CN108490775A - Spacecraft temperature stability control device and control method - Google Patents
Spacecraft temperature stability control device and control method Download PDFInfo
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- CN108490775A CN108490775A CN201810223265.6A CN201810223265A CN108490775A CN 108490775 A CN108490775 A CN 108490775A CN 201810223265 A CN201810223265 A CN 201810223265A CN 108490775 A CN108490775 A CN 108490775A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B13/00—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion
- G05B13/02—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
- G05B13/04—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators
- G05B13/042—Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric involving the use of models or simulators in which a parameter or coefficient is automatically adjusted to optimise the performance
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D23/00—Control of temperature
- G05D23/19—Control of temperature characterised by the use of electric means
- G05D23/1927—Control of temperature characterised by the use of electric means using a plurality of sensors
- G05D23/193—Control of temperature characterised by the use of electric means using a plurality of sensors sensing the temperaure in different places in thermal relationship with one or more spaces
- G05D23/1931—Control of temperature characterised by the use of electric means using a plurality of sensors sensing the temperaure in different places in thermal relationship with one or more spaces to control the temperature of one space
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D23/00—Control of temperature
- 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 purpose of the present invention is to provide a kind of spacecraft temperature stability control devices and control method.The spacecraft temperature stability control device includes temperature stability controller, heat-proof device and installation base plate.Temperature stability controller includes：The temperature of its present position and the temperature detecting part of output temperature detected value are detected respectively with multiple temperature detecting elements；The heating part heated with multiple heaters and according to the instruction of control unit；And control unit, the control unit receive temperature detection value, it is compared with setting value and calculates controlling value using it to control heating part.Control unit is so that can ensure that the mode that heating power is constant needed for next controlling cycle, according to the size of controlling value and the quantity of heater come the multiple heaters of the random selection of by stages and configuration switch state and time.According to the present invention, it can be easy to implement, is light-weight, stable temperature control degree is high, heater life is long, system designed reliability is strong and it is few to occupy housekeeping software resource.
Description
Technical field
The present invention relates to spacecraft temperature stability control devices and control method, specifically, are related to being suitable for boat
The temperature stability control device of its device and its improvement of control method.
Background technology
In general, the task of spacecraft thermal control system be in, under the conditions of orbit determination road, posture and operating mode, protect
All appts equipment meets its temperature index requirement on card star.In recent years, with the continuous development of space technology, more and more
Satellite load equipment (especially scientific experiment load) is proposed more temperature uniformity, temperature stability and rate of temperature change
High requirement.For example, certain navigation satellite atomic clock mounting surface operating temperature stability requirement is not more than ± 0.5 DEG C/15h, certain is distant
Feel satellite load camera primary mirror radial symmetry gradient and be no more than 0.5 DEG C, rate of temperature change is no more than 1 DEG C/h.Correspondingly, to thermal control
The control module and algorithm of software also proposed high requirement.
In general, the in-orbit during flight of spacecraft, in orbit external thermal flux variation and star heat power consumption variation can all influence whole star
Temperature levels and situation of change.In general, orbit external thermal flux includes that direct sunlight hot-fluid, earth reflection hot-fluid and the earth are infrared
These three parts of radiant heat flux.Moreover, the Orbital heat flux that a certain position is absorbed can be with its surface thermo-optical property, position and posture
Change and periodically variable rule is presented.Equipment for more demanding temperature stability and position, pass through it is proposed that having
The temperature stability of whole star is controlled to realize this mode of the High-temperature stabilization degree of specific region, but which can wave
Precious resources on Fei Xing, such as weight, power consumption, remote measuring and controlling etc..Thus, consider first using the external thermal agitation of isolation every
From measure, and using the electrical heating Active thermal control technology of grading control, to carry out the temperature control of high stability.
Existing spacecraft temperature stability control system is made of electric heater, controller and temperature sensor three parts
Close loop control circuit further uses electrical heating Active thermal control mode generally on the basis of using passive thermal control mode.It sets
Meter thinking is：Heating power is designed according to worst cold case by taking relatively low temperature design method, and is ensured simultaneously in high temperature
Also there is corresponding temperature control ability, to realize active temperature control under operating mode.
