CN103324787B - Criticize and produce Satellite Thermal Design verification method - Google Patents
Criticize and produce Satellite Thermal Design verification method Download PDFInfo
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Abstract
The present invention relates to a kind of batch and produce Satellite Thermal Design verification method, belong to spacecraft Evolution of Thermal Control Technique field.First each Platform Satellite heat balance test basal temperature data under obtaining designing technique state after selecting the starting star of same platform to carry out heat balance test, then instrument and equipment actual measurement hear rate data in follow-up every satellite are added up, thermal vacuum test Instrumental equipment is at worst hot case temperature and worst cold case temperature data, recycle starting star heat balance test temperature data, to the equipment in hot simulation analysis model, contact heat transfer coefficient is installed improve and optimize, realistic model is made to meet the actual techniques state of satellite, last with the test figure of starting star for benchmark, the actual measurement hear rate of the equal instrument and equipment of comparison subsequent satellites and the difference of thermal vacuum test temperature and starting star are evaluated subsequent satellites thermal design adaptability.Present invention eliminates same platform subsequent satellites heat balance test checking, optimize satellite development flow process.
Description
Technical field
Invention relates to a kind of verification method, is specifically related to a kind of batch and produces Satellite Thermal Design verification method, belong to spacecraft Evolution of Thermal Control Technique field.
Background technology
What Navsat adopted is whole star short run operation pattern.By traditional single star development mode, after developing the starting satellite of platform, curing technology state, subsequent satellites carries out the manufacture of short run by starting star design point.
Satellite development mode traditionally, for Navsat, each satellite all needs to carry out heat balance test and verifies whether thermal design and equipment installation meet the demands.If adopt traditional development mode, testing expenses are high and the lead time is long, are not suitable with the short run operation pattern of Navsat.Due to Navsat small serial production pattern, the relatively-stationary feature of the state that possesses skills, in same Platform Satellite, only carry out heat balance test checking to first satellite developed, other follow-up satellites developed possess the prerequisite cancelling heat balance test.
Owing to being small serial production, instrument and equipment commercialization degree of ripeness selected by satellite is not the same, the difference of the actual hear rate of instrument and equipment as thermal design basis may be caused, satellite is not being carried out on the basis of heat balance test, is needing to find a kind of method to verify that can thermal design adapt to the change of the actual hear rate of instrument and equipment.
In addition, most of instrument and equipment is installed as artificial enforcement, as the coating of thermal grease conduction, the size of multi-layer heat dissipation face opening, also will affect the installment state of equal instrument and equipment between satellite, and there are differences with thermal design state.Can the instrument and equipment in satellite is installed meet designing requirement, also needs a kind of new method and verifies.
Summary of the invention
In view of this, the invention provides a kind of batch and produce Satellite Thermal Design verification method, the new model of satellite short run development can be adapted to, reduce the dependence that thermal design is verified heat balance test, optimize satellite development flow process.
Criticize and produce Satellite Thermal Design verification method, its verification step is as follows:
The first step: whole star heat balance test is carried out to first satellite (being called for short starting star) of same Platform Satellite, test simulation satellite is high temperature and worst cold case under Live Flying state in-orbit, the thermal design of satellite is verified, can verifying satellites thermal design ensure satellite working flight temperature requirement in-orbit, obtains the minimum equilibrium temperature of inside satellite every platform instrument and equipment under designing technique state and the highest equilibrium temperature; If the minimum equilibrium temperature of inside satellite every platform instrument and equipment, the highest equilibrium temperature all within the scope of designing requirement, are then considered as starting star thermal design qualified, and perform second step; If minimum equilibrium temperature or the highest equilibrium temperature of inside satellite every platform instrument and equipment exceed designing requirement scope, be then considered as thermal design defective, need thermal design be improved until qualified rear execution second step;
Second step: to add up in starting star instruments and equipment checking test gained actual hear rate data and starting star whole star thermal vacuum test Instrumental equipment at worst hot case temperature and worst cold case temperature data, as subsequent satellites metewand;
3rd step: on satellite finite element thermal analysis realistic model basis, the starting star whole star heat balance test temperature data utilizing the first step to obtain, to the equipment in hot simulation analysis model, contact heat transfer coefficient value is installed improve and optimize, realistic model is made to meet the actual techniques state of satellite, for subsequent thermal design qualification determination;
