This paper presents a Linear Reference Governor (LRG) approach to rate-limited spacecraft attitude maneuvers, addressing the constraints imposed by reaction wheel torque and spacecraft angular velocity. By formulating the problem as an Optimal Control Problem (OCP), the LRG modifies quaternion and angular rate references for a closed-loop system with a state-feedback attitude controller. The method leverages linear approximations, leading to a Quadratic Programming (QP) problem that could be solved onboard VZLU AEROSPACE's upcoming mission. Simulation results demonstrate significant improvements in maneuver duration compared to standard quaternion-based trajectory generation while maintaining adherence to reaction wheel torque constraints. The proposed solution advances spacecraft agility and operational efficiency in challenging mission scenarios.