The mentality of designing of known thermal control mode is：First, a relatively stable thermal environment is provided for controlled device, and
Reduce the temperature fluctuation of controlled device using passive thermal control mode, on this basis, with using the active of corresponding control algolithm
Thermal control mode is come the heat affecting inside and out eliminating.Specifically, taking following measures：
1. Design on thermal insulation：Reduce radiation thermal coupling by coating multilayer insulation component and reducing material surface emissivity by virtue；Pass through
It adds heat insulating mattress and reduces contact area to reduce heat conduction thermal coupling；
2. control algorithm design：Using electrically heated active temperature control technology, inclined low temperature method is taken to design radiating surface and heating
Power, and ensure that also there is corresponding temperature control ability under worst hot case；
Invention content
The technical problems to be solved by the invention
As the control algolithm for realizing Active thermal control, for example, proposing there is switch control algolithm, which is boat
Common temperature control algorithm in its device Active thermal control.Its feature is that control is simple, can meet most of for temperature stability
The temperature control demand of the equipment in (within the scope of the several years) of less demanding.But there is the control for temperature stability in the control method
The not high enough problem of ability processed.
Also, as other control algolithms for realizing Active thermal control, for example, proposing proportional control algolithm.Although comparing
Control algolithm is switched, ratio control algolithm has higher control accuracy, still, in the algorithm, in order to ensure system temperature control
The requirement of stability needs the controlling cycle using the short period, thus the number of heater progress switch motion is more frequent,
To which the reduction of service life can be caused, further, since ratio control algolithm generally use PULSE HEATING mode, thus temperature control is bent
Line easy tos produce spike, to influence temperature stability.
On the other hand, as other the another control algolithms for realizing Active thermal control, for example, proposing there are PI control algolithms.It is logical
It crosses and uses PI control algolithms, static deviation can be eliminated and reduce the overshoot condition during temperature control, it is high-precision to meet simultaneously
The control requirement of degree and High-temperature stabilization degree.But when using the algorithm, heater carries out the number more frequency of switch motion
It is numerous, to which the reduction of service life can be caused, in addition, the algorithm is to the more demanding of housekeeping software computing capability.
In addition, as other another control algolithms for realizing Active thermal control, for example, proposing there is pid control algorithm.The PID
The stable temperature control of control algolithm is good, reliability is high, can eliminate static deviation and overshoot is few, can realize high-precision, Gao Wen
Surely the temperature control spent.But pid control algorithm has the following problems：Dependent on the mathematical models of controlled device, and algorithm
More complicated, control parameter is generally required to be optimized by experiment, in addition, heater carries out the number of switch motion more
Frequently, service life is influenced, and can also occupy more software resource.
Although as described above, proposing various control algolithms in the past, it is not enough.The present invention is to consider the above problem
And complete, its purpose is to provide one kind to be easy to implement, light-weight, stable temperature control degree is high, heater life is long, system
Designed reliability is strong and occupies housekeeping software resource less spacecraft temperature stability control device and its control method.
Technical scheme applied to solve the technical problem
The present invention spacecraft temperature stability control device include：Temperature stability controller, installation base plate and
Heat-proof device,
The temperature stability controller is used to carry out temperature stability control to specific region, is installed on the installation base
Plate,
The heat-proof device by cover the temperature stability controller and by temperature regulating device in a manner of be fixed on the installation base
Plate,
The temperature stability controller includes：
Temperature detecting part, the temperature detecting part have multiple temperature detecting elements, detect the temperature of its present position and defeated respectively
Go out temperature detection value,
Heating part, the heating part have multiple heaters, are heated according to the instruction of control unit,
Control unit, the control unit receive the temperature detection value that is transmitted to by the temperature detecting part, by its with setting value into
Row relatively and using its calculating controlling value controls the heating part,
The control unit is so that can ensure that the mode that heating power is constant needed for next controlling cycle, according to the controlling value
Size and the quantity of the heater randomly choose the multiple heater with coming by stages and set corresponding on off state and
Time.
The control unit of the present invention includes heater setting module, temperature Effective judgement module, data processing module, switch
Control module and segmentation scales control module,
The heater setting module instructs that the multiple heater is set as enabled respectively according to externally input setting
State/illegal state, and setting result is output to the segmentation scales control module,
The temperature Effective judgement module instructs the multiple temperature detecting element to be detected in each sampling interval successively,
And be compared temperature detection value with preset effective temperature section, it is being judged as that it is described effective that temperature detection value is located at
When temperature range, it is output to data processing module as effective temperature sampled value, is being judged as not being located at effective temperature
When spending section, excluded and automatically switch to next temperature detection value to re-start judgement,
The data processing module is no to the effective temperature sampled value to be judged positioned at preset ratio control interval,
In the case where being judged as that the effective temperature sampled value is located at the ratio control interval, calculates next controlling cycle theory and account for
Sky compares and is output to segmentation scales control module,
It is judged as that the effective temperature sampled value is less than or equal to the temperature control of the ratio control interval in the data processing module
When bottom threshold, switch control module opens all heaters for being in enabled state,
It is judged as that the effective temperature sampled value is more than or equal to the temperature control of the ratio control interval in the data processing module
When upper threshold, the switch control module closes all heaters for being in enabled state,
The segmentation scales control module is enabled according to the next controlling cycle theory duty ratio and described be in that receive
The quantity of the heater of state, so that can ensure that the mode that heating power is constant needed for next controlling cycle, with coming by stages
The heater in enabled state is selected at random, and sets corresponding on off state and time.
