Aiming at the special requirement of high stiffness in deployed configuration of solar wing for certain small satellites, a single-arm supported solar wing is designed. In the middle of the support arm, tape spring hinge is used to bend and straighten, and spherical joint hinges are used at both ends which connect with solar panel and sidewall of satellite respectively. Between the solar panel and satellite sidewall, a pair of self-adaptive locking root hinges are used to realize the reliable locking function of an auxiliary supported solar wing. The load bearing capacity of the substrate, modal analysis and deployment dynamics analysis of the solar wing are carried out. The results show that the strength margin of the solar wing meets the application requirements，the fundamental frequency of the deployed solar wing is up to 8 Hz, and the deployment process is smooth. The solar wing’s mechanical test, deployment test, lighting test, etc. which are designed to simulate the launching process and in orbit environment of the satellite are carried out, verifying the matching with the mission. In-orbit flight verification shows that the auxiliary-supported solar wing has good function and performance, and meets the special requirements of high stiffness.