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- W2316033155 abstract "Two direct optimization methods have been applied to the Aeroassisted Orbital Transfer problem: a direct multiple shooting method, and a direct collocation method. The objective has been to provide optimal t'rajectories for a vehicle with a high lift over drag ratio that minimizes the energy loss during the atmospheric part of an Aeroglide maneuver subject to practical values of heating rate limits. In addition thrusting segments have been inserted within the atmospheric part of the trajectory, and both Aeroglide and Aerocruise trajectories have been evaluated. Here, the objective has been to maximize the achievable inclination change subject t,o limits on heating rate, total heat load, and lift coefficient. The respective parameter optimization procedures have been set up as multi-phase optimization problems. All guidance related parameters along the trajectory together with the deorbiting, boost,, and circularizing impulses have been optimized. The Aeroglide nlaneuver with a free thrusting segrnent has been found to be the most suitable maneuver in order to perform a11 aeroa~sist~ed orbital plane change." @default.
- W2316033155 created "2016-06-24" @default.
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- W2316033155 date "1995-08-07" @default.
- W2316033155 modified "2023-09-23" @default.
- W2316033155 title "Aeroassisted orbital transfer trajectory optimization using direct methods" @default.
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- W2316033155 doi "https://doi.org/10.2514/6.1995-3478" @default.
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