CN110171584A - Vacuum thermal test method for mass production of satellite constellation system - Google Patents
Vacuum thermal test method for mass production of satellite constellation system Download PDFInfo
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- CN110171584A CN110171584A CN201910531363.0A CN201910531363A CN110171584A CN 110171584 A CN110171584 A CN 110171584A CN 201910531363 A CN201910531363 A CN 201910531363A CN 110171584 A CN110171584 A CN 110171584A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G99/00—Subject matter not provided for in other groups of this subclass
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
- B64G2007/005—Space simulation vacuum chambers
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Abstract
The invention provides a vacuum thermal test method for a satellite constellation system produced in batch, which is characterized in that a plurality of satellites are simultaneously placed in a space environment simulation device, a heat balance star and a heat vacuum star are respectively selected, and the heat control state of the heat balance star is worse than that of the heat vacuum star; carrying out a heat balance test on the heat balance star; in the process of the heat balance test, equipment on the heat balance satellite is powered up according to an on-orbit set working mode, and meanwhile, each surface of the heat balance satellite is applied according to external heat flow design parameters; simulating the external heat flow influence of the heat balance satellite brought by the mutual shielding condition of each satellite, and correcting the external heat flow of the heat balance satellite in real time; in the process of the thermal balance test, equipment on the thermal vacuum satellite is powered up according to an on-orbit set working mode, but external heat flow is not applied; and after the thermal balance test is finished, determining the high and low temperature maintaining range of the thermal vacuum test of the satellite system according to the thermal balance test result, and performing the thermal vacuum test of the satellite system.
Description
Technical field
The present invention relates to field of aerospace technology, in particular to a kind of mass production constellation system vacuum heat examination
Proved recipe method.
Background technique
With the continuous development of space technology, spacecraft functional density is higher and higher, has realized that spacecraft minimizes at present
And mass development, production capacity.Satellite constellation is that transmitting is entered the orbit and can be worked normally, and function is close, combines by certain way
Into several or the set of multi-satellite.For completing global communication, the tasks such as navigation and environmental monitoring, it is necessary to the earth be made to take up an official post
Where point, any moment can cover by satellite, to accomplish this point with a satellite be it is far from being enough, need more to defend
Star forms satellite network by certain way, and then realizes above-mentioned function.Miniaturization satellite constellation is widely used to mutually at this stage
The fields such as connected network communication, remote sensing, navigation and environmental monitoring, in recent years with the propulsion of domestic civil-military inosculation policy, spacecraft is ground
System and launch cost further decrease, and fast-developing situation is presented in mass production satellite constellation at present.
Spacecraft thermal control system task is to guarantee all appts on star under the conditions of orbit determination road, posture and operating mode
Equipment meets its temperature index requirement.For allomeric function of the verifying spacecraft under space environment, guarantee that spacecraft is in-orbit reliable
Operation, it is desirable to which all spacecrafts must carry out vacuum thermal test examination in the ground development stage, most important one, most complicated
, the period it is longest test be the whole star vacuum thermal test carried out in space environment simulation equipment.Spacecraft ground Vacuum Heat
Test is divided into heat balance test and thermal vacuum test, the former is to verify thermal control design correctness as the main purpose, emphasis examination heat
Control system maintains ability of each instrument and equipment in defined operating temperature range on star, examination dress star thermal control product working performance
And the validity of various thermal control measures, improve heat analysis physical model and for thermal vacuum test high/low temperature temperature hold in range into
Row indication；Ability of the latter to examine each instrument and equipment on star to be resistant to high and low temperature and temperature alternating under vacuum conditions, ahead of time cruelly
Reveal single machine, raw material, component and defective workmanship on star, obtains under different temperatures environmental condition based on test data.
Constellation of Low Earth Orbit Satellites is with light-weight, small in size, quantity is more, several satellite in a rocket intensively emits, quickly networking at this stage
The characteristics of, conventional test methods have been unable to meet task development progress requirement.Therefore, it is badly in need of proposing a kind of mass production satellite
The parallel vacuum thermal test method of the more stars of constellation produces the heat test of satellite constellation ground vacuum for criticizing at this stage.
To ensure that spacecraft is resistant to space vacuum and high and low temperature environment ability, it is desirable that all spacecrafts are in the ground development stage
It must carry out vacuum thermal test examination.Are generallyd use by satellite and first carries out thermal balance for single satellite or single serial development satellite
Test carries out thermal vacuum test again, determines that the mode of thermal vacuum test condition carries out according to heat balance test result, i.e., one is defended
Star completes two verification experimental verification contents into primary space environmental simulation equipment.And for mass production and thermal control state it is identical
Satellite only chooses a progress heat balance test, remaining satellite carries out thermal vacuum test, therefore, two according to heat balance test result
A test process is serially connected.But also need individually to carry out verification experimental verification when subsequent satellites thermal control state changes, it is existing
Test method at least needs individually to be tested twice, and satellite at least needs to pass in and out space environment simulation equipment twice, implements
Journey is complicated and time-consuming, can seriously restrict batch development for producing satellite for a fairly large number of this test method of mass production satellite
Progress and Launch Program.
Defect existing for existing test method is as follows:
One, existing test method requires first to carry out single star heat balance test, then carries out more star thermal vacuum tests, and two examinations
Testing process needs successively series connection to carry out, and being equivalent to progress, vacuum thermal test, test period are longer twice；
Two, existing test method requires batch production satellite at least to carry out vacuum thermal test twice, i.e., first chooses a satellite
Single star heat balance test is done, then carries out more star thermal vacuum tests, experimentation cost is higher；
Three, existing test method needs to pass in and out space environment simulation equipment at least twice, to preparation, test before testing
Equipment operation and thermal control process implementing are more demanding, and repeatedly pass in and out testing equipment, repeatedly implement to turn over to satellite of participating in the experiment, hang
Dress and transfer operation substantially increase the celestial body probability that is damaged；
Four, existing test method is required to pass in and out at least twice and be tested in space environment simulation equipment, to needed for test
Heat control material and the waste such as test consumable it is more；
Five, existing test method requires first to carry out single star heat balance test, need to carry out in pilot plant unit, subsequent more
Star thermal vacuum test is needed again in large-scale experiment equipment.Therefore, complicated to testing equipment type and index request, need more families to match
Set unit is held jointly grinds；
Six, existing test method has seriously restricted the test period of mass production satellite constellation, development progress, has been developed into
The completion of this and task, has been unsatisfactory for the manufacture claim of existing mass production satellite constellation.
