Coupled Shape and Reentry Trajectory Optimization of Entry Vehicle for Lunar Return

Xu Zhong Wu; Sheng Jing Tang; Jie Guo

doi:10.4028/www.scientific.net/AMR.591-593.2624

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 591-593Coupled Shape and Reentry Trajectory Optimization...

Coupled Shape and Reentry Trajectory Optimization of Entry Vehicle for Lunar Return

Abstract:

This paper deals with the reentry trajectory optimization problem for lunar return with consideration of entry vehicle’s fore-body shape. Three performance objectives are applied in this work: cross range, peak heat flux and total heat load. Aerothermodynamic models are based on modified Newtonian impact theory and semi-empirical correlations for convective and radiative stagnation-point heat transfer. A population based evolutionary algorithm has been executed to optimize the multidisciplinary problem. At last the numerical example showed the Pareto frontiers for spherical segment and sphere cone respectively, one of optimal trajectory designs selected from the Pareto frontiers are showed in this paper. The mission requirements are satisfied through the aerothermodynamic balance.

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Periodical:

Advanced Materials Research (Volumes 591-593)

Pages:

2624-2627

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.591-593.2624

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Online since:

November 2012

Authors:

Xu Zhong Wu, Sheng Jing Tang, Jie Guo

Keywords:

Entry Vehicle, Lunar Return, Multi-Objective Optimization (MOP), Trajectory Optimization

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