This study introduces a new optimization-based methodology in linear attitude controller design, specifically for solid launch vehicles during atmospheric ascent phase. A conventional proportional-derivative (PD) feedback structure with dedicated structural filter are employed to stabilize aerodynamic instability and phase-stabilize the structural bending effects. Considering rapidly time-varying nature of launch vehicle states and environments, we devise set of optimization problems to obtain time-scheduled design parameters that satisfies prescribed design criteria by heuristic optimization algorithm. Moreover, the iterative optimization scheme is proposed to resolve the trade-off relationship between the feedback algorithm and the filter. The effectiveness of the proposed methodology is verified by extensive Monte-Carlo sampling based linear analysis and high-fidelity 6-DOF simulations, thereby underlining the proposed method’s capabilities in assisting heuristic design process for engineers or automatically attaining optimal control parameters.