Summary of the invention
The purpose of the present invention is to provide a kind of mass production constellation system vacuum thermal test methods, existing to solve
Some mass production satellite constellation test methods seriously restrict the problem of development progress and Launch Program of batch production satellite.
In order to solve the above technical problems, the present invention provides a kind of mass production constellation system vacuum thermal test side
Method, the satellite system include the same or similar multi-satellite of thermal control state, the satellite system vacuum thermal test method packet
It includes:
The multi-satellite is put into space environment simulation equipment simultaneously, choose wherein a satellite as thermal balance star,
For other satellites as thermal vacuum star, the thermal control state of the thermal balance star is more in bad condition than the thermal control of the thermal vacuum star；
Heat balance test is carried out to the thermal balance star；
During the heat balance test, the equipment on the thermal balance star is added by in-orbit set operating mode
Electricity, while Orbital heat flux is applied by Orbital heat flux design parameter to each outer surface of the thermal balance star；
During the heat balance test, the thermal balance star is brought by the mutual circumstance of occlusion to each satellite
Orbital heat flux influence is emulated, and is corrected in real time according to simulation result to the Orbital heat flux for being applied to the thermal balance star；
During the heat balance test, the equipment on the thermal vacuum star is added by in-orbit set operating mode
Electricity；
After the completion of the heat balance test of the thermal balance star, the satellite system is determined according to the heat balance test result
Thermal vacuum test temperature hold in range, the thermal vacuum test of the satellite system is carried out according to the temperature hold in range.
In the present invention, term " thermal control state is same or similar " refers to satellite flight orbit parameter, configuration layouts, hot merit
The factor that consumption, operating mode and thermal control scheme etc. influence whole star thermal control state is same or similar." the thermal control state of the first satellite
Thermal control than the second satellite is in bad condition " refer to should have certain representative by the thermal balance star to the above Parameter analysis, selection
Property and thermal control parameter it is more severe, as flight orbit external thermal flux result is severe, whole star heat power consumption is bigger than normal compared with other celestial bodies, work when
Between the longer equal satellite for being unfavorable for whole star thermal control design and heat dissipation as thermal balance star, other celestial bodies are then used as thermal vacuum star,
That is, parameter represented by thermal control state of the parameter than the second satellite represented by the thermal control state of the first satellite is worse,
That is, differing bigger or more undesirable with ideal parameters.
Optionally, in the satellite system vacuum thermal test method, the satellite system vacuum thermal test method is also
Include:
The space environment simulation equipment, the sky are selected according to the size of satellite each in the satellite system and quantity
Between environmental simulation equipment be usually vertical cylinder or Horizontal cylinder body；
The orientation of each satellite is put by minimum test unit, connects electrical testing cable and measuring and controlling temp cable, institute
Electrical testing cable is stated for being powered on to satellite borne equipment, the measuring and controlling temp cable is used for the outer surface to the thermal balance star
Apply Orbital heat flux；
According to the position of each satellite and azimuth design heat test tooling is put, so that the knot of the heat test tooling
Structure intensity and rigidity meet the vacuum thermal test requirement, and the heat test tooling includes guide rail, strut and suspender, to it is each
Strut and suspender that satellite directly contacts carry out temperature-compensating, during the vacuum thermal test, to the guide rail, strut and
Suspender carries out active temperature control.
Optionally, in the satellite system vacuum thermal test method, the satellite system vacuum thermal test method is also
Include:
The outer surface of the thermal balance star has main radiating surface and auxiliary radiating surface；
When the multi-satellite is put into the space environment simulation equipment, space environment described in the main radiating surface face
The inner surface of analog machine, the inner surface of space environment simulation equipment described in the auxiliary radiating surface face or the thermal vacuum star
Non- radiating surface, so that the thermal balance star is blocked by the thermal vacuum star influences minimum.
Optionally, in the satellite system vacuum thermal test method, the heat balance test includes but is not limited to heat
Blance test worst cold case and heat balance test worst hot case,
The heat balance test worst cold case includes steady state cold temperature operating condition, quasi-steady state worst cold case, periodical transient state low temperature
Operating condition and transient state worst cold case；
The heat balance test worst hot case includes stable state worst hot case, quasi-steady state worst hot case, periodical transient high temperature
Operating condition and transient high temperature operating condition.
Optionally, in the satellite system vacuum thermal test method,
The Orbital heat flux of the heat balance test worst hot case according to the end of lifetime of the thermal balance star, near the winter solstice,
Maximum heat trajectory road parameters simulation result is configured, and is modified according to the circumstance of occlusion of each satellite, so that the heat
Balance star works by maximum heat consumption mode, obtains heat balance test worst hot case temperature results；
The Orbital heat flux of the heat balance test worst cold case according to the beginning of lifetime of the thermal balance star, the summer solstice nearby,
Minimum thermal flux orbit parameter simulation result is configured, and is modified according to the circumstance of occlusion of each satellite, so that the heat
Balance star works by minimum heat consumption mode, obtains heat balance test worst cold case temperature results.
Optionally, in the satellite system vacuum thermal test method, the thermal vacuum test is protected according to the temperature
It holds range and carries out several high/low temperature circulations, in the high/low temperature cyclic process of thermal vacuum test:
By setting auxiliary warming heater and Orbital heat flux simulate heat source to the thermal balance star and the thermal vacuum star into
Row warming temperature sets identical powering state and thermal control state for each satellite in heating and cooling process；
Maximum temperature in the temperature hold in range carries out true according to the heat balance test worst hot case temperature results
Fixed, the minimum temperature in temperature hold in range is determined according to the heat balance test worst cold case temperature results；
Heat source is simulated to the thermal balance star and the heat by closing the auxiliary warming heater and the Orbital heat flux
Vacuum star carries out cooling operation；
Test mode and telemetry parameter to each satellite are acquired, compare and analyze, and judge the satellite of each satellite
Whether state is consistent with performance, finds and position abnormal data and parameter, handles incipient fault.
