and realize whole control process.
The method that testpieces surface temperature is regulated by control system is: control system is by the temperature on testpieces surface
Sensor measured value carries out with target temperature value after real-time operation compares, obtaining temperature controlled quentity controlled variable output signal,
And temperature controlled quentity controlled variable output signal is sent to Power Regulation power supply, by Power Regulation equipment needed for heating element heater exports
Power, heating element heater provides radiant heat energy according to the power obtained to testpieces, forms testpieces surface temperature
Closed loop control.
Temperature control method is: during on-test, first by pressure modulation initial target value in vacuum test cabin,
Start heating system and cooling system, the radiant heat produced under different input power by regulation heating element heater
Surface of test piece temperature can be regulated, during must be by time zero-bit corresponding for pressure target value and temperature target
Corresponding time zero-bit matches, with this ensure the aircraft obtained reenter during orbit altitude change time
Pressure environment matches with Aerodynamic Heating environment.
Beneficial effect
(1) present invention is by tri-differences of a, b, c of vacuum-pumping system vacuum line A downstream parallel connection
On bore vacuum suction pipeline can be on rapidly opened and closed electromagnetic valve A, B, C and air compensating system vacuum line
The coordinated signals of QI invigorating ball valve, is successfully realized the Real-time and Dynamic regulatory function of cabin, vacuum test cabin pressure, solves
Aircraft in-orbit with become trailer and move in flight course pressure environment during residing differing heights Orbit revolutionary
Dynamically regulate problem continuously, in the range of certain vacuum degree, achieve the continuous of experimental cabin vacuum (cabin pressure)
Accurately regulation, it is possible to flight (pressure) ring during simulation a new generation aircraft atmospheric reentry the most truly
Border.
(2) present invention is by under electromagnetic valve A, electromagnetic valve B and electromagnetic valve C in parallel for vacuum line A downstream
The pipe diameter determing swimming each self-corresponding vacuum line a, b, c is different size, uses PWM generator to lead to
The switch gap crossing control electromagnetic valve A, electromagnetic valve B and electromagnetic valve C carries out amount control switch time, will
Switching value pwm signal is delivered to electromagnetic valve A, electromagnetic valve B and electromagnetic valve C respectively and reaches control and bleed speed
The purpose of rate size.
(3) monitoring system in the present invention and leak test plant can be to the protections of other testing equipments with repair
To positive role.
(4) gas that the air compensating system in the present invention supplements is noble gas, preferably nitrogen.In rough vacuum
Under the conditions of hot test during, nitrogen can hinder the reaction between testpieces surfacing and oxygen, protect
Confirmatory test safety.
(5) present invention uses testpieces surface temperature closed loop control, is effectively increased testpieces surface temperature
Control accuracy and response speed, it is possible to carry out synchronizing control with the function that synchronization continuously adjusts of cabin, vacuum test cabin pressure
System, the Aerodynamic Heating environment during combined simulation aircraft atmospheric reentry and surface pressing environment.
(6) the high temperature heat radiation test method that the temperature and pressure in the present invention synchronizes to continuously adjust has specific heat
Environment (temperature) and orbit altitude (pressure) are simulated respectively and are simulated effect more really.Especially for needs
Making the aircraft of new generation flying for a long time and becoming rail maneuvering flight in-orbit, its outer layer is anti-/ the hot thing of heat-barrier material
Property situation that parameter and anti-/ heat-conductive characteristic of heat insulation structural changes in real time with the change of ambient pressure will more
It is applicable.
(7) in the present invention, change according to aircraft altitude carries out the method that pressure continuously adjusts is to control
System is realized by the QI invigorating speed controlling the vacuum-pumping system speed of exhaust and air compensating system simultaneously.The party
The aircraft outer layer that method can overcome composite to make prevents/insulation product inside stuffing in thermal histories
Volatilizing from matrix in gaseous form, when producing relatively final relief amount produce the accurately control of vacuum is bigger
Impact.
(8) control system in the present invention can (pressure target value be corresponding according to unified target zero moment
The time zero-bit time zero-bit corresponding with temperature target matches) to pressure and testpieces in vacuum test cabin
Surface temperature is controlled.
(9) for aircraft outer layer anti-/ heat-barrier material and the thermal environment ground simulation test of structure, infrared spoke
Penetrate the Assessment that heat run mode is the important ground simulation test of one of which.Employing infra-red radiation adds
Aerodynamic Heating in by the use of thermal means simulated flight device flight course or other heating environments, be the base from energy coincidence
Present principles is set out, the most truly the heat transfer mode of simulated flight device inside configuration.In vacuum test cabin
Middle employing radiant heating pattern is capable of aircraft section structure entirety and local 1:1 large-scale experiment part
/ heat insulation test is prevented on the ground of the vacuum load loading Tong Bu with thermal force of (Φ 1500mm × 4500mm).
Accompanying drawing explanation
The composition schematic diagram of the assay device of Fig. 1 present invention；
Fig. 2 (a) is the right view in vacuum test cabin；
Fig. 2 (b) is the left view in vacuum test cabin；
Fig. 3 be air compensating system composition and with the connection diagram in vacuum test cabin；
Fig. 4 is the control block diagram of air compensating system；
Fig. 5 be vacuum-pumping system composition and with the connection diagram in vacuum test cabin；
Fig. 6 is the control block diagram of vacuum-pumping system；
Fig. 7 is the composition schematic diagram of heating system；
Fig. 8 is the control block diagram of heating system；
Pressure energy curve chart in vacuum test cabin when Fig. 9 is vacuum-pumping system work；
The controlling curve figure of pressure in vacuum test cabin when Figure 10 is testpieces material surface difference discharge quantity；
Figure 11 (a) is metallographictest part material model skin temperature profile figure；
Figure 11 (b) is nonmetal testpieces material model skin temperature profile figure；
Figure 12 is testpieces surface temperature control curve chart.
