CN105928723A - Flight model satellite test method and system of minisatellite - Google Patents
Flight model satellite test method and system of minisatellite Download PDFInfo
- Publication number
- CN105928723A CN105928723A CN201610247945.2A CN201610247945A CN105928723A CN 105928723 A CN105928723 A CN 105928723A CN 201610247945 A CN201610247945 A CN 201610247945A CN 105928723 A CN105928723 A CN 105928723A
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- Prior art keywords
- star
- heat
- positive sample
- microsatellite
- module
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M99/00—Subject matter not provided for in other groups of this subclass
- G01M99/002—Thermal testing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
Abstract
The present invention provides a flight model satellite test method and system of a minisatellite. The method comprises the steps of (S1) carrying out thermal modification on a flight model satellite, (S2) loading a satellite for the flight model satellite, (S3) carrying out vacuum testing on the flight model satellite, and (S4) carrying out multiple-layer heat insulation material coating finishing on the flight model satellite. According to the method and the system, the overall task targets of low cost, short cycle and large volume of the minisatellite are achieved, the flight model test verification of the minisatellite is simply and rapidly completed, and the development cost and development cycle of a flight model development phase thermal control satellite are reduced.
Description
Technical field
The present invention relates to the technical field of microsatellite, particularly relate to positive sample star thermal test method and the system of a kind of microsatellite.
Background technology
Positive sample star is to have passed through ground acceptance test in the positive sample development stage, can be used for the satellite launched.According to satellite procedure of development,
Positive sample star development should be developed task at first sample star and be completed to start afterwards, i.e. requires according to the design of positive sample and is confirmed after first sample satellite experiment
Structure and state of the art, design, test can be used for launch satellite.The positive sample development stage generally develops a positive sample thermal control star
Star is launched with a positive sample.Positive sample thermal control star carries out the thermal vacuum test on ground, launches star and carries out various acceptance test, such as vibration
Test, electric performance test, electromagnetic compatibility test, seasoned test etc..Positive sample thermal control star all uses Zhenyang to launch in addition to structural member
Product.In conventional satellite develops flow process, the heat of positive sample star implements and experiment process comprises the following steps:
1) positive sample thermal control star heat repacking
I.e. structural member sprays paint, cabling pasted by Orbital heat flux heating plate, thermocouple and thermistor
2) positive sample thermal control star dress star
3) positive sample thermal control star heat repacking
I.e. weld heater, acting thermocouple plug/cladding multilayer etc.
4) positive sample vacuum thermal test
5) positive sample thermal control star tears star open
6) repacking of star heat launched by positive sample
I.e. structural member sprays paint, active heater, thermistor paste wire bonding
7) star dress star launched by positive sample
8) star multilayer coating structure launched by positive sample
From the foregoing, it will be observed that the heat at positive sample star is implemented and during test, two noose components, twice whole star heat repacking and positive sample is needed to produce
Product fill star for twice and once tear star open, thus cause whole process cost height, cycle length, risk big.
For some lead time length, large satellite that research fund is sufficient, in order to heat test simulation more accurately, test data more
Fully, can develop by above-mentioned flow process completely.But the small-sized micro-nano satellite that, research fund short for the lead time is nervous,
Time and funds the most do not allow the development flow process of such long period, high cost.
It addition, microsatellite structure is relatively easy, during heat test, need not too many point for measuring temperature, and positive sample layout does not changes the most greatly
Dynamic.Therefore, how to simplify the development flow process of satellite positive sample thermal control, be a big key point of microsatellite market existence.
Summary of the invention
The shortcoming of prior art in view of the above, it is an object of the invention to provide the positive sample star heat test side of a kind of microsatellite
Method and system, by the positive sample thermal control star of microsatellite and the integrated design of launching star, it is only necessary to a set of structural member, once
The repacking of whole star heat and once positive sample product dress star can realize the heat test of positive sample star, thus reduce microsatellite development cost,
Shorten the lead time.
