CN110294149A - Transient temperature simulation system and method under hypobaric - Google Patents
Transient temperature simulation system and method under hypobaric Download PDFInfo
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- CN110294149A CN110294149A CN201910589824.XA CN201910589824A CN110294149A CN 110294149 A CN110294149 A CN 110294149A CN 201910589824 A CN201910589824 A CN 201910589824A CN 110294149 A CN110294149 A CN 110294149A
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- temperature
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G5/00—Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B9/00—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point
- F25B9/002—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point characterised by the refrigerant
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- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Thermal Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses transient temperature simulation system and methods under a kind of hypobaric, by the simulation for realizing hypobaric temperature curve under ground environment, the system is made of compressor, heat exchanger, gas conditioner, electric furnace, heat sink, vacuum tank, realizes adjustable environment temperature within the scope of 150K-350K in vacuum tank by the control of heat sink temperature.Equally also correspondence discloses analogy method.The present invention realizes transient temperature under hypobaric and simulates, and solves the problems, such as that transient temperature simulates and has the temperature in the case of convective heat transfer accurately to control under corresponding low pressure.
Description
Technical field
The invention belongs to spacecraft ground environmental test technical fields, and in particular to transient temperature under a kind of hypobaric
Analogy method, the simulation that this method passes through the realization hypobaric temperature curve under ground environment.
Background technique
Mars is the most planet of the planet and human detection nearest apart from the earth.Martian surface has 600-
1000Pa, the atmosphere that main component is carbon dioxide, surface temperature changes within the scope of -110-20 DEG C, therefore Mars environment phase
It is more increasingly complex than conventional orbital environment.There are multiple Mars probes in history, is resulted in due to insufficient to environmental awareness
Failure or partial failure after arrival martian surface.Currently, aerospace mechanism, various countries is more likely on the ground open Mars probes
Exhibition includes the environment comprehensive test of low pressure, gas componant, temperature, wind speed, to reach amendment spacecraft thermal model, examine space flight
The purpose of device discharge performance, verifying system works in extreme circumstances.
During Mars Spacecraft guidance and control, the day-night change that Mars rotation is formed can bring martian surface atmospheric temperature
Corresponding change need to verify spacecraft temperature sensitive material performance for the success for guaranteeing detection mission.In order to verify temperature
Performance change state of the sensitive material under temperature change dramatically, it is desirable that the temperature environment state of test process is carried out whole high
Precision analog.
For example, Chinese patent CN201510410105.9 is " with the back-heating type enclosed thermoregulating system of gas as a heat transfer medium
And its temperature control method " in have similar temprature control method, but the temprature control method is only merely control heat sink temperature, is not had
It relates to further carry out accurate transient control to low pressure gas in vacuum tank by heat sink.
Chinese patent CN201711121010.0 discloses a kind of gas nitrogen thermostat units for heat sink thermoregulating system, this article
System in offering has increased Recuperative heat exchanger newly so that the low-pressure gas temperature for returning to press is gone up, prevent low temperature nitrogen into
Enter press and cause equipment damage, on the other hand can recycle a large amount of cooling capacity, the liquid nitrogen dosage that reduction system requires supplementation with.But
It is that the system does not refer to the problem of implementation of transient temperature under hypobaric equally yet.
Therefore, for the situation, this invention contemplates transient temperature simulation systems under a kind of hypobaric, for related material
Material, component provide test support.
Summary of the invention
The technical problem to be solved in the present invention is to provide transient temperature simulation system and simulations under a kind of hypobaric
Method, to meet the ground experiment testing requirement of spacecraft.
To solve the above problems, The technical solution adopted by the invention is as follows:
Transient temperature simulation system under the hypobaric of Mars temperature environment simulation, including compressor, heat exchanger, gas
Adjuster, several electric furnaces and heat sink and vacuum tank, heat sink to be vertically arranged in vacuum tank two sides, heat sink centre holds in vacuum
Trial zone in being formed in device, wherein heat exchanger passes through main body pipeline and each heat sink gas connection respectively, provides gas circulation power
Compressor, high temperature and pressure nitrogen from compressor outlet enter with from heat sink outlet come out low-temp low-pressure nitrogen in heat exchanger
Heat exchange is carried out, high-temperature low-pressure nitrogen returns to compressor, the nitrogen of the high pressure low temperature of formation and is supplemented into gas conditioner
In a small amount of liquid nitrogen mixing, formed be lower than target temperature cryogenic gas, respectively enter each road using the adjusting of each road electric furnace
It is heat sink, it is that trial zone forms adjustable environment temperature within the scope of 150K-350K in vacuum tank.
Wherein, it is identical to correspond to heat sink quantity for the quantity of electric furnace.
Wherein, heat sink and electric furnace quantity is even number and the heat sink two sides in vacuum tank form and are symmetrically arranged structure.
Wherein, the cryogenic gas lower than target temperature that gas conditioner is formed is respectively communicated with each by main body pipeline
On electric furnace.