Detailed description of the invention
Big bulk temperature and pressure can synchronize the high temperature heat radiation assay device continuously adjusted, this assay device bag
Include control system, vacuum-pumping system, heating system, cooling system and vacuum test cabin, also include QI invigorating
System；Heating system and cooling system are respectively positioned in vacuum test cabin, control system, air compensating system and vacuum
Extract system is positioned at vacuum test out of my cabin, and this pilot system can also include leak test plant, measurement system and prison
Viewing system, monitoring system is positioned at vacuum test cabin, and measurement system and leak test plant are positioned at vacuum test out of my cabin；
Described vacuum test cabin is the experimental enviroment needed for testpieces offer, and downstream, vacuum test cabin is by true
Blank pipe road A and valve are connected with vacuum-pumping system, and vacuum line D and valve are passed through in the upstream in vacuum test cabin
Door is connected with air compensating system；
Described control system is connected by cable with vacuum-pumping system, air compensating system, is used for controlling vacuum
Pressure in vacuum test cabin is regulated by extract system and air compensating system, the pressure in needing vacuum test cabin
During reduction, the air compensation simultaneously being reduced air compensating system by the rate of air sucked in required increasing extract system is regulated, when needing
When wanting the pressure in vacuum test cabin to increase, increase air compensating system by the rate of air sucked in required reducing extract system simultaneously
Air compensation regulate, supplement gas be noble gas, preferably nitrogen；
Described control system is connected by cable with heating system, cooling system, is used for controlling heating system
With cooling system, the temperature in vacuum test cabin is regulated；
Described leak test plant is connected with vacuum test cabin by pipeline, for detecting the leakage in vacuum test cabin
Rate and the leakage point position found on vacuum test cabin and vacuum line；
Described measurement system is by temperature sensor, liquid flow sensor, cable and heating system and cold
But system connects, for measuring and record the flow cooling down water in the temperature in vacuum test cabin and cooling system；
Described measurement system is by pressure transducer, gas flow sensor, cable and vacuum-pumping system
Connect with air compensating system, for measuring and record pressure in vacuum test cabin, the bleeding of vacuum-pumping system
Amount and the air compensation of air compensating system；
Described measurement system is connected with control system by cable, in real time by the temperature in vacuum test cabin
The air compensation of degree, pressure, cooling water flow, the rate of air sucked in required of vacuum-pumping system and air compensating system feeds back to control
System processed；
Described monitoring system is connected with the system of measurement by cable, for recording the test in vacuum test cabin
State and process；
Described air compensating system includes QI invigorating main valve, QI invigorating ball valve and air relief valve, and one end of QI invigorating main valve is with true
Being connected by vacuum line between empty experimental cabin, the other end of QI invigorating main valve and one end of QI invigorating ball valve are by true
Blank pipe road connects, and the other end of QI invigorating ball valve is connected by vacuum line with one end of air relief valve, air relief valve
The other end is connected by vacuum line with the input of pressure-air；
Described vacuum-pumping system includes slide valve A, slide valve B, heat exchanger, electromagnetic valve A, electromagnetism
Valve B, electromagnetic valve C, master take out valve A, lead and take out valve B, thick pump group and molecular pump group；Thick pump group includes
The lobe pump that bench-types No. two are identical；Molecular pump group includes a molecular pump and a backing pump；Wherein lobe pump,
Molecular pump and backing pump are the matured product of Edward company of the U.S., and lobe pump model is
GXS450/4200, molecular pump model is ixa2206c, and backing pump model is GXS160；
One end of slide valve A is connected by vacuum line A with vacuum test cabin, the other end of slide valve with change
One end of hot device is connected by vacuum line A, and the other end of heat exchanger passes through diameter with one end of electromagnetic valve A
Vacuum line for a connects, and the other end of heat exchanger passes through a diameter of b's with one end of electromagnetic valve B simultaneously
Vacuum line connects, and the other end of heat exchanger passes through the vacuum tube of a diameter of c with one end of electromagnetic valve C simultaneously
Road connects, caliber a ＞ b ＞ c；The other end of electromagnetic valve A and master take out one end of valve A, master smokes valve B's
One end is connected by vacuum line B, and the other end of electromagnetic valve B and master take out one end of valve A, master takes out valve B
One end connected by vacuum line B, the other end of electromagnetic valve C with main take out one end of valve A, main take out valve B
One end connected by vacuum line B；The diameter of vacuum line A is identical with the diameter of vacuum line B,
The value of the caliber a+b+c value not less than vacuum line A；The main valve A that takes out respectively connects with the main downstream taking out valve B
One lobe pump；The diameter on the tubule road that diameter is minimum is heated according to the anti-heat-barrier material on aircraft outer surface
During discharge quantity determine, according to existing engineering experience,Wherein, c is vacuum line
Diameter, ω is the volume flow of the medium in the vacuum line of a diameter of c, and v is the vacuum tube of a diameter of c
The flow velocity of the medium in road.
One end of slide valve B is connected by vacuum line C with vacuum test cabin, the other end of slide valve B
Being connected by vacuum line C with one end of molecular pump, the other end of molecular pump and backing pump pass through vacuum line
C connects, true by with KF25 type snap joint in the middle of the vacuum line connecting molecular pump and backing pump
Blank pipe road E connects leak detector, and leak detector is the matured product of ADIXEN company of France, and leak detector model is
ASM GRAPH。
Described heating system includes Power Regulation equipment and heater, and wherein heater includes heating element heater and water-cooled
Plate, Power Regulation equipment choosing controllable silicon class power supply, separate unit 100kW, 10 amount to 1MW, and every Power Regulation sets
A standby corresponding heater；Heating element heater in heater uses 3000W quartz lamp, in each heater
Flat heated is formed by 33 quartz lamps；Cooled plate is positioned at the both sides of the flat heated that heating element heater is formed；
Cooled plate is sandwich, including metallic plate and the snakelike water-cooling channel being positioned in the middle of two metallic plates at two ends,
Water-cooling channel is with the fin of material with metallic plate；Testpieces is fixed in the cooled plate that heating element heater is irradiated；
Control system receives the measurement temperature of the testpieces that temperature sensor is passed back, and control system will measure temperature and examination
Testing after the design temperature on part surface compares, obtain control signal, control signal is sent to by control system
Power Regulation equipment, Power Regulation equipment power needed for heating element heater exports, heating element heater provides radiation to testpieces
Heat energy, forms the closed loop control of testpieces surface temperature；
Described cooling system includes water-cooled carbon steel pipeline, regulation valve and filter, and filter is arranged on water-cooled
The upstream of carbon steel pipeline, regulation valve is arranged on the downstream of water-cooled carbon steel pipeline, and this cooling system leads to supercooled water
The unnecessary hyperthermia radiation heat produced by heating system in absorbing vacuum test cabin, it is possible to effectively reduce heat test
During in vacuum test cabin temperature raise the heat damage effect to vacuum test cabin, regulation valve changes for control
Heat, filter is for protecting upstream device from the destruction of solid impurity.