For achieving the above object and other relevant purposes, the present invention provides the positive sample star thermal test method of a kind of microsatellite, including
Following steps: step S1, align sample star carry out heat repacking；Step S2, align sample star carry out fill star；Step S3, align sample
Star carries out vacuum thermal test；Step S4, align sample star carry out multilayer insulation material cladding arrange.
According to the positive sample star thermal test method of above-mentioned microsatellite, wherein: in described step S1, the repacking of positive sample star heat includes knot
Component sprays paint, actively heating plate pastes bonding wire, cabling pasted by thermistor, one-wire bus formula temp measuring system pastes cabling.
Further, according to the positive sample star thermal test method of above-mentioned microsatellite, wherein: described one-wire bus formula temp measuring system
Employing parallel way, and become thermometric interface to access house keeping computer.
According to the positive sample star thermal test method of above-mentioned microsatellite, wherein: in described step S2, during positive sample star dress star, all
Heater, thermistor, one-wire bus formula temp measuring system, multilayer insulation material are positive sample and launch part.
According to the positive sample star thermal test method of above-mentioned microsatellite, wherein: in described step S3, infrared heating cage is used to carry out
Orbital heat flux is simulated, and uses one-wire bus formula temp measuring system to carry out temperature field monitoring.
Meanwhile, the present invention also provides for the positive sample star heat test system of a kind of microsatellite, including heat repacking module, dress star module,
Heat test module and multilayer sorting module；
Described heat repacking module is used for aligning sample star and carries out heat repacking；
Described dress star module is used for aligning sample star and carries out filling star；
Described heat test module is used for aligning sample star and carries out vacuum thermal test；
Described sorting module is used for aligning sample star and carries out multilayer insulation material cladding arrangement.
According to the positive sample star heat test system of above-mentioned microsatellite, wherein: in described heat repacking module, positive sample star heat repacking bag
Include structural member spray paint, actively heating plate paste bonding wire, thermistor paste cabling, one-wire bus formula temp measuring system paste cabling.
Further, according to the positive sample star heat test system of above-mentioned microsatellite, wherein: described one-wire bus formula temp measuring system
Use parallel way, and become a thermometric interface to access house keeping computer.
According to the positive sample star heat test system of above-mentioned microsatellite, wherein: in described dress star module, during positive sample star dress star, institute
Having heaters, thermistor, one-wire bus formula temp measuring system, multilayer insulation material are positive sample and launch part.
According to the positive sample star heat test system of above-mentioned microsatellite, wherein: in described heat test module, infrared heating cage is used
Carry out Orbital heat flux simulation, use one-wire bus formula temp measuring system to carry out temperature field monitoring.
As it has been described above, the positive sample star thermal test method of the microsatellite of the present invention and system, have the advantages that
(1) microsatellite low cost, short cycle and large batch of overall tasks target have been effectively achieved；
(2) the positive sample heat test checking of microsatellite is completed quickly and easily；
(3) development cost and the lead time of positive sample development stage thermal control star are decreased.
Accompanying drawing explanation
Fig. 1 is shown as the flow chart of the positive sample satellite thermal test method of the present invention；
Fig. 2 is shown as the working state schematic representation of one-wire bus formula intelligent temperature measurement system；
Fig. 3 is shown as the structural representation of the positive sample satellite heat test system of the present invention.
Element numbers explanation
1 heat repacking module
2 dress star modules
3 heat test modules
4 multilayer sorting module
Detailed description of the invention
Below by way of specific instantiation, embodiments of the present invention being described, those skilled in the art can be by disclosed by this specification
Content understand other advantages and effect of the present invention easily.The present invention can also be added by the most different detailed description of the invention
To implement or application, the every details in this specification can also be based on different viewpoints and application, in the essence without departing from the present invention
Various modification or change is carried out under god.It should be noted that, the feature in the case of not conflicting, in following example and embodiment
Can be mutually combined.
It should be noted that the diagram provided in following example illustrates the basic conception of the present invention the most in a schematic way, then scheme
Component count, shape and size when only showing the assembly relevant with the present invention rather than implement according to reality in formula are drawn, in fact
When border is implemented, the kenel of each assembly, quantity and ratio can be a kind of random change, and its assembly layout kenel is likely to the most multiple
Miscellaneous.
