小卫星动态传热特性分析与热控设计方法研究
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摘要
小卫星技术以其短研制周期、低成本、低风险的优势，成为当今航天领域研究的热点，随着卫星小型化的发展，传统的热控制技术受到了极大挑战，小卫星的低热惯性势必带来热的不稳定性。在传统卫星热控稳态设计、分析、试验的基础上，对小卫星动态传热机制、瞬态温度分析方法和瞬态试验技术进行研究，将有益于促进小卫星热控技术的发展。本文以此为背景，重点研究了以下内容：
建立小卫星双层集总参数模型，在得到温度时均量解析解基础上，利用傅里叶变换法求解温度波动量解析解，并探讨了解析解与数值解的一致性。类比阻尼振荡系统，应用传递函分析的方法，对表征温度与热流波动量间幅值传递关系的幅值特性和相位传递关系的相位特性变化规律进行了分析。以此为基础提出了小卫星“最佳温度动态范围”热控设计方法。
在某型微小卫星设计轨道高低温工况下,对其被动热控系统进行了设计。根据“最佳温度动态范围”热控设计方法，通过设计参数匹配计算和热控方式设计，得到了符合设计要求的热控设计方案，为该方法的应用提供例证。数值仿真对比研究了符合与两种不符合“最佳温度动态范围”的热控设计，说明其设计方法的正确性。在该方法的指导下提出“适度隔热-周体散热”热控布局设计理念，相对传统“整体隔热-集中散热”热控设计布局，在可靠性和重量上新型布局都有明显优势。
针对稳态标定热流计导致红外加热笼模拟瞬态外热流误差大的问题，采用热流计瞬态标定的方法，并引入瞬态参数识别和控制技术，提高红外加热笼模拟平缓变化外热流的精度，采用开环输出功率调节的方法，来改善热流大幅突升或突降时的热流模拟精度。在某型微小卫星瞬态热平衡试验应用中，改进方法有效的提高了瞬态热流模拟精度。
对某型微小卫星符合与不符合“最佳温度动态范围”的热控设计，进行了瞬态热平衡试验，对比试验结果验证“最佳温度动态范围”热控设计方法的正确性。卫星在轨温度遥测量与热分析和试验结果一致，为本文提出的热控设计方法和新型热控布局设计理念的合理可行,提供了有利证据。
在建立瞬态热分析模型修正参数集合的基础上，以瞬态热平衡试验高温工况数据为标准，采用蒙特卡洛混合方法对某型微小卫星瞬态热分析模型进行分层修正，建立瞬态温度误差评价方法，对修正效果进行评价，并讨论了比热容参数的修正对瞬态热分析模型修正准确性的影响。通过低温、特殊工况下修正前后模型瞬态温度误差比较，以及修正后模型在热真空试验、在轨动态温度预计中的应用效果，说明修正方法的有效性。
本文的研究为小卫星热控设计方法提供新思路，为提高瞬态热分析精度提供了新方法，为小卫星的瞬态热试验提供新的试验手段。
Micro-satellite technology is a focus of research in astronautics domain because of its short leadtime、low cost and low risk. Traditional thermal control technologies received challenge from thedevelopment of miniaturized satellite. Micro-satellite with low thermal inertia must have an instabilitytemperature. Micro-satellite thermal control technology will be benefit from the research about therules of dynamic heat transfer, analysis method of dynamic temperature and the technology ofdynamic experiment. The research content based on that of this article is summarized:
Two-layer model with lumped parameters was built. After the analytic solutions of temperaturemean value was gained, the the analytic solutions of temperature fluaction value was aquired bymeans of Fourier transform (FFT). The uniformity between analytic solution and numerical solutionwas researched. Making an analogy with damping oscillatory system, the rules of amplitudecharacterictics and phase characterictics were researched by means of transfer function in frequencydomain, which standed for transfer relation of amplitude and phase between the heat fluaction andtemperature fluaction. Based on that, The theramal control designing method of “optimum dynamictemperature range” was brought forward.
