CN109552675A - Multiple orbital attitudes background radiation Dynamic Simulation Method and device - Google Patents
Multiple orbital attitudes background radiation Dynamic Simulation Method and device Download PDFInfo
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- 230000005855 radiation Effects 0.000 title claims abstract description 276
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Abstract
The present invention relates to a kind of multiple orbital attitudes background radiation Dynamic Simulation Method, device, computer storage medium and background radiation simulators, its method includes: according to spacecraft orbit height to be simulated, and spacecraft model calculates the Net long wave radiation radius of background radiation simulator radiating surface at a distance from the radiating surface of background radiation simulator in simulation system；Background radiation simulator includes the radiation block of multiple arcs, and all radiation blocks first form the circular annular region of different radii, and the entire radiating surface for constituting background radiation simulator is concentrically arranged in the circular annular region of all different radiis；According to the Net long wave radiation radius of calculating, radius is warming up to first object value range no more than the radiation block of Net long wave radiation radius in control background radiation simulator, and controls the radiation block that radius is greater than Net long wave radiation radius in background radiation simulator and be cooled to the second target zone value.The present invention can simulate multiple orbital attitudes radiant heat flux by the heating or cooling of the radiation block of control background radiation simulator different radii position.
Description
Technical field
The present invention relates to a kind of radiomimesis method more particularly to a kind of multiple orbital attitudes background radiation dynamic analog sides
Method, device, computer storage medium and background radiation simulator.
Background technique
In existing space environment simulation test, background radiation simulator does not consider flying height to radiant heat flux
It influences, i.e., at a distance from not considering target between radiation block in radiant heat flux simulation process, angular relationship.
Therefore, how in space environment simulation test system, the radiant heat flux of multiple orbital attitudes is effectively simulated
It is a urgent problem to be solved.
Summary of the invention
It is an object of the invention to solve at least part technical problem in the prior art, a kind of different tracks are provided
Highly context radiates Dynamic Simulation Method, device, computer storage medium and background radiation simulator, can pass through concentric loop
Radiation block arrangement and temperature control realize multiple orbital attitudes background radiation dynamic analog.
In order to solve the above-mentioned technical problem, it is dynamic to provide a kind of multiple orbital attitudes background radiation for first aspect present invention
State analogy method, the described method comprises the following steps:
S1, it is simulated according to spacecraft model in spacecraft orbit height and simulation system to be simulated and background radiation
The distance of the radiating surface of device calculates the Net long wave radiation radius of background radiation simulator radiating surface；The background radiation simulator packet
The radiation block of multiple arcs is included, all radiation blocks first form the circular annular region of different radii, the circular ring shape of all different radiis
The entire radiating surface for constituting background radiation simulator is concentrically arranged in region.
S2, the Net long wave radiation radius according to calculating control radius in background radiation simulator and are not more than the Net long wave radiation
The radiation block of radius is warming up to first object value range, and controls radius in background radiation simulator and be greater than the Net long wave radiation half
The radiation block of diameter is cooled to the second target zone value.
In multiple orbital attitudes background radiation Dynamic Simulation Method according to the present invention, optionally, the step
S1 includes:
1) spacecraft orbit height is calculated to background radiation source subtended angle θ；
Wherein R is the radius in background radiation source, and h is spacecraft orbit height；
2) the radiating surface Net long wave radiation radius r of background radiation simulator is calculated；
Wherein H is spacecraft model at a distance from the radiating surface of background radiation simulator.
In multiple orbital attitudes background radiation Dynamic Simulation Method according to the present invention, optionally, each radiation
Block includes the radiant panel being sequentially overlapped, heating film, liner plate and heat sink；The radiation block further include temperature sensor, temperature control module,
Power-supply controller and liquid nitrogen controller；The step S2 includes:
Each radiation block passes through the temperature signal of temperature control module temperature collection sensor measurement, the temperature with current radiation block
Control target zone value compares, and is judged by temperature, obtains power supply control instruction and liquid nitrogen control instruction；
Power-supply controller is instructed according to the power supply control of temperature control module, power source supplying voltage control is completed, by power supply power supply
It exports to heating film, controls heating film and radiant panel is heated；
Liquid nitrogen controller completes the control of liquid nitrogen supply amount, by the liquid of liquid nitrogen source according to the liquid nitrogen control instruction of temperature control module
Nitrogen is exported to heat sink, is controlled and heat sink is cooled down to radiant panel.
