## Optimum Maneuvers of Hypervelocity Vehicles, Volume 1078 |

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altitude distribution approximate solution atmospheric mass density bounded control bounded lift control constant of integration control is bounded cubic equation curve JK defined by Eq differential equation dimensionless drag ratio elliptic integrals end-conditions expression flight path angle flown without inflexion given by Eq given velocity loss Hamiltonian Hence hypervelocity regime inflexion point exists inflexion point occurs initial altitude integrating Eq lift and drag lift coefficient lift to drag lower lift maximizing the final maximum final altitude maximum final velocity maximum lift minimum velocity loss negative initial flight obtained by solving optimal control optimal trajectory optimum flight OPTIMUM MANEUVERS parabolic drag polar positive lift quartic equation range is free singular perturbation siny sinyy slightly constrained range small angle approximation small flight path switching altitude terminal flight path terminal position trajectory is flown type of trajectories V1+ai Variable control velocity ratio zero-lift drag coefficient