CN110196609A - Tracking switch simulation temperature control method suitable for on-board equipment Orbital heat flux simulation system - Google Patents
Tracking switch simulation temperature control method suitable for on-board equipment Orbital heat flux simulation system Download PDFInfo
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- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
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- G05D23/19—Control of temperature characterised by the use of electric means
- G05D23/20—Control of temperature characterised by the use of electric means with sensing elements having variation of electric or magnetic properties with change of temperature
- G05D23/24—Control of temperature characterised by the use of electric means with sensing elements having variation of electric or magnetic properties with change of temperature the sensing element having a resistance varying with temperature, e.g. a thermistor
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Abstract
The invention discloses a kind of tracking of spacecraft storage tank ground vacuum heat test switch Orbital heat flux to simulate temperature control method, under the premise of at control point, temperature is uniform, using storage tank surface temperature as control object, using the thermistor of storage tank outer surface as monitoring point, control point temperature is maintained between threshold temperature upper and lower limit, in each control cycle, the peak for measuring temperature reference point and minimum are made the difference, segment processing is carried out to temperature difference, the vacuum thermal test of the practical in-orbit state of storage tank Orbital heat flux is established using different Orbital heat flux simulation temperature control method.Present invention efficiently solves the problems of traditional switch Orbital heat flux simulation temperature control method temperature control uniformity difference, realize uniformity, high efficiency and the high-precision control of temperature in spacecraft storage tank heat test.
Description
Technical field
The invention belongs to the ground vacuum heat test technical fields of spacecraft propulsion cabin storage tank, and specifically, the present invention relates to
And a kind of tracking switch Orbital heat flux simulation temperature control used in ground progress vacuum thermal test for accurate Simulated Spacecraft storage tank
Method, for improving the uniformity of temperature control when spacecraft storage tank simulates in-orbit Orbital heat flux.
Background technique
Spacecraft thermal vacuum test is to verify the various performances of spacecraft and function under defined vacuum and thermal cycle conditions
Test.It is one of the important tests in the positive sample development stage multinomial environmental simulation test of spacecraft.The main purpose of test
It is that spacecraft is made to expose Spacecraft Material and manufacturing process defect under vacuum and thermal cycle conditions, excludes initial failure, thus
Greatly improve the reliability of spacecraft in orbit.
In spacecraft thermal vacuum test, in addition to vacuum to be simulated, cryogenic conditions, with greater need for component each on spacecraft
Temperature is controlled, and with the practical in-orbit state of accurate simulation on-board equipment, this correctness for verifying spacecraft thermal design is mentioned
High spacecraft development quality, it is ensured that Mission Success is very necessary.
Traditional switch Orbital heat flux simulation temperature control method is to export power supply according to switch control mode, specific control mode
As follows: a) temperature control thermistor temp is lower than temperature control bottom threshold Tmin, power supply power-up；B) temperature control thermistor temp is higher than control
Warm upper threshold Tmax, power cut-off；C) temperature control thermistor temp is in temperature control threshold range, the shape before power supply maintenance
State is constant.
Above-mentioned traditional switch Orbital heat flux simulation temperature control method software flow is simple, but this temperature control method is in the presence of as follows
Problem:
(1) temperature height deviation is larger during the test, and uniformity is poor；
(2) temperature control precision is low during the test, be easy to cause control overshoot.
In conclusion traditional switch Orbital heat flux analog temperature control method Control platform is lower at present, lead to test mass
It cannot fundamentally be guaranteed.And spacecraft storage tank needs accurately to simulate its outer heat when ground carries out vacuum thermal test
The practical in-orbit state of stream and the correctness for verifying thermal design.To meet test requirements document, the simulation in-orbit Orbital heat flux of on-board equipment is improved
When temperature control uniformity, avoid the occurrence of overshoot, and propose the present invention.
