Minimum Acceleration Guidance Law for Spaceplane in Ascent Phase via Exact Linearization

概要

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A new guidance and control system for a spaceplane is presented. The dynamics of the spaceplane has strong nonlinearity, due to which it is difficult to determine the optimal trajectory analytically and to design a stable trajectory tracking system. Therefore, in this study, we attempt to design a guidance and control system using a state-space exact linearization method without any approximation. Then, a minimum acceleration guidance law is derived analytically by solving a two-point boundary-value problem. Lastly, a trajectory control system is designed to track the vehicle with respect to the reference trajectory generated by the guidance system. The numerical simulation results confirm the validity of the linearized model, the optimality of the guidance system and the good tracking property of the developed system.
社団法人日本航空宇宙学会の論文
2005-11-04