Optimal Trajectory Design for the Lunar Module in Ascent Stage

doi:10.3780/j.issn.1000-758X.2013.02.009

Abstract

Abstract: To realize the trajectory optimization of the lunar module in ascent stage, the dynamical model of the lunar module was established and nondimensionalized to construct the optimal control-oriented model. Based on Pontryagin's minimal principle and taking the fuel consumption as the optimizing index, the optimal problem was converted into a time free two-point boundary value problem ( TPBVP) . Using one of initial value hypothesizing methods, combined with the forward sweep algorithm, the TPBVP was solved and the optimized trajectory was obtained. Numerical simulation was conducted. The simulation results justify the rapid convergence rate and high reliability of the proposed method.

Key words: Lunar departure trajectory , Trajectory design , Optimal control, Two-point boundary value problem, Lunar module

MA Ke-Mao, CHEN Hai-Peng. Optimal Trajectory Design for the Lunar Module in Ascent Stage[J]. Chinese Space Science and Technology, 2013, 33(2): 54-60.

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URL: https://journal26.magtechjournal.com/kjkxjs/EN/10.3780/j.issn.1000-758X.2013.02.009

https://journal26.magtechjournal.com/kjkxjs/EN/Y2013/V33/I2/54

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Optimal Trajectory Design for the Lunar Module in Ascent Stage

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