Summary of the invention
In view of this, the present invention provides a kind of spacecraft storage tanks that is directed in the tracking of ground progress vacuum thermal test
The temprature control method of Orbital heat flux simulation temperature-controlling system is switched, to overcome shortcomings and deficiencies in the prior art, it is made to guarantee control
Warm spot temperature uniformity, target temperature control non-overshoot.To realize above-mentioned target, the invention provides the following technical scheme:
The tracking switch Orbital heat flux of spacecraft storage tank ground vacuum heat test simulates temperature control method, comprising the following steps:
Zoning monitoring is carried out to each surface temperature of spacecraft storage tank using thermistor, arrangement is active and standby in the same area
Each thermistor of part, a corresponding temperature point；
Main part thermistor temp is acquired as tracking temperature reference point；
The control method of corresponding heating circuit in each subregion are as follows:
A) period is controlled in each 12s, first determines whether the peak TKmax and minimum of storage tank surface temperature reference point
TKmin；
If b) TKmax-TKmin≤4 DEG C, temperature control is carried out according to traditional switch control mode；
If c) 4 DEG C of TKmax-TKmin >, executes tracking switch Orbital heat flux and simulate temperature control program, by the corresponding temperature control of TKmin
Active and standby part heating circuit in circuit is set as " normal open ", and active and standby part heating circuit in the corresponding temperature control circuit TKmax is set as
" normal off " gives infrared heating cage power supply, control with " normal open ", " normal off " the current target value driving programmable power supply that pre-set
Storage tank surface temperature；
D) temperature difference for comparing two temperature reference points of peak TKmax and minimum TKmin in real time, when the temperature difference is not more than 1
DEG C when (TKmax-TKmin≤1 DEG C), corresponding heating circuit reverts to normal temperature control；During this period, other temperature controlling points are according to tradition
Switch control mode carries out temperature control；
E) when temperature≤8 DEG C for any temperature reference point occur or >=35 DEG C, the prompting that reports an error is issued, if executing
Temperature control program is tracked, then exits the program, reverts to normal temperature control；
F) when temperature difference absolute value >=8 DEG C of any two temperature reference point, alarm is issued.
Preferably, tracking switch Orbital heat flux simulation temperature control method is using the preferential uniformity for guaranteeing control point temperature.Pass through
" normal open " and " normal off " of two temperature reference point peak TKmax and minimum TKmin is controlled, to control storage tank surface temperature
Degree, and other temperature controlling points carry out temperature control according to traditional switch control mode.
Preferably, real-time monitoring compares the temperature difference of two temperature reference point peak TKmax and minimum TKmin, works as temperature
When difference is not more than 1 DEG C (TKmax-TKmin≤1 DEG C), corresponding heating circuit reverts to normal temperature control；It is each to then proceed to real-time monitoring
The temperature value of reference point, (the TKmax-TKmin > 4 when being greater than 4 DEG C there are the temperature difference of peak TKmax and minimum TKmin
DEG C), start the tracking switch Orbital heat flux simulation temperature control process of a new round, the preferential uniformity for guaranteeing control point temperature.
Preferably, tracking switch Orbital heat flux simulation temperature control method makes storage tank Orbital heat flux simulation temperature-controlled precision reach ± 0.5 DEG C,
And the temperature-controlled precision requirement is not achieved in existing traditional switch Orbital heat flux simulation temperature control method.
Wherein, the peak TKmax and minimum TKmin that storage tank surface temperature reference point is obtained by monitoring, by the two
It makes the difference to obtain the temperature difference, with 4 DEG C of the temperature difference for value of statistical indicant, be established outside storage tank using two kinds of Orbital heat flux simulation temperature control methods in two stages
The vacuum thermal test of the practical in-orbit state of hot-fluid；If TKmax-TKmin≤4 DEG C, temperature control is carried out according to traditional switch control mode；
If 4 DEG C of TKmax-TKmin >, executing tracking switch Orbital heat flux and simulating temperature control program, set the corresponding heating circuit of TKmin to
" normal open " is heated according to the pre-set starting current driving programmable power supply of program to infrared cage, by the corresponding heating of TKmax
Circuit is set as " normal off ", i.e., drives programmable power supply according to the pre-set current value of program, infrared cage is powered off or reduces it
Temperature；The sampling discriminant function for establishing corresponding temperature control program, obtains corresponding current value to drive programmable power supply, to control storage tank
Surface temperature.
Preferably, tracking switch Orbital heat flux simulation temperature control program has intelligent monitoring function.When any temperature is joined
Temperature≤8 DEG C of examination point or at >=35 DEG C, Yi Fasheng temperature control overshoot, sending report an error promptings, if controlled executing tracking switch
Warm process then exits the process, reverts to normal temperature control；When temperature difference absolute value >=8 DEG C of any two temperature reference point, hair
It alarms out.