Invention effect
In accordance with the invention it is possible to realize be easy to implement, be light-weight, stable temperature control degree is high, heater life is long, system
Designed reliability is strong and occupies housekeeping software resource less spacecraft spacecraft temperature stability control device and its control
Method.
Description of the drawings
Fig. 1 is the signal of the structure for the spacecraft temperature stability control device 100 for indicating embodiments of the present invention 1
Figure.
Fig. 2 is the block diagram for the temperature stability controller 1 for schematically showing embodiments of the present invention 1.
Fig. 3 is the flow chart of the action of the control unit 101 in the temperature stability controller 1 indicated involved by embodiment 1.
Fig. 4 is schematically the block diagram of the variation 1a of the temperature stability controller 1 involved by embodiments of the present invention 1.
Fig. 5 is the schematic diagram for nearby amplifying the end of the installation base plate 3 in Fig. 1 and showing.
Specific implementation mode
Hereinafter, based on the attached drawing embodiment that the present invention will be described in detail.In addition, the present invention is not limited to following embodiment party
Formula.Identical label in each figure indicates identical part.
Embodiment 1
Fig. 1 is the schematic diagram of the structure for the spacecraft temperature stability control device 100 for indicating embodiments of the present invention 1.
As shown in Figure 1, spacecraft temperature stability control device 100 includes for the specific region to spacecraft into trip temperature
Stability control temperature stability controller 1, for installing temperature stability controller 1 and by the installation base of temperature regulating device 2
Plate 3 and by cover temperature stability controller 1 and by temperature regulating device 2 in a manner of be configured at the heat-proof device 4 of installation base plate 3.
Herein, it is illustrated so that 3 by temperature regulating device 2 as an example, but not limited to this.
Spacecraft temperature stability control device 100 is for example fixed on device mounting plate 6 by connecting elements 5.
Fig. 2 is the block diagram for the temperature stability controller 1 for schematically showing embodiments of the present invention 1.
Temperature stability controller 1 is configured to：Control unit 101, temperature detecting part 201 and heating part 301, and formed
Close loop control circuit.
As shown in Fig. 2, control unit 101 includes heater setting module 101a, temperature Effective judgement module 101b, data processing
Module 101c, switch control module 101d and segmentation scales control module 101e.It will hereinafter be specifically described.
(temperature detecting part 201)
Temperature detecting part 201 has 2 or more multiple temperature detecting elements, this sentences 3 temperature detecting element 201a
It is illustrated for~201c, but it is not limited to this.In the present embodiment, said by taking negative temperature coefficient temperature detecting element as an example
It is bright, but not limited to this.
Multiple temperature detecting element 201a~201c are detected the temperature change of its present position, and output detection letter respectively
Number to control unit 101 input terminal.
As temperature detecting element, such as it can be properly used high precision measuring temperature thermistor or platinum resistance.In addition, multiple temperature
Detecting element 201a~201c configurations close to each other are spent, and are backuped each other, the case where some temperature detecting element breaks down,
Backup temperature detecting element can be automatically switched to.In addition, the installation position of temperature detecting element and quantity can be wanted according to design
It asks and is suitably adjusted.
(heating part 301)
Heating part 301 is heated according to the instruction of control unit 101, to form active temperature control region.It is with multiple
Power is identical and position similar in heater, this is illustrated for sentencing 4 heater 301a~301d.
Multiple heater can be evenly distributedly arranged, can also subregion it is densely distributed, subregion distribution it is sparse.It is right
It in the position of multiple heaters and quantity, can be determined according to design requirement, as long as having with multiple temperature detecting elements
Thermal response relationship.
(control unit 101)
Fig. 3 is the flow of the action of the control unit 101 in the temperature stability controller 1 indicated involved by embodiment 1
Figure.
Control unit 101 receives the detection signal being transmitted to by temperature detecting part 201, and it is compared to control with setting value
Heating part 301 randomly chooses and adds so that can ensure that the mode that heating power is constant needed for next controlling cycle with coming by stages
Multiple heaters in hot portion 301 simultaneously set its on off state and switch time.Hereinafter it will be described in more detail.