In multiple orbital attitudes background radiation Dynamic Simulation Method according to the present invention, optionally, the step
The specific steps of the judgement of temperature described in S2 are as follows:
Step 1: the temperature signal T of the real-time temperature collection sensor measurement of temperature control module, within the scope of control target temperature
Value T0It compares；
Step 2: judging T-T0<TminIt is whether true；If so, liquid nitrogen, which is issued, to liquid nitrogen controller does not supply instruction, to
Power-supply controller issues the instruction that power source supplying voltage value is U1, enters step seven；If not, enter step three；
Step 3: judging T-T0<TLIt is whether true；If so, liquid nitrogen is issued to liquid nitrogen controller and does not supply instruction, to confession
Electric controller issues the instruction that power source supplying voltage value is U2, enters step seven；If not, enter step four；
Step 4: judging TH<T-T0<TmaxIt is whether true；If so, power supply not output order is issued to power-supply controller,
The instruction that the Y% that liquid nitrogen supply amount is maximum supply amount is issued to liquid nitrogen controller, enters step seven；If not, enter step
Rapid five；
Step 5: judging T-T0>TmaxIt is whether true；If so, power supply not output order is issued to power-supply controller, to
Liquid nitrogen controller issues the instruction for (Y+5) % that liquid nitrogen supply amount is maximum supply amount, enters step seven；If not, enter
Step 6；
Step 6: judging T-T0 > TNIt is whether true；If so, power supply not output order is issued to power-supply controller, to liquid
Nitrogen controller issues liquid nitrogen and does not supply instruction, and Temperature fall enters step seven；If not, enter step seven；
Step 7: temperature judgement terminates.
In multiple orbital attitudes background radiation Dynamic Simulation Method according to the present invention, optionally, the liquid nitrogen
The ratio Y that the amount of being initially supplied to accounts for maximum supply amount is 5~10.
In multiple orbital attitudes background radiation Dynamic Simulation Method according to the present invention, optionally, the method
Further include: when the spacecraft orbit height change wait simulate, step S1 is repeated to step S2.
Second aspect of the present invention provides a kind of multiple orbital attitudes background radiation dynamic analog device, described device packet
It includes:
Radius computing unit, according to spacecraft model in spacecraft orbit height to be simulated and simulation system and back
The distance of the radiating surface of scape radiation simulator calculates the Net long wave radiation radius of background radiation simulator radiating surface；The background spoke
The radiation block that simulator includes multiple arcs is penetrated, all radiation blocks first form the circular annular region of different radii, all differences half
The entire radiating surface for constituting background radiation simulator is concentrically arranged in the circular annular region of diameter；
Block control unit is radiated, according to the Net long wave radiation radius of calculating, radius in background radiation simulator is controlled and is not more than
The radiation block of the Net long wave radiation radius is warming up to first object value range, and controls radius in background radiation simulator and be greater than institute
The radiation block for stating Net long wave radiation radius is cooled to the second target zone value.
Third aspect present invention provides a kind of computer storage medium, and being stored in the computer storage medium can
The instruction code executed by computer equipment；Described instruction code executes foregoing side when being executed by computer equipment
Method.
Fourth aspect present invention provides a kind of background radiation simulator, radiation block and power supply including multiple arcs
And liquid nitrogen source, all radiation blocks first form the circular annular region of different radii, the circular annular region concentric rows of all different radiis
The entire radiating surface of cloth composition background radiation simulator；
Each radiation block includes the radiant panel being sequentially overlapped, heating film, liner plate and heat sink；The radiation block further includes temperature
Sensor, temperature control module, power-supply controller and liquid nitrogen controller；
The radiant panel constitutes the radiation of background radiation simulator for simulating radiant heat flux, the radiant panel of all radiation blocks
Face；
The heating film is used for heating radiating board；
The liner plate is for connecting radiant panel, heating film and heat sink；
It is described heat sink for cooling down to radiant panel, heating film and liner plate；
The temperature sensor is used for the temperature signal of real-time measurement radiant panel.
The temperature signal of the temperature control module temperature collection sensor measurement, the control target temperature model with current radiation block
It encloses value to compare, be judged by temperature, obtain power supply control instruction and liquid nitrogen control instruction；
The power-supply controller is instructed according to the power supply control of temperature control module, power source supplying voltage control is completed, by power supply
For electricity output to heating film, controls heating film and radiant panel is heated；
The liquid nitrogen controller completes the control of liquid nitrogen supply amount, by liquid nitrogen source according to the liquid nitrogen control instruction of temperature control module
Liquid nitrogen export to heat sink, control and heat sink cool down to radiant panel.
