Abstract
The results of a Pluto landing analysis study for a fast, hyperbolic approach trajectory are presented by assuming the use of a novel entry, descent, and landing system called an enveloping aerodynamic decelerator. A landing site uncertainty analysis is performed for an 11 September 2040 arrival by means of a Monte Carlo simulation to map key trajectory, aerodynamic, system, and atmosphere uncertainties to landing zone errors. The estimated 3 landing error ellipse is about 430 by 190 km. The band of feasible landing sites is between 35°N and 10°S latitude on the surface of Pluto.
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