摘要：AbstractThis paper discusses the design of controller using ‘Eigenstructure Assignment Method’ which is to be used in the critical flight regime of a typical Reusable Launch Vehicle (RLV). In this critical flight regime, there is sudden increase in dynamic pressure causing increased coupling between yaw and roll dynamics. Two controllers were designed for this purpose. First with full output feedback and second with constrained output feedback. The controller with full output feedback was found to reduce the coupling and also provide good time response as well as stability margins. It has shown good robustness under plant perturbations.
