Fuel/Time Optimal Control of Spacecraft Maneuvers
نویسنده
چکیده
which clearly reduces to the vacuum case de ned by Eq. (3) as ̄ ! 0. The velocity- ight-path-angle pro le is shown in Fig. 2 for a range of drag parameters ̄ . It can be seen that as the effect of air drag increases, the trajectory curves more quickly toward the local vertical.Because the effect of drag is to increasethe effectivethrustweight ratio of the vehicle, the descentmaneuvermay be completed with a lower thrust-inducedacceleration thanwould be required for the vacuum descent case.
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