Big bulk temperature and pressure can synchronize the high temperature heat radiation test method continuously adjusted, and step is:
(1) testpieces of 1:1 size is fixed in the cooled plate that heating element heater is irradiated, by testpieces
It is positioned over together with heater in vacuum test cabin；
(2) goal pressure curve and target temperature profile are input in control system；
(3) run extract system, air compensating system, heating system, cooling system, measurement system, control system
System and monitoring system, measurement system to surface of test piece temperature, vacuum test cabin pressure, cooling water flow, take out
Gas system rate of air sucked in required and the Real-time Feedback of air compensating system air compensation and record, completed to try vacuum by control system
The synchronization of hatch checking pressure and testpieces surface temperature continuously adjusts；
Pressure controlled method is: control system is by the pressure transducer measured value in vacuum test cabin and target
After force value carries out real-time operation relatively, obtaining Stress control amount output signal, control system is by Stress control
Amount output signal is delivered simultaneously to extract system and air compensating system, and wherein extract system is by under vacuum line A
Electromagnetic valve A on the vacuum line of a diameter of a that trip connects, the electromagnetic valve on the vacuum line of a diameter of b
The rapidly opened and closed of electromagnetic valve C on the vacuum line of B and a diameter of c controls real-time rate of air sucked in required, leads to simultaneously
Cross the real-time air compensation of opening and closing extent control of QI invigorating ball valve on QI invigorating pipeline, by rate of air sucked in required and air compensation
In having jointly controlled vacuum test cabin, the dynamic of pressure regulates；Detailed process is as follows: during on-test,
In vacuum test cabin, pressure is normal pressure, i.e. 105Pa；Now opening control and the system of measurement, opens true
Slide valve A in empty extract system, heat exchanger, electromagnetic valve A, electromagnetic valve B, electromagnetic valve C, main take out valve A,
Master takes out valve B and two lobe pumps, keeps above-mentioned whole valve to be in normally open, now pressure in vacuum chamber
Fall is gradually reduced；When pressure is down to about 10Pa in vacuum experimental cabin, open lock in vacuum-pumping system
Plate valve B, molecular pump and backing pump, be evacuated to design limit 1Pa by pressure in vacuum test cabin and (assume this
Part is the pressure environment away from 100KM high-altitude, ground), now work continuously due to molecular pump group, therefore vacuum
In experimental cabin, pressure can not will be stablized less than 1Pa, need air relief valve, the QI invigorating ball opening in air compensating system
Valve and QI invigorating main valve, wherein decompressor and QI invigorating main valve are full-gear, according to air compensation size by controlling are
System is automatically adjusted the opening and closing degree of QI invigorating ball valve.If process of the test needs the change according to aircraft altitude
Change and carry out pressure when continuously adjusting, can be by increasing the aperture of QI invigorating ball valve, simultaneously according to rate of pressure rise
Close electromagnetic valve A (corresponding caliber a) or electromagnetic valve B (corresponding caliber b) or electromagnetic valve C selectively
(corresponding caliber c), it is possible to simultaneously close off electromagnetic valve A and electromagnetic valve B or electromagnetic valve A and electromagnetic valve C or electricity
Magnet valve B and electromagnetic valve C, it is possible to do not close electromagnetic valve A, electromagnetic valve B, electromagnetic valve C, only by regulation
Three can be rapidly opened and closed the opening/closing time (i.e. reducing ETAD expected time of arrival and departure) of electromagnetic valve make in vacuum test cabin on pressure
Rise；Otherwise, when pressure in needs reduce vacuum test cabin, by closing or opening of QI invigorating ball valve can be adjusted and reduced
Close degree, extend simultaneously rapidly opened and closed electromagnetic valve A, electromagnetic valve B, electromagnetic valve C (can three while,
Also can any two simultaneously, it is possible to arbitrarily individually carry out) ETAD expected time of arrival and departure, make rate of air sucked in required be more than air compensation and reality
Existing；Concrete control algolithm is: by the measured value of gas pressure in acquisition vacuum test cabin in real time, with target
Force value compares, and the deviation value obtained is as the input quantity of controller, for air compensating system, and control
The opening information that output controlled quentity controlled variable is QI invigorating ball valve of device processed, the aperture of regulation QI invigorating ball valve, thus regulate benefit
Tolerance size；For vacuum-pumping system, the output control signal of controller passes through PWM generator
The pwm signal that the generation cycle is certain, entered electromagnetic valve A, electromagnetic valve B, the service time of electromagnetic valve C
Row controls.By air compensating system and vacuum-pumping system are jointly controlled, it is possible to achieve the most dynamically regulation
The purpose of gas pressure in vacuum test cabin, completes a Closed loop operation, repeats and realize whole control
Journey.
Thermoregulator method is: control system is by the temperature sensor measured value on testpieces surface and target temperature
After angle value carries out real-time operation relatively, obtain temperature controlled quentity controlled variable output signal, and by temperature controlled quentity controlled variable output letter
Number being sent to Power Regulation power supply, by Power Regulation equipment power needed for heating element heater exports, heating element heater is according to must
To power provide radiant heat energy to testpieces, form the closed loop control of testpieces surface temperature；Detailed process
As follows: during on-test, first by pressure modulation initial target value in vacuum test cabin, start heating system and
Cooling system, the radiant heat energy regulation surface of test piece produced under different input power by regulation heating element heater
Temperature, during must be by time zero-bit corresponding with temperature target for time zero-bit corresponding for pressure target value
Match, with this ensure the aircraft obtained reenter during orbit altitude change time pressure environment with pneumatic
Thermal environment has higher matching；Concrete control algolithm is: target temperature value input control system chronologically,
As program set-point, the temperature sensor observed temperature on testpieces is as value of feedback, through control system
Carry out interpolation arithmetic relatively after, control system control signal is i.e. controlled voltage (0～10V) export to Power Regulation
Equipment, Power Regulation equipment according to input control voltage press linear scale (1:20) output voltage (0～
200V), it is achieved the control to quartz lamp running voltage.Power Regulation equipment output electric current follows Ohm's law, defeated
Go out current value size and depend on quartz lamp resistance sizes.Quartz lamp is radiated testpieces surface, it is achieved to test
The heating on part surface, temperature sensor by the Temperature Feedback of testpieces temperature control point to control system, control system
Output controls voltage again, completes a Closed loop operation, repeats and realize whole control process.
Monitoring system carries out record to the process of the test in vacuum test cabin；
Owing to the temperature and pressure in vacuum test cabin is all to be controlled by same control system, same
Moment controls while temperature and pressure, it is achieved the synchronization of temperature and pressure continuously adjusts；
(4) close extract system, air compensating system, heating system, cooling system, measurement system, control system
System and monitoring system, off-test.
The invention will be further described with embodiment below in conjunction with the accompanying drawings.
Embodiment
As it is shown in figure 1, big bulk temperature and pressure can synchronize the high temperature heat radiation assay device continuously adjusted,
This assay device includes control system, vacuum-pumping system, heating system, cooling system and vacuum test cabin,
Also include air compensating system；Heating system and cooling system are respectively positioned in vacuum test cabin, control system, QI invigorating
System and vacuum-pumping system are positioned at vacuum test out of my cabin, and this pilot system can also include leak test plant, survey
Amount system and monitoring system, monitoring system is positioned at vacuum test cabin, and measurement system and leak test plant are positioned at very
Outside empty experimental cabin；Testpieces be outer surface with the 1:1 size of anti-heat-barrier material aircraft partly or wholly
Structure；This assay device has big rate of air sucked in required and high automatic controlling level, it is possible to realize vacuum pressure load
Accurate regulatory function is changed with the synchronization real-time continuous of high-temperature hot load.System the key technical indexes is: vacuum
Experimental cabin design limit vacuum 1.0Pa, total leak rate≤1 × 10-4Pa L/s, vacuum steady state controling precision
≤ ± 5.0%, temperature regulating range: room temperature～1200 DEG C, temperature steady state controling precision≤± 1.0%, test
Time >=3600s.