Under the high and low temperature conditions for designing obit parameters, the passivethermal control system of some micro-satellite was designed. The designing scheme of thermalcontrol system was gained through the computing of designing parameters and designing of thethermal control method, according to thermal control designing method of “optimum dynamictemperature range”, which gived an example for this method. Corresponding and not corresponding to“optimum dynamic temperature range” thermal control design were compared by means of numericalsimulation, the result gave evidence to the validity of designing method. Based on that, The designingidea of new thermal control layout “appropriate heat insulation-heat radiation through circumference”was raised. Maching the traditional thermal control layout “whole heat insulation-heat radiationthrough radiating surface”, new layout was superior on mass and reliability.
The accuracy of infrared heating cage imitating dyramic heat flux was low due to heat flowmeter of steady calibration. Heat flow meter was calibrated by dynamic method, and thediscriminating and controlling of dyramic parameters was used, in order to improve the the accuracyof imitating gently changing dyramic heat flux. The way of outputing power adjusting with open-loopcontrol was used, in order to sovle the accuracy problem when dyramic heat flux changed with a largescope in a moment. The effect of improving method was proved by the result of thermal equilibriumexperiment.
Some micro-satellite’s thermal equilibrium experiment was launched. The rules of dyramictemperatures is compared between corresponding and not corresponding to “optimum dynamictemperature range” thermal control design, it proves that thermal control designing method of“optimum dynamic temperature range” is effective. The telemetering temperature in orbit showed nodifference with the result of numerical simulation and experiment, it gave beneficial evidence to thenew thermal control designing method and new layout designing idea.
Based on buliting the parameter assembling, dynamic thermal analysis model was revisedthrough Montecarlo mixing method layer by layer, in which the high temperature condition data ofdynamic experiment was standard. Dynamic temperature error was seted up and used to evaluate therevising effect. The influence of specific heat capacity to revising effect of dynamic thermal analysismodel was discussed. The revising method’accuracy was proved by comparing the numericalsimulation and experiment data under low temperature and special conditions. The applying effect inthermal vacuum experiment and dynamic temperature evalution in orbit also gave evidence to that.
The research of this article supported a new thought of thermal control designing method formicro-satellite, a new imitating method to dynamic thermal equilibrium experiment, a new referenceto raise the accuracy of analysis.
建立小卫星双层集总参数模型，在得到温度时均量解析解基础上，利用傅里叶变换法求解温度波动量解析解，并探讨了解析解与数值解的一致性。类比阻尼振荡系统，应用传递函分析的方法，对表征温度与热流波动量间幅值传递关系的幅值特性和相位传递关系的相位特性变化规律进行了分析。以此为基础提出了小卫星“最佳温度动态范围”热控设计方法。
在某型微小卫星设计轨道高低温工况下,对其被动热控系统进行了设计。根据“最佳温度动态范围”热控设计方法，通过设计参数匹配计算和热控方式设计，得到了符合设计要求的热控设计方案，为该方法的应用提供例证。数值仿真对比研究了符合与两种不符合“最佳温度动态范围”的热控设计，说明其设计方法的正确性。在该方法的指导下提出“适度隔热-周体散热”热控布局设计理念，相对传统“整体隔热-集中散热”热控设计布局，在可靠性和重量上新型布局都有明显优势。
针对稳态标定热流计导致红外加热笼模拟瞬态外热流误差大的问题，采用热流计瞬态标定的方法，并引入瞬态参数识别和控制技术，提高红外加热笼模拟平缓变化外热流的精度，采用开环输出功率调节的方法，来改善热流大幅突升或突降时的热流模拟精度。在某型微小卫星瞬态热平衡试验应用中，改进方法有效的提高了瞬态热流模拟精度。
对某型微小卫星符合与不符合“最佳温度动态范围”的热控设计，进行了瞬态热平衡试验，对比试验结果验证“最佳温度动态范围”热控设计方法的正确性。卫星在轨温度遥测量与热分析和试验结果一致，为本文提出的热控设计方法和新型热控布局设计理念的合理可行,提供了有利证据。
在建立瞬态热分析模型修正参数集合的基础上，以瞬态热平衡试验高温工况数据为标准，采用蒙特卡洛混合方法对某型微小卫星瞬态热分析模型进行分层修正，建立瞬态温度误差评价方法，对修正效果进行评价，并讨论了比热容参数的修正对瞬态热分析模型修正准确性的影响。通过低温、特殊工况下修正前后模型瞬态温度误差比较，以及修正后模型在热真空试验、在轨动态温度预计中的应用效果，说明修正方法的有效性。
本文的研究为小卫星热控设计方法提供新思路，为提高瞬态热分析精度提供了新方法，为小卫星的瞬态热试验提供新的试验手段。