4th step: subsequent satellites thermal design qualification determination criterion: the actual hear rate data of instruments and equipment checking test gained in statistics subsequent satellites, and the actual hear rate data of the instrument and equipment corresponding with in star starting described in second step are compared; Add up each instrument and equipment of subsequent satellites worst hot case temperature and worst cold case temperature data in thermal vacuum test again, and the worst hot case temperature of the instrument and equipment corresponding with in star starting described in second step and worst cold case temperature data are compared; If follow-up star were no more than with the actual hear rate comparing intensity of variation of corresponding instrument and equipments all in starting star ± 10%, and hear rate more than 5W instrument and equipment thermal vacuum test temperature variation≤5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment≤3 DEG C, be considered as subsequent satellites state consistent with starting star, then the minimum equilibrium temperature of subsequent satellites instrument and equipment, the highest equilibrium temperature are equally also within the scope of designing requirement, judge that the thermal design of follow-up star is qualified; If actual hear rate comparing intensity of variation were no more than ± 10%, but in thermal vacuum test in worst hot case temperature and the comparison of worst cold case temperature data, hear rate more than 5W instrument and equipment thermal vacuum test temperature variation > 5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment thermal vacuum test temperature variation > 3 DEG C, need reinstall by designing requirement the equipment of transfiniting, until the scope that the instrument and equipment satisfied temperature change after installing requires;
If in follow-up star and starting star, the actual hear rate comparing intensity of variation of all same instruments equipment exceeded ± 10%, carry out analyzing with improvement in the 3rd step and the hot realistic model after optimizing and thermal design improvement is carried out to instrument and equipment, until the instrument and equipment after improvement thermal design meets the requirement of actual hear rate comparing intensity of variation super only ± 10%, then thermal design is improved to thermal vacuum test worst hot case temperature and the comparison of worst cold case temperature data of rear instrument and equipment, hear rate more than 5W instrument and equipment thermal vacuum test temperature variation≤5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment thermal vacuum test temperature variation≤3 DEG C, be considered as the minimum equilibrium temperature after subsequent satellites instrument and equipment improvement thermal design, the highest equilibrium temperature is equally also within the scope of designing requirement, judge to improve thermal design qualified, if, hear rate more than 5W instrument and equipment thermal vacuum test temperature variation > 5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment thermal vacuum test temperature variation > 3 DEG C, judge that the installation of instrument and equipment does not meet designing requirement, need reinstall by designing requirement the equipment of transfiniting, the instrument and equipment after installation meets the thermal vacuum test temperature variation requirement after thermal design improvement,
5th step: when all appts equipment in whole star be determined qualified after, the thermal design being considered as subsequent satellites is qualified; Heat balance test checking is cancelled with platform subsequent satellites.
In described second step, worst hot case temperature refers to that satellite runs the maximum temperature that may run at the outer space, and worst cold case temperature refers to that satellite runs the minimum temperature that may run at the outer space;
The process of establishing of the satellite finite element thermal analysis realistic model in described 3rd step is: set up finite element model by the structure of satellite, the layout of instrument and equipment, the nominal hear rate data of configure instrument equipment, by the structure of satellite, the surface state of instrument and equipment, thermophysical property is set, the contact heat transfer coefficient of instrument and equipment and satellite structure is set, thus sets up satellite finite element thermal analysis realistic model;
Thermal design in described 4th step improves the area of dissipation referring to and expand or reduce instrument and equipment installation region, strengthens or weaken the heat conductivility between instrument and equipment and satellite structure surface of contact.
Beneficial effect:
1, through the development of multiple satellite, in-orbit flight validation, after adopting of the present invention batch to produce Satellite Thermal Design verification method, only the starting satellite of each platform carries out heat balance test, subsequent satellites heat balance test is all cancelled, thermal design evaluation method is reasonable, satellite in-orbit flight temperature meets re-set target, and meets satellite general requirement.
2, the present invention effectively optimizes and has simplified whole star development flow process, saves whole star heat test funds, substantially reduces the lead time of satellite.