Transient temperature analogy method under hypobaric is to carry out transient temperature mould under hypobaric using above system
Quasi-, comprising the following steps:
When simulating Mars environment round the clock, heat sink temperature corresponding to object gas temperature is calculated, tests process
In, for system environments under hypobaric, gas is continuous media flowing, passes through the low density gas in vacuum tank therebetween
Free convection and heat radiation exchange heat, according to heat transfer formula:
In formula, Q is heat flow density, and h is convection transfer rate, and ε is radiation heat transfer coefficient, and A is radiation heat transfer area, TaFor
The gas temperature measured, TsFor heat sink temperature, TbIt is substantially constant during test for vacuum vessel wall boundary temperature；
For the gas measuring point in system environments, then have:
In formula, C is the equivalent thermal capacitance around gas temperature measuring point；
It is collated to obtain:
A in formula, b, c, d are the coefficient of heat transfer, during the test, measure the temperature of gas measuring point and Ge Lu heat sink temperature point
Degree obtains the average value and all heat sink temperature average values of the gas temperature point that 6 or more measure by test data, carries out
The Fitting Calculation obtains each term coefficient under different pressures；
According to the coefficient of heat transfer, the corresponding heat sink temperature of different target gas temperature is calculated, forms fixed time temperature control table
It is single, it is controlled according to list, i.e., transient temperature is simulated under realization hypobaric；
The present invention compares the above-mentioned prior art, solves transient temperature under corresponding low pressure and simulates and have convective heat transfer feelings
The problem of temperature under condition accurately controls.
Detailed description of the invention
Fig. 1 is transient temperature simulation system structural schematic diagram under hypobaric of the invention.
Wherein, 1 is compressor；2 be heat exchanger；3 be gas conditioner；4 be a small amount of liquid nitrogen；5 be electric furnace；6 be heat sink；7
For vacuum tank；8 be test block.
Fig. 2 is Mars target temperature profile and gas temperature in transient temperature analogy method under hypobaric of the invention
Simulation curve.
Specific embodiment
The transient temperature simulation system under hypobaric that is adapted to of the invention is described in detail referring to the drawings,
But this describes merely illustrative, it is no intended to carry out any restrictions to protection scope of the present invention.
Referring to attached drawing 1, Fig. 1 shows transient temperature simulation system structural schematic diagram under hypobaric of the invention.It should
Transient temperature simulation system under hypobaric, including providing compressor 1, the heat exchanger 2, gas conditioner of gas circulation power
3, six electric furnaces 5 and six heat sink 6 and vacuum tank 7,6 heat sink are divided to two groups each three to be vertically arranged in vacuum tank respectively
Two sides inside 7, formed in vacuum tank 7 among heat sink 6 in trial zone 8, wherein heat exchanger 2 passes through main body pipeline respectively
With each heat sink 6 gas connection, high temperature and pressure nitrogen enters heat exchanger 2 from the outlet of compressor 1 and comes out with from six heat sink 6
Low-temp low-pressure nitrogen carry out heat exchange, the nitrogen for becoming high-temperature low-pressure returns to compressor 1, nitrogen and supplement in heat exchanger 2
The a small amount of liquid nitrogen 4 entered in gas conditioner 3 mixes, and the cryogenic gas for being lower than target temperature is formed, using No. 6 electric furnaces 5
Adjusting respectively enter corresponding heat sink 6, be that trial zone 8 forms adjustable environment temperature within the scope of 150K-350K in vacuum tank
Degree.The gas of slightly below target temperature is heated after entering electric furnace, the accurate control of heat sink entrance temperature is realized, to control
Heat sink temperature processed, the heat sink low density gas in trial zone are exchanged heat by free convection and heat radiation, and heat exchange rule follows
Heat exchange formula (3) before.
Below by taking the simulation of Mars temperature environment as an example, illustrate transient temperature simulation system under hypobaric of the invention
Use process is described in detail.
Mars diurnal temperature carries out temperature change at any time, and desired target temperature profile is as shown in Fig. 2, curve is
Target temperature profile under 1400Pa environment, according to -105 DEG C of minimum temperature, rapid increase, -30 DEG C of mitigations of high temperature, fast downlink,
Downlink changes at a slow speed.
According to invention the method, fitting coefficient under low pressure heat-transfer environment is calculated according to legacy data, such as table 1.
Fitting coefficient under 1 low pressure heat-transfer environment of table
| Pressure | a | b | c | d |
| 1400Pa | -1.79×10-10 | -0.0324 | 0.0259 | 1.5848 |
According to Fig. 2 black temperature objectives curve, it is as shown in table 2 to calculate corresponding heat sink temperature.
2 temperature of table corresponds to table
According to above-mentioned heat sink temperature data, compressor 1 provides the power of gas circulation, high temperature and pressure for gas nitrogen thermoregulating system
Nitrogen enters heat exchanger 2 from compressor outlet, heat exchange is carried out with the low-temp low-pressure nitrogen come out from heat sink 6 outlet, from heat exchange
The high pressure low temperature gas that device 2 comes out enters gas conditioner 3, mixes with a small amount of liquid nitrogen 4 for being supplemented into gas conditioner 3, shape
It is adjusted according to temperature in table 2 into heat sink 6 at the cryogenic gas for being lower than target temperature using each road electric furnace 5.