Micro-satellite technology is a focus of research in astronautics domain because of its short leadtime、low cost and low risk. Traditional thermal control technologies received challenge from thedevelopment of miniaturized satellite. Micro-satellite with low thermal inertia must have an instabilitytemperature. Micro-satellite thermal control technology will be benefit from the research about therules of dynamic heat transfer, analysis method of dynamic temperature and the technology ofdynamic experiment. The research content based on that of this article is summarized:
Two-layer model with lumped parameters was built. After the analytic solutions of temperaturemean value was gained, the the analytic solutions of temperature fluaction value was aquired bymeans of Fourier transform (FFT). The uniformity between analytic solution and numerical solutionwas researched. Making an analogy with damping oscillatory system, the rules of amplitudecharacterictics and phase characterictics were researched by means of transfer function in frequencydomain, which standed for transfer relation of amplitude and phase between the heat fluaction andtemperature fluaction. Based on that, The theramal control designing method of “optimum dynamictemperature range” was brought forward.
Under the high and low temperature conditions for designing obit parameters, the passivethermal control system of some micro-satellite was designed. The designing scheme of thermalcontrol system was gained through the computing of designing parameters and designing of thethermal control method, according to thermal control designing method of “optimum dynamictemperature range”, which gived an example for this method. Corresponding and not corresponding to“optimum dynamic temperature range” thermal control design were compared by means of numericalsimulation, the result gave evidence to the validity of designing method. Based on that, The designingidea of new thermal control layout “appropriate heat insulation-heat radiation through circumference”was raised. Maching the traditional thermal control layout “whole heat insulation-heat radiationthrough radiating surface”, new layout was superior on mass and reliability.
The accuracy of infrared heating cage imitating dyramic heat flux was low due to heat flowmeter of steady calibration. Heat flow meter was calibrated by dynamic method, and thediscriminating and controlling of dyramic parameters was used, in order to improve the the accuracyof imitating gently changing dyramic heat flux. The way of outputing power adjusting with open-loopcontrol was used, in order to sovle the accuracy problem when dyramic heat flux changed with a largescope in a moment. The effect of improving method was proved by the result of thermal equilibriumexperiment.
Some micro-satellite’s thermal equilibrium experiment was launched. The rules of dyramictemperatures is compared between corresponding and not corresponding to “optimum dynamictemperature range” thermal control design, it proves that thermal control designing method of“optimum dynamic temperature range” is effective. The telemetering temperature in orbit showed nodifference with the result of numerical simulation and experiment, it gave beneficial evidence to thenew thermal control designing method and new layout designing idea.
Based on buliting the parameter assembling, dynamic thermal analysis model was revisedthrough Montecarlo mixing method layer by layer, in which the high temperature condition data ofdynamic experiment was standard. Dynamic temperature error was seted up and used to evaluate therevising effect. The influence of specific heat capacity to revising effect of dynamic thermal analysismodel was discussed. The revising method’accuracy was proved by comparing the numericalsimulation and experiment data under low temperature and special conditions. The applying effect inthermal vacuum experiment and dynamic temperature evalution in orbit also gave evidence to that.
The research of this article supported a new thought of thermal control designing method formicro-satellite, a new imitating method to dynamic thermal equilibrium experiment, a new referenceto raise the accuracy of analysis.
引文
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