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- W1978498520 abstract "The problem of transferring a rocket vehicle from a given circular orbit to a larger coplanar circular orbit in minimum time, using a constant low-thrust rocket engine, is considered. Parameters are chosen to correspond to a transfer from the earth's orbit in heliocentric space to the orbit of Mars. A path satisfying the first order necessary conditions of variational calculus is shown to be locally minimizing by application of a set of second order conditions. A physical explanation is offered to justify the retrothrust period occurring during the flight. A neighboring optimum feedback control law, based on estimated time-to-go, is applied to this problem. State variable and terminal constraint feedback gains are calculated while one of the second order conditions, involving the backward integration of a matrix Riccati equation, is being tested." @default.
- W1978498520 created "2016-06-24" @default.
- W1978498520 creator A5050879841 @default.
- W1978498520 date "1972-08-16" @default.
- W1978498520 modified "2023-09-27" @default.
- W1978498520 title "Perturbation guidance for minimum time flight paths of spacecraft" @default.
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- W1978498520 doi "https://doi.org/10.2514/6.1972-915" @default.
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