Optionally, in the satellite system vacuum thermal test method, in the high/low temperature cyclic process of thermal vacuum test
In:
Within the high temperature holding stage of the thermal vacuum test, 80% or more temperature measuring point temperature is higher than the heat balance test
Warm working temperature result is 10 DEG C high~and 15 DEG C, and lower than checking and accepting grade highest test temperature；
Within the low temperature holding stage of the thermal vacuum test, 20% or more temperature measuring point temperature is lower than the heat balance test
Warm working temperature result is 5 DEG C~15 DEG C low, and is higher than and checks and accepts the minimum test temperature of grade.
Optionally, in the satellite system vacuum thermal test method, the satellite system vacuum thermal test method is also
Include:
Before heat balance test progress, initial testing is carried out to the satellite system, the initial testing includes low
Air pressure measurement condition, thermal control software test operating condition and whole star high temperature outlet operating condition；
After the completion of the thermal vacuum test, the seasoned test of vacuum is carried out to the satellite system.
Optionally, in the satellite system vacuum thermal test method,
Under the low pressure measurement condition, vacuum pumping is carried out to the space environment simulation equipment, is kept each
The minimum system equipment of satellite is in powering state, so that the vacuum degree inside the space environment simulation equipment is dropped by 1000Pa
Down to 0.1Pa, the powering state and telemetry parameter of each satellite are monitored, power-up when minimum system equipment is satellite launch is set
It is standby.
Optionally, in the satellite system vacuum thermal test method, under the thermal control software test operating condition, according to
Thermal control software module temperature control threshold value and the permitted minimum temperature of the auxiliary warming heater determine each satellite temperature control
Section；
Test the ability that the thermal control software module maintains whole star temperature；
Carry out switch control logic test and the ratio control logic test of the thermal control software module；
Carry out whole star safe mode and thermal control software module minimum functional test；
Carry out the auxiliary warming heater open-loop test and closed loop test.
Optionally, in the satellite system vacuum thermal test method, under whole star high temperature outlet operating condition, using described
Auxiliary warming heater, Orbital heat flux simulation heat source and celestial body Active thermal control heater increase the temperature of the satellite system,
So that the temperature of the satellite system it is 5 DEG C higher than maximum heat trajectory road parameters simulation result~10 DEG C and keep, when holding
Between be greater than 24 hours, deflate to the structural slab of each satellite, dress star single machine, cable and dress star auxiliary material.
Optionally, in the satellite system vacuum thermal test method, the seasoned test of vacuum includes: in the sky
Between in environmental simulation equipment, the temperature of each satellite is adjusted by the auxiliary warming heater, while each satellite is pressed
The set operating mode of rail is powered up, and be can be carried out test to the electrical property of each satellite, is simulated seasoned accelerated test.
It optionally, include sensitive using star in the satellite system vacuum thermal test method, in the satellite system
Device determines the satellite of appearance, and star map simulator is installed on the satellite for determining appearance using star sensor, and the survey of closed loop attitude control software is carried out to it
Examination carries out active temperature control and temperature monitoring to the star map simulator.
Optionally, in the satellite system vacuum thermal test method, the thermal balance star and the thermal vacuum star
Removable radiation shield is set at main radiating surface；
Resistance silicone tube and ionization silicone tube are set at the powerful device of the satellite system；
Heat sink apparatus is set at the thermal balance star.
In satellite system vacuum thermal test method provided by the invention, by carrying out heat balance test to thermal balance star,
The Orbital heat flux for being applied to thermal balance star is corrected in real time, after the completion of the heat balance test of thermal balance star, is tried according to thermal balance
The temperature hold in range that result determines the thermal vacuum test of satellite system is tested, the heat of satellite system is carried out according to temperature hold in range
Vacuum test can significantly shorten the development of batch satellite and test period, reduce experimentation cost.It is operated by a vacuum thermal test
Heat balance test purpose can be realized, and thermal vacuum test check requirements can be met, multi-satellite parallel carries out vacuum thermal test,
Can also Rapid Accumulation batch produce testing time of the satellite under hot vacuum environment, be very suitable to batch produce satellite scale development；It realizes
Test period is short, and experimentation cost is low, only need to once pass in and out space environment simulation equipment, sets to preparation, test before testing
Standby operation and the requirement of thermal control process implementing are lower, avoid repeatedly implementing to turn over to satellite of participating in the experiment, and lifting and transfer operation make star
Body be damaged probability reduction, save test needed for heat control material and test consumable, testing equipment type and index are wanted
Ask simple.
As spacecraft thermal control analysis software is increasingly mature, accuracy is stepped up, and is mutually tied using test with simulation analysis
The mode of conjunction corrects ermal physics model, using ermal physics model after amendment to the in-orbit temperature range of instrument and equipment each on star and variation
Rule is indicated.By the way that heat balance test purpose once can be realized into space environment simulation equipment operation, thermal vacuum is had both
Experiment examination requirement, while meeting mass production satellite and developing mission requirements.
The present invention relates to a kind of methods of the more star parallel ground vacuum thermal test verifyings of mass production satellite (spacecraft).
These satellites should have same or similar thermal control state, which can be widely applied to low rail communication satellite constellation, remote sensing is defended
Star seat, navigation satellite constellation and internet satellite constellation etc. produce satellite in batches and carry out vacuum heat examination simultaneously or in batches
It tests, in particular by " several satellite in a rocket " radiation pattern, the more consistent business space industry of satellite thermal control state.
