摘要
针对卫星碳纤维复合材料–铝蜂窝夹层结构因热变形而导致星敏感器基准面偏转的问题,文章基于ABAQUS软件,采用映射场方法施加稳态温度进行热–结构直接耦合仿真,并结合惯性释放与几何中心平移方法,实现温度–应力场同步求解;通过最小二乘平面拟合算法在局部坐标系中计算星敏感器基准面及载荷安装面的偏转角。结果显示:低温工况(ΔT=89.31℃)和高温工况(ΔT=102.26℃)下,最大位移分别为2.153mm和2.725mm;随着低温向高温的变化,星敏感器基准面偏转角由-270.44″增至-386.90″,关键载荷安装面的最大偏转角增大了41.1%。研究表明,非对称热应力与惯性约束驱动倾斜–扭转耦合变形,隔板热阻与界面微裂纹进一步加剧了偏转。该研究为热控设计与姿态测控裕量预留提供了量化依据。
To address the precision attitude control requirements of satellites in complex space thermal environments,this study investigates thermal deflection in carbon fiber reinforced polymer(CFRP)-aluminum honeycomb sandwich structures due to anisotropic thermal expansion coefficients.A thermal-structural direct coupling model was developed in ABAQUS,integrating a steady-state mapped temperature field with inertia relief and geometric center translation to achieve a coupled solution of the temperature and stress fields.In a local coordinate system,the angular deflections of the star tracker reference plane and payload installation surfaces werecalculatedusingtheleast-squaresplane-fittingmethod.Resultsshowthatunderlow-temperature(ΔT=89.31℃)and high-temperature(ΔT=102.26℃)conditions,the maximum displacements reach 2.153 mm and 2.725 mm,respectively,while the angular deflection of the star tracker reference plane increases from-270.44″to-386.90″.The maximum angular deflection of the payload installation surface increases by 41.1%with rising temperature.This study elucidates the tilt-twist coupling mechanism induced by asymmetric thermal stress and inertial constraints,while the thermal resistance of baffles and microcracks along the interface further exacerbate this deflection.The study offers quantitative insights for thermal control design,on-orbit compensation strategies,and deflection margin planning.
作者
阮颖琴
王开浚
张娜娜
吴佰建
郭小明
RUAN Yingqin;WANG Kaijun;ZHANG Nana;WU Baijian;GUO Xiaoming(School of Civil Engineering,Southeast University,Nanjing 211189,China;Shanghai Institute of Satellite Engineering,Shanghai 201109,China)
出处
《航天器环境工程》
2025年第4期420-429,共10页
Spacecraft Environment Engineering
关键词
碳纤维-铝蜂窝夹层结构
热-结构耦合仿真
热变形
偏转
卫星姿态控制
CFRP-aluminum honeycomb sandwich structure
thermo-structural coupled simulation
thermal deformation
deflection
satellite attitude control
