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An optimal guidance method for the reentry maneuverable spacecraft

An optimal guidance method using the range as an independent variable for the reentry maneuverable spacecraft is presented in this paper. Firstly, the aerodynamic coefficients are estimated by using the strong tracking filter (STF). Then, the linear deviation equations are formulated by linearising the original nonlinear equations of motion around the nominal trajectory. Finally, the optimal linear regulator theory is used to design the linear state feedback control law and the simulation results for a conceptual RLV are provided