It according to described previously, by debugging and calculates, obtaining different moments requires temperature spot, and carries out in electric furnace control
Setting, the automatic adjusting for carrying out temperature during test.Observed temperature curve is tested as shown in Fig. 2 red curve, can be completed
Simulation test requirement.
Although giving detailed description and explanation to the specific design method and thinking of this patent above, it should be noted that
, we can the conception of patent according to the present invention various equivalent changes and modification are carried out to above embodiment, produced
It, should all be within protection scope of the present invention when the spirit that raw function is still covered without departing from specification and attached drawing.
Claims (5)
1. transient temperature simulation system under hypobaric, including compressor, heat exchanger, gas conditioner, several electric furnaces and heat
Heavy and vacuum tank, heat sink to be vertically arranged in vacuum tank two sides, heat sink centre forms interior trial zone in vacuum tank,
In, heat exchanger passes through main body pipeline and each heat sink gas connection respectively, provides the compressor of gas circulation power, high temperature and pressure nitrogen
Gas enters from compressor outlet carries out heat exchange, high-temperature low-pressure with the low-temp low-pressure nitrogen come out from heat sink outlet in heat exchanger
Nitrogen returns to compressor, and the nitrogen of the high pressure low temperature of formation is mixed with a small amount of liquid nitrogen being supplemented into gas conditioner, shape
At the cryogenic gas for being lower than target temperature, it is heat sink that each road is respectively enterd using the adjusting of each road electric furnace, is examination in vacuum tank
It tests area and forms adjustable environment temperature within the scope of 150K-350K.
2. transient temperature simulation system under hypobaric as described in claim 1, wherein the quantity of electric furnace corresponds to heat sink
Quantity it is identical.
3. transient temperature simulation system under hypobaric as described in claim 1, wherein heat sink and electric furnace quantity is even
The several and heat sink two sides in vacuum tank, which are formed, is symmetrically arranged structure.
4. transient temperature simulation system under hypobaric as described in any one of claims 1-3, wherein gas conditioner shape
At the cryogenic gas lower than target temperature be respectively communicated on each electric furnace by main body pipeline.
5. transient temperature analogy method under hypobaric is to carry out low pressure using any one of the claim 1-4 system
Transient temperature is simulated under environment, comprising the following steps:
When simulating Mars environment round the clock, heat sink temperature corresponding to object gas temperature is calculated, during test, is
Environment unite under hypobaric, gas is continuous media flowing, natural by the low density gas in vacuum tank therebetween
Convection current and heat radiation exchange heat, according to heat transfer formula:
In formula, Q is heat flow density, and h is convection transfer rate, and ε is radiation heat transfer coefficient, and A is radiation heat transfer area, TaTo measure
Gas temperature, TsFor heat sink temperature, TbIt is substantially constant during test for vacuum vessel wall boundary temperature；
For the gas measuring point in system environments, then have:
In formula, C is the equivalent thermal capacitance around gas temperature measuring point；
It is collated to obtain:
A in formula, b, c, d are the coefficient of heat transfer, during the test, measure the temperature of gas measuring point and Ge Lu heat sink temperature point,
By test data, the average value and all heat sink temperature average values of the gas temperature point that 6 or more measure are obtained, is fitted
It calculates, obtains each term coefficient under different pressures；
According to the coefficient of heat transfer, the corresponding heat sink temperature of different target gas temperature is calculated, fixed time temperature is formed and controls list, press
It is controlled according to list, i.e., transient temperature is simulated under realization hypobaric.
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| CN201910589824.XA CN110294149A (en) | 2019-07-02 | 2019-07-02 | Transient temperature simulation system and method under hypobaric |
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| CN201910589824.XA CN110294149A (en) | 2019-07-02 | 2019-07-02 | Transient temperature simulation system and method under hypobaric |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115127846A (en) * | 2022-06-28 | 2022-09-30 | 北京航天试验技术研究所 | Extremely strong convection environment simulation device and method for torch test |
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| CN103318427A (en) * | 2013-06-25 | 2013-09-25 | 上海宇航系统工程研究所 | Space environment simulation testing system |
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| CN107539502A (en) * | 2016-07-18 | 2018-01-05 | 北京卫星环境工程研究所 | Temperature-adjustment pressure-adjustment device for spacecraft environment experiment |
| CN107940853A (en) * | 2017-11-14 | 2018-04-20 | 北京卫星环境工程研究所 | Gas nitrogen thermostat units for heat sink thermoregulating system |
| CN108414260A (en) * | 2018-03-15 | 2018-08-17 | 北京卫星环境工程研究所 | Martian surface thermal environment simulation system |
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| CN107940853A (en) * | 2017-11-14 | 2018-04-20 | 北京卫星环境工程研究所 | Gas nitrogen thermostat units for heat sink thermoregulating system |
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| CN115127846A (en) * | 2022-06-28 | 2022-09-30 | 北京航天试验技术研究所 | Extremely strong convection environment simulation device and method for torch test |
| CN115127846B (en) * | 2022-06-28 | 2024-07-16 | 北京航天试验技术研究所 | Extremely strong convection environment simulation device and method for torch test |
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Application publication date: 20191001 |