Implement multiple orbital attitudes background radiation Dynamic Simulation Method, device, computer storage medium and back of the invention
Scape radiation simulator, has the advantages that
1, the present invention can adjust in real time according to spacecraft under different flight track height to the subtended angle relationship in background radiation source
The Net long wave radiation radius of the radiating surface of whole background radiation simulator makes the radiation of the background radiation simulator in Net long wave radiation radius
Plate realizes radiant heat flux simulation by heat temperature raising；For the radiant panel of the background radiation simulator except Net long wave radiation radius
By cooling, the radiant heat flux in the region that cools down is very low, does not influence the total Net long wave radiation of space background radiation simulator radiant panel
Hot-fluid realizes the dynamic analog effect of the background radiation under different flying heights.
2, present invention employs closed loop control method, it can be realized and calculate spacecraft orbit height in real time to background radiation source
Subtended angle, the Net long wave radiation radius of the radiating surface of real-time adjustment space background radiation simulator have dynamic analog ability.
It 3, can be more accurate present invention employs the method for the radiant panel independent control of space background radiation simulator
The Net long wave radiation radius for simulating the radiating surface of the corresponding background radiation simulator of multiple orbital attitudes, improves background radiation hot-fluid
Simulation precision；
4, the present invention by a series of temperature deterministic process, reasonably to heating film and it is heat sink control, can make
Reach while block fast and stable must be radiated desired temperature, adapts to the Fast transforms of different height radiant heat flux.
5, there is background radiation simulator of the invention the radiation block of concentric loop to design, and can control difference as needed
The radiation block of radius works, and realizes for multiple orbital attitudes background radiation dynamic analog effect.
Detailed description of the invention
Fig. 1 is the flow chart according to preferred embodiment of the present invention multiple orbital attitudes background radiation Dynamic Simulation Method.
Fig. 2 is the diagrammatic cross-section of simulation system according to the present invention；
Fig. 3 is the radiation block distribution map of background radiation simulator in simulation system；
Fig. 4 is the schematic diagram of the section structure that block is radiated in background radiation simulator according to the present invention；
Fig. 5 is the temperature principle of adjustment and control schematic diagram of each radiation block in background radiation simulator；
Fig. 6 is the detailed process of temperature judgement in multiple orbital attitudes background radiation Dynamic Simulation Method according to the present invention
Figure；
Fig. 7 is the functional unit according to the multiple orbital attitudes background radiation dynamic analog device of the preferred embodiment of the present invention
Block diagram.
Specific embodiment
The feature and exemplary embodiment of various aspects of the invention is described more fully below, in order to make mesh of the invention
, technical solution and advantage be more clearly understood, with reference to the accompanying drawings and embodiments, the present invention is further retouched in detail
It states.It should be understood that specific embodiment described herein is only configured to explain the present invention, it is not configured as limiting the present invention.
To those skilled in the art, the present invention can be real in the case where not needing some details in these details
It applies.Below the description of embodiment is used for the purpose of better understanding the present invention to provide by showing example of the invention.
It should be noted that, in this document, relational terms such as first and second and the like are used merely to a reality
Body or operation are distinguished with another entity or operation, are deposited without necessarily requiring or implying between these entities or operation
In any actual relationship or order or sequence.Moreover, the terms "include", "comprise" or its any other variant are intended to
Non-exclusive inclusion, so that the process, method, article or equipment including a series of elements is not only wanted including those
Element, but also including other elements that are not explicitly listed, or further include for this process, method, article or equipment
Intrinsic element.In the absence of more restrictions, the element limited by sentence " including ... ", it is not excluded that including
There is also other identical elements in the process, method, article or equipment of the element.
