Nowadays, many space missions require highly accurate pointing for Earth observation or cosmic vision purposes. However, the vibration environment from a spacecraft's structure and reaction wheels can cause disturbances in its line-of-sight stability and severely impact image quality. Additionally, these effects are not known precisely due to limitations in ground testing, and this uncertainty leads to significant challenges in control. This thesis tackles these problems by creating a control design and verification framework. Modern scientific literature explores three solutions: high-fidelity nonlinear modelling, advanced control design methods, and optimized verification campaigns. Respectively, they provide a reliable testing environment, directly handle structural dynamics, and guarantee system stability. While the three approaches are usually studied separately, the thesis proposes a novel combination using a payload isolation platform. The synergy of the framework offers a robust solution for precise pointing in flexible spacecraft and enables further mass reductions in the future of space exploration.