Tracking switch Orbital heat flux simulation temperature control method of the invention extends in all spacecraft ground vacuum thermal tests,
It has broad application prospects, for improving spacecraft thermal vacuum test technical level, improves whole star and subsystem heat test
Stability is of great significance.Tracking switch Orbital heat flux simulation temperature-controlling system is before preferentially guaranteeing control point temperature uniformity
It puts, control point temperature is maintained between threshold temperature upper and lower limit.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is the required attached drawing used in technical description to be briefly described.
Fig. 1 is the tracking switch Orbital heat flux simulation temperature control of spacecraft storage tank of the invention in ground progress vacuum thermal test
The schematic diagram of method；
Fig. 2 is the tracking switch Orbital heat flux simulation temperature control of spacecraft storage tank of the invention in ground progress vacuum thermal test
The flow chart of process.
Specific embodiment
Technical solution of the present invention is clearly and completely described with reference to the accompanying drawings and detailed description.
The invention discloses a kind of spacecraft storage tanks to carry out the tracking switch Orbital heat flux simulation of vacuum thermal test on ground
Temperature control method is specifically shown in following embodiment to solve the problems, such as that temperature control uniformity is poor in the prior art, easy overshoot.
Embodiment
Spacecraft storage tank disclosed by the invention simulates temperature control in the tracking switch Orbital heat flux that ground carries out vacuum thermal test
Method schematic diagram is as shown in Figure 1, comprising the following steps:
Step S11: spacecraft storage tank is first subjected to subregion, including oxygen case and combustion two subregions of case, each subregion, difference cloth
Active and standby each 1 circuit temperature-controlling circuit and 2 drive test temperature loops are set, giving temperature control section is [19 DEG C -21 DEG C], then control on threshold temperature,
Lower limit is respectively 19 DEG C and 21 DEG C.
Step S12: infrared heating cage work electricity is calculated according to the resistance value of temperature control heating circuit and the voltage that can be born
Stream target value is 0.238A.
Step S13: the infrared heating cage operating current being calculated according to step S12 adjusts programmable power supply output phase and answers
Current value.
Step S14: the Orbital heat flux simulation heating system that programmable power supply drives infrared heating cage to constitute, to spacecraft storage tank 2
A master control temperature loops apply corresponding hot-fluid.
Step S15: change spacecraft storage tank surface temperature by heating, 4 thermometric temperature-sensitives for causing its surface fixed
The resistance value of resistance generates variation.
Step S16: the resistance value of data collecting instrument temperature collection sensor thermistor, and analog quantity is changed into temperature
Digital quantity is supplied to tracking switch temperature control algorithm routine.
Spacecraft storage tank disclosed by the invention switchs Orbital heat flux simulation system in the tracking that ground carries out vacuum thermal test
Temprature control method, using the method for temperature difference Discrete control, by the peak TKmax of the storage tank surface temperature measurement point of acquisition and
Minimum TKmin makes the difference, by judging that difference location accordingly controls the infrared cage of heating circuit, temperature control method refering to
Shown in Fig. 2.
The flow chart of tracking switch Orbital heat flux simulation temperature control algorithm in control zone is shown refering to Fig. 2, the following steps are included:
Step S21: the upper and lower limit for setting final temperature control threshold range is respectively 19 DEG C and 21 DEG C；Set temperature measuring point most
At 19 DEG C of high level TKmax <, according to step S12 starting current 0.238A driving programmable power supply heating, the minimum of temperature measuring point
At 21 DEG C of TKmin >, programmable power supply power-off cooling；As 19 DEG C≤TKmax of temperature measuring point, TKmin≤21 DEG C, set temperature difference
TKmax-TKmin≤4 DEG C, according to traditional switch control mode carry out temperature control, 4 DEG C of > of temperature measuring point temperature gap TKmax-TKmin,
It executes tracking switch Orbital heat flux and simulates temperature control program, set " normal open " for the corresponding heating circuit of TKmin, that is, press starting current
0.238A drives programmable power supply heating, sets the corresponding heating circuit of TKmax to " normal off ", i.e., programmable power supply powers off, output
Electric current is 0.