As shown in Fig. 2 (a) and Fig. 2 (b), vacuum test cabin uses cylindrical horizontal type structure, and vacuum is tried
Hatch checking includes nacelle, dished (torispherical) head (two, is removable hatch door), water interface, power supply interface, electricity
Survey interface, observation window, spare interface.Wherein nacelle maximum outside diameter 4.5m, material selection 304 rustless steel,
There is the features such as corrosion-resistant, gas efficiency is low, air-tightness good, good welding performance；Dished (torispherical) head is positioned at nacelle two
Side, side end socket is fixing seal structure, and opposite side end socket is removable hatch door；This hatch door uses motor to drive
Dynamic big door pivot flipped form, removable hatch door uses pneumatic gripper with nacelle, can automatic shutter, close
Envelope also moves along nacelle radial direction, is provided with emergent manual actuation and position display and stopping means；Water interface
For connecting the cooling water pipeline of cooling system；Power supply interface is used for connecting power current；Electrical measurement interface is for even
Connect test cable；Process of the test can check situation in vacuum test cabin by observation window；Spare interface is used for
Test capability is expanded according to testing demand future；This vacuum test cabin can be for the proving ring needed for testpieces offer
Border, matched with vacuum pipeline is used for connecting vacuum test cabin and vacuum-pumping system and air compensating system, vacuum test
Downstream, cabin is connected with vacuum-pumping system by vacuum line A and valve, and the upstream in vacuum test cabin is by true
Blank pipe road D and valve are connected with air compensating system；
As shown in Figure 3,4, air compensating system includes QI invigorating main valve, QI invigorating ball valve and air relief valve, QI invigorating main valve
One end be connected by vacuum line between vacuum test cabin, the other end of QI invigorating main valve and QI invigorating ball valve
One end is connected by vacuum line, and the other end of QI invigorating ball valve is connected by vacuum line with one end of air relief valve,
The other end of air relief valve is connected by vacuum line with the input of pressure-air；In process of the test, work as vacuum
Force value in experimental cabin is less than entering QI invigorating state during target pressure value, elevated pressure nitrogen source of the gas carrys out stream need to be through over subtraction
After depressor is decompressed to 0.8MPa, flow through vacuum line, enter vacuum by QI invigorating ball valve and QI invigorating main valve and try
Hatch checking, wherein QI invigorating main valve is in normally open during QI invigorating, by regulating the opening and closing journey of QI invigorating ball valve
Degree controls the size of air inflow, and actual air compensation carries out reality to the aperture of QI invigorating ball valve after being calculated by control system
Time control.Control process is by the reality in measurement system feedback to a certain moment vacuum test cabin of control system
Pressure measurement force value carries out difference operation with the target pressure value of synchronization in control program, and control system will obtain
Difference input to controller, then by controller, controlled quentity controlled variable signal is delivered to QI invigorating ball valve, regulates QI invigorating ball
The actual aperture of valve, changes and actually enters the air compensation in vacuum test cabin, complete vacuum test cabin intrinsic pressure
The increment control algorithm of power.The size of above-mentioned vacuum line, decompressor, QI invigorating ball valve and QI invigorating main valve is
DN100。
As shown in Figure 5,6, vacuum-pumping system includes slide valve A, slide valve B, heat exchanger, electromagnetism
Valve A, electromagnetic valve B, electromagnetic valve C, master take out valve A, lead and take out valve B, thick pump group and molecular pump group；Slightly
Pump group includes the lobe pump that bench-types No. two are identical；Molecular pump group includes a molecular pump and a backing pump；
Wherein lobe pump, molecular pump and backing pump are the matured product of Edward company of the U.S., and lobe pump model is
GXS450/4200, molecular pump model is ixa2206c, and backing pump model is GXS160；Vacuum suction
Vacuum in vacuum test cabin is evacuated within the 1Pa time is 2h by system.
One end of slide valve A is connected by vacuum line A with vacuum test cabin, the other end of slide valve with change
One end of hot device is connected by vacuum line A, and the other end of heat exchanger passes through diameter with one end of electromagnetic valve A
Vacuum line for a connects, and the other end of heat exchanger passes through a diameter of b's with one end of electromagnetic valve B simultaneously
Vacuum line connects, and the other end of heat exchanger passes through the vacuum tube of a diameter of c with one end of electromagnetic valve C simultaneously
Road connects, caliber a ＞ b ＞ c；The other end of electromagnetic valve A and master take out one end of valve A, master smokes valve B's
One end is connected by vacuum line B, and the other end of electromagnetic valve B and master take out one end of valve A, master takes out valve B
One end connected by vacuum line B, the other end of electromagnetic valve C with main take out one end of valve A, main take out valve B
One end connected by vacuum line B；The diameter of vacuum line A is identical with the diameter of vacuum line B,
The value of the caliber a+b+c value not less than vacuum line A；The main valve A that takes out respectively connects with the main downstream taking out valve B
One lobe pump；
One end of slide valve B is connected by vacuum line C with vacuum test cabin, the other end of slide valve B
Being connected by vacuum line C with one end of molecular pump, the other end of molecular pump and backing pump pass through vacuum line
C connects, true by with KF25 type snap joint in the middle of the vacuum line connecting molecular pump and backing pump
Blank pipe road E connects leak detector, and leak detector is the matured product of ADIXEN company of France, and leak detector model is
ASM GRAPH.Leak test plant is used in process of the test vacuum test cabin and matched with vacuum pipeline, interface
The structures such as flange are hunted leak, to ensure that vacuum system normally works.The vacuum leak hunting equipment selected is maximum
The helium mass spectrometer leak detector of inlet pressure 1KPa, minimum leak detection rate is 10-12Pa.m3/s；
During on-test, opening control and the system of measurement, open slide valve A in vacuum-pumping system,
Heat exchanger, electromagnetic valve A, electromagnetic valve B, electromagnetic valve C, master take out valve A, lead and take out valve B and two lobe pumps,
Keeping above-mentioned whole valve to be in normally open, now in vacuum chamber, pressure drop is gradually reduced；Work as vacuum test
When pressure is down to about 100Pa in cabin, open slide valve B, molecular pump and backing pump in vacuum-pumping system,
Pressure in vacuum test cabin is evacuated to design limit 1Pa and (assumes that this condition is away from 100KM high-altitude, ground
Pressure environment), use leak test plant that vacuum test cabin and vacuum line carry out leak rate detection and leak source location,
When without leak source and meet slip require time, formal test can be started；Now by continually varying in time
Target pressure value input control system, after on-test, system of measuring is implemented to measure pressure in vacuum test cabin
Value, and by this data feedback to control system；If feedback pressure value is more than target pressure value, then enters and take out
Gaseity, control process is by the reality in measurement system feedback to a certain moment vacuum test cabin of control system
Pressure measurement force value carries out difference operation with the target pressure value of synchronization in control program, and control system will obtain
Difference input to controller, then by controller, controlled quentity controlled variable signal is delivered to PWM generator, PWM sends out
The major function of raw device is that the switch gap to its electromagnetic valve A controlled, electromagnetic valve B and electromagnetic valve C is entered
Row switch time, amount controlled, will switching value pwm signal be delivered to respectively electromagnetic valve A, electromagnetic valve B and
Electromagnetic valve C；Owing to corresponding for electromagnetic valve the A a diameter of DN200 of vacuum line a, electromagnetic valve B are corresponding
The a diameter of DN100 of vacuum line b, vacuum line c a diameter of DN25 (diameter corresponding for electromagnetic valve C
The diameter on minimum tubule road is true according to the discharge quantity in the anti-heat-barrier material thermal histories on aircraft outer surface
Fixed.) and tri-pipeline parallel connections of a, b, c, its upstream and downstream vacuum line A and B diameter identical (DN300),
Therefore by controlling electromagnetic valve A, electromagnetic valve B and electromagnetic valve C corresponding in tri-pipeline parallel connections of a, b, c
Switching value, can reach control the speed of exhaust purpose；During formal test, by vacuum suction system
Air compensation is jointly controlled by system by rate of air sucked in required and air compensating system, can meet institute's warp during aircraft reenters
The true pressure environmental simulation requirement being subject to.