(heater setting module 101a)
Control unit 101 is instructed according to externally input setting come respectively will be multiple first when each controlling cycle starts
Heater 301a~301d is set as " enabled state/illegal state " (that is, " 1/0 "), and setting result is output to segmentation
Ratio control module 101e.Here, it is assumed that be instructed according to externally input setting, heater 301a~301d is set as
" enabled state ".(step 1)
(temperature Effective judgement module 101b)
Then, temperature Effective judgement module 101b instructs 3 temperature detecting elements successively according to certain sampling time sequence
201a~201c was detected and stores in the respective sampling period, and (wherein, m is indicated m-th by its detected value Vmi
Temperature detecting element, m=1,2,3；I indicates ith sampling, i=1,2,3 ...) have with preset as temperature sampling value
Effect temperature range [Vmin, Vmax] is compared.Herein, Vmin, Vmax are under the preset effective temperature section of difference
Limit threshold value and upper limit threshold, sampling number i can be preset according to parameters such as sampling periods.(step 2)
Temperature Effective judgement module 101b is being judged as that detected value Vmi is located in effective temperature section [Vmin, Vmax]
When (be judged as "Yes" in step 2), as effective temperature sampled value Vnt, (wherein, n indicates the sampling of n-th effective temperature
Value, n=1,2,3 ...) output is used for subsequent closed loop control algorithm to data processing module 101c.
Temperature Effective judgement module 101b is when being judged as that detected value Vmi is not located in effective temperature section [Vmin, Vmax]
(being judged as "No" in step 2), which is excluded and automatically switch to next detected value such as Vmi+1 (steps 3) with
Re-start Effective judgement.
Thus, it is possible to prevent from damaging because of temperature element, abnormal data is used for closed loop algorithm caused by the reasons such as external disturbance
Control, so that it is guaranteed that the uninterrupted continuous and steady operation of temperature control system.
Herein, preferable temperature Effective judgement module 101b with certain sample rate commanded temperatures detecting element 201a~
201c is detected in respective sampling period, and only using the median of obtained multiple detected values per second as temperature sampling
Value, is compared with preset effective temperature section [Vmin, Vmax].Such as assume that sample rate is 3 times/second, then
Temperature Effective judgement module 101b commanded temperatures detecting element 201a are detected with the speed of 3 times/second, in sampling week
3 detected value V14, V15, V16 (V14 obtained at the 2nd second of the phase<V15<V16), in-between value V15 is adopted as temperature
Sample value is compared with preset effective temperature section [Vmin, Vmax].
More preferably for last k seconds of sampling period, temperature Effective judgement module 101b will be per second as described above
It is detected according to certain sample rate, the median that compares and obtain is stored, and on this basis, intermediate to this k
Value calculates arithmetic mean of instantaneous value, then comes calculated arithmetic mean of instantaneous value as temperature sampling value and preset comfort zone
Between [Vmin, Vmax] be compared.For example, it is assumed that k=3, sample rate is 3 times/second, then every 1 second for last 3 seconds, according to
The secondary median obtained in 3 detected values per second, then to 3 middle-value calculating arithmetic mean of instantaneous values, and by the arithmetic mean of instantaneous value
It is compared with [Vmin, Vmax].Thereby, it is possible to more effectively exclude abnormal data, to more reliably ensure temperature control system
Uninterrupted continuous and steady operation.
(data processing module 101c) (switch control module 101d)
As described above, data processing module 101c receives the effective temperature being transmitted to by temperature Effective judgement module 101b
Sampled value Vnt (wherein, n indicates n-th of effective temperature sampled value, n=1,2,3 ...) is spent, to effective temperature sampled value Vnt
Whether being judged positioned at ratio control interval [Vst- Δs V, Vst+ Δ V], wherein Vst is the corresponding voltage value of target temperature,
Δ V is ratio control interval voltage deviation.(step 4)
(the step in the case where being judged as that effective temperature sampled value Vnt is located at ratio control interval [Vst- Δ V Vst+ Δs V]
In rapid 4 be "Yes"), data processing module 101c calculated according to following equation 1 next controlling cycle theory duty ratio η and by its
It is output to segmentation scales control module 101e.(step 5)
η=Kpe=Kp (Vnt-Vst) (formula 1)
In formula,
The next controlling cycle theory duty ratios of η-
The rate mu-factor of Kp- data processing modules 101c
The corresponding voltage value of n-th of effective temperature sampled value of Vnt-, n=1,2,3 ...；
The corresponding voltage value of Vst-target temperature；
In the case where being judged as that effective temperature sampled value Vnt is not located at ratio control interval [Vst- Δ V Vst+ Δs V]
(being "No" in step 4), data processing module 101c are further controlled whether effective temperature sampled value Vnt is more than or equal to ratio
The temperature control upper threshold in section is (Vst+ Δ V), and is judged (step less than effective temperature section upper threshold Vmax simultaneously
6)。
In the case of being judged as "Yes" in step 6, which is exported to switch and controls mould by data processing module 101c
Block 101d, switch control module 101d open all heater (steps 7) in " enabled state ".
