In order to fulfill the attitude control mission of micro flight vehicle delivered from a certain kind of ballistic missile, a fast attitude maneuver control approach based on the GPM (Gauss pseudospectral method) was proposed. Firstly, the accurate attitude control model was established and the coupling torque term of the reaction wheels was taken into account. Secondly, the GPM was adopted to obtain the optimal attitude trajectories. Moreover, a quasisliding mode controller was designed to track the optimal trajectories. Numerical simulation results demonstrate the optimality of the attitude maneuver trajectories obtained by using the GPM， the good performances of the quasisliding mode controller in tracking the optimal trajectories, and the good effect in rejecting the external disturbance torque.