As shown in Figure 7,8, heating system mainly includes heating element heater, cooled plate, Power Regulation equipment, sensing
Device and connection cable.Heating element heater is quartz lamp, and heating unit framework is made up of water-cooled reflector, has water-cooled
Interface and lamp tube electrode interface.Power Regulation equipment completes power current to the conversion of heating element heater running voltage, selects
The controllable silicon class power supply of separate unit 100kW, the Power Regulation equipment general power being made up of the power supply of 10 same sizes
Add up to 1MW.Sensor and connection cable survey test specimen generating surface temperature in process of the test, will be real
Measured value feeds back to control system and regulates the output of voltage for Power Regulation equipment in real time, measured data is deposited simultaneously
It is stored in measurement system.When formal test starts, start heating system and cooling system, first by regulation heating
Radiant heat energy that part produces under different input power regulation surface of test piece temperature, during must be by pressure mesh
Time zero-bit that scale value the is corresponding time zero-bit corresponding with temperature target matches, and ensures that obtain flies with this
Row device reenter during orbit altitude change time pressure environment and Aerodynamic Heating environment there is higher matching；
Cooling system mainly include water-cooled carbon steel pipeline, effusion meter, out temperature sensor, regulation valve and
Filter.This system leads in supercooled water absorbs vacuum test cabin the unnecessary hyperthermia radiation produced by heating system
Heat, it is possible to effectively during reduction heat test, in vacuum test cabin, temperature raises the heat damage effect to nacelle.
Effusion meter and temperature sensor are for detecting the virtual condition in work process.Regulation valve is used for controlling heat exchange amount.
Filter is for protecting upstream device from the destruction of solid impurity.
Control system is divided into two subdivisions, i.e. vacuum degree control part and temprature control unit.Wherein, very
Reciprocal of duty cycle control part in order in realizing vacuum test cabin pressure at 1Pa～105Continuously adjustabe function between Pa,
In using the unit interval, rate of air sucked in required is confronted with each other with discharge quantity, to reach what the method for dynamic equilibrium realized.
Control computer microprocessor with general industry and complete 1Pa～10 for core5Between Pa, multiple ranges is automatic
Switching, pressure target value is compared by processor with the real-time measurement values of pressure in vacuum test cabin, and its difference is believed
Number amplified, integration rear drive electromagnetic valve A, electromagnetic valve B, electromagnetic valve C and the different opening of QI invigorating ball valve,
Make electromagnetic valve export different size of flow, be finally reached stationary value；It is right that temprature control unit mainly realizes
Power Regulation equipment, heater and the closed loop control of testpieces surface temperature in trial test system.This control sets
Standby control computer for general industry, the temperature signal in these most ten regions, computer acquisition testpieces surface,
Obtaining multi-way control signals through control algolithm, the PLC exported respectively to Power Regulation equipment is in order to control
The output voltage values of ten power supplys, thus the heating power of heater, the temperature signal of testpieces are often organized in regulation
Again collect industrial control computer, constitute closed loop control, reach the control purpose of target temperature profile.
Measurement system is divided into three subdivisions, i.e. vacuum measurement part, temperature measuring section and flow measurement
Part.Wherein, vacuum measurement part, for quick and precisely measuring pressure in vacuum test cabin, is pressed for cabin
Closed loop control provides feedback data accurately.Here use and survey with fine vacuum based on low-vacuum measurement resistance unit
The compound vacuum gauge of amount ionization gauge technical combinations, it is achieved to company from coarse vacuum to fine vacuum in vacuum test cabin
Continuous accurately measurement.The sensor selected is that resistance vacuum gauge 1 overlaps, and measures scope 105～10-1Pa, type
Number: ZDR-II, including ZJ-52T Pirani gauge 2.Compound vacuum gauge 1 overlaps, and measures scope 105～10-6Pa,
Model: ZDF-III, including ZJ-52T Pirani gauge 1, ZJ-27 ionization gauge 1.The sensor all selects
Matured product with Chengdu Zheng Hua Electronics Factory.Temperature measuring section is for testpieces surface temperature in heater
Quick and precisely measurement, provide feedback data accurately for temperature scaling factor.The sensor selected is K-type
Thermocouple and Type B thermocouple, data sampling frequency < 100S/s, acquisition resolution 16；Flow measurement
Part is for the duty of monitoring device, it is judged that whether equipment is in nominal situation, cools down including heater
The air compensation of discharge, the rate of air sucked in required of vacuum-pumping system and air compensating system is measured, and the flow of selection is calculated as general
Logical liquid flow sensor and gas flow sensor.
Monitoring system include video camera, monitor main frame, complete in process of the test to vacuum test below deck equipment,
The process monitoring of test specimen state.Video camera normally can work in vacuum high-temperature environment.
In test set-up procedure, first have to be fixed on inside vacuum test cabin testpieces, take out afterwards
Vacuum.Vacuum-pumping system completes the pumping process to vacuum test cabin, electromagnetism therein by vacuum pump group
The vacuum line b of valve A and the vacuum line a of its correspondence, electromagnetic valve B and its correspondence is used for nacelle from normal pressure
State is to the big flow pumping process of test original state, and the vacuum line c of electromagnetic valve C and its correspondence is then
It is for the trim process of pressure in vacuum test cabin, when in cabin, the rate of change of pressure exceeds electromagnetic valve C
During with the regulation range of the vacuum line c of its correspondence, available electromagnetic valve A and the vacuum line a of its correspondence or
The vacuum line b of electromagnetic valve B and its correspondence coordinates the vacuum line c of electromagnetic valve C and its correspondence to adjust
Joint.Bleeding regulating amount is carried out, the pressure in final vacuum experimental cabin thus control is bled by controlling duration of ventilation.Logical
The gas time then by control system and measure system according to goal pressure, vacuum test cabin pressure according to control algolithm
Calculate, control electromagnetic valve C, electromagnetic valve A and the open and close time interval of electromagnetic valve B, progressively enter
Row Stress control.In design vacuum range 1Pa～105In Pa, it is divided into three intervals, in vacuum
Being respectively controlled, the pid control algorithm of control principle such as formula (1) is controlled.
Wherein, Kp is proportionality coefficient；Ti is integration time constant；Td is derivative time constant；E (t) is
Deviation value, e (t)=p0-pdDifference for goal pressure Yu observed pressure.
As it is shown in figure 9, in vacuum, when in thick pump group, two lobe pumps work simultaneously, do not examine
Consider testpieces surfacing in process of the test under conditions of the discharge quantity of decomposes, slide valve A, electromagnetism
Vacuum line a standard-sized sheet (the vacuum line b closedown of electromagnetic valve B and its correspondence, the electricity of valve A and its correspondence
Magnet valve C and the vacuum line c of its correspondence, slide valve B and molecular pump group close), by vacuum test cabin
Gas pressure is evacuated to 10 by normal pressure3To 104About Pa；In order to increase vacuum pumping rate, by electromagnetic valve B and
Vacuum line b standard-sized sheet (electromagnetic valve C and the vacuum line c of its correspondence, slide valve B and the molecule of its correspondence
Pump group is closed), gas pressure in vacuum test cabin is evacuated to about 10Pa by normal pressure；The most whole thick pump
Group is in bigger load condition, can pass through standard-sized sheet slide valve B and open molecular pump group by gas in vacuum test cabin
Body pressure is evacuated to 1Pa or following.Now possess experimental condition, testpieces can be started simultaneously at pressure environment
Simulate with the consecutive variations of thermal environment.
