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- W2577657792 abstract "Taking advantage of the aerodynamic force to capture the vehicle from hyperbolic orbit to planetary orbit is a preferable approach because of the lower fuel consumption. This paper aims to research the Mars aerocapture process using the ballistic coefficient as control variable, and the inflatable deceleration device is used to change the ballistic coefficient. Firstly, the corridor is described in detail considering the different ballistic coefficients. Besides, the optimal aerocapture trajectories are analyzed, which show that they have bang-bang control structures. Additionally, the optimal results are showed under the different control structures, and the corresponding performances are presented. Finally, the optimal constant control problem is analyzed through the statistical results with the different initial conditions, and the change rules of the peak heating rate and the ballistic coefficient are given." @default.
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- W2577657792 date "2016-08-01" @default.
- W2577657792 modified "2023-09-26" @default.
- W2577657792 title "Optimal ballistic coefficient control for Mars aerocapture" @default.
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- W2577657792 doi "https://doi.org/10.1109/cgncc.2016.7829129" @default.
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