Referring to Fig. 1, for according to the stream of preferred embodiment of the present invention multiple orbital attitudes background radiation Dynamic Simulation Method
Cheng Tu.Fig. 2 and Fig. 3 are please referred to, wherein Fig. 2 is the diagrammatic cross-section of simulation system according to the present invention, and Fig. 3 is simulation system
The radiation block distribution map of background radiation simulator in system.Multiple orbital attitudes background radiation Dynamic Simulation Method of the invention can be with
Based on but be not limited to the structure of the simulation system and background radiation simulator and realize.As shown in Fig. 2, being opened using the method for the present invention
When opening up the heat source body Dynamic radiation heat flux simulation test of multiple orbital attitudes, spacecraft model 3 is installed in Vacuum Spherical Tank 2,
And it is spaced apart with the background radiation simulator 1 installed in Vacuum Spherical Tank 2.Vacuum environment is established using Vacuum Spherical Tank 2, it can
With Simulated Spacecraft in space by background radiation source radiation when environment.The background radiation source refers to spacecraft in flight
Other radiation sources in locating space in addition to the sun.The background radiation simulator 1 includes the radiation block 10 of multiple arcs, is owned
Radiation block first forms the circular annular region of different radii, and composition background radiation is concentrically arranged in the circular annular region of all different radiis
The entire radiating surface of simulator 1.The embodiment provide multiple orbital attitudes background radiation Dynamic Simulation Method include at least with
Lower step:
Step S1: according to spacecraft model and background radiation in spacecraft orbit height to be simulated and simulation system
The distance of the radiating surface of simulator calculates the Net long wave radiation radius of background radiation simulator radiating surface.
Preferably, the Net long wave radiation radius of 1 radiating surface of background radiation simulator is calculated in the step by following steps:
1) practical spacecraft orbit height is calculated to background radiation source subtended angle θ；
Wherein R is the radius in background radiation source to be simulated, and h is the orbit altitude of spacecraft；
2) in calculating simulation system background radiation simulator 1 radiating surface Net long wave radiation radius r；
Wherein H is that for spacecraft model 3 at a distance from the radiating surface of background radiation simulator 1, θ is step 1) in simulation system
The background radiation source subtended angle θ being calculated.
Step S2: according to the Net long wave radiation radius r of calculating, control radius in background radiation simulator 1 has no more than described
The radiation block of effect radiation radius r is warming up to first object value range, and controls in background radiation simulator 1 radius and be greater than and described have
The radiation block of effect radiation radius is cooled to the second target zone value.Preferably, the first object value range of heating be 249K~
254K, the second target zone value of cooling are 145K~150K.
In one embodiment of the invention, radiation block 10 arrangement as shown in Figure 2, forms 7 annulus, divides from inside to outside
It Wei not the 1st ring to the 7th ring.Preferably, to guarantee that system power supply is unified, the radiation block inside every ring is designed to sizableness
Arc.The radiation block of every piece of arc is as an independent heating module.The present invention can be with the outer of the radiation block of every piece of arc
The radius of diameter or internal-and external diameter average value as current radiation block.For example, working as the radiating surface Net long wave radiation of background radiation simulator
When the calculated result of radius is 3.4m.By radius no more than 3.4m the 1st ring to the 3rd ring radiation block be warming up to 249K~
The radiation block of 254K, the 4th ring to the 7th ring by radius greater than 3.4m are cooled to 145K~150K.
The present invention through the above steps, can be according to spacecraft under different flight track height to the subtended angle in background radiation source
Relationship adjusts the Net long wave radiation radius of the radiating surface of background radiation simulator in real time, makes the background radiation in Net long wave radiation radius
The radiation block of simulator realizes radiant heat flux simulation by heat temperature raising；For the background radiation mould except Net long wave radiation radius
For the radiation block of quasi- device by cooling, the radiant heat flux in the region that cools down is very low, does not influence space background radiation simulator radiant panel
Total Net long wave radiation hot-fluid realizes background radiation dynamic analog effect under different flying heights.
In embodiment of the invention preferred, this method further include in the spacecraft orbit height change wait simulate,
Step S1 to step S2 is repeated, to realize that multiple orbital attitudes background radiation dynamic analog is simulated.
