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- W2616351319 startingPage "125" @default.
- W2616351319 abstract "Abstract A method for designing an autonomous orbit controller for spacecraft on elliptical orbits is presented. For the derivation of the linearized differential and difference equations of motion, a non-inertial coordinate frame is utilized which coincides with the one which is applied in the well-known Clohessy-Wiltshire equations for small excentricities. The derivation takes atmospheric drag into account. The resulting time-discrete periodic system is augmented by an integrator state. A control law is obtained by applying linear optimal periodic control. The orbit controller is tested and verified in simulation runs." @default.
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- W2616351319 date "2001-08-01" @default.
- W2616351319 modified "2023-09-23" @default.
- W2616351319 title "Autonomous Orbit Control for Spacecraft on Elliptical Orbits Using a Non-Inertial Coordinate Frame" @default.
- W2616351319 cites W1516952899 @default.
- W2616351319 doi "https://doi.org/10.1016/s1474-6670(17)34073-9" @default.
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