An Optimal Low Thrust Trajectory to the Moon
John T. Betts, Ph.D.
The direct transcription or collocation method has demonstrated notable success in the solution of trajectory optimization and optimal control problems. This approach combines a sparse nonlinear programming algorithm with a discretization of the trajectory dynamics. A challenging class of optimization problems occurs when the spacecraft trajectories are characterized by thrust levels that are very low relative to the vehicle weight. Low thrust trajectories are demanding because realistic forces due to oblateness, and third-body perturbations often dominate the thrust. Furthermore because the thrust is so low, significant changes to the orbits require very long duration trajectories. When a collocation method is applied to a problem of this type, the resulting nonlinear program is very large because the trajectories are long, and very nonlinear because of the perturbing forces.
This paper describes the application of the transcription method to compute an optimal low thrust transfer from an earth orbit to a specified lunar mission orbit. It is representative of the SMART-1 or "Small Missions for Advanced Research in Technology", of the ESA scientific program. The spacecraft is deployed from an Ariane-5 into an elliptic earth centered park orbit. The goal is to insert the spacecraft into a lunar orbit that is polar, elliptic, and has its pericenter above the south pole. The spacecraft utilizes a solar electric propulsion system. The goal is to compute the optimal steering during the orbit transfer which takes over 200 days, so that the fuel consumption is minimized.
The vehicle dynamics are defined using a modified set of equinoctial
coordinates, and the trajectory modeling is described using these
dynamics. A solution is presented that requires the solution of a sparse
optimization problem with 383672 variables and 265766 constraints. Issues
related to the numerical conditioning and problem formulation are