meetings - Space Flight Mechanics Committee

14:30 AAS Approximation of Constraint Low-Thrust Space Trajectories in Three Body
13-251 Dynamic Models using Fourier Series
Ossama Abdelkhalik, Michigan Tech University
Finite Fourier series has been implemented successfully in approximating two-dimensional
continuous-thrust trajectories in two-body dynamic models. In this paper, the Finite Fourier
series is implemented for rapid low-thrust trajectory approximation, in the presence of
thrust acceleration constraints, in the three body dynamic model. This approximation
enables the rapid feasibility assessment of low-thrust trajectories, especially in the presence
of thrust level constraint. The resulting approximated trajectory can be used as initial guess
in optimization techniques.
14:50 AAS A Quaternion-Based Formulation for Electric Orbit-Raising from SSPO to
13-253 GEO
Paola Libraro, Princeton University; Atri Dutta, Princeton University; Jeremy
Kasdin, Princeton University; Edgar Choueiri, Princeton University
15:10 Break
The main focus of this paper is the low-thrust orbit-raising optimization problem for a
geostationary satellite. We investigate the feasibility of injecting the satellite into a Sun-
Synchronous Polar Orbit (SSPO). Two reasons motivate this choice: SSPO high inclination
reduces the incidence of radiation and having constant solar exposure during part of the
orbit-raising reduces the time the satellite spends in eclipse. We use a quaternion-based
formulation to investigate the problem. We will provide a comparison of our proposed
methodology with previous approaches in order to determine its applicability to any lowthrust
orbit-raising problem.
15:35 AAS Multi-objective Optimisation of Many-revolution, Low-thrust Orbit Raising
13-257 for Destiny Mission
Federico Zuiani, University of Glasgow / ISAS
This work will present a Multi-Objective approach to the design of the initial, Low-Thrust
orbit raising phase for JAXA’s proposed technology demonstrator mission DESTINY. The
proposed approach includes a simplified model for Low Thrust, many-revolution transfers,
based on an analytical orbital averaging technique and a simplified control
parameterisation. This is combined with a stochastic optimisation algorithm which will
solve optimisation problems in which conflicting performance figures of DESTINY’s
trajectory design are concurrently optimised.
15:55 AAS A Low Energy, Low Thrust Unified Solver for Rapid Mission Design
13-255 Nitin Arora, Georgia Institute of Technology / NASA / Caltech JPL; Nathan
Strange, NASA / Caltech JPL
Recent studies of a manned cislunar way point base at the moon are driving the need to
rapidly compute low-Energy, low thurst (le-lt) trajectories to Earth-Moon L1/L2 Lagrange
23 rd AAS / AIAA Space Flight Mechanics Meeting Page 33