Referring to Fig. 4, to radiate the schematic diagram of the section structure of block in background radiation simulator according to the present invention.Fig. 5 is
The temperature principle of adjustment and control schematic diagram of each radiation block in background radiation simulator.Each radiation block 10 includes the radiation being sequentially overlapped
Plate 11, heating film 12, liner plate 13 and heat sink 14.Radiating block 10 further includes temperature control device, by temperature sensor 15, temperature control mould
Block 16, power-supply controller 17 and liquid nitrogen controller 18 form.The background radiation simulator further includes power supply and liquid nitrogen source.Radiant panel
11 for simulating radiant heat flux, and the radiant panel 11 of all radiation blocks 10 constitutes the radiating surface of background radiation simulator, heating film 12
It is the heating source of radiant panel 11, liner plate 13 is for connecting radiant panel 11, heating film 12 and heat sink 14, and heat sink 14 for radiant panel
11, heating film 12 and liner plate 13 cool down, and temperature sensor 15 is used for the temperature signal of real-time measurement radiant panel 11.Heating film
12 are located at the opposite direction of 11 radiant heat flux of radiant panel, and radiant panel 11 is close in the side of heating film 12；The side of liner plate 13 and heating
Film 12 and radiant panel 11 connect, and the other side of liner plate 13 is connect with heat sink 14；Temperature sensor 15 is located at 11 radiant heat of radiant panel
The opposite direction of stream is close to radiant panel 11.Power-supply controller 17 receives the control instruction of temperature control module 16, completes power source supplying voltage
Control, power supply power supply is exported to heating film 13, heating film 13 exports different heating according to the difference of power source supplying voltage value
Power heats radiant panel 11；Liquid nitrogen controller 18 receives the control instruction of temperature control module 16, completes the control of liquid nitrogen supply amount
System, the liquid nitrogen of liquid nitrogen source is exported to heat sink 14；Heat sink 14 be porous structure, and liquid nitrogen source flows after liquid nitrogen controller regulating flow
The porous structure for crossing heat sink 14 is reached for the purpose that radiant panel 11, heating film 12 and liner plate 13 cool down.Each radiation block 10
Interior temperature control module 16, power-supply controller 17, liquid nitrogen controller 18, radiant panel 11, heating film 12, liner plate 13, heat sink 14, temperature
Sensor 15 is closed loop control access, and the component between difference radiation block does not intersect.The radiant panel of each radiation block is equal
It can carry out independent heating or cooling control.
Control radiation block is warming up to the first mesh in step S2 in above-mentioned multiple orbital attitudes background radiation Dynamic Simulation Method
Value range is marked, or the step of being cooled to the second target zone value can be realized by the following method:
1) each radiation block 10 passes through the temperature signal that 16 temperature collection sensor 15 of temperature control module measures, with current radiation
The control target temperature value range of block compares, and is judged by temperature, obtains power supply control instruction and liquid nitrogen control instruction, supplies
Electric control instruction is sent to power-supply controller, and liquid nitrogen control instruction is sent to liquid nitrogen controller；
2) power-supply controller 17 receives the power supply control instruction of temperature control module 16, completes power source supplying voltage control, will be electric
Source, to heating film 12, controls heating film 12 and is heated for electricity output；Meanwhile liquid nitrogen controller 18 is according to the liquid of temperature control module 16
Nitrogen control instruction completes the control of liquid nitrogen supply amount, the liquid nitrogen of liquid nitrogen source is exported to heat sink 14, control heat sink 14 cools down.
Wherein heating film 12 heats radiant panel 11 according to power source supplying voltage, and radiant panel 11 simulates radiant heat flux；Heat sink 4 basis
Liquid nitrogen input quantity cools down to radiant panel 11, heating film 12 and liner plate 13.
The present invention also studies the temprature control method of radiation block, and can be fast by the control flow of optimization
Speed and accurately the temperature for radiating block is controlled to target zone value.Referring to Fig. 6, being multiple orbital attitudes according to the present invention
The specific flow chart that temperature judges in background radiation Dynamic Simulation Method.Preferably, above-mentioned steps 1) in temperature judgement it is specific
Step are as follows:
Step 1: the value T in temperature control module 16 in set temperature control target zone0, real-time temperature collection sensor 15
The temperature signal T of measurement；
Step 2: judging T-T0<TminIt is whether true, T in the present embodimentminFor -50K；If so, to liquid nitrogen controller 18
It issues liquid nitrogen and does not supply instruction, issue power source supplying voltage value to power-supply controller 17 as U1 instruction, U1 value is 100V, heating
Film 12 exports maximum heating power, enters step seven in supply voltage 100V；If not, enter step three；
Step 3: judging T-T0 < TLIt is whether true, T in the present embodimentLFor -2K；If so, it is issued to liquid nitrogen controller 18
Liquid nitrogen does not supply instruction, issues power source supplying voltage value to power-supply controller 17 as U2 instruction, U2 value is 45V, heating film 12
In supply voltage 45V, normal heating power is exported, enters step seven；If not, enter step four；
Step 4: judging TH<T-T0<TmaxIt is whether true, T in the present embodimentmaxFor 100K, THFor 20K；If so, to confession
Electric controller 17 issues power supply not output order, issues the Y% that liquid nitrogen supply amount is maximum supply amount to liquid nitrogen controller 18
Instruction, in the present embodiment the liquid nitrogen amount of being initially supplied to of liquid nitrogen controller 18 account for the ratio Y of the percentage of maximum supply amount be 5~
10, enter step seven；If not, enter step five；
Step 5: judging T-T0>TmaxIt is whether true；If so, power supply not output order is issued to power-supply controller 17,
The instruction that (Y+5) % that liquid nitrogen supply amount is maximum supply amount is issued to liquid nitrogen controller 18, enters step seven；If not,
Enter step six；
Step 6: judging T-T0>TNIt is whether true, T in the present embodimentNFor 2K；If so, it is issued to power-supply controller 17
Power supply not output order issues liquid nitrogen to liquid nitrogen controller 18 and does not supply instruction, and Temperature fall enters step seven；If not,
Enter step seven；
Step 7: temperature judgement terminates, waits into next temperature and judge cycle period.
