In order to solve the problem that the CubeSat solar wing cannot be verified by multiple ground unlocking tests under strict dimensional constraints， a lightweight and high stiffness solar wing with repeatable electromagnetic unlocking mechanism is proposed. Firstly， a micro hinged deployment mechanism with the functions of deployment， locking and in-position indication is proposed. Secondly， the proposed electromagnet unlocking mechanism solves the problem that the compression release device cannot be unlocked repeatedly. Meanwhile， it has the advantages of low impact， no pollution and rapid response. Finally， the sensitivity analysis and optimization are performed after the dimensional configuration and auxiliary support layout of the solar wing. The simulation results indicate that the weight of the solar wing is reduced by 20%， and the fundamental frequency in the unfolded state is raised by 16%， which meet the requirements of light weight and high stiffness. The ground qualification level vibration， shock response spectrum， thermal vacuum test and on-orbit flight verification of the BY-03 satellite are carried out， which show this solar wing meets the application requirements. This concept can be used as a reference for design and development of CubaSat solar wing.