Embodiment
The invention provides a kind of batch and produce Satellite Thermal Design verification method, its verification step is as follows:
The first step: whole star heat balance test is carried out to first satellite (being called for short starting star) of same Platform Satellite, test simulation satellite is high temperature and worst cold case under Live Flying state in-orbit, the thermal design of satellite is verified, can verifying satellites thermal design ensure satellite working flight temperature requirement in-orbit, obtains the minimum equilibrium temperature of inside satellite every platform instrument and equipment under designing technique state and the highest equilibrium temperature; If the minimum equilibrium temperature of inside satellite every platform instrument and equipment, the highest equilibrium temperature all within the scope of designing requirement, are then considered as starting star thermal design qualified, and perform second step; If minimum equilibrium temperature or the highest equilibrium temperature of inside satellite every platform instrument and equipment exceed designing requirement scope, be then considered as thermal design defective, need thermal design be improved until qualified rear execution second step;
Second step: to add up in starting star instruments and equipment checking test gained actual hear rate data and starting star whole star thermal vacuum test Instrumental equipment at worst hot case temperature and worst cold case temperature data, as subsequent satellites metewand;
3rd step: on satellite finite element thermal analysis realistic model basis, the starting star whole star heat balance test temperature data utilizing the first step to obtain, to the equipment in hot simulation analysis model, contact heat transfer coefficient value is installed improve and optimize, realistic model is made to meet the actual techniques state of satellite, for subsequent thermal design qualification determination;
4th step: subsequent satellites thermal design qualification determination criterion: the actual hear rate data of instruments and equipment checking test gained in statistics subsequent satellites, and the actual hear rate data of the instrument and equipment corresponding with in star starting described in second step are compared; Add up each instrument and equipment of subsequent satellites worst hot case temperature and worst cold case temperature data in thermal vacuum test again, and the worst hot case temperature of the instrument and equipment corresponding with in star starting described in second step and worst cold case temperature data are compared; If follow-up star were no more than with the actual hear rate comparing intensity of variation of corresponding instrument and equipments all in starting star ± 10%, and hear rate more than 5W instrument and equipment thermal vacuum test temperature variation≤5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment≤3 DEG C, be considered as subsequent satellites state consistent with starting star, then the minimum equilibrium temperature of subsequent satellites instrument and equipment, the highest equilibrium temperature are equally also within the scope of designing requirement, judge that the thermal design of follow-up star is qualified; If actual hear rate comparing intensity of variation were no more than ± 10%, but in thermal vacuum test in worst hot case temperature and the comparison of worst cold case temperature data, hear rate more than 5W instrument and equipment thermal vacuum test temperature variation > 5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment thermal vacuum test temperature variation > 3 DEG C, need reinstall by designing requirement the equipment of transfiniting, until the scope that the instrument and equipment satisfied temperature change after installing requires;
If in follow-up star and starting star, the actual hear rate comparing intensity of variation of all same instruments equipment exceeded ± 10%, carry out analyzing with improvement in the 3rd step and the hot realistic model after optimizing and thermal design improvement is carried out to instrument and equipment, until the instrument and equipment after improvement thermal design meets the requirement of actual hear rate comparing intensity of variation super only ± 10%, then thermal design is improved to thermal vacuum test worst hot case temperature and the comparison of worst cold case temperature data of rear instrument and equipment, hear rate more than 5W instrument and equipment thermal vacuum test temperature variation≤5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment thermal vacuum test temperature variation≤3 DEG C, be considered as the minimum equilibrium temperature after subsequent satellites instrument and equipment improvement thermal design, the highest equilibrium temperature is equally also within the scope of designing requirement, judge to improve thermal design qualified, if, hear rate more than 5W instrument and equipment thermal vacuum test temperature variation > 5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment thermal vacuum test temperature variation > 3 DEG C, judge that the installation of instrument and equipment does not meet designing requirement, need reinstall by designing requirement the equipment of transfiniting, the instrument and equipment after installation meets the thermal vacuum test temperature variation requirement after thermal design improvement,
5th step: when all appts equipment in whole star be determined qualified after, the thermal design being considered as subsequent satellites is qualified; Heat balance test checking is cancelled with platform subsequent satellites.
In described second step, worst hot case temperature refers to that satellite runs the maximum temperature that may run at the outer space, and worst cold case temperature refers to that satellite runs the minimum temperature that may run at the outer space;
The process of establishing of the satellite finite element thermal analysis realistic model in described 3rd step is: set up finite element model by the structure of satellite, the layout of instrument and equipment, the nominal hear rate data of configure instrument equipment, by the structure of satellite, the surface state of instrument and equipment, thermophysical property is set, the contact heat transfer coefficient of instrument and equipment and satellite structure is set, thus sets up satellite finite element thermal analysis realistic model;
Thermal design in described 4th step improves the area of dissipation referring to and expand or reduce instrument and equipment installation region, strengthens or weaken the heat conductivility between instrument and equipment and satellite structure surface of contact.