Detailed description of the invention
Fig. 1 is in the horizontal space environment simulation equipment of one embodiment of the invention, and minimum test unit is that the satellite of double star is put
Put schematic diagram；
Fig. 2 is in the horizontal space environment simulation equipment of one embodiment of the invention, and minimum test unit is that the satellite of Samsung is put
Put schematic diagram；
Fig. 3 is in the horizontal space environment simulation equipment of one embodiment of the invention, and minimum test unit is that the satellite of four stars is put
Put schematic diagram；
Fig. 4 is in the vertical space environment simulation equipment of one embodiment of the invention, and minimum test unit is that the satellite of double star is put
Put schematic diagram；
Fig. 5 is in the vertical space environment simulation equipment of one embodiment of the invention, and minimum test unit is that the satellite of Samsung is put
Put schematic diagram；
Fig. 6 is in the vertical space environment simulation equipment of one embodiment of the invention, and minimum test unit is that the satellite of four stars is put
Put schematic diagram；
Fig. 7 is each satellite parallel vacuum thermal test flow diagram of one embodiment of the invention；
It is as shown in the figure: 0- space environment simulation equipment (space environment simulation equipment)；1- thermal balance star；2- thermal vacuum star；
3- thermal vacuum star；4- thermal vacuum star；10- initial testing；11- heat balance test；12- thermal vacuum test；The seasoned examination of 13- vacuum
It tests；101- low pressure measurement condition；102- thermal control software test operating condition；The whole star high temperature outlet operating condition of 103-；The examination of 104- thermal balance
Test worst hot case；105- heat balance test worst cold case；106- thermal vacuum test the 1st recycles；107- thermal vacuum test the 2nd follows
Ring；108- thermal vacuum test the 3rd recycles；109- thermal vacuum test the 4th recycles；110- thermal vacuum test n-th recycles；111- vacuum
Seasoned test.
Specific embodiment
Satellite system vacuum thermal test method proposed by the present invention is made below in conjunction with the drawings and specific embodiments further
It is described in detail.According to following explanation and claims, advantages and features of the invention will be become apparent from.It should be noted that attached drawing
It is all made of very simplified form and uses non-accurate ratio, only to convenient, lucidly the aid illustration present invention is implemented
The purpose of example.
Core of the invention thought is to provide a kind of mass production constellation system vacuum thermal test method, with solution
Certainly existing mass production satellite constellation test method seriously restricts the problem of development progress and Launch Program of batch production satellite.
To realize above-mentioned thought, the present invention provides a kind of mass production constellation system vacuum thermal test method,
The satellite system includes the same or similar multi-satellite of thermal control state, and the satellite system vacuum thermal test method includes:
The multi-satellite is put into space environment simulation equipment simultaneously, choose wherein a satellite as thermal balance star, other satellites
As thermal vacuum star, the thermal control state of the thermal balance star is more in bad condition than the thermal control of the thermal vacuum star；To the thermal balance
Star carries out heat balance test；During the heat balance test, the equipment on the thermal balance star presses in-orbit set Working mould
Formula is powered up, while applying Orbital heat flux by Orbital heat flux design parameter to each outer surface of the thermal balance star；In the heat
During blance test, imitated by the Orbital heat flux influence that the mutual circumstance of occlusion on each satellite brings the thermal balance star
Very, the Orbital heat flux for being applied to the thermal balance star is corrected in real time according to simulation result；In the heat balance test process
In, the equipment on the thermal vacuum star is powered up by in-orbit set operating mode；The heat balance test of the thermal balance star
After the completion, the temperature hold in range that the thermal vacuum test of the satellite system is determined according to the heat balance test result, according to
The temperature hold in range carries out the thermal vacuum test of the satellite system.
The present invention provides a kind of mass production constellation system vacuum thermal test method, described as shown in Fig. 1~7
Satellite system includes the same or similar multi-satellite of thermal control state, and the satellite system vacuum thermal test method includes: by institute
It states multi-satellite while being put into space environment simulation equipment 0, choose a wherein satellite and make as thermal balance star 1, other satellites
Thermal control state for thermal vacuum star 2,3,4, the thermal balance star 1 is more in bad condition than the thermal control of the thermal vacuum star 2,3,4；To institute
It states thermal balance star 1 and carries out heat balance test 11；During heat balance test 11, the equipment on the thermal balance star 1 is pressed
In-orbit set operating mode is powered up, while being applied to each outer surface of the thermal balance star 1 by Orbital heat flux design parameter
Orbital heat flux；During heat balance test 11, the thermal balance star 1 is brought by the mutual circumstance of occlusion to each satellite
Orbital heat flux influence emulated, the Orbital heat flux for being applied to the thermal balance star 1 is corrected in real time according to simulation result；?
During the heat balance test 11, the equipment on the thermal vacuum star 2,3,4 is powered up by in-orbit set operating mode；
After the completion of the heat balance test 11 of the thermal balance star 1, the satellite system is determined according to 11 result of heat balance test
The temperature hold in range of thermal vacuum test 12 carries out the thermal vacuum test of the satellite system according to the temperature hold in range
12。
Specifically, the satellite system vacuum thermal test method is also in the satellite system vacuum thermal test method
It include: that the space environment simulation equipment 0, the space are selected according to the size and quantity of satellite each in the satellite system
Environmental simulation equipment 0 is vertical cylinder or Horizontal cylinder body；The orientation of each satellite is put simultaneously by minimum test unit
Each star level-off operation is carried out, electrical testing cable and measuring and controlling temp cable are connected, the electrical testing cable is used for on satellite
Device power-on, the measuring and controlling temp cable are used to apply Orbital heat flux to the outer surface of the thermal balance star 1；It each is defended according to described
The position of star and put azimuth design heat test tooling so that the structural strength and rigidity of the heat test tooling meet it is described true
Empty heat test requirement, the heat test tooling includes guide rail, strut and suspender, to the strut directly contacted with each satellite and is hung
Tool carries out temperature-compensating, and test process is consistent in adjacent celestial body temperature by the control of tooling temperature, and it is right to reduce system leakage heat
The influence of heat balance test result；During the vacuum thermal test, active temperature is carried out to the guide rail, strut and suspender
Control rises again the progress of the positions such as the slower guide rail of process, supporting tool and sunpender actively to testing equipment in heat test process
Computer heating control carries out Active thermal control in process of rising again, reduces the heat test time；
Fig. 1 horizontal equipment double star single test status diagram, Fig. 2 horizontal equipment Samsung single test status diagram,
Four star single test status diagram of Fig. 3 horizontal equipment, Fig. 4 vertical equipment double star single test status diagram, Fig. 5 is vertical to be set
Standby Samsung single test status diagram, four star single test status diagram of Fig. 6 vertical equipment, 0 is that space environment simulation is set
Standby (i.e. space environment simulation equipment), 1 is the satellite (i.e. thermal balance star) for not only having participated in heat balance test but also having participated in thermal vacuum test,
2,3,4 be the satellite (i.e. thermal vacuum star) for being only involved in thermal vacuum test, and Fig. 1 to Fig. 3 is that selection horizontal test equipment is tested,
Left side graphical representation is participated in the experiment minimum test unit, and intermediate pattern is trystate front view, and right figure is trystate side view
Figure indicates the combination of minimum test unit.Fig. 4 to fig. 6 is that vertical testing equipment is selected to be tested, and left side graphical representation is participated in the experiment
Minimum test unit, right figure are trystate side view, indicate the combination of minimum test unit.