Step S22: thermistor acquires the temperature of 4 temperature measuring points in the control zone Liang Ge of storage tank surface.
Step S23: within each 12s control period, the maximum temperature for obtaining 4 temperature measuring points in storage tank surface is judged by program
TKmax=21.5 DEG C of value；
Step S24: within each 12s control period, the minimum temperature for obtaining 4 temperature measuring points in storage tank surface is judged by program
TKmin=17 DEG C of value.
Step S25: being calculated the difference of temperature measuring point peak and minimum, and 21.5 DEG C -17 DEG C=4.5 DEG C.
Step S26: according to the preset target temperature difference control interval of step S22, judge temperature gap 21.5
DEG C -17 DEG C=4.5 DEG C 4 DEG C of > of temperature range executes tracking switch Orbital heat flux and simulates temperature control program.
Step S27: temperature control program, the temperature measuring point highest temperature are simulated according to the preset tracking switch Orbital heat flux of step S22
The control loop of subregion where TKmax=21.5 DEG C of angle value, programmable power supply starting current are 0.238A；Temperature measuring point lowest temperature angle value
The control loop of subregion where TKmin=17 DEG C, programmable power supply starting current are 0.
Step S28: programmable power supply drives the thin film heater in temperature control circuit by instruction output electric current.
Step S29: thin film heater discharges hot-fluid, changes storage tank surface temperature according to the change of hot-fluid.
Step S210: temperature sensor thermistor acquires 4 temperature measuring points of two subregions in storage tank surface again, and incite somebody to action this
The temperature data in next period is supplied to tracking switch Orbital heat flux simulation temperature control algorithm by the temperature in period, current data storage
Program, when the temperature difference is not more than 1 DEG C (TKmax-TKmin≤1 DEG C), corresponding heating circuit reverts to normal temperature control, and examines repeatedly
Survey loop control.
The present invention has the characteristics that compared with existing temprature control method and advantageous effects:
(1) the present invention provides a kind of spacecraft storage tanks that is directed to outside the tracking switch that ground carries out vacuum thermal test
The temprature control method of heat flux simulation temperature-controlling system sets temperature reference point peak TKmax and minimum TKmin heating circuit
It is set to " normal open " and " normal off ", real-time monitoring compares the temperature difference of two reference points, (the TKmax-TKmin when the temperature difference is not more than 1 DEG C
≤ 1 DEG C), corresponding heating circuit reverts to normal temperature control, and is repeatedly detected loop control.This method solve hot outside traditional switch
The problem of flow field simulation temperature control method uniformity difference, preferentially ensure that the uniformity of control point temperature.
(2) the present invention provides a kind of spacecraft storage tanks that is directed to outside the tracking switch that ground carries out vacuum thermal test
The temprature control method of heat flux simulation temperature-controlling system establishes the sampling discriminant function of temperature control program, reaches temperature-controlling system precision
± 0.5 DEG C, efficiently solve the problems, such as that traditional switch Orbital heat flux simulation temperature control method temperature-controlled precision is low.
(3) the present invention provides a kind of spacecraft storage tanks that is directed to outside the tracking switch that ground carries out vacuum thermal test
The temprature control method of heat flux simulation temperature-controlling system can immediately obtain " often when meeting tracking switch simulation controlled temperature conditions
It is logical ", the starting current value under the conditions of " normal off " drive programmable power supply, the temperature control speed of system on startup can be improved, and make
Its temperature rate meets certain requirement, so that the temperature control method has the ability of rapid temperature rise and drop.
(4) the present invention provides a kind of spacecraft storage tanks that is directed to outside the tracking switch that ground carries out vacuum thermal test
The temprature control method of heat flux simulation temperature-controlling system, when temperature≤8 DEG C of any temperature reference point are perhaps >=35 DEG C or any
When temperature difference absolute value >=8 DEG C of two temperature reference points, system can issue the prompting that reports an error, and exit tracking temperature control program in time,
So that temperature-controlling system has intelligent monitoring function, and temperature value can be acquired in real time, read, stored and be recalled.
