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In a previous paper, we addressed the problem of choosing constant values of altitude, speed, and angle of attack such that the orbital plane change during hypersonic flight is maximized for a fixed amount of propellant consumption. In the present paper, the restrictions of constant speed and angle of attack are removed. Necessary conditions for solutions to the resulting optimal control problem are derived. Numerical solutions are obtained for several specific cases under the assumption thatdoi:10.2514/3.20715 fatcat:kplnufmgtrehzdyckixzr2fhra