Further, in the satellite system vacuum thermal test method, the satellite system vacuum thermal test method
Further include: the outer surface of the thermal balance star 1 has main radiating surface and auxiliary radiating surface；The multi-satellite is put into the space
When environmental simulation equipment 0, the inner surface of space environment simulation equipment 0 described in the main radiating surface face, the auxiliary radiating surface is just
The non-radiating surface of inner surface or the thermal vacuum star 2,3,4 to the space environment simulation equipment 0, so that the thermal balance star
1 is blocked by the thermal vacuum star 2,3,4 and influences minimum.Fig. 1 into Fig. 61 indicate this test thermal balance star, 2,3,4
It indicates to participate in this thermal vacuum star tested.Celestial body heavy line indicates that main radiating surface, celestial body thick dashed line indicate auxiliary radiating surface, celestial body
Fine line indicates non-radiating area.It is set in placement process in thermal balance star and thermal vacuum championship, guarantee thermal balance championship as far as possible empties
Between, make its auxiliary main radiating surface face testing equipment inner surface, do not influenced by other celestial bodies, when major-minor radiating surface cannot ensure simultaneously
When in face of equipment inner surface, it should preferentially guarantee that main radiating surface, auxiliary radiating surface can make thermal balance star towards the non-radiating area of other celestial bodies
Being blocked influences minimum, is carried out Orbital heat flux amendment by simulation analysis by occlusion area.
Select each test unit of horizontal test equipment that can be arranged by Fig. 1 to Fig. 3, vertical each test unit of testing equipment
It can be arranged by fig. 4 to fig. 6, but be not limited to affiliated position relation in figure, also include being pushed away by Fig. 1 to Fig. 6 position relation
Other celestial body placement position relationships of performance.In implementation process, it should preferentially guarantee that there is thermal balance star sufficient position to put
It is heat sink can to add low temperature around thermal balance star when necessary for space and direction.
Start the parallel heat test of more stars, complete testing equipment self-test, after satellite power-on test, closes testing equipment gate,
Start to carry out the parallel vacuum thermal test of more stars.Test process is divided into initial test phase, heat balance test stage, thermal vacuum test
Stage, the seasoned experimental stage of vacuum amount to four-stage.But it is not limited to the above four-stage, the group again including above four stage
It closes；
As shown in fig. 7, in the satellite system vacuum thermal test method, the heat balance test 11 includes but unlimited
In heat balance test worst cold case 105 and heat balance test worst hot case 104, the heat balance test worst cold case 105 includes
Steady state cold temperature operating condition, quasi-steady state worst cold case, periodical transient state worst cold case and transient state worst cold case；The heat balance test is high
Warm operating condition 104 includes stable state worst hot case, quasi-steady state worst hot case, periodical transient high temperature operating condition and transient high temperature operating condition.Institute
State the Orbital heat flux of heat balance test worst hot case 104 according to the end of lifetime of the thermal balance star 1, near the winter solstice, maximum heat
Trajectory road parameters simulation result is configured, and is modified according to the circumstance of occlusion of each satellite, so that the thermal balance star 1
It works by maximum heat consumption mode, obtains heat balance test worst hot case temperature results；The heat balance test worst cold case
105 Orbital heat flux according to the beginning of lifetime of the thermal balance star 1, the summer solstice nearby, minimum thermal flux orbit parameter simulation result into
Row setting, and be modified according to the circumstance of occlusion of each satellite, so that the thermal balance star 1, which presses minimum heat consumption mode, carries out work
Make, obtains heat balance test worst cold case temperature results.The satellite that remaining is not involved in heat balance test during heat balance test
(thermal vacuum star) is configured according to thermal balance astrology with operating mode, when celestial body temperature being maintained to increase satellite power-on test
Between, but do not apply Orbital heat flux.
In addition, the thermal vacuum test 12 is protected according to the temperature in the satellite system vacuum thermal test method
It holds range and carries out several high/low temperature circulations, such as in Fig. 7,106 indicate that thermal vacuum test the 1st recycles；107 indicate thermal vacuum test
2nd circulation；108 indicate that thermal vacuum test the 3rd recycles；109 indicate that thermal vacuum test the 4th recycles；Subsequent may further include more
Circulation (110 ...)；In the high/low temperature cyclic process of thermal vacuum test 12: passing through setting auxiliary warming heater and Orbital heat flux
It simulates heat source and warming temperature is carried out to the thermal balance star 1 and the thermal vacuum star 2,3,4, defended in heating and cooling process by each
Star is set as identical powering state and thermal control state；Maximum temperature in the temperature hold in range is tried according to the thermal balance
It tests worst hot case temperature results to be determined, the minimum temperature in temperature hold in range is according to the heat balance test worst cold case
Temperature results are determined；Heat source is simulated to the thermal balance star by closing the auxiliary warming heater and the Orbital heat flux
1 and the thermal vacuum star 2,3,4 carry out cooling operation；Test mode and telemetry parameter to each satellite are acquired, compare
And analysis, judge whether the satellitosis of each satellite is consistent with performance, find and position abnormal data and parameter, handles potential
Failure.
The thermal vacuum test stage can be divided into several high/low temperature temperature cycles processes according to demand, and wherein high-temperature temperature keeps model
It encloses and is determined according to the heat balance test worst hot case test result of thermal balance star, cryogenic temperature hold in range is according to thermal balance
The heat balance test worst cold case test result of star is determined, and can pass through setting auxiliary heating in temperature cycles temperature-rise period
Device and Orbital heat flux simulation heat source way are rapidly heated, and temperature-fall period is realized by closing corresponding temperature control area heat source heater,
Platform and loading device master backup can be set as needed when airliner state in the circulation incipient stage every time, and then realizes to active and standby list
Machine test, all standing of examination.The thermal vacuum test stage need to be acquired each star test mode and telemetry parameter, compare and divide
Analysis confirms whether respectively participate in the experiment satellitosis, performance are consistent, should be arranged to all satellites of participating in the experiment in heating and cooling process identical
Powering state and thermal control state, position abnormal data during test and parameter, find in time and handle incipient fault
Mode.