Referring to Fig. 7, the present invention also provides a kind of multiple orbital attitudes background radiation dynamic analog devices.The device packet
It includes: radius computing unit 100 and radiation block control unit 200.The device can be based on software and or hardware realization.
Wherein, radius computing unit 100 is used for according to space flight in spacecraft orbit height and simulation system to be simulated
Device model calculates the Net long wave radiation radius of background radiation simulator radiating surface at a distance from the radiating surface of background radiation simulator.
Wherein background radiation simulator includes the radiation block of multiple arcs, and all radiation blocks first form the circular annular region of different radii,
The entire radiating surface for constituting background radiation simulator is concentrically arranged in the circular annular region of all different radiis；The radius computing unit
The operation of 100 execution is identical as abovementioned steps S1.
The Net long wave radiation radius that radiation block control unit 200 is used to be calculated according to radius computing unit 100, controls background spoke
It penetrates the radiation block that radius is not more than the Net long wave radiation radius in simulator and is warming up to first object value range, and control background spoke
It penetrates the radiation block that radius is greater than the Net long wave radiation radius in simulator and is cooled to the second target zone value.Radiation block control is single
The operation that member 200 executes is identical as aforementioned combinations filter step S2.
Those skilled in the art can be understood that, for convenience and simplicity of description, only with above-mentioned each function list
The division progress of member for example, in practical application, can according to need and by above-mentioned function distribution by different functional units
It completes, i.e., the internal structure of device is divided into different functional units, to complete all or part of the functions described above.
The specific work process of foregoing description functional unit, can refer to corresponding processes in the foregoing method embodiment, no longer superfluous herein
It states.
The embodiment of the invention also provides a kind of computer readable storage mediums, are stored thereon with computer program instructions,
It is realized when computer program instructions are executed by processor such as multiple orbital attitudes background radiation dynamic analog in above embodiment
Quasi- method.
The embodiment of the invention also provides a kind of multiple orbital attitudes background radiation dynamic analog devices, comprising: at least one
A processor, at least one processor and computer program instructions stored in memory, when computer program instructions quilt
It is realized when processor executes such as multiple orbital attitudes background radiation Dynamic Simulation Method in above embodiment.
Functional unit shown in routine described above module frame chart can be implemented as hardware, software, firmware or it
Combination.When realizing in hardware, electronic circuit, specific integrated circuit (ASIC), appropriate solid may, for example, be
Part, plug-in unit, function card etc..When being realized with software mode, element of the invention is used to execute the program of required task
Or code segment.Perhaps code segment can store in machine readable media program or the data by carrying in carrier wave are believed
It number is sent in transmission medium or communication links." computer readable storage medium " may include being capable of storage or transmission information
Any medium.The example of computer readable storage medium include electronic circuit, semiconductor memory devices, ROM, flash memory, can
Wipe ROM (EROM), floppy disk, CD-ROM, CD, hard disk, fiber medium, radio frequency (RF) link, etc..Code segment can be via
The computer network of internet, Intranet etc. is downloaded.
It should be clear that the invention is not limited to specific configuration described above and shown in figure and processing.
For brevity, it is omitted here the detailed description to known method.In the above-described embodiments, several tools have been described and illustrated
The step of body, is as example.But method process of the invention is not limited to described and illustrated specific steps, this field
Technical staff can be variously modified, modification and addition after understanding spirit of the invention, or suitable between changing the step
Sequence or several steps are performed simultaneously.