In process of the test, along with being gradually lowered of spacecraft orbit height, cabin pressure gradually rises, the most adjoint
The rising of aerothermal load (i.e. testpieces surface temperature).When supercharging in needs vacuum test cabin, mend
Gas system, by carrying clean, the cleaning nitrogen of certain pressure in vacuum test cabin, completes pressurization.
Now QI invigorating main valve standard-sized sheet, QI invigorating ball valve can realize the regulation of air inflow by regulation area of passage, thus
Control pressure in the cabin after QI invigorating.Area of passage is pressed according to observed pressure in goal pressure, cabin by control system
Calculate according to control algolithm, and then control the area of passage of QI invigorating ball valve, progressively carry out Stress control.Very
Empty extract system needs jointly to coordinate with air compensating system to realize continuously adjusting of vacuum test cabin pressure.
In process of the test, it is important to consider the pyrolysis situation of testpieces surfacing.Testpieces surfacing exists
Cracking in various degree can occur in thermal histories, thus produce a certain amount of gas, this portion gas can be made
The rising of gas pressure in one-tenth vacuum experimental cabin, when the discharge quantity of testpieces surfacing reaches to a certain degree,
The exhaust capacity of vacuum-pumping system is balanced each other with the discharge quantity of material, and in tank, gas pressure no longer declines
(in some cases, owing to there is the influence factor of material self discharge quantity, have and closing air compensating system,
And under conditions of electromagnetic valve A and electromagnetic valve B standard-sized sheet, in vacuum test cabin, pressure is still above goal pressure
Phenomenon), correspond to the discharge quantity of different materials, need by the vacuum line a of electromagnetic valve A and its correspondence,
The cooperation of the vacuum line c of electromagnetic valve B and the vacuum line b of its correspondence, electromagnetic valve C and its correspondence is carried out
Cabin pressure regulation.Such as, during test, the discharge quantity of testpieces surfacing is 100g/s, and vacuum test cabin is initial
Pressure is 40kPa, and temperature is 293K, when goal pressure is 30kPa, needs to adjust and reduce rapidly air compensation,
Cabin pressure by electromagnetic valve C standard-sized sheet while electromagnetic valve A and electromagnetic valve B is interrupted opening and closing, under above-mentioned state
Controlling curve as shown in Figure 10, as seen from the figure, in vacuum-pumping system limit of power, it is possible to achieve pressure
Effective control of power；When the discharge quantity of testpieces surfacing is 50g/s, need to adjust and reduce air compensation,
By electromagnetic valve C standard-sized sheet while electromagnetic valve A closedown, electromagnetic valve B interruption opening and closing；When testpieces surface material
When the discharge quantity of material is 30g/s, need to adjust and reduce air compensation, while electromagnetic valve A, electromagnetic valve B close
By electromagnetic valve C standard-sized sheet；According to existing engineering experience, the discharge quantity of testpieces surfacing pyrolysis is the most little
In 100g/s.Vacuum steady state controling precision≤± 5.0% requirement is all disclosure satisfy that under the conditions of above-mentioned.
With the typical metal under heater and nonmetal testpieces material as theoretical calculation model, to model table
Face temperature rise response is analyzed, as shown in Figure 11 (a) and Figure 11 (b).As seen from the figure, examination
Test part surface temperature and all can reach the requirement of 1200 DEG C.To the nonmetal testpieces material under the conditions of 1000 DEG C
Temperature control effect is surveyed, as shown in figure 12.It can be seen that temperature steady state controling precision can
Meet the requirement less than ± 1%.
The temperature of anti-for hyperthermia radiation formula/heat insulation test system is the most accurately regulated control skill by this project
Art and experimental cabin cabin press the accurate regulation technology of state and are jointly applied to 130m3In big volume vacuum test equipment,
Combine and constitute the high temperature heat radiation pilot system that big bulk temperature and pressure can synchronize to continuously adjust.This test system
System can carry out the height under certain vacuum environment for all kinds of aircraft section structures are overall with local 1:1 test specimen
Temperature infrared radiation type thermal environment ground equivalent simulation test, realize the most really near space vehicle long time
Between in-orbit/become trailer move the orbit altitude change modeling in flight course and pneumatic thermal environment simulation function, for not
Carry out aircraft heat structure and heat seal certification test provides reliable technical guarantee.
The development of the high temperature heat radiation pilot system continuously adjusted can be synchronized by big bulk temperature and pressure, for
All kinds of aircraft large-size components carry out the high temp, infrared radiation formula thermal environment ground equivalent under certain vacuum environment
Simulation test is laid a good foundation, it is possible to the most truly simulation near space vehicle long-time the most in-orbit/become trailer
Orbit altitude change in dynamic flight course and pneumatic thermal environment, examine for future aircraft heat structure and heat seal
Nuclear test provides reliable technical guarantee.