Specifically, in the satellite system vacuum thermal test method, in the high temperature circulation process of thermal vacuum test 12
In: within the high temperature holding stage of the thermal vacuum test 12,80% or more temperature measuring point temperature is than the heat balance test high temperature
Working temperature result is 10 DEG C high~and 15 DEG C, and lower than checking and accepting grade highest test temperature；It is protected in the low temperature of the thermal vacuum test 12
It holds in the stage, 20% or more temperature measuring point temperature is 5 DEG C~15 DEG C lower than the heat balance test worst cold case temperature results, and is higher than
The minimum test temperature of grade is checked and accepted, the examination grade highest test temperature is determined according to design objective and code requirement, thermal vacuum
Test worst hot case, which keeps temperature that must not be higher than examination grade highest test temperature, (to be ensured to allow most under equipment safety operating condition
High-temperature) or it is set as design objective lower limit；The minimum test temperature of the examination grade is determined according to design objective code requirement
Thermal vacuum test worst cold case keeps temperature (must not ensure to permit under equipment safety operating condition lower than the minimum test temperature of grade is checked and accepted
Perhaps minimum temperature).It (checks and accepts the most high/low test temperature of grade and refers to equipment total allowed highest/low temperature working properly, exceed
The temperature range is possible to cause to damage to equipment, does not also allow during style beyond the temperature range)
Further, in the satellite system vacuum thermal test method, the satellite system vacuum thermal test method
Further include: before the heat balance test 11 progress, initial testing 10 is carried out to the satellite system, the initial testing 10 is wrapped
Include low pressure measurement condition 101, thermal control software test operating condition 102 and whole star high temperature outlet operating condition 103；But it is not limited to three kinds of works
Condition setting also includes the combination of above each operating condition of test.After the completion of thermal vacuum test 12, the satellite system is carried out
The seasoned test 13 of vacuum.The seasoned test rank of vacuum requires to determine that celestial body temperature hold in range carries out a period of time according to general technical
Power-on test.
Under the low pressure measurement condition 101, vacuum pumping is carried out to the space environment simulation equipment 0, is kept
The minimum system equipment of each satellite is in powering state so that the vacuum degree inside the space environment simulation equipment 0 by
1000Pa is reduced to 0.1Pa, monitors the powering state and telemetry parameter of each satellite, when minimum system equipment is satellite launch
Powered device examines powered device tolerance low pressure performance on emission process star；It is (big that low temperature environment is established in heat test
Part on-board equipment is not powered on) the whole star temperature relatively low stage carries out thermal control software module testing operating condition (102), including heater is opened
Ring test, closed loop test (switch control logic test, ratio control logic test) and heat control system remain whole in this stage
The ability of star temperature；Under the thermal control software test operating condition 102, risen according to thermal control software module temperature control threshold value and the auxiliary
The warm permitted minimum temperature of heater determines each satellite temperature control interval；It tests the thermal control software module and maintains whole star
The ability of temperature；Carry out switch control logic test and the ratio control logic test of the thermal control software module；Carry out whole star
Safe mode and thermal control software module minimum functional test；Carry out the auxiliary warming heater open-loop test and closed loop test.
Under whole star high temperature outlet operating condition 103, the auxiliary warming heater, Orbital heat flux simulation heat source and celestial body active thermal are used
Control heater increases the temperature of the satellite system, so that the temperature of the satellite system is more imitative than the maximum heat stream orbit parameter
True result is 5 DEG C high~10 DEG C and keep, the retention time is greater than 24 hours, to the structural slab of each satellite, dress star single machine, cable and
It fills star auxiliary material and carries out vacuum deflation processing.Vacuum deflation refers to that vacuumizing mode by heating removes in structural slab or stand-alone device
Organic macromolecule gas or other polluted gas ingredients.
In addition, after thermal vacuum test, can be ground according to model in the satellite system vacuum thermal test method
Schedule requirement processed adds the seasoned test of vacuum, maintains whole star temperature in certain level using auxiliary heater, and then normal to satellite
Warm power-up time carries out equivalent acceleration, reduces the subsequent room temperature seasoned time；The seasoned test 13 of vacuum includes: in the space
In environmental simulation equipment 0, the temperature of each satellite is adjusted by the auxiliary warming heater, at the same each satellite press it is in-orbit
Set operating mode is powered up, and be can be carried out test to the electrical property of each satellite, is simulated seasoned accelerated test.The seasoned test of vacuum
It needs to decide whether to carry out according to satellite development, if you need to which carry out then should be between vacuum seasoned stage whole star temperature hold zone clear first
And the state of power-up working equipment, think that vacuum is seasoned under normal circumstances and plays the role of accelerated test time, accelerated factor
(ordinary circumstance takes 1.3~1.5) related to temperature levels, but the seasoned test temperature of vacuum should not also choose it is excessively high, so as not to influence
Whole star safety.
In addition, including using star sensor in the satellite system in the satellite system vacuum thermal test method
The satellite for determining appearance, installs star map simulator on the satellite for determining appearance using star sensor, and closed loop attitude control software test is carried out to it,
Active temperature control and temperature monitoring are carried out to the star map simulator.For using star sensor to determine the satellite of appearance scheme,
Mountable star mould (star map simulator) carries out the software test of closed loop attitude control during heat test, and thermal control at this time need to be to star in testing equipment
Mould (star map simulator) carries out active temperature control.Vacuum gauge can also be set in thermal balance star stellar interior and ionization gauge carries out entirely
Process vacuum measurement, it is ensured that powerful device booting and use process safety in star.
Removable radiation shield is set at the main radiating surface of the thermal balance star 1 and the thermal vacuum star 2,3,4；Testing
In the case of conditions permit, removable radiation shield is added in thermal balance star and the main radiating surface region of thermal vacuum star, improves thermal balance examination
Test result precision and thermal vacuum star rate of temperature fall；Resistance silicone tube and ionization are set at the powerful device of the satellite system
Silicone tube；Vacuum gauge (including resistance silicone tube and ionization silicone tube) is added near celestial body powerful device in heat test process,
Realize the vacuum measurement in test overall process star；Heat sink apparatus is set at the thermal balance star 1.
