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10:25 AAS An Algorithm for Trajectory Propagation and Uncertainty Mapping on GPU 13-376 Navid Nakhjiri, University of California, Irvine; Benjamin Villac, University of California, Irvine This paper introduces an efficient parallel numerical integrator for use on graphics processing units (GPUs) to propagate large sets of trajectories. The method is based on modifying Picard iterations to fit the structure of GPUs. This enables the efficient computation of orbital properties on sections of initial conditions of a dynamical system. This is applied to the problem of state uncertainty propagation, where the use of an unscented transformation further allows to optimize the grid of initial conditions to propagate. Thereby, it reduces the overall computational load for such problems. 10:45 AAS Trajectory Evolution Under Laser Photonic Propulsion in The Two-Body 13-377 Problem Fu-Yuen Hsiao, Tamkang University The photonic laser propulsion (PLP) system can produce continuous and constant thrust. This paper reviews its basics and then studies its application in the two-body interplanetary trajectory. This study also derives the equations of motion (EOM) for a spacecraft for the two-body problem, and variation of orbit elements. This study introduces the normalized Gauss' Equations to evaluate the evolution of orbit elements with parameters of mother ship. The evolution of orbit elements also confirms the constraint on the smallest thrust as proposed in the previous study. Numerical simulations are also provided for potential applications to interplanetary travel. 11:05 AAS A Semi-Analytical Approach to Study Resonances Effects on the Orbital 13-378 Motion of Artificial Satellites Rodolpho Moraes, UNIFESP; Sandro da Silva Fernandes, ITA; Jarbas Sampaio, UNESP/FEG; Jorge Formiga, FATEC A semi-analytical approach is proposed to study resonances effects on the orbital motion of artificial satel-lites. Applying successive Mathieu transformations, the order of dynamical system is reduced and the final system is solved by numerical integration. Here simulations are presented showing the variations of the orbital elements of artificial satellites orbiting in the neighbourhood of the 2:1 and of the 15:1 resonance condition. Through the resonance overlap criterion the possible regular and irregular motions are investigated by the time behaviour of orbital elements. The largest Lyapunov exponent is used as tool to verify chaotic motions. 11:25 AAS Accurate and fast orbit propagation with a new complete set of elements 13-491 Giulio Baù, University of Pisa; Claudio Bombardelli, Technical University of Madrid (UPM) We present a new complete set of eight elements to propagate the perturbed two-body problem, which is obtained by applying the following improvements to a very efficient propagator published by Peláez et al. in 2007, and known as dromo: the method generalizes dromo to account for disturbing potentials and it introduces a time element as a dependent Page 74 23 rd AAS / AIAA Space Flight Mechanics Meeting
variable in place of the time. Our scheme shows the best performance when compared with dromo and two efficient elements methods derived from the Kustaanheimo-Stiefel and Sperling-Burdet regularizations for the J2 perturbation of Earth and J2 + Moon's perturbations. 23 rd AAS / AIAA Space Flight Mechanics Meeting Page 75
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Tuesday 12 February Monday 11 Febru
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CONFERENCE CENTER LAYOUT Page 6 23
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RECREATION Swimming 26,000 square-
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This paper applies the transformati
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Feb 11, 2013 Kauai Salon 2 SESSION
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10:25 AAS Modeling of 3D Slosh Moti
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Page 88 and 89: 13-406 Being Lost in Space Yuya Mim
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