柔性太阳翼桅杆材料属性对热诱发振动影响分析

发布时间：2017-12-27 15:09

本文关键词：柔性太阳翼桅杆材料属性对热诱发振动影响分析　出处：《南京航空航天大学》2016年硕士论文　论文类型：学位论文

【摘要】：柔性太阳翼多被用于大型空间站的供电系统,工作期间由中央支撑桅杆展开。空间站在轨期间会进出地球阴影区,因此太阳翼系统受到周期性的热辐射,使太阳翼各部件产生变化的温度载荷,引起太阳翼的热变形甚至振动。在太阳翼系统各部件中,支撑桅杆的热变形会带动柔性电池阵面发生振动,为保证柔性电池阵面的正常工作,支撑桅杆的热变形需保持在安全范围内。本文以某空间站的大型柔性太阳翼为研究对象,从太阳翼中央支撑桅杆材料属性入手,研究桅杆在不同的热控涂层和不同的材料下,太阳翼柔性阵面的热诱发振动特性。柔性太阳翼热诱发振动结合了传热学、热弹性力学、动力学等基础理论,使用热-结构非耦合的假设,将太阳翼在轨受热辐射的温度载荷转化为热激励来计算热诱发振动。根据此理论采用顺序耦合的工程计算方法,将温度载荷和热诱发振动分开计算,使用有限元软件NX I-deas计算太阳翼在轨的温度分布,然后使用有限元软件ABAQUS将温度结果作为振动的激励计算太阳翼的振动响应。为对比不同材料属性对太阳翼热诱发振动的影响,将分热控涂层和材料两部分进行对比。桅杆热控材料选择电镀涂层和白漆涂层与未镀层的桅杆进行对比,分析不同涂层对太阳翼柔性阵面热诱发振动的影响。桅杆材料的改变需要对桅杆尺寸进行优化,使用modeFRONTIER优化软件结合ABAQUS软件对铝合金、钛合金和不锈钢三种材料的桅杆按相同的力学性能进行优化,然后对比计算。分析结果可作为太阳翼桅杆设计的依据和评估。
[Abstract]:The flexible solar wing is mostly used for the power supply system of large space stations and is carried out by the central support mast during the operation. During the orbit, the space station will enter the shadow area of the earth. Therefore, the solar wing system is subjected to periodic thermal radiation, so that the components of the solar wing will generate varying temperature loads, causing the thermal deformation and even vibration of the solar wings. In the components of the solar system, the thermal deformation of the supporting mast will drive the vibration of the flexible battery array. In order to ensure the normal operation of the flexible battery surface, the thermal deformation of the mast must be kept in a safe range. Taking the large flexible solar wing of a space station as the research object, starting from the material properties of the central support mast, the thermal induced vibration characteristics of mast under different thermal control coatings and different materials are studied. The thermal induced vibration of flexible solar wings is combined with the basic theories of heat transfer, thermoelasticity, dynamics and so on. Based on the assumption of thermal structure coupling, the thermal load of the solar radiation on the orbit is transformed into thermal excitation to calculate the thermally induced vibration. According to the calculation method of this theory by using sequential coupling engineering, temperature load and heat induced vibration are calculated separately, using the finite element software NX I-deas to calculate the temperature distribution of the solar wing vibration in orbit, and then use the finite element software ABAQUS the temperature as a result of vibration response calculation of the solar wing. In order to compare the effects of different material properties on the heat induced vibration of the solar wing, the two parts of the thermal control coating and the material are compared. The mast thermal control material is selected to compare the electroplating coating and white paint coating with the mast without coating. The influence of different coatings on the thermal induced vibration of the solar wing flexible array is analyzed. Mast material changes need to optimize the mast size. The modeFRONTIER optimization software combined with ABAQUS software is used to optimize the mechanical properties of three kinds of mast, aluminum alloy, titanium alloy and stainless steel, and then the comparative calculation is made. The analysis results can be used as the basis and evaluation of the design of the Sun Wing mast.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V414

【参考文献】