@inproceedings{f3c4bac330554daf8fddc5e20aec7b67,
title = "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.",
keywords = "Entry vehicle, Lunar return, Multi-objective optimization, Trajectory optimization",
author = "Wu, {Xu Zhong} and Tang, {Sheng Jing} and Jie Guo",
year = "2012",
doi = "10.4028/www.scientific.net/AMR.591-593.2624",
language = "English",
isbn = "9783037855362",
series = "Advanced Materials Research",
pages = "2624--2627",
booktitle = "Manufacturing Engineering and Automation II",
note = "2012 International Conference on Manufacturing Engineering and Automation, ICMEA 2012 ; Conference date: 16-11-2012 Through 18-11-2012",
}