The aim of this study is to develop and test a robust guidance strategy for use on the flyback mission of a winged launch booster. The guidance system employs a numerical Newton-Raphson restoration technique to update steering parameters, coupled with heuristic logic, to improve robustness. The guidance system uses a prediction of the final state of the launch vehicle to close the feedback loop and is therefore called "predictive guidance".M.R. Tetlow, U.M. Schottle, M.E. Evans and G.M. Schneiderhttp://ieeexplore.ieee.org/xpl/freeabs_all.jsp?arnumber=142674
