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- W2054871345 abstract "Equations are derived by relating variations in the state of a vehicle at the end of an elliptical transfer to the variations in the state at the start of the transfer. Simplified sets of equations are presented for the more important special cases of transfer orbits. Some of the results are presented in the form of curves tha t are easily applied for estimating quickly the transfer errors for ascent and orbital transfers. These results are applicable in particular for rendezvous conditions, where time in orbit is important." @default.
- W2054871345 created "2016-06-24" @default.
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- W2054871345 date "1962-12-01" @default.
- W2054871345 modified "2023-10-05" @default.
- W2054871345 title "Error Sensitivities in Satellite Ascent and Orbital Transfer" @default.
- W2054871345 doi "https://doi.org/10.2514/8.6408" @default.
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