| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 8056938 | Acta Astronautica | 2014 | 5 Pages |
Abstract
Minimum-mass propulsion specifications using a H2O2/kerosene bipropellant rocket system for a small lunar lander were derived. A multivariable optimization was conducted with propulsion specifications and propellant consumptions obtained by solving optimal control problems for a lunar soft landing. In this paper, the optimal specifications, trajectory, and mass budget are presented.
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Authors
Yongjun Moon, Sejin Kwon,