Mission Analysis for Landing on Pluto from a Fast, Hyperbolic Trajectory

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 σ 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.