In the case of being judged as "No" in step 6, become following situations：That is, effective temperature sampled value Vnt is less than or equal to ratio
The temperature control bottom threshold (Vst- Δ V) of control interval, and simultaneously greater than effective temperature section bottom threshold Vmin, then data processing
Module 101c exports the judging result to switch control module 101d, and switch control module 101d closings are all in " enabled
Heater (the step 8) of state ".
As described above, switch control module 101d is based on switch control algolithm, controlled beyond ratio in effective temperature sampled value Vnt
In the case of section [Vst- Δs V, Vst+ Δ V], the heater in " enabled state " is all turned on or Close All, to
It can realize that the detection temperature for making temperature detecting element rapidly carries out convergent technique effect towards target temperature.
(segmentation scales control module 101e)
In segmentation scales control module 101e, on the basis of conventional proportional control algolithm, further according to next control
The size of cyclical theory duty ratio η and in " enabled state " heater quantity N (N is natural number), with coming by stages from
The heater of respective numbers is selected at random in the above-mentioned heater in " enabled state ", and it is timely to set corresponding on off state
Between carry out power output, to realize segmentation scales control.
For example, it is assumed that temperature stability controller 1 has 3 heaters for being in " enabled state ".It is shown in table 1
In the case of different theories duty ratio, on off state and time for the heater that is in " enabled state " are (corresponding to actually accounting for
Empty ratio) setting.Such as in the case of 0 ＜ η≤0.3 of theoretical duty ratio, from 3 heaters in " enabled state " with
Machine selects a heater, and makes it according to this duty ratio of 3.0 η to be controlled.
| Theoretical duty ratio η | The heater of 3 " enabled state " | Actual duty cycle η ＇ |
| η≥1 | It is all turned on | 1 |
| 0.6 ＜ η ＜ 1 | All select | η |
| 0.3 η≤0.6 ＜ | 2 heaters are selected at random | 1.5η |
| 0 η≤0.3 ＜ | 1 heater is selected at random | 3.0η |
| η≤0 | Close All | 0 |
Table 1
It returns to Fig. 3 to continue to illustrate, in the present embodiment, segmentation scales control module 101e first determines whether (0<η≤1/N)
Whether true (step 9) (herein, N=4 because there are 4 be in " enabled state " heater 301a~301d), in step
In the case that 9 set up, 1 heater is arbitrarily selected from N number of heater 301a~301d in " enabled state ", and make it
(step 10) is switched according to N* η.
In the case where step 9 is invalid, segmentation scales control module 101e judges (1/N<η≤2/N) whether true (step
11) (herein, N=4) appoints in the case where step 11 is set up from N number of heater 301a~301d in " enabled state "
Meaning 2 heaters of selection, and it is made to be switched (step 12) according to (N/2) * η.
In the case where step 11 is invalid, segmentation scales control module 101e judges (2/N<η≤3/N) whether true (step
13) (herein, N=4) appoints in the case where step 13 is set up from N number of heater 301a~301d in " enabled state "
Meaning selects 3 heaters (herein for select entirely), and it is made to be switched (step 14) according to (N/3) * η.
In the case where step 13 is invalid, it is judged as (3/N<η≤4/N) set up (step 13) (herein, N=4), segmentation scales
Control module 101e all chooses 4 heater 301a~301d in " enabled state ", and make its according to (N/4) * η into
Row switch (step 15).
Segmentation scales control module illustrated above according to the quantity N of the heater in " enabled state ", by [0,1] this
One section is averagely divided into several subintervals, and successively by the theoretical duty ratio η of next controlling cycle and several subintervals
It is compared, selects an appropriate number of heater from the heater in " enabled state " based on comparative result and set phase
The specific example of the on off state and time answered.But the either dividing mode in section, or for being in " enabled state "
The quantity of heater selects and is not limited to this for the setting of its on off state and time, as long as can ensure that next control week
Heating power needed for phase, and heater is had holidays by turns when theoretical duty ratio is smaller.
Thereby, it is possible on the basis of ensuring that heating power needed for next controlling cycle is constant, realize to a certain given zone
The High-temperature stabilization degree in domain controls.Each heater can be kept smaller in theoretical duty ratio in the case where ensuring High-temperature stabilization degree
Controlling cycle in carry out " having holidays by turns ", to reduce action frequency of the switch control device of each heater in lifetime, by
This improves the designed reliability of system.
