星载大型可展开天线热分析技术研究
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摘要
本文结合某星载大型可展开天线的设计工作,吸取了国内外星载天线热控设计的最新研究成果,运用CAD/CAE、热——结构集成分析等先进手段,深入探讨了星载可展开天线的热分析技术,提出了解决星载可展开天线热分析问题的热优化设计方法。本文阐述的主要内容包括:
1.对国内外星载天线热控技术(包括热设计、热分析与热试验)的研究现状与发展趋势进行了概述,总结了星载天线的一般热设计原则和步骤,给出了星载天线热分析流程的框架结构,提出了研究大型可展开天线的一体化热—结构分析方法。
2.对于复杂天线结构,为提高计算地球反照辐射和地球红外辐射外热流的精度和速度,提出了采用蒙特卡洛法计算星载天线表面轨道外热流的原理和方法。
3.针对天线的复杂桁架结构对于不同热源的遮挡问题,提出了采用光线投影算法计算星载天线太阳直接辐射的外热流的方法,推导了天线桁架杆件之间和天线面之间的遮挡系数计算公式。
4.针对某大型可展开天线的具体结构特点,建立了热分析有限单元方案并设置了天线在轨计算工况。开展了周边桁架式星载可展开天线的在轨瞬态温度场的计算,首次从全轨道角度对不同工况下天线温度场进行了全面分析计算,热分析结果对天线的热控设计具有十分现实的指导意义。
5.采用热—结构一体化的分析方法,计算出组成可展开天线主要结构——桁架杆单元由于温度引起的等效结点热载荷,并建立了相应的热弹性有限元方程。求解了周边桁架式星载可展开天线的热变形和热应力,并首次全面分析了在轨位置、不同热物性参数、天线约束位置对天线型面均方根误差的影响,给出了能达到天线工程设计要求的热控方案。
6.对影响星载天线温度水平及梯度的诸多因素进行了全面分析,利用TMG和正交试验法安排的试验方案进行了多种试验仿真分析,并在此建立了星载天线在轨热—结构耦合优化设计的数学模型;采用改进的基本遗传算法+模拟退火算法组成的混合遗传算法对星载天线的热参数进行了优化设计。
7.研究了在轨热环境对地面网面调整结果的影响,首次提出了基于在轨热环境下结合距离权因子与遗传算法进行周边桁架网面优化调整的方法。结合大型可展开天线编程进行了基于在轨热环境下网面优化调整仿真。
本文所完成的热分析技术的研究能够为星载天线的热设计提供更科学的依据,可大大提高我国星载天线热分析的水平,以此为基础的热优化设计可以有效的减少试验费用。希望通过本文的研究工作使我国的星载天线的热分析技术更趋于系统、完善,从而提高星载天线的电性能指标。
In this paper, for designing a large deployable antenna, the thermal analysis technology is deeply studied based on CAD/CAE, thermal-structure integrative analysis and latest researching results in the word. Research methods of thermal optimal design are used to settle the problem of thermal analysis for the deployable antenna. The paper includes the following contents:
1. Thermal control technology for space-borne antenna (including thermal design, thermal analysis and thermal test) to home and abroad studying current situation and the developing trend have carried out a summary. It has summed up the designing principle and the step, given the framed structure of thermal analysis technological process with space-borne antenna. The methods of thermal-structure integrative analysis on studying space-borne antenna are brought forward.
2. Specifically for complicated antenna structure, in order to improve accuracy and speed for calculating outer thermal flux of the earth albedo and emitted radiation, it has suggested that the approach adopt the Monte-Carlo method to calculating outer thermal flux of the space-borne antenna.
3. To complicated antenna's truss structure for shading problem of the different heat sources, the method adopt the light projection algorithm to calculate outer thermal flux with direct sun radiation is brought forward. It deduce the formula to calculate shading factors between truss rods or antenna faces.
4. Towards structure characters of the large deployable antenna, it establish the finite element of thermal analysis scheme and propose the calculating on-orbit working condition. The transient temperature on-orbit is calculated for the peripheral truss deployable antenna on satellite. For the first time, the antenna's temperature distribution witch is in different work area in the full orbit has carried out completely under working condition. The thermal analysis result has practical significance to the antenna's thermal control.
5. Using the Thermal-Structure integrative analysis method, it can figure out thermal loads of equivalent node resulted from the temperature of truss pole element which is the primary structure of the deployable antenna, and it also construct the relevant finite element equation of thermal elasticity. The thermal distortion and thermal stress of the peripheral truss deployable antenna on satellite have been solved, and completely analysis, for the first time, the effect to RMS of the reflector surface that antenna with different location on orbit, thermal physics parameter, constraint position. and then given out the thermal control scheme that satisfy the projects design required.
6. It completely analysis many factors which effected the temperature level, temperature grads of antenna on satellites, Using the TMG and orthogonal test as test scheme, we do many simulation analysis. Based on these, It establish the thermal-structure coupling mathematics module of antenna on satellite for optimize design; adopting the mixed genetic algorithms which is composed of the improved base genetic algorithms and simulated annealing, it has manipulate the optimized design of the antenna thermal parameters.
7. It has studied the influence of thermal environment on-orbit to the net surface adjustment results on the ground. It proposed the method of adjustment and optimization of the peripheral truss net surface integrating distance weighted factor and the genetic algorithm based on-orbit thermal environment for the first time, Optimization adjustment simulation of the net surface has been carried based on-orbit thermal environment for the large deployable antenna.
