载人月球车柔性太阳翼设计与分析

Design and Analysis of Flexible Solar Array for Manned Lunar Rover

为满足载人月球车关于太阳翼的高刚度、可重复收展和轻量化的性能要求,在国内外星球车太阳翼、柔性太阳翼研究的基础上,提出了一种基于连杆机构的柔性太阳翼展开机构总体方案,根据能量守恒原理对太阳翼进行了展开运动学分析。将太阳翼结构简化为张拉索-梁模型,建立了柔性阵面和太阳翼的结构动力学分析模型,基于刚度需求对太阳翼结构进行轻量化优化设计,并通过ABAQUS有限元模型验证了结构优化设计的可行性和合理性。结果表明:太阳翼在涡卷弹簧驱动下展开到位时存在一定的冲击,但是对阵面影响较小。该张拉膜结构等效结构动力学模型可用于柔性太阳翼结构的快速迭代和优化设计,并实现柔性太阳翼支撑结构刚度和阵面张力的高效匹配。

This paper analyzes the functional and technical requirements of future manned lunar ex⁃ploration missions.To meet the requirements of high stiffness,scalability and lightweight,a new type of flexible solar array unfolded by a linkage mechanism was proposed on the basis of the re⁃search and development of the existing Mars and Lunar Rovers and flexible solar arrays.The unfol⁃ding kinematics were modeled and analyzed according to the principle of energy conservation.Then,the solar array was simplified to a tensile cable beam model,and the structural dynamics of the blan⁃ket and the array were modeled analytically.According to the stiffness requirement,the lightweight optimization design of the array was carried out and verified by ABAQUS software.The results show that the solar array generates a certain impact when it is unfolded into place driven by the vortex spring,but the impact on the array is negligible;the equivalent structural dynamics model of the tensioned membrane structure proposed in this paper can be used for the rapid iteration and optimi⁃zation design of the flexible solar cell array structure to achieve the effective matching of the stiffness of the support structure and the tension of the blanket.