Compared to using in the case of conventional proportional control algolithm, the heater of closed-loop control is participated in each control cycle
It is primary to be both needed to progress switch motion, it is assumed that each controlling cycle is 30s, and projected life is 10 years, then each heater is opened
The number of pass action is close to thousands of times.In contrast, using the segmentation scales control algolithm of present embodiment, if
Required heating power reasonable design can then be reduced the switch motion number of respective heater nearly 3,000,000 times, to significantly
Improve heat control system designed reliability in ground.
As described above, the control unit 101 of present embodiment switchs control algolithm by combined use and segmentation scales control
Algorithm, temperature control is gentle when having small duty ratio, and temperature controls rapid advantage when big space rate.In addition, during control,
Power applies gently, so as to efficiently reduce the appearance for the overshoot condition that pulsed controls in conventional proportional control algolithm,
Improve the stability of system temperature control.And the on-off times of each heater during control can be significantly decreased, in turn
The designed reliability of raising system.Additionally it is possible to eliminate inside and outside heat affecting and changed by temperature controlling instruments itself heat consumption etc.
Influence to temperature control area temperature stability.
In addition, in present embodiment, in the system control carried out by control unit 101, directly obtained using by sampling
Detected value, that is, the voltage value obtained is calculated again without being translated into after temperature data, and thereby, it is possible to reduce housekeeping software meter
Calculation amount and the temperature-controlled precision for improving system.The reason is that temperature data need to usually carry out multinomial with voltage value conversion formula
Or power exponent calculates, transfer process can occupy more software resource, and the meeting after temperature data and voltage value carry out multiple conversions
Influence system temperature-controlled precision.
Fig. 4 is schematically that the variation temperature of the temperature stability controller 1 involved by embodiments of the present invention 1 is stablized
Spend the block diagram of controller 1a.
As shown in figure 4, temperature stability controller 1a also has pre-buried heat pipe portion 401.The pre-buried heat pipe portion includes multiple
To be located in parallel to one another in a manner of by temperature regulating device 2 in by the pre-buried heat pipe component of linear of 2 lower section of temperature regulating device.This
Wen Zhong is illustrated by taking 4 pre-buried heat pipe component 401a~401d as an example, and but it is not limited to this.In addition, pre-buried heat pipe component
401a~401d can also use the heat transfer unit (HTU)s such as L-shaped heat pipe or U-shaped heat pipe, and shape and quantity can be according to installation base plates 3
Size and setting is adjusted by the position of temperature regulating device 2 and heating part 301 etc..
Pre-buried heat pipe portion 401 is preheated according to the output of control unit 101, in the active formed by heating part 301
The hot path that energy efficient heat transfer is formed between temperature controlled zone and temperature detecting part 201 further increases heating part 301 and is examined with temperature
Response relation between survey portion 201.In addition, by the way that pre-buried heat pipe portion 401 is arranged, can more effectively balanced each region and equipment it
Between the temperature difference, reduce local temperature difference simultaneously realize isothermal, so as to further increase the higher temperature of spacecraft specific region
Spend stability control.
As shown in Figure 1, heat-proof device 4 by cover temperature stability controller 1 and by temperature regulating device 2 in a manner of be configured at peace
Fill substrate 3.Wherein, heat-proof device 4 uses multilayered structure, and counting unit aluminizer is arranged by interval is constituted with terylene hairnet,
Its thickness (unit number) can be set according to specific insulation requirement, be not limited to fixed cell number.
Furthermore it is preferred that the surfaces externally and internally of heat-proof device 4 is both provided with polyester metallized film, to reduce system radiation leakage heat, from
And improve the stable temperature control degree of spacecraft temperature stability control device 100.It, can also in the setting of heat-proof device
Using such as porous materials such as fibrous material, foamed material.
Fig. 5 is the schematic diagram for nearby amplifying the end of the installation base plate 3 in Fig. 1 and showing.As shown, spacecraft is used
The installation base plate 3 of temperature stability control device 100 is fixed on device mounting plate 6 by connecting elements 5.
Connecting elements 5 is anchored on the inner wall of the hole installing face of installation base plate 3 and device mounting plate 6.Connecting elements 5 includes screw
7 and screw lining 8.7 screw of screw is anchored on the inner wall of the hole installing face of screw lining 8 and device mounting plate 6, head not with peace
Dress substrate 3 is in contact.
Screw lining 8 is inserted between screw 7 and installation base plate 3, the upper and lower surface of the upper end of structure annular in shape when overlooking
Abutted respectively with the surface on the head of screw 7 and installation base plate 3, side of sidewall portion respectively with the screw rod cylinder of screw 7 and installation base
The inner wall of the hole installing face of plate 3 is in contact.Using screw 7 connection installation base plate 3 is compressed come through-hole via screw lining 8.By setting
Screw lining 8 is set, can be in direct contact to avoid screw 7 and installation base plate 3, to play heat-blocking action, and improve space flight
The stable temperature control degree of device temperature stability control device 100.