In satellite system vacuum thermal test method provided by the invention, by carrying out heat balance test to thermal balance star 1
11, the Orbital heat flux for being applied to thermal balance star 1 is corrected in real time, after the completion of the heat balance test 11 of thermal balance star 1, according to heat
11 result of blance test determines the temperature hold in range of the thermal vacuum test 12 of satellite system, is defended according to temperature hold in range
The thermal vacuum test 12 of star system can significantly shorten the development of batch satellite and test period, reduce experimentation cost.By primary true
11 purpose of heat balance test can be realized in empty heat test operation, and can meet 12 check requirements of thermal vacuum test, and multi-satellite is simultaneously
Row carries out vacuum thermal test, can also Rapid Accumulation batch produce testing time of the satellite under hot vacuum environment, be very suitable to batch produce and defend
Star scale development；It realizes that the test period is short, and experimentation cost is low, only space environment simulation equipment need to be once passed in and out, to test
Preceding preparation, testing equipment operation and the requirement of thermal control process implementing are lower, avoid repeatedly implementing to turn over to satellite of participating in the experiment, hang
Dress and transfer operation, make celestial body be damaged probability reduction, save test needed for heat control material and test consumable, to test
Device type and index request are simple.
Thermal balance star carries out radiating area according to related specifications standard requirements and non-radiating area Orbital heat flux is simulated, and shape is implemented in thermal control
State and in-orbit state consistency improve heat balance test result precision；Thermal vacuum star is simulated without Orbital heat flux, and shape is implemented in thermal control
The more in-orbit state of state is simplified, and complex operation and implementation cycle are reduced, and reduces experimentation cost.Thermal balance star multilayer group
Part carries out Orbital heat flux amendment by simulation analysis and test process temperature measurement result, increasingly with spacecraft thermal control analysis software
Maturation, accuracy step up, and correct ermal physics model in such a way that test is combined with simulation analysis, using hot after amendment
Physical model indicates the in-orbit temperature range of instrument and equipment each on star and changing rule.By once into space environment simulation
11 purpose of heat balance test can be realized in equipment operation, has both 12 check requirements of thermal vacuum test, while meeting mass production
Satellite develops mission requirements.
The present invention relates to a kind of methods of the more star parallel ground vacuum thermal test verifyings of mass production satellite (spacecraft).
These satellites should have same or similar thermal control state, which can be widely applied to low rail communication satellite constellation, remote sensing is defended
Star seat, navigation satellite constellation and internet satellite constellation etc. produce satellite in batches and carry out vacuum heat examination simultaneously or in batches
It tests, in particular by " several satellite in a rocket " radiation pattern, the more consistent business space industry of satellite thermal control state.
To sum up, the various configuration of satellite system vacuum thermal test method is described in detail in above-described embodiment, certainly,
The present invention includes but is not limited to configuration cited in above-mentioned implementation, any enterprising on configuration basis provided by the above embodiment
The content of row transformation belongs to the range that the present invention is protected.Those skilled in the art can be according to the content of above-described embodiment
Draw inferences about other cases from one instance.
Foregoing description is only the description to present pre-ferred embodiments, not to any restriction of the scope of the invention, this hair
Any change, the modification that the those of ordinary skill in bright field does according to the disclosure above content, belong to the protection of claims
Range.
Claims (14)
1. a kind of mass production constellation system vacuum thermal test method, the satellite system include thermal control state it is identical or
Similar multi-satellite；It is characterized in that, the satellite system vacuum thermal test method includes:
The same or similar satellite of the more thermal control states is put into space environment simulation equipment simultaneously, selection is wherein defended for one
Star is as thermal balance star, other satellites are as thermal vacuum star, the heat of the thermal control state of the thermal balance star than the thermal vacuum star
It controls in bad condition；
Heat balance test is carried out to the thermal balance star；
During the heat balance test, the equipment on the thermal balance star is powered up by in-orbit set operating mode, together
When Orbital heat flux is applied by Orbital heat flux design parameter to each outer surface of the thermal balance star；
During the heat balance test, the outer heat of the thermal balance star is brought by the mutual circumstance of occlusion to each satellite
Stream influences to be emulated, and is corrected in real time according to simulation result to the Orbital heat flux for being applied to the thermal balance star；
During the heat balance test, the equipment on the thermal vacuum star is powered up by in-orbit set operating mode；
After the completion of the heat balance test of the thermal balance star, the heat of the satellite system is determined according to the heat balance test result
The temperature hold in range of vacuum test carries out the thermal vacuum test of the satellite system according to the temperature hold in range.
2. satellite system vacuum thermal test method as described in claim 1, which is characterized in that the satellite system vacuum heat examination
Proved recipe method further include:
The space environment simulation equipment, the spatial loop are selected according to the size of satellite each in the satellite system and quantity
Border analog machine is vertical cylinder or Horizontal cylinder body；
The orientation of each satellite is put by minimum test unit, connects electrical testing cable and measuring and controlling temp cable, the electricity
Test cable is used to be powered on satellite borne equipment, and the measuring and controlling temp cable is used to apply the outer surface of the thermal balance star
Orbital heat flux；
According to the position of each satellite and azimuth design heat test tooling is put, so that the structure of the heat test tooling is strong
Degree and rigidity meet the vacuum thermal test requirement, and the heat test tooling includes guide rail, strut and suspender, to each satellite
The strut and suspender directly contacted carries out temperature-compensating, during the vacuum thermal test, to the guide rail, strut and suspender
Carry out active temperature control.
3. satellite system vacuum thermal test method as described in claim 1, which is characterized in that the satellite system vacuum heat examination
Proved recipe method further include:
The outer surface of the thermal balance star has main radiating surface and auxiliary radiating surface；
When the multi-satellite is put into the space environment simulation equipment, space environment simulation described in the main radiating surface face
The inner surface of equipment, the inner surface of space environment simulation equipment described in the auxiliary radiating surface face or the non-of the thermal vacuum star dissipate
Hot face, so that the thermal balance star is blocked by the thermal vacuum star influences minimum.
