【作者】 杨俊；

【导师】 任革学；

【作者基本信息】 清华大学 ， 航空工程（专业学位）， 2013， 硕士

【摘要】 展开机构是太阳翼的主要承力部件，其在轨能否正常将太阳翼从发射时的折叠状态展开至工作时的展开状态直接关系到航天器的能源供给与任务成败。大型航天器，如空间站，多采用柔性原理设计展开机构以支撑大面积太阳翼，典型的有盘绕式、可折叠铰接四边形式展开机构。本文建立了大型盘绕式展开机构的柔性多体动力学模型和两翼电池阵的多刚体模型，研究了整个系统的展收可靠性、参数敏感性，分析了柔性部件应变变化规律。主要工作如下：建立了盘绕式展开机构的刚柔耦合多体动力学模型。采用铁木辛柯梁单元、刚体、约束、接触、单向弹簧力建立了盘绕式展开机构中横纵杆、螺母、导槽、底盘、收藏筒、斜拉索等的计算模型和构件连接关系。其中柔性部件允许在三维空间发生任意大位移、大转动、小应变变形。揭示了传动比与节距是影响机构展收可靠性的敏感物理参数，进而提出改进盘绕式展开机构展收可靠性的四种策略：调整传动比、添加引导槽、增加收藏筒高度、改变节距。仿真表明盘绕式展开机构依靠横梁的交替失稳和纵梁盘绕实现展收，顺利展收的关键在于靠近螺母的接头正常进入导轨，而这主要取决于过渡段的三维空间构型，其主要制约因素是传动比和节距。这里提出的四种策略在调整参数后，仿真中均能改善展收可靠性。分析了展收过程中，横、纵梁的截面应变以及驱动螺母力矩的变化规律。指出纵梁位于过渡区时除受双方向弯矩外，还受正压和扭转载荷作用，为材料选型和结构尺寸优化提供设计依据。揭示了随动和联动模式下展收速度对螺母驱动力矩随的影响规律，指出驱动力矩的大小由展开机构的弹性变形起决定作用，联动式较随动式需更大的外力驱动。建立了电池阵的多刚体模型并进行展开机构与电池阵的联合仿真分析。采用力函数模拟导向绳，揭示了两侧电池阵收展不对称的根源在于展开机构运动过程端部的扭转振动，增大板间铰链的阻尼和刚度有助于电池阵的对称收展。根据过载工况下展开机构的变形进行整体平动、转动的最大过载加速度计算，并分析了平动转动各个方向最大过载加速度不同的原因。更多还原

【Abstract】 The deployment mast is the main load-bearing parts of the solar array, whether itdeploys solar array from folded state to the expanded state is directly related to theenergy supply of the spacecraft and success of mission. Large scale spacecraft such asthe space station often use flexible principles to design mast supporting large scale solararray, the typical sample includes coilable mast, FAST mast. This paper establishesflexible multi-body dynamic model of large coil mast and multi-rigidbody model of thebattery array. The reliability of the entire system during deployment, parametersensitivity and the flexible member strain are studied. The works includes:The dynamic model of coilable mast and solar array are established based on themulti-body dynamic solver Thudynamics, the parameter sensitivity that influence thereliability of coilable mast deployment is revealed. By simplifying the factual physicalrealistic, using Timoshenko beam element, rigid model, constraints, contacts andunidirectional spring force, batten, longeron, canister, diagonal are established. Coilablemast established allows arbitrarily large displacements occurred in three-dimensionalspace, large rotation and small strain deformation. The model of solar array on bothsides is established by using the function analog guy wires. Morever, battery array’sparameter sensitivity is found which cause the asymmetry during movement.Two sensitive parameters drive ratio and bay length are revealed which decide thereliability of deployment, so four solutions: adjusting the transmission ratio, increasingthe height cylinder canister height, adding guide groove, shortening the bay areproposed against the failure of coilable mast deployment, which make the mast deployand coil smoothly.The key of successful expansion and coil of coilable mast is theconnector enter into the guide. By simulating the model the section of longeron andbatten are changed, the principle of coilable mast coil and deployment is more clear: thecoil and deployment of coilable mast achieve by the batten’s buckling instability, theration of longeron and batten’s section should keep at appropriate range, if not, thedeployment and coil will fail.The law of drive torque when base is constrained and base free, axial force act onthe base, the relationship of drive velocity with drive torque are revealed: the key factor affecting axial force is transition arcs, drive torque is decided by the elasticitydeformation of mast in canister, the drive torque when base is constrained is greater thanfree. Then, tensile and shear strain of longeron and batten are extracted for reliabilityanalysis, the dangerous areas of longeron and batten are pointed out, which shows thatthe longeron and batten should be made of material own big proportion limit to meetlarge deformation and strain of coilable mast during movement, such as fiberglass. Thetense of diagonals are extracted which reveal the batten’s buckling.The integral simulation of coilable mast and solar array is completed. By studyingthe asymmetry of solar array indicates that torsion vibration of coilable mast tip is thesource, but the asymmetry can be reduced by adding stiffness and damp of connectorsbetween battery panels. The overload acceleration of transmission and rotation arecomputed and difference of acceleration is analyzed.更多还原