Furthermore it is preferred that screw 7, using high intensity, the titanium alloy material of low thermal conductivity, screw lining 8 uses epoxy resin
Class material, such as glass steel.
It is connected and fixed installation base plate 3 and device mounting plate 6 by using connecting elements 5, so as to avoid screw 7 and device
Mounting plate 6 is in contact, and efficiently reduces system heat conduction leakage heat.In addition it is also possible to which spacecraft is used using other connecting elements
Temperature stability control device 100 is fixed on device mounting plate 6.
It is preferred that heat insulating component is directly arranged in installation base plate 3 and device mounting plate 6, to be further reduced installation base plate 3
Heat-transfer couple between outside.
As described above, according to embodiment 1, reduced between celestial body by the way that heat-proof device 4 and connecting elements 5 is arranged
Heat conduction and radiation thermal coupling, and using control algolithm carry out active thermal control, so as to realize spacecraft specific region compared with
High temperature stability control.
Embodiments of the present invention are illustrated above, embodiment is only shown as example, and does not limit invention
Range.In addition, embodiment can be implemented in a variety of manners, without departing from the spirit of the invention, various provinces can be carried out
Slightly, it replaces, change.Embodiment and its variation are all contained in the range and its purport of invention, are similarly included in right
In invention and its equivalent scope recorded in claimed range.
Industrial practicability
Spacecraft of the present invention High-temperature stabilization degree temperature regulating device and spacecraft High-temperature stabilization degree temperature control side
Method has many advantages, such as to be easy to implement, is light-weight, control stability is high, it is few to occupy housekeeping software resource, can be widely applied to navigate
The fields such as sky, space flight, but it is not limited to the field.
Claims (16)
1. a kind of spacecraft temperature stability control device, which is characterized in that including：Temperature stability controller, heat-insulated dress
It sets and installation base plate,
The temperature stability controller is used to carry out temperature stability control to specific region, is installed on the installation base
Plate,
The heat-proof device by cover the temperature stability controller and by temperature regulating device in a manner of be fixed on the installation base
Plate,
The temperature stability controller includes：
Temperature detecting part, the temperature detecting part have multiple temperature detecting elements, detect the temperature of its present position and defeated respectively
Go out temperature detection value,
Heating part, the heating part have multiple heaters, are heated according to the instruction of control unit,
Control unit, the control unit receive the temperature detection value that is transmitted to by the temperature detecting part, by its with setting value into
Row relatively and using it calculates controlling value, to control the heating part,
The control unit is so that can ensure that the mode that heating power is constant needed for next controlling cycle, according to the controlling value
Size and the quantity of the heater carry out the multiple heater of random selection of by stages and set corresponding on off state and
Time.
2. spacecraft as described in claim 1 temperature stability control device, which is characterized in that
The control unit includes heater setting module, temperature Effective judgement module, data processing module, switch control mould
Block and segmentation scales control module,
The heating electrical appliance setting module instructs respectively to make the setting of the multiple heater mark according to externally input setting
Energy state/illegal state, and setting result is output to the segmentation scales control module,
The temperature Effective judgement module instructs the multiple temperature detecting element to be detected in each sampling interval successively,
And be compared temperature detection value with preset effective temperature section, it is being judged as that it is described effective that temperature detection value is located at
When temperature range, it is output to data processing module as effective temperature sampled value, is being judged as not being located at effective temperature
When spending section, excluded and automatically switch to next temperature detection value to re-start judgement,
The data processing module is no to the effective temperature sampled value to be judged positioned at preset ratio control interval,
In the case where being judged as that the effective temperature sampled value is located at the ratio control interval, calculates next controlling cycle theory and account for
It is empty than and be output to the segmentation scales control module,
It is judged as that the effective temperature sampled value is less than or equal to the temperature control of the ratio control interval in the data processing module
When bottom threshold, the switch control module closes all heaters for being in enabled state,
It is judged as that the effective temperature sampled value is more than or equal to the temperature control of the ratio control interval in the data processing module
When upper threshold, the switch control module opens all heaters for being in enabled state,
The segmentation scales control module is enabled according to the next controlling cycle theory duty ratio and described be in that receive
The quantity of the heater of state, so that can ensure that the mode that heating power is constant needed for next controlling cycle, with coming by stages
The heater in enabled state is selected at random, and sets corresponding on off state and time.
3. spacecraft as claimed in claim 2 temperature stability control device, which is characterized in that
The multiple temperature detecting element of temperature Effective judgement module instruction is in each sampling interval according to certain sampling
Speed is detected, and only compares the median of obtained multiple temperature detection values per second with the effective temperature section
Compared with.