The present invention further correspondingly provides foregoing background radiation simulator, which includes multiple
The radiation block 10 and power supply and liquid nitrogen source of arc, all radiation blocks 10 first form the circular annular regions of different radii, it is all not
The entire radiating surface of composition background radiation simulator 1 is concentrically arranged with the circular annular region of radius.Each radiation block 10 include according to
Radiant panel 11, heating film 12, the liner plate 13 and heat sink 14 of secondary superposition；The radiation block 10 further includes temperature sensor 15, temperature control
Module 16, power-supply controller 17 and liquid nitrogen controller 18.The specific structure and function of the radiation block 10 are in previous embodiment
In be described in detail, no longer repeated herein.Above-mentioned background radiation simulator can also include that aforementioned different tracks are high
Background radiation dynamic analog device is spent, it is connect with the temperature control module 16 of each radiation block 10, is set for each temperature control module 16
Set the value T in temperature controlled target zone0, so that the control to each region radiation block 10 is realized, to reach different tracks
The purpose of height hot-fluid radiomimesis.
Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although
Present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: it still may be used
To modify the technical solutions described in the foregoing embodiments or equivalent replacement of some of the technical features；
And these are modified or replaceed, technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution spirit and
Range.
Claims (10)
1. a kind of multiple orbital attitudes background radiation Dynamic Simulation Method, which is characterized in that the described method comprises the following steps:
Spacecraft model and background radiation simulator in S1, basis spacecraft orbit height and simulation system to be simulated
The distance of radiating surface calculates the Net long wave radiation radius of background radiation simulator radiating surface；The background radiation simulator includes more
The radiation block of a arc, all radiation blocks first form the circular annular region of different radii, the circular annular region of all different radiis
The entire radiating surface for constituting background radiation simulator is concentrically arranged；
S2, the Net long wave radiation radius according to calculating control radius in background radiation simulator and are not more than the Net long wave radiation radius
Radiation block be warming up to first object value range, and control radius in background radiation simulator and be greater than the Net long wave radiation radius
Radiation block is cooled to the second target zone value.
2. multiple orbital attitudes background radiation Dynamic Simulation Method according to claim 1, which is characterized in that the step
S1 includes:
1) spacecraft orbit height is calculated to background radiation source subtended angle θ；
Wherein R is the radius in background radiation source, and h is spacecraft orbit height；
2) the radiating surface Net long wave radiation radius r of background radiation simulator is calculated；
Wherein H is spacecraft model at a distance from the radiating surface of background radiation simulator.
3. multiple orbital attitudes background radiation Dynamic Simulation Method according to claim 1, which is characterized in that each radiation
Block includes the radiant panel being sequentially overlapped, heating film, liner plate and heat sink；The radiation block further include temperature sensor, temperature control module,
Power-supply controller and liquid nitrogen controller；
The step S2 includes:
Each radiation block passes through the temperature signal of temperature control module temperature collection sensor measurement, controls with the temperature of current radiation block
Target zone value compares, and is judged by temperature, obtains power supply control instruction and liquid nitrogen control instruction；
Power-supply controller is instructed according to the power supply control of temperature control module, completes power source supplying voltage control, power supply power supply is exported
To heating film, controls heating film and radiant panel is heated；
Liquid nitrogen controller completes the control of liquid nitrogen supply amount according to the liquid nitrogen control instruction of temperature control module, and the liquid nitrogen of liquid nitrogen source is defeated
Out to heat sink, controls and heat sink cools down to radiant panel.