With reference to Fig. 1, the positive sample star thermal test method of the microsatellite of the present invention comprises the following steps:
Step S1, align sample star carry out heat repacking.
Specifically, positive sample star heat repacking include structural member spray paint, actively heating plate paste bonding wire, thermistor paste cabling, one
Line bus type temp measuring system pastes cabling.Wherein, actively heating plate is the heater element carrying out heating compensation to unit on star.
Preferably, in the present invention, one-wire bus formula temp measuring system uses DS18B20 temperature transducer.
Unlike traditional handicraft, the present invention use one-wire bus formula temp measuring system replace traditional thermocouple to carry out thermometric.
Compared to thermocouple temperature measurement, one-wire bus formula temp measuring system thermometric has the advantage that
1) reason line, the weldering plug work using thermocouple to bring is decreased
Conventional satellite heat test uses a large amount of thermocouples (200-500) to monitor satellite temperature, and conventional thermocouple is copper constantan heat
Galvanic couple, except pasting cabling during repacking, in addition it is also necessary to each thermocouple copper constantan two class line separately, right latter class be welded into plug,
One class is merged into single line and draws access ice bucket, then carries out thermometric, causes workload the hugest.And use one-wire bus formula
Temp measuring system thermometric is not in the case of cost raises, and the lead-in wire of all points for measuring temperature is finally merged into three lines, connects Star Service
Computer interface, carries out temperature acquisition, greatly reduces workload.
2) cleaning work of fifth wheel on star after employing hot thermocouple is tested is avoided
For monitoring each unit temperature during positive sample heat test, can paste thermocouple on each unit, heat test can remain in after terminating
On positive sample unit, comprehend with launching star entrance space as unclear.Thermocouple kish thing etc. may affect unit performance.And
One-wire bus formula temp measuring system thermometric is to carry out temperature acquisition by house keeping computer, can be continuing with after off-test on star,
, there is not fifth wheel on star in monitoring satellite temperature.
3) solve house keeping computer and the problem that thermometric interface is not enough is provided
Small-sized micro-nano satellite house keeping computer resource is the most nervous, it is provided that less to the thermometric interface of thermal control subsystem.Such as figure
Shown in 2, when using one-wire bus formula intelligent temperature measurement system, all points for measuring temperature use parallel way, one group of one-wire bus formula thermometric
System is less than 50 points for measuring temperature, a thermometric interface and can be become to access house keeping computer, thus save house keeping computer resource.
4) the dismounting work of whole star after conventional thermal is tested is eliminated
Tradition thermal control star and transmitting star use two noose components, and heat test needs to tear star open after terminating, and all units are contained in transmitting star
On structural slab, cause whole during can there is certain risk.
Step S2, align sample star carry out fill star.
Specifically, positive sample star uses and once fills star, no longer dismounts.During positive sample star dress star, institute's having heaters, thermistor, one
Line bus type temp measuring system, multilayer insulation material are positive sample and launch part.
Step S3, align sample star and carry out vacuum thermal test.
Specifically, when carrying out vacuum thermal test, use infrared heating cage to carry out Orbital heat flux simulation, use one-wire bus formula thermometric system
System carries out temperature field monitoring.
Step S4, align sample star carry out multilayer insulation material cladding arrange.
Specifically, after satellite enters launching site, multilayer insulation material finally checked, arrange, fix.
In sum, in the positive sample star thermal test method of the microsatellite of the present invention, test thermal control star and transmitting star use a noose
Component, whole star once fills star shaping；During vacuum thermal test, use infrared heating cage simulation Orbital heat flux heating；Use one-wire bus
Formula temp measuring system thermometric replaces thermocouple temperature measurement；And after experiment, strengthen launching on star single by one-wire bus formula temp measuring system
Machine temperature monitoring.Therefore, the positive sample star thermal test method of the microsatellite of the present invention reduces microsatellite development cost, shortening
Lead time, there is the strongest practicality.