4. spacecraft as claimed in claim 3 temperature stability control device, which is characterized in that
For last k seconds each seconds of the sampling period, the temperature Effective judgement module obtain respectively k it is described in
Between be worth, and to the k middle-value calculating arithmetic mean of instantaneous values, will calculate and the arithmetic mean of instantaneous value and the effective temperature
Section is compared, and herein, k is natural number.
5. spacecraft as claimed in claim 3 temperature stability control device, which is characterized in that
The sample rate is 3 times per second.
6. spacecraft as claimed in claim 4 temperature stability control device, which is characterized in that
The k=3.
7. spacecraft as claimed in claim 2 temperature stability control device, which is characterized in that
The control unit directly uses acquired temperature detection value i.e. voltage value to be calculated.
8. spacecraft as described in claim 1 temperature stability control device, which is characterized in that
The multiple temperature detecting element is configured and is backuped each other in a manner of close to each other, using temperature-measuring thermistor or
Platinum resistance.
9. spacecraft as described in claim 1 temperature stability control device, which is characterized in that
The heat-proof device is the multilayered structure constituted by counting unit aluminizer and terylene hairnet is arranged by interval.
10. spacecraft as claimed in claim 9 temperature stability control device, which is characterized in that
The surfaces externally and internally of the heat-proof device is both provided with polyester metallized film.
11. spacecraft as described in claim 1 temperature stability control device, which is characterized in that
The installation base plate is fixed on the mounting plate using connecting elements,
The connecting elements includes screw and the screw lining that is inserted between the screw and the installation base plate.
12. spacecraft as claimed in claim 11 temperature stability control device, which is characterized in that
The screw is made of titanium alloy material, and the screw lining is made of epoxy resin material.
13. spacecraft as described in claim 1 temperature stability control device, which is characterized in that
The temperature stability controller also has pre-buried heat pipe portion,
The pre-buried heat pipe portion include it is multiple by across it is described by temperature regulating device in a manner of be set to it is described by below temperature regulating device
Pre-buried heat pipe component.
14. spacecraft as claimed in claim 13 temperature stability control device, which is characterized in that
The pre-buried heat pipe component uses linear heat pipe, L-type heat pipe or U-shaped heat pipe.
15. a kind of spacecraft temperature stability control device, which is characterized in that spacecraft temperature stability control device
For spacecraft temperature stability control device, which includes temperature stability control
Device, installation base plate and heat-proof device,
The temperature stability controller is used to carry out temperature stability control to specific region, is installed on the installation base plate
And there is temperature detecting part, heating part and control unit,
The heat-proof device by cover the temperature stability controller and by temperature regulating device in a manner of be fixed on the installation base
Plate,
The temperature detecting part has multiple temperature detecting elements, detects the temperature of its present position and output temperature detection respectively
Value,
The spacecraft temperature stability control device includes：The multiple of the heating part are added according to the instruction of the control unit
The heating stepses that hot device is heated；The temperature detection value is compared with setting value and the temperature detection value is utilized to calculate
Controlling value, to control the rate-determining steps of the heating part,
Wherein, so that can ensure that the mode that heating power is constant needed for next controlling cycle, according to the size of the controlling value
The multiple heater is randomly choosed with the quantity of the heater with coming by stages and set corresponding on off state and time.
16. spacecraft as claimed in claim 15 temperature stability control device, which is characterized in that
The rate-determining steps：
It is instructed according to externally input setting the multiple heater is set as enabled state/illegal state respectively, and will
Set the heater setting procedure of result output；
Instruct the multiple temperature detecting element to be detected in each sampling interval successively, and by temperature detection value with set in advance
Fixed effective temperature section is compared, and when being judged as that the temperature detection value is located at the effective temperature section, is made
It is exported for effective temperature sampled value, when being judged as not being located at the effective temperature section, is excluded and automatically switched to down
One temperature detection value re-starts the temperature Effective judgement step of judgement；
It is no to the effective temperature sampled value to judge positioned at preset ratio control interval, be judged as it is described effectively
In the case that temperature sampling value is located at the ratio control interval, calculates next controlling cycle theory duty ratio and output it
Data processing step；
When being judged as that the effective temperature sampled value is less than or equal to the temperature control bottom threshold of the ratio control interval, institute is closed
There is the heater for being in enabled state, and is being judged as the effective temperature sampled value more than or equal to ratio control
When the temperature control upper threshold in section, the switch rate-determining steps of all heaters in enabled state are opened；
According to the quantity of the when described heater in enabled state of the next controlling cycle theory duty received, with
So that can ensure that the mode that heating power is constant needed for next controlling cycle, enabled state is in described with coming by stages at random
Heater selected, and set corresponding on off state and the segmentation scales rate-determining steps of time.
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