4. multiple orbital attitudes background radiation Dynamic Simulation Method according to claim 3, which is characterized in that the step
The specific steps of the judgement of temperature described in S2 are as follows:
Step 1: the temperature signal T of the real-time temperature collection sensor measurement of temperature control module, with the value within the scope of control target temperature
T0It compares；
Step 2: judging T-T0<TminIt is whether true；If so, liquid nitrogen is issued to liquid nitrogen controller and does not supply instruction, to for automatically controlled
Device processed issues the instruction that power source supplying voltage value is U1, enters step seven；If not, enter step three；
Step 3: judging T-T0<TLIt is whether true；If so, liquid nitrogen is issued to liquid nitrogen controller and does not supply instruction, to for automatically controlled
Device processed issues the instruction that power source supplying voltage value is U2, enters step seven；If not, enter step four；
Step 4: judging TH<T-T0<TmaxIt is whether true；If so, power supply not output order is issued to power-supply controller, to liquid
Nitrogen controller issues the instruction for the Y% that liquid nitrogen supply amount is maximum supply amount, enters step seven；If not, enter step five；
Step 5: judging T-T0>TmaxIt is whether true；If so, power supply not output order is issued to power-supply controller, to liquid nitrogen control
Device processed issues the instruction for (Y+5) % that liquid nitrogen supply amount is maximum supply amount, enters step seven；If not, enter step six；
Step 6: judging T-T0 > TNIt is whether true；If so, power supply not output order is issued to power-supply controller, to liquid nitrogen control
Device processed issues liquid nitrogen and does not supply instruction, and Temperature fall enters step seven；If not, enter step seven；
Step 7: temperature judgement terminates.
5. multiple orbital attitudes background radiation Dynamic Simulation Method according to claim 4, which is characterized in that the liquid nitrogen
The ratio Y that the amount of being initially supplied to accounts for maximum supply amount is 5~10.
6. multiple orbital attitudes background radiation Dynamic Simulation Method according to claim 1, which is characterized in that the method
Further include: when the spacecraft orbit height change wait simulate, step S1 is repeated to step S2.
7. a kind of multiple orbital attitudes background radiation dynamic analog device, which is characterized in that described device includes:
Radius computing unit, according to spacecraft model in spacecraft orbit height to be simulated and simulation system and background spoke
The distance of the radiating surface of simulator is penetrated, the Net long wave radiation radius of background radiation simulator radiating surface is calculated；The background radiation mould
Quasi- device includes the radiation block of multiple arcs, and all radiation blocks first form the circular annular region of different radii, all different radiis
The entire radiating surface for constituting background radiation simulator is concentrically arranged in circular annular region；
Block control unit is radiated, according to the Net long wave radiation radius of calculating, radius is not more than described in control background radiation simulator
The radiation block of Net long wave radiation radius is warming up to first object value range, and controls in background radiation simulator radius and be greater than and described have
The radiation block of effect radiation radius is cooled to the second target zone value.
8. multiple orbital attitudes background radiation dynamic analog device according to claim 7, which is characterized in that the radius
Computing unit calculates the Net long wave radiation radius of background radiation simulator radiating surface by following steps:
1) spacecraft orbit height is calculated to background radiation source subtended angle θ；
Wherein R is the radius in background radiation source, and h is spacecraft orbit height；
2) the radiating surface Net long wave radiation radius r of background radiation simulator is calculated；
Wherein H is spacecraft model at a distance from the radiating surface of background radiation simulator.
9. a kind of computer storage medium, which is characterized in that being stored in the computer storage medium can be by computer equipment
The instruction code of execution；
Described instruction code by computer equipment when being executed, method described in any one of perform claim requirement 1~6.
10. a kind of background radiation simulator, which is characterized in that the background radiation simulator include the radiation block of multiple arcs with
And power supply and liquid nitrogen source, all radiation blocks first form the circular annular region of different radii, the circular annular region of all different radiis
The entire radiating surface for constituting background radiation simulator is concentrically arranged；
Each radiation block includes the radiant panel being sequentially overlapped, heating film, liner plate and heat sink；The radiation block further includes temperature sensing
Device, temperature control module, power-supply controller and liquid nitrogen controller；
The radiant panel constitutes the radiating surface of background radiation simulator for simulating radiant heat flux, the radiant panel of all radiation blocks；
The heating film is used for heating radiating board；
The liner plate is for connecting radiant panel, heating film and heat sink；
It is described heat sink for cooling down to radiant panel, heating film and liner plate；
The temperature sensor is used for the temperature signal of real-time measurement radiant panel；
The temperature signal of the temperature control module temperature collection sensor measurement, the control target temperature value range with current radiation block
It compares, is judged by temperature, obtain power supply control instruction and liquid nitrogen control instruction；
The power-supply controller is instructed according to the power supply control of temperature control module, power source supplying voltage control is completed, by power supply power supply
It exports to heating film, controls heating film and radiant panel is heated；
The liquid nitrogen controller completes the control of liquid nitrogen supply amount, by the liquid of liquid nitrogen source according to the liquid nitrogen control instruction of temperature control module
Nitrogen is exported to heat sink, is controlled and heat sink is cooled down to radiant panel.
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