【作者】 张庆；

【导师】 朱敏波；

【作者基本信息】 西安电子科技大学 ， 机械设计及理论， 2007， 硕士

【摘要】 针对星载天线在轨运行时面临的恶劣热循环环境,往往容易导致反射面型面精度难以得到保证的现状,着眼于航天器所主要采用的被动热控技术,本文对星载天线的在轨热性能进行了分析与优化。为得到设计变量,本文对具有一定结构、尺寸的星载天线,在运行轨道及姿态固定的情况下,进行了正交试验,通过改变其材料性质及表面状态来研究影响反射面均方根误差的主要因素,并得出了有益的灵敏度分析结论。随后,以反射器表面热控涂层的发射率、太阳吸收率为设计变量,反射面均方根误差为目标函数,并考虑到设计变量的搜索空间限定,建立了星载天线在轨热性能热-结构耦合优化设计的数学模型。本文进一步基于蜂窝夹层结构的等效板理论,结合I-DEAS内嵌机制,针对一典型星载单块实体标准圆旋转抛物面天线,利用I-DEAS对其天线反射器进行了参数化建模、在轨温度场与热变形计算的自动化设计与实现。在此基础上,对基本遗传算法进行了改进,采用由改进的基本遗传算法+模拟退火算法组成的混合遗传算法,利用Delphi开发了星载天线在轨热性能优化的应用程序,使用著名的Rosenbrock函数对程序进行了验证,并利用该程序,对星载天线在轨热性能进行了初步的优化,还进一步从优化结果出发,分析了目标函数与设计变量之间的收敛关系。更多还原

【Abstract】 As a satellite antenna runs along an orbit, there is always a thermally induced deformation on the surface of reflector due to atrocious thermal circulation environment. This paper made analysis and optimization of its on-orbit thermal performance in passive thermal control way which is used as the main thermal control way in spacecrafts.For getting design variables, suppose satellite antenna is in set structure and shape, runs in set orbit and attitude, carry out orthogonal experiment by changing material properties and surface states to study main factors impacting RMS of reflector and get some useful conclusions about sensitivity analysis. Subsequently set emissivity and solar absorptivity of surface thermal control coating on reflector as design variables, RMS of reflector as object function and searching area limit of design variables as constraints, build the mathematical model of thermal-structure coupling optimization design of on-orbit thermal performance for satellite antenna.Further realize modeling satellite antenna reflector refer to a classic single solid standard round rotating parabolic satellite antenna in parametric mode upon equivlent plane theory of honeycomb interlining structure, calculating its on-orbit temprature and deformation in I-DEAS using program file. Based on it, make improvements to SGA (Simple Genetic Algorithms), develop an application in Delphi for optimization of its on-orbit thermal performance using a new hybrid genetic algorithms which is made up of improved SGA and SA (Simulated Annealing) and test it using the famous Rosenbrock function. Subsequently make preliminary optimization of its on-orbit thermal performance. From the results, make further analysis of convergence relationships between design variables and object function.更多还原