With reference to Fig. 3, the positive sample star heat test system of the microsatellite of the present invention includes heat repacking module 1, the dress star mould being sequentially connected
Block 2, heat test module 3 and multilayer sorting module 4.
Heat repacking module 1 is used for aligning sample star and carries out heat repacking.
Specifically, positive sample star heat repacking include structural member spray paint, actively heating plate paste bonding wire, thermistor paste cabling, one
Cabling pasted by line bus type temp measuring system sensor.
Unlike traditional handicraft, the present invention use one-wire bus formula temp measuring system replace traditional thermocouple to carry out thermometric.
Wherein, all one-wire bus formula temp measuring systems use parallel way, and a thermometric interface and can be become to access house keeping computer, from
And save house keeping computer resource.
Dress star module 2 is used for aligning sample star and carries out filling star.
Specifically, positive sample star uses and once fills star, no longer dismounts.During positive sample star dress star, institute's having heaters, thermistor, one
Line bus type temp measuring system, multilayer insulation material are positive sample and launch part.
Heat test module 3 is used for aligning sample star and carries out vacuum thermal test.
Specifically, when carrying out vacuum thermal test, use infrared heating cage to carry out Orbital heat flux simulation, use one-wire bus formula thermometric system
System carries out temperature field monitoring.
Sorting module 4 is used for aligning sample star and carries out multilayer insulation material cladding arrangement.
Specifically, after satellite enters launching site, multilayer insulation material finally checked, arrange, fix.
Conventional satellite thermal control star structural slab the Orbital heat flux heating plate of viscous note, thermocouple, after finishing test launch star can not use again,
It is thus desirable to throw a set of again.And in the positive sample star heat test system of the microsatellite of the present invention, do not glue note Orbital heat flux heating plate, heat
Galvanic couple, satellite once fills star and no longer dismounts, and it is same star that thermal control star launches star, it is only necessary to a set of structural member, whole star once fills
Star is molded；During vacuum thermal test, use infrared heating cage simulation Orbital heat flux heating；Use one-wire bus formula temp measuring system thermometric generation
For thermocouple temperature measurement；And after experiment, strengthen launching unit temperature monitoring on star by one-wire bus formula temp measuring system.Therefore,
The positive sample star heat test system of the microsatellite of the present invention reduces microsatellite development cost, shortens the lead time, has very
Strong practicality.
In sum, the positive sample star thermal test method of the microsatellite of the present invention and system effectively achieved microsatellite low cost,
Short cycle and large batch of overall tasks target；Complete the positive sample heat test checking of microsatellite quickly and easily；Just decrease
The development cost of sample development stage thermal control star and lead time.So, the present invention effectively overcomes various shortcoming of the prior art
And have high industrial utilization.
The principle of above-described embodiment only illustrative present invention and effect thereof, not for limiting the present invention.Any it is familiar with this skill
Above-described embodiment all can be modified under the spirit and the scope of the present invention or change by the personage of art.Therefore, such as
All that in art, tool usually intellectual is completed under without departing from disclosed spirit and technological thought etc.
Effect is modified or changes, and must be contained by the claim of the present invention.
Claims (10)
1. the positive sample star thermal test method of a microsatellite, it is characterised in that: comprise the following steps:
Step S1, align sample star carry out heat repacking；
Step S2, align sample star carry out fill star；
Step S3, align sample star and carry out vacuum thermal test；
Step S4, align sample star carry out multilayer insulation material cladding arrange.
The positive sample star thermal test method of microsatellite the most according to claim 1, it is characterised in that: in described step S1, just
The repacking of sample star heat includes that structural member sprays paint, actively heating plate pastes bonding wire, thermistor pastes cabling, one-wire bus formula thermometric
System pastes cabling.
The positive sample star thermal test method of microsatellite the most according to claim 2, it is characterised in that: described one-wire bus formula thermometric
The employing parallel way of system, and become a thermometric interface to access house keeping computer.
The positive sample star thermal test method of microsatellite the most according to claim 1, it is characterised in that: in described step S2, just
During sample star dress star, institute's having heaters, thermistor, one-wire bus formula temp measuring system, multilayer insulation material are positive sample and launch
Part.