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (1)
1. batch product Satellite Thermal Design verification method, is characterized in that verification step is as follows:
The first step: whole star heat balance test is carried out to first satellite of same Platform Satellite, this star is called for short starting star, test simulation satellite is high temperature and worst cold case under Live Flying state in-orbit, the thermal design of satellite is verified, can verifying satellites thermal design ensure satellite working flight temperature requirement in-orbit, obtains the minimum equilibrium temperature of inside satellite every platform instrument and equipment under designing technique state and the highest equilibrium temperature; If the minimum equilibrium temperature of inside satellite every platform instrument and equipment, the highest equilibrium temperature all within the scope of designing requirement, are then considered as starting star thermal design qualified, and perform second step; If minimum equilibrium temperature or the highest equilibrium temperature of inside satellite every platform instrument and equipment exceed designing requirement scope, be then considered as thermal design defective, need thermal design be improved until qualified rear execution second step;
Second step: to add up in starting star instruments and equipment checking test gained actual hear rate data and starting star whole star thermal vacuum test Instrumental equipment at worst hot case temperature and worst cold case temperature data, as subsequent satellites metewand;
3rd step: on satellite finite element thermal analysis realistic model basis, the starting star whole star heat balance test temperature data utilizing the first step to obtain, to the equipment in hot simulation analysis model, contact heat transfer coefficient value is installed improve and optimize, realistic model is made to meet the actual techniques state of satellite, for subsequent thermal design qualification determination;
4th step: subsequent satellites thermal design qualification determination criterion: the actual hear rate data of instruments and equipment checking test gained in statistics subsequent satellites, and the actual hear rate data of the instrument and equipment corresponding with in star starting described in second step are compared; Add up each instrument and equipment of subsequent satellites worst hot case temperature and worst cold case temperature data in thermal vacuum test again, and the worst hot case temperature of the instrument and equipment corresponding with in star starting described in second step and worst cold case temperature data are compared; If follow-up star were no more than with the actual hear rate comparing intensity of variation of corresponding instrument and equipments all in starting star ± 10%, and hear rate more than 5W instrument and equipment thermal vacuum test temperature variation≤5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment thermal vacuum test temperature variation≤3 DEG C, be considered as subsequent satellites state consistent with starting star, then the minimum equilibrium temperature of subsequent satellites instrument and equipment, the highest equilibrium temperature are equally also within the scope of designing requirement, judge that the thermal design of follow-up star is qualified; If actual hear rate comparing intensity of variation were no more than ± 10%, but in thermal vacuum test in worst hot case temperature and the comparison of worst cold case temperature data, hear rate more than 5W instrument and equipment thermal vacuum test temperature variation > 5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment thermal vacuum test temperature variation > 3 DEG C, need reinstall by designing requirement the equipment of transfiniting, until the scope that the instrument and equipment satisfied temperature change after installing requires;
If in follow-up star and starting star, the actual hear rate comparing intensity of variation of all same instruments equipment exceeded ± 10%, carry out analyzing with improvement in the 3rd step and the hot realistic model after optimizing and instrument and equipment is carried out to thermal design and improve the area of dissipation namely expanding or reduce instrument and equipment installation region, the heat conductivility strengthening or weaken between instrument and equipment and satellite structure surface of contact, until the instrument and equipment after improvement thermal design meets the requirement of actual hear rate comparing intensity of variation super only ± 10%, then thermal design is improved to thermal vacuum test worst hot case temperature and the comparison of worst cold case temperature data of rear instrument and equipment, hear rate more than 5W instrument and equipment thermal vacuum test temperature variation≤5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment thermal vacuum test temperature variation≤3 DEG C, be considered as the minimum equilibrium temperature after subsequent satellites instrument and equipment improvement thermal design, the highest equilibrium temperature is equally also within the scope of designing requirement, judge to improve thermal design qualified, if, hear rate more than 5W instrument and equipment thermal vacuum test temperature variation > 5 DEG C or hear rate is less than 5W and without hear rate instrument and equipment thermal vacuum test temperature variation > 3 DEG C, judge that the installation of instrument and equipment does not meet designing requirement, need reinstall by designing requirement the equipment of transfiniting, the instrument and equipment after installation meets the thermal vacuum test temperature variation requirement after thermal design improvement,
5th step: when all appts equipment in whole star be determined qualified after, the thermal design being considered as subsequent satellites is qualified; Heat balance test checking is cancelled with platform subsequent satellites.
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| CN106275496B (en) * | 2016-08-12 | 2019-03-29 | 上海卫星工程研究所 | A kind of heat balance test method of the more stars of a tank |
| CN109018455A (en) * | 2018-06-20 | 2018-12-18 | 上海卫星工程研究所 | Spacecraft heat distortion test method |
| CN112946404B (en) * | 2018-08-20 | 2024-01-26 | 上海微小卫星工程中心 | Comprehensive test method for batch production satellite |
| CN110006639A (en) * | 2019-03-29 | 2019-07-12 | 北京空间飞行器总体设计部 | A method of heat test is carried out using heater substitution thermal simulation part |
| CN110171584B (en) * | 2019-06-19 | 2020-09-15 | 上海微小卫星工程中心 | Vacuum thermal test method for mass production of satellite constellation system |
| CN111274686B (en) * | 2020-01-15 | 2022-08-19 | 哈尔滨工业大学 | Batch microsatellite test method and device |
| 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 |
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| CN101769825A (en) * | 2008-12-29 | 2010-07-07 | 北京卫星环境工程研究所 | Tracking temperature control device for spacecraft thermal vacuum test |
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