为了提高2.4 m Ku频段球形充气天线的面形精度,开展了天线初始形态结构设计优化。通过建立2.4 m球形充气天线有限元模型,采用Zernike多项式及法向误差计算表面误差的方法对反射面形态进行了优化设计,使其在充气后达到预期的抛物面形状,...为了提高2.4 m Ku频段球形充气天线的面形精度,开展了天线初始形态结构设计优化。通过建立2.4 m球形充气天线有限元模型,采用Zernike多项式及法向误差计算表面误差的方法对反射面形态进行了优化设计,使其在充气后达到预期的抛物面形状,确保了表面误差在0.5 mm以内的要求。仿真结果表明,在400 Pa压差和下半球气压7000 Pa的不同角度工况下,面形精度满足Ku频段表面误差的精度要求。经上述研究,优化设计后的反射面在充气后能够实现较高的面形精度,满足工程应用需求。展开更多
An innovative design method is outlined in this paper for the pointing control mechanism of large space flexible antennas.This method focuses on enhancing the accuracy and stability that are crucial for large spacecra...An innovative design method is outlined in this paper for the pointing control mechanism of large space flexible antennas.This method focuses on enhancing the accuracy and stability that are crucial for large spacecraft applications,such as space solar power stations.Utilizing potential energy function analysis,the dynamics of the antenna are modeled,treating it as an equivalent n-joint robotic arm.This approach simulates the rigid-flexible coupling effect through joint angle manipulations.The proposed HJI(Hamilton-Jacobi-Inequality)sliding mode robust control integrates HJI principle,dissipative system theory,and sliding mode control,offering improved pointing accuracy and robustness.Simulation results underscore the superiority of HJI sliding mode robust control over traditional PD(proportional-derivative)control in initial response,precision,and control smoothness,albeit at the cost of higher control torque requirements.This research underscores the potential of HJI sliding mode robust control in facilitating precise pointing control for future large space structures,enabling efficient space missions and reliable energy transmission.展开更多
基金Sponsored by Strategic Priority Research Program on Space Science,Chinese Academy of Sciences(Grant No.XDA1502030505).
文摘An innovative design method is outlined in this paper for the pointing control mechanism of large space flexible antennas.This method focuses on enhancing the accuracy and stability that are crucial for large spacecraft applications,such as space solar power stations.Utilizing potential energy function analysis,the dynamics of the antenna are modeled,treating it as an equivalent n-joint robotic arm.This approach simulates the rigid-flexible coupling effect through joint angle manipulations.The proposed HJI(Hamilton-Jacobi-Inequality)sliding mode robust control integrates HJI principle,dissipative system theory,and sliding mode control,offering improved pointing accuracy and robustness.Simulation results underscore the superiority of HJI sliding mode robust control over traditional PD(proportional-derivative)control in initial response,precision,and control smoothness,albeit at the cost of higher control torque requirements.This research underscores the potential of HJI sliding mode robust control in facilitating precise pointing control for future large space structures,enabling efficient space missions and reliable energy transmission.