The positive sample star thermal test method of microsatellite the most according to claim 1, it is characterised in that: in described step S3, adopt
Carry out Orbital heat flux simulation with infrared heating cage, use one-wire bus formula temp measuring system to carry out temperature field monitoring.
6. the positive sample star heat test system of a microsatellite, it is characterised in that: include heat repacking module, dress star module, heat test mould
Block and multilayer sorting module；
Described heat repacking module is used for aligning sample star and carries out heat repacking；
Described dress star module is used for aligning sample star and carries out filling star；
Described heat test module is used for aligning sample star and carries out vacuum thermal test；
Described sorting module is used for aligning sample star and carries out multilayer insulation material cladding arrangement.
The positive sample star heat test system of microsatellite the most according to claim 6, it is characterised in that: in described heat repacking module,
Positive sample star heat repacking includes that structural member sprays paint, actively heating plate pastes bonding wire, cabling pasted by thermistor, one-wire bus formula is surveyed
Temperature system pastes cabling.
The positive sample star heat test system of microsatellite the most according to claim 7, it is characterised in that: described one-wire bus formula thermometric
System uses parallel way, and becomes a thermometric interface to access house keeping computer.
The positive sample star heat test system of microsatellite the most according to claim 6, it is characterised in that: in described dress star module, just
During sample star dress star, institute's having heaters, thermistor, one-wire bus formula temp measuring system, multilayer insulation material are positive sample and launch
Part.
The positive sample star heat test system of microsatellite the most according to claim 6, it is characterised in that: described heat test module
In, use infrared heating cage to carry out Orbital heat flux simulation, use one-wire bus formula temp measuring system to carry out temperature field monitoring.
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| CN201610247945.2A CN105928723A (en) | 2016-04-20 | 2016-04-20 | Flight model satellite test method and system of minisatellite |
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| CN201610247945.2A CN105928723A (en) | 2016-04-20 | 2016-04-20 | Flight model satellite test method and system of minisatellite |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107861400A (en) * | 2017-08-31 | 2018-03-30 | 王洋 | A kind of control method and device for adjusting the in-orbit Orbital heat flux simulation of microsatellite |
| CN108181120A (en) * | 2017-12-27 | 2018-06-19 | 中国科学院国家空间科学中心 | A kind of more equipment thermal cycling test devices |
| CN111605742A (en) * | 2020-06-03 | 2020-09-01 | 中国科学院微小卫星创新研究院 | Multi-satellite vacuum thermal test method and system |
| CN111651837A (en) * | 2020-06-03 | 2020-09-11 | 中国科学院微小卫星创新研究院 | Satellite thermal control management system and method |
| CN112836351A (en) * | 2021-01-11 | 2021-05-25 | 上海利正卫星应用技术有限公司 | Design method and system for sine vibration test of commercial microsatellite satellite-mounted product |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107861400A (en) * | 2017-08-31 | 2018-03-30 | 王洋 | A kind of control method and device for adjusting the in-orbit Orbital heat flux simulation of microsatellite |
| CN108181120A (en) * | 2017-12-27 | 2018-06-19 | 中国科学院国家空间科学中心 | A kind of more equipment thermal cycling test devices |
| CN111605742A (en) * | 2020-06-03 | 2020-09-01 | 中国科学院微小卫星创新研究院 | Multi-satellite vacuum thermal test method and system |
| CN111651837A (en) * | 2020-06-03 | 2020-09-11 | 中国科学院微小卫星创新研究院 | Satellite thermal control management system and method |
| CN113665853A (en) * | 2020-06-03 | 2021-11-19 | 中国科学院微小卫星创新研究院 | Vacuum thermal test method of satellite system |
| CN111651837B (en) * | 2020-06-03 | 2023-03-24 | 中国科学院微小卫星创新研究院 | Satellite thermal control management system and method |
| CN112836351A (en) * | 2021-01-11 | 2021-05-25 | 上海利正卫星应用技术有限公司 | Design method and system for sine vibration test of commercial microsatellite satellite-mounted product |
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