Claims (10)
1. big bulk temperature and pressure can synchronize the high temperature heat radiation assay device continuously adjusted, it is characterised in that:
This assay device include control system, vacuum-pumping system, heating system, cooling system, air compensating system,
Measurement system and vacuum test cabin, heating system and cooling system are respectively positioned in vacuum test cabin, control system,
Air compensating system, vacuum-pumping system and measurement system are positioned at vacuum test out of my cabin；
Described vacuum test cabin is the experimental enviroment needed for testpieces offer, and downstream, vacuum test cabin is by true
Blank pipe road A and valve are connected with vacuum-pumping system, and vacuum line D and valve are passed through in the upstream in vacuum test cabin
Door is connected with air compensating system；
Described control system is connected by cable with vacuum-pumping system, air compensating system, is used for controlling vacuum
Pressure in vacuum test cabin is regulated by extract system and air compensating system, the pressure in needing vacuum test cabin
During reduction, the air compensation simultaneously being reduced air compensating system by the rate of air sucked in required increasing vacuum-pumping system is regulated,
When needing the pressure in vacuum test cabin to increase, increased by the rate of air sucked in required reducing vacuum-pumping system simultaneously
The air compensation of air compensating system regulates；
Described control system is connected by cable with heating system, cooling system, is used for controlling heating system
With cooling system, the temperature in vacuum test cabin is regulated；
Described air compensating system includes QI invigorating main valve, QI invigorating ball valve and air relief valve, and one end of QI invigorating main valve is with true
Being connected by vacuum line between empty experimental cabin, the other end of QI invigorating main valve and one end of QI invigorating ball valve are by true
Blank pipe road connects, and the other end of QI invigorating ball valve is connected by vacuum line with one end of air relief valve, air relief valve
The other end is connected by vacuum line with the input of extraneous high-pressure air source；
Described vacuum-pumping system includes slide valve A, slide valve B, heat exchanger, electromagnetic valve A, electromagnetism
Valve B, electromagnetic valve C, master take out valve A, lead and take out valve B, thick pump group and molecular pump group；Thick pump group includes
Two lobe pumps；Molecular pump group includes a molecular pump and a backing pump；
One end of slide valve A is connected by vacuum line A with vacuum test cabin, the other end of slide valve A
Being connected by vacuum line A with one end of heat exchanger, the other end of heat exchanger passes through with one end of electromagnetic valve A
The vacuum line of a diameter of a connects, and the other end of heat exchanger passes through a diameter of with one end of electromagnetic valve B simultaneously
The vacuum line of b connects, and the other end of heat exchanger the most also passes through a diameter of c's with one end of electromagnetic valve C
Vacuum line connects, a ＞ b ＞ c；The other end of electromagnetic valve A and master take out one end of valve A, master smokes valve B's
One end is connected by vacuum line B, and the other end of electromagnetic valve B and master take out one end of valve A, master takes out valve B
One end connected by vacuum line B, the other end of electromagnetic valve C with main take out one end of valve A, main take out valve B
One end connected by vacuum line B；The diameter of vacuum line A is identical with the diameter of vacuum line B,
Caliber a, b, c be three's and not less than the value of vacuum line A；Master takes out valve A and the main downstream taking out valve B
One lobe pump of each connection；
One end of slide valve B is connected by vacuum line C with vacuum test cabin, the other end of slide valve B
Being connected by vacuum line C with one end of molecular pump, the other end of molecular pump and backing pump pass through vacuum line
C connects；
Described heating system includes Power Regulation equipment and heater, the control that Power Regulation equipment sends according to control system
Output power signal processed heats to testpieces to heater, the power that heater inputs according to Power Regulation equipment；
Cooling system is for cooling down vacuum test cabin；
Described measurement system is connected with heating system by temperature sensor, cable, and measurement system passes through liquid
Body flow transducer, cable are connected with cooling system, and measurement system is used for measuring and recording in vacuum test cabin
Temperature and cooling system in cool down the flow of water；
Described measurement system is connected with vacuum-pumping system by pressure transducer, cable, and system of measuring is led to
Cross gas flow sensor, cable is connected with air compensating system, for measuring and record the pressure in vacuum test cabin
Power, the rate of air sucked in required of vacuum-pumping system and the air compensation of air compensating system；
Described measurement system is connected with control system by cable, in real time by the temperature in vacuum test cabin
The air compensation of degree, pressure, cooling water flow, the rate of air sucked in required of vacuum-pumping system and air compensating system feeds back to control
System processed.
Big bulk temperature the most according to claim 1 and pressure can synchronize the high-temperature hot spoke continuously adjusted
Penetrate assay device, it is characterised in that: this assay device also includes leak test plant and monitoring system, monitoring system
Being positioned at vacuum test cabin, leak test plant is positioned at vacuum test out of my cabin；
Described leak test plant is connected with vacuum test cabin by pipeline, for detecting the leakage in vacuum test cabin
Rate and the leakage point position found on vacuum test cabin and vacuum line；
Described monitoring system is connected with the system of measurement by cable, for recording the test in vacuum test cabin
State and process.
Big bulk temperature the most according to claim 1 and pressure can synchronize the high-temperature hot spoke continuously adjusted
Penetrate assay device, it is characterised in that: the diameter of the vacuum line of a diameter of cWherein, c is true
The diameter on blank pipe road, ω is the volume flow of the medium in the vacuum line of a diameter of c, and v is a diameter of c's
The flow velocity of the medium in vacuum line.
Big bulk temperature the most according to claim 1 and pressure can synchronize the high-temperature hot spoke continuously adjusted
Penetrate assay device, it is characterised in that: by with KF25 in the middle of the vacuum line connecting molecular pump and backing pump
The vacuum line E of type snap joint connects leak detector.
Big bulk temperature the most according to claim 1 and pressure can synchronize the high-temperature hot spoke continuously adjusted
Penetrate assay device, it is characterised in that: the described heater in heating system includes heating element heater and cooled plate,
Power Regulation equipment is 10 controllable silicon class power supplys, separate unit 100kW, every corresponding heater of Power Regulation equipment；
Heating element heater in heater uses 3000W quartz lamp, is made up of 33 quartz lamps and adds in each heater
Hot plane；Cooled plate is positioned at the both sides of the flat heated that heating element heater is formed；
Cooled plate is sandwich, including metallic plate and the snakelike water-cooled being positioned in the middle of two metallic plates at two ends
Passage, water-cooling channel is with the fin of material with metallic plate；Testpieces is fixed on the water that heating element heater is irradiated
On cold drawing；Control system receives the measurement temperature of the testpieces that temperature sensor is passed back, and control system will be measured
After the design temperature on temperature and testpieces surface compares, obtaining control signal, control is believed by control system
Number sending Power Regulation equipment to, Power Regulation equipment power needed for heating element heater exports, heating element heater is to testpieces
Radiant heat energy is provided, forms the closed loop control of testpieces surface temperature.
Big bulk temperature the most according to claim 1 and pressure can synchronize the high-temperature hot spoke continuously adjusted
Penetrate assay device, it is characterised in that: described cooling system includes water-cooled carbon steel pipeline, regulation valve and filtration
Device, filter is arranged on the upstream of water-cooled carbon steel pipeline, and regulation valve is arranged on the downstream of water-cooled carbon steel pipeline.
7. one kind carries out the height that temperature and pressure synchronizes to continuously adjust to the assay device described in claim 5
Warm radiation test method, it is characterised in that step is:
(1) testpieces of 1:1 size is fixed in the cooled plate that heating element heater is irradiated, by testpieces
It is positioned over together with heater in vacuum test cabin；
(2) goal pressure curve and target temperature profile are input in control system；
(3) vacuum-pumping system, air compensating system, heating system, cooling system and control system are run, by
Control system completes to continuously adjust the synchronization of vacuum test cabin pressure and testpieces surface temperature；
(4) vacuum-pumping system, air compensating system, heating system, cooling system, off-test are closed.
High temperature heat radiation test method the most according to claim 7, it is characterised in that: step (3)
The pressure controlled method in vacuum test cabin is by middle control system: control system is by the pressure in vacuum test cabin
Force transducer measured value carries out with target pressure value after real-time operation compares, obtaining Stress control amount output signal,
Stress control amount output signal is delivered simultaneously to vacuum-pumping system and air compensating system, Qi Zhongzhen by control system
Empty extract system controls real-time rate of air sucked in required by electromagnetic valve A, electromagnetic valve B and the rapidly opened and closed of electromagnetic valve C,
Simultaneously by the real-time air compensation of opening and closing extent control of the QI invigorating ball valve on air compensating system, by rate of air sucked in required and benefit
Tolerance jointly controlled the most dynamically regulation of pressure in vacuum test cabin: during on-test, vacuum is tried
In hatch checking, pressure is normal pressure, now opening control, opens slide valve A, heat exchange in vacuum-pumping system
Device, electromagnetic valve A, electromagnetic valve B, electromagnetic valve C, master take out valve A, lead and take out valve B and two lobe pumps to often
Open state, now in vacuum test cabin, pressure will be gradually reduced；When in vacuum experimental cabin, pressure is down to no more than
During 10Pa, open slide valve B, molecular pump and backing pump in vacuum-pumping system, by vacuum test cabin
Pressure is evacuated to set ultimate value 1Pa, opens the air relief valve in air compensating system, QI invigorating ball valve and QI invigorating main valve,
Wherein decompressor and QI invigorating main valve are full-gear, are automatically adjusted QI invigorating according to air compensation size by control system
The opening and closing degree of ball valve, in process of the test, the change according to aircraft altitude carries out continuously adjusting of pressure.
