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Current spacecraft is always equipped with large flexible appendages and payloads, and the high-precision attitude control is therefore a challenging problem. This paper addresses the robust $$H_{\infty }$$ output feedback control to achieve attitude stabilization of a flexible spacecraft. The Lagrange-like model of attitude dynamics is firstly proposed. Then a LMI-based output feedback controller is designed in the presence of disturbances. The stability of closed-loop system is discussed by the Lyapunov method. To deal with the model uncertainties, the convex optimization algorithm is presented. Numerical simulations are finally provided to illustrate the performance of the proposed controllers. [ABSTRACT FROM AUTHOR]