Claims (6)
1. the tracking switch Orbital heat flux of spacecraft storage tank ground vacuum heat test simulates temperature control method, comprising the following steps:
Zoning monitoring is carried out to each surface temperature of spacecraft storage tank using thermistor, the active and standby part of arrangement is each in the same area
One thermistor, a corresponding temperature point；
Main part thermistor temp is acquired as tracking temperature reference point；
The control method of corresponding heating circuit in each subregion are as follows:
A) period is controlled in each 12s, first determines whether the peak TKmax and minimum of storage tank surface temperature reference point
TKmin；
If b) TKmax-TKmin≤4 DEG C, temperature control is carried out according to traditional switch control mode；
If c) 4 DEG C of TKmax-TKmin >, executes tracking switch Orbital heat flux and simulate temperature control program, the corresponding temperature control of TKmin is returned
Active and standby part heating circuit on road is set as " normal open ", and active and standby part heating circuit in the corresponding temperature control circuit TKmax is set as " often
It is disconnected ", infrared heating cage power supply, control storage are given with " normal open ", " normal off " the current target value driving programmable power supply that pre-set
Case surface temperature；
D) temperature difference for comparing two temperature reference points of peak TKmax and minimum TKmin in real time, when the temperature difference is not more than 1 DEG C
(TKmax-TKmin≤1 DEG C), corresponding heating circuit revert to normal temperature control；During this period, other temperature controlling points are according to traditional switch
Control mode carries out temperature control;
E) when temperature≤8 DEG C for any temperature reference point occur or >=35 DEG C, sending reports an error promptings, if execution with
Track temperature control program, then exit the program, reverts to normal temperature control；
F) when temperature difference absolute value >=8 DEG C of any two temperature reference point, alarm is issued.
2. the method for claim 1, wherein tracking switch Orbital heat flux simulation temperature control method guarantees control point using preferential
The uniformity of temperature, by controlling " normal open " and " normal off " of two temperature reference point peak TKmax and minimum TKmin,
Control storage tank surface temperature, and other temperature controlling points carry out temperature control according to traditional switch control mode.
3. the method for claim 1, wherein real-time monitoring compares two temperature reference point peak TKmax and minimum
The temperature difference of value TKmin, when the temperature difference is not more than 1 DEG C (TKmax-TKmin≤1 DEG C), corresponding heating circuit reverts to normal temperature control；
The temperature value for then proceeding to each reference point of real-time monitoring, when there are the temperature difference of peak TKmax and minimum TKmin to be greater than 4 DEG C
When (4 DEG C of TKmax-TKmin >), start the tracking switch Orbital heat flux simulation temperature control process of a new round, it is preferential to guarantee control point temperature
The uniformity of degree.
4. the method according to claim 1, wherein tracking switch Orbital heat flux simulation temperature control method makes the outer heat of storage tank
Flow field simulation temperature-controlled precision reaches ± 0.5 DEG C.
5. the method according to claim 1, wherein obtain the highest of storage tank surface temperature reference point by monitoring
Value TKmax and minimum TKmin, the two is made the difference to obtain the temperature difference, with 4 DEG C of the temperature difference for value of statistical indicant, uses two kinds in two stages
Orbital heat flux simulation temperature control method establishes the vacuum thermal test of the practical in-orbit state of storage tank Orbital heat flux；If TKmax-TKmin≤4 DEG C,
Temperature control is carried out according to traditional switch control mode；If 4 DEG C of TKmax-TKmin >, executing tracking switch Orbital heat flux and simulating temperature control journey
The corresponding heating circuit of TKmin is set " normal open " by sequence, i.e., drives programmable power supply according to the pre-set starting current of program
It is heated to infrared cage, sets " normal off " for the corresponding heating circuit of TKmax, i.e., driven according to the pre-set current value of program
Infrared cage is powered off or is reduced its temperature by programmable power supply；The sampling discriminant function for establishing corresponding temperature control program, obtains corresponding electric current
Value drives programmable power supply, to control storage tank surface temperature.
6. the method according to claim 1, wherein the tracking switch Orbital heat flux simulation temperature control program has
Intelligent monitoring function, when temperature≤8 DEG C of any temperature reference point or >=35 DEG C, Yi Fasheng temperature control overshoot, sending reports an error
It reminds, if tracking switch temperature control process executing, exits the process, revert to normal temperature control；When any two temperature is joined
When temperature difference absolute value >=8 DEG C of examination point, alarm is issued.
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