4. satellite system vacuum thermal test method as described in claim 1, which is characterized in that the heat balance test include but
It is not limited to heat balance test worst cold case and heat balance test worst hot case,
The heat balance test worst cold case includes steady state cold temperature operating condition, quasi-steady state worst cold case, periodical transient state worst cold case
And transient state worst cold case；
The heat balance test worst hot case includes stable state worst hot case, quasi-steady state worst hot case, periodical transient high temperature operating condition
And transient high temperature operating condition.
5. satellite system vacuum thermal test method as claimed in claim 4, which is characterized in that
The Orbital heat flux of the heat balance test worst hot case according to the end of lifetime of the thermal balance star, near the winter solstice, it is maximum
Hot-fluid orbit parameter simulation result is configured, and is modified according to the circumstance of occlusion of each satellite, so that the thermal balance
Star works by maximum heat consumption mode, obtains heat balance test worst hot case temperature results；
The Orbital heat flux of the heat balance test worst cold case according to the beginning of lifetime of the thermal balance star, the summer solstice nearby, it is minimum
Hot-fluid orbit parameter simulation result is configured, and is modified according to the circumstance of occlusion of each satellite, so that the thermal balance
Star works by minimum heat consumption mode, obtains heat balance test worst cold case temperature results.
6. satellite system vacuum thermal test method as claimed in claim 5, which is characterized in that the thermal vacuum test is according to institute
It states temperature hold in range and carries out several high/low temperature circulations, in the high/low temperature cyclic process of thermal vacuum test:
Heat source is simulated by setting auxiliary warming heater and Orbital heat flux to rise the thermal balance star and the thermal vacuum star
Temperature operation, sets identical powering state and thermal control state for each satellite in heating and cooling process；
Maximum temperature in the temperature hold in range is determined according to the heat balance test worst hot case temperature results, temperature
Minimum temperature in degree hold in range is determined according to the heat balance test worst cold case temperature results；
Heat source is simulated to the thermal balance star and the thermal vacuum by closing the auxiliary warming heater and the Orbital heat flux
Star carries out cooling operation；
Test mode and telemetry parameter to each satellite are acquired, compare and analyze, and judge the satellitosis of each satellite
It is whether consistent with performance, abnormal data and parameter are found and positioned, incipient fault is handled.
7. satellite system vacuum thermal test method as claimed in claim 6, which is characterized in that in the high/low temperature of thermal vacuum test
In cyclic process:
Within the high temperature holding stage of the thermal vacuum test, 80% or more temperature measuring point temperature is than the heat balance test high temperature work
Condition temperature results are 10 DEG C high~and 15 DEG C, and lower than checking and accepting grade highest test temperature；
Within the low temperature holding stage of the thermal vacuum test, 20% or more temperature measuring point temperature is than the heat balance test low temperature work
Condition temperature results are 5 DEG C~15 DEG C low, and are higher than and check and accept the minimum test temperature of grade.
8. satellite system vacuum thermal test method as claimed in claim 6, which is characterized in that the satellite system vacuum heat examination
Proved recipe method further include:
Before heat balance test progress, initial testing is carried out to the satellite system, the initial testing includes low pressure
Measurement condition, thermal control software test operating condition and whole star high temperature outlet operating condition；
After the completion of the thermal vacuum test, the seasoned test of vacuum is carried out to the satellite system.
9. satellite system vacuum thermal test method as claimed in claim 8, which is characterized in that
Under the low pressure measurement condition, vacuum pumping is carried out to the space environment simulation equipment, keeps each satellite
Minimum system equipment be in powering state so that the vacuum degree inside the space environment simulation equipment is reduced to by 1000Pa
0.1Pa monitors the powering state and telemetry parameter of each satellite, powered device when minimum system equipment is satellite launch.
10. satellite system vacuum thermal test method as claimed in claim 8, which is characterized in that in the thermal control software test
Under operating condition, each defend is determined according to thermal control software module temperature control threshold value and the permitted minimum temperature of the auxiliary warming heater
Between star temperature-controlled area；
Test the ability that the thermal control software module maintains whole star temperature；
Carry out switch control logic test and the ratio control logic test of the thermal control software module；
Carry out whole star safe mode and thermal control software module minimum functional test；
Carry out the auxiliary warming heater open-loop test and closed loop test.
11. satellite system vacuum thermal test method as claimed in claim 8, which is characterized in that in whole star high temperature outlet operating condition
Under, the satellite is increased using the auxiliary warming heater, Orbital heat flux simulation heat source and celestial body Active thermal control heater
The temperature of system so that the temperature of the satellite system it is 5 DEG C higher than maximum heat trajectory road parameters simulation result~10 DEG C simultaneously
It keeps, the retention time is greater than 24 hours, deflates to the structural slab of each satellite, dress star single machine, cable and dress star auxiliary material.
12. satellite system vacuum thermal test method as claimed in claim 8, which is characterized in that the seasoned test packet of vacuum
It includes: in the space environment simulation equipment, the temperature of each satellite is adjusted by the auxiliary warming heater, while each
Satellite is powered up by in-orbit set operating mode, be can be carried out test to the electrical property of each satellite, is simulated seasoned accelerated test.
13. satellite system vacuum thermal test method as described in claim 1, which is characterized in that include in the satellite system
The satellite that appearance is determined using star sensor, installs star map simulator on the satellite for determining appearance using star sensor, carries out closed loop to it
Attitude control software test carries out active temperature control and temperature monitoring to the star map simulator.
14. satellite system vacuum thermal test method as described in claim 1, which is characterized in that the thermal balance star and described
Removable radiation shield is set at the main radiating surface of thermal vacuum star；
Resistance silicone tube and ionization silicone tube are set at the powerful device of the satellite system；
Heat sink apparatus is set at the thermal balance star.
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| CN113602537A (en) * | 2021-06-11 | 2021-11-05 | 北京卫星环境工程研究所 | Spacecraft vacuum thermal environment simulation structure and temperature adjusting method |
| CN116263595A (en) * | 2022-11-16 | 2023-06-16 | 长光卫星技术股份有限公司 | Universal automatic test platform for satellite single machine environment test and control method thereof |
| CN116263595B (en) * | 2022-11-16 | 2024-05-10 | 长光卫星技术股份有限公司 | Universal automatic test platform for satellite single machine environment test and control method thereof |
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