High temperature heat radiation test method the most according to claim 8, it is characterised in that: process of the test
The middle change according to aircraft altitude carries out the method that pressure continuously adjusts: when needs increase vacuum examination
During pressure in hatch checking, by increasing the aperture of QI invigorating ball valve, the most selective according to rate of pressure rise
Electromagnetic valve A or electromagnetic valve B or electromagnetic valve C is closed on ground, or simultaneously closes off electromagnetic valve A and electromagnetic valve B or electricity
Magnet valve A and electromagnetic valve C or electromagnetic valve B and electromagnetic valve C or regulation three can be rapidly opened and closed the opening of electromagnetic valve
When closing, in chien shih vacuum test cabin, pressure rises；
When pressure in needs reduce vacuum test cabin, by closing or adjust and reduce the opening and closing degree of QI invigorating ball valve,
Extend rapidly opened and closed electromagnetic valve A, electromagnetic valve B, the ETAD expected time of arrival and departure of electromagnetic valve C simultaneously, make rate of air sucked in required be more than
Air compensation and realize；Concrete control algolithm is: by the actual measurement of gas pressure in acquisition vacuum test cabin in real time
Value, compares with target pressure value, and the deviation value obtained is as the input quantity of control system, for QI invigorating
For system, the opening information that output controlled quentity controlled variable is QI invigorating ball valve of control system, opening of regulation QI invigorating ball valve
Degree, thus regulate air compensation size；For vacuum-pumping system, the output control signal of control system
Electromagnetic valve A, electromagnetic valve B, the service time of electromagnetic valve C are controlled；By to air compensating system and true
Jointly controlling of empty extract system, it is achieved the most dynamically purpose of gas pressure in regulation vacuum test cabin, complete
Become a Closed loop operation, repeat and realize whole control process.
High temperature heat radiation test method the most according to claim 7, it is characterised in that: step (3)
The method that testpieces surface temperature is regulated by middle control system is: the temperature on testpieces surface is passed by control system
Sensor measured value carries out with target temperature value after real-time operation compares, obtaining temperature controlled quentity controlled variable output signal, and
Temperature controlled quentity controlled variable output signal is sent to Power Regulation power supply, by Power Regulation equipment merit needed for heating element heater exports
Rate, heating element heater provides radiant heat energy according to the power obtained to testpieces, forms testpieces surface temperature
Closed loop control；
Temperature control method is: during on-test, first pressure in vacuum test cabin is adjusted to initial target value,
Start heating system and cooling system, the radiant heat produced under different input power by regulation heating element heater
Surface of test piece temperature can be regulated, during must be by time zero-bit corresponding for pressure target value and temperature target
Corresponding time zero-bit matches, with this ensure the aircraft obtained reenter during orbit altitude change time
Pressure environment matches with Aerodynamic Heating environment.
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| CN106444946A (en) * | 2016-09-20 | 2017-02-22 | 天津航天瑞莱科技有限公司 | Constant pressure module of large constant-pressure thermal test system |
| CN108121128B (en) * | 2016-11-30 | 2023-07-11 | 北京航天计量测试技术研究所 | Novel high-speed water-cooling shutter |
| CN107065951B (en) * | 2017-04-10 | 2024-02-09 | 淄博真空设备厂有限公司 | Accurate pressure regulating control device and method for dynamic simulation vacuum system |
| CN108318376B (en) * | 2017-12-19 | 2020-06-23 | 兰州空间技术物理研究所 | Method for judging gas yield of sealed cesium-beam tube material |
| CN111141586A (en) * | 2020-03-01 | 2020-05-12 | 贝士德仪器科技(北京)有限公司 | Physical adsorption instrument with program-controlled pressure-resistant flying degassing system |
| CN111610009B (en) * | 2020-05-20 | 2024-08-09 | 中国科学院西安光学精密机械研究所 | Test device with temperature compensation function |
| CN112730502A (en) * | 2020-12-22 | 2021-04-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Automatic radiation heating test system who changes |
| CN113125501A (en) * | 2021-04-30 | 2021-07-16 | 北京卫星环境工程研究所 | Heat-proof performance testing system suitable for spacecraft heat-insulating material in low-pressure environment |
| CN113961022B (en) * | 2021-12-21 | 2022-03-11 | 中国飞机强度研究所 | Pressure control system and pressure control method for aircraft test |
| CN114513867A (en) * | 2021-12-30 | 2022-05-17 | 北京航天益森风洞工程技术有限公司 | Heating control system and heating control method for aircraft simulation test |
| CN114813199A (en) * | 2022-06-29 | 2022-07-29 | 中国飞机强度研究所 | Closed high-temperature test device and method for aerospace plane structure |
| CN117554083B (en) * | 2024-01-11 | 2024-04-12 | 天津航天瑞莱科技有限公司 | Method for loading system by adopting engine casing thermal internal pressure fatigue test |
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| US4387467A (en) * | 1981-07-27 | 1983-06-07 | The United States Of America As Represented By The Secretary Of The Air Force | Satellite test chamber with electromagnetic reflection and resonance damping for simulating system generated electromagnetic pulses |
| JP3767052B2 (en) * | 1996-11-30 | 2006-04-19 | アイシン精機株式会社 | Multistage vacuum pump |
| CN201348569Y (en) * | 2008-12-29 | 2009-11-18 | 北京卫星环境工程研究所 | Space ship environment simulation test device utilizing mixed work substance refrigerating technology |
| CN101776063B (en) * | 2010-01-21 | 2012-01-04 | 储继国 | Large high-vacuum air pumping set |
| CN102536735A (en) * | 2010-12-20 | 2012-07-04 | 北京卫星环境工程研究所 | Cleaning vacuum air exhaust technology for large-sized space environmental simulator |
| CN103318427B (en) * | 2013-06-25 | 2016-03-30 | 上海宇航系统工程研究所 | A kind of space environment simulation test system |
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Inventor after: Xia Linshi Inventor after: Zhao Ling Inventor after: Na Wei Inventor after: Cao Zhihong Inventor after: Wang Lei Inventor after: Meng Gang Inventor after: Zhu Lianbo Inventor after: Bi Chen Inventor after: Zhang Chunwei Inventor after: Li Hongliang Inventor after: Song Wenxiao Inventor after: Qi Bin Inventor after: Wang Shuxin Inventor after: Zhang Nie Inventor after: Tian Ning Inventor after: Zou Yanghui Inventor after: Zhang Kai Inventor after: Zhang Lisong Inventor after: Yang Chi Inventor after: Cao Yuqing Inventor after: Yue Hui Inventor before: Xia Linshi Inventor before: Zhao Ling Inventor before: Na Wei Inventor before: Cao Zhihong Inventor before: Wang Lei Inventor before: Qi Bin Inventor before: Tian Ning Inventor before: Zou Yanghui Inventor before: Zhang Kai Inventor before: Zhang Lisong Inventor before: Yang Chi Inventor before: Cao Yuqing Inventor before: Yue Hui |