The research of thermal analysis technology in this article would provide more scientific foundation for thermal design of antenna on satellite, it would greatly improved thermal design level for satellite antenna of our country, the thermal optimize design which were based on those would effective reduce the costs of test. we hope the thermal analysis technology for antenna on satellite of our country will be more systematically, perfectly through the research of this article, consequently improve the electronic performance of antenna.
1.对国内外星载天线热控技术(包括热设计、热分析与热试验)的研究现状与发展趋势进行了概述,总结了星载天线的一般热设计原则和步骤,给出了星载天线热分析流程的框架结构,提出了研究大型可展开天线的一体化热—结构分析方法。
2.对于复杂天线结构,为提高计算地球反照辐射和地球红外辐射外热流的精度和速度,提出了采用蒙特卡洛法计算星载天线表面轨道外热流的原理和方法。
3.针对天线的复杂桁架结构对于不同热源的遮挡问题,提出了采用光线投影算法计算星载天线太阳直接辐射的外热流的方法,推导了天线桁架杆件之间和天线面之间的遮挡系数计算公式。
4.针对某大型可展开天线的具体结构特点,建立了热分析有限单元方案并设置了天线在轨计算工况。开展了周边桁架式星载可展开天线的在轨瞬态温度场的计算,首次从全轨道角度对不同工况下天线温度场进行了全面分析计算,热分析结果对天线的热控设计具有十分现实的指导意义。
5.采用热—结构一体化的分析方法,计算出组成可展开天线主要结构——桁架杆单元由于温度引起的等效结点热载荷,并建立了相应的热弹性有限元方程。求解了周边桁架式星载可展开天线的热变形和热应力,并首次全面分析了在轨位置、不同热物性参数、天线约束位置对天线型面均方根误差的影响,给出了能达到天线工程设计要求的热控方案。
6.对影响星载天线温度水平及梯度的诸多因素进行了全面分析,利用TMG和正交试验法安排的试验方案进行了多种试验仿真分析,并在此建立了星载天线在轨热—结构耦合优化设计的数学模型;采用改进的基本遗传算法+模拟退火算法组成的混合遗传算法对星载天线的热参数进行了优化设计。
7.研究了在轨热环境对地面网面调整结果的影响,首次提出了基于在轨热环境下结合距离权因子与遗传算法进行周边桁架网面优化调整的方法。结合大型可展开天线编程进行了基于在轨热环境下网面优化调整仿真。
本文所完成的热分析技术的研究能够为星载天线的热设计提供更科学的依据,可大大提高我国星载天线热分析的水平,以此为基础的热优化设计可以有效的减少试验费用。希望通过本文的研究工作使我国的星载天线的热分析技术更趋于系统、完善,从而提高星载天线的电性能指标。
In this paper, for designing a large deployable antenna, the thermal analysis technology is deeply studied based on CAD/CAE, thermal-structure integrative analysis and latest researching results in the word. Research methods of thermal optimal design are used to settle the problem of thermal analysis for the deployable antenna. The paper includes the following contents:
1. Thermal control technology for space-borne antenna (including thermal design, thermal analysis and thermal test) to home and abroad studying current situation and the developing trend have carried out a summary. It has summed up the designing principle and the step, given the framed structure of thermal analysis technological process with space-borne antenna. The methods of thermal-structure integrative analysis on studying space-borne antenna are brought forward.
2. Specifically for complicated antenna structure, in order to improve accuracy and speed for calculating outer thermal flux of the earth albedo and emitted radiation, it has suggested that the approach adopt the Monte-Carlo method to calculating outer thermal flux of the space-borne antenna.
3. To complicated antenna's truss structure for shading problem of the different heat sources, the method adopt the light projection algorithm to calculate outer thermal flux with direct sun radiation is brought forward. It deduce the formula to calculate shading factors between truss rods or antenna faces.
4. Towards structure characters of the large deployable antenna, it establish the finite element of thermal analysis scheme and propose the calculating on-orbit working condition. The transient temperature on-orbit is calculated for the peripheral truss deployable antenna on satellite. For the first time, the antenna's temperature distribution witch is in different work area in the full orbit has carried out completely under working condition. The thermal analysis result has practical significance to the antenna's thermal control.
5. Using the Thermal-Structure integrative analysis method, it can figure out thermal loads of equivalent node resulted from the temperature of truss pole element which is the primary structure of the deployable antenna, and it also construct the relevant finite element equation of thermal elasticity. The thermal distortion and thermal stress of the peripheral truss deployable antenna on satellite have been solved, and completely analysis, for the first time, the effect to RMS of the reflector surface that antenna with different location on orbit, thermal physics parameter, constraint position. and then given out the thermal control scheme that satisfy the projects design required.
6. It completely analysis many factors which effected the temperature level, temperature grads of antenna on satellites, Using the TMG and orthogonal test as test scheme, we do many simulation analysis. Based on these, It establish the thermal-structure coupling mathematics module of antenna on satellite for optimize design; adopting the mixed genetic algorithms which is composed of the improved base genetic algorithms and simulated annealing, it has manipulate the optimized design of the antenna thermal parameters.
7. It has studied the influence of thermal environment on-orbit to the net surface adjustment results on the ground. It proposed the method of adjustment and optimization of the peripheral truss net surface integrating distance weighted factor and the genetic algorithm based on-orbit thermal environment for the first time, Optimization adjustment simulation of the net surface has been carried based on-orbit thermal environment for the large deployable antenna.
The research of thermal analysis technology in this article would provide more scientific foundation for thermal design of antenna on satellite, it would greatly improved thermal design level for satellite antenna of our country, the thermal optimize design which were based on those would effective reduce the costs of test. we hope the thermal analysis technology for antenna on satellite of our country will be more systematically, perfectly through the research of this article, consequently improve the electronic performance of antenna.
引文
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