Research on Shape-Based Approximation Methods for Initial Conditions for Low-Thrust Spacecraft Trajectory Optimization
Faculty Mentor Name
Bradley Wall
Format Preference
Poster
Abstract
In the realm of low-thrust spacecraft trajectories, there are many different ways to solve for optimal trajectories. Given a set of boundary conditions, such as the initial position, final position, and time of flight (Lambert’s problem), there is no trivial solution to finding the optimal route. There are currently several solutions to the boundary conditions problem of low-thrust spacecraft trajectories used as a starting point for optimization methods. These methods facilitate the ability to look through the large sample sizes of options that are inherent in low-thrust trajectory problems and make an accurate, near-optimal initial guess. The initial guess can then be processed using an optimization model such that the ideal solution may be acquired. Shaped-based approximation methods used to find a viable initial guess use the method of defining a curve and then designing a control for the thrust such that a spacecraft follows that shape. One can then simulate the trajectory and use the results in an optimization algorithm. During the course of this research, a variety of shape-based approximation methods will be tested against different sets of initial conditions. The shapes used will come from different literature that defines different available shapes as well as a new shape that will developed during the course of this research.
- POSTER PRESENTATION
Location
ERAU - Prescott, AZ; AC1-Atrium, 11 am - 3 pm | Eagle Gym, 7 - 9 pm
Start Date
3-29-2019 11:00 AM
End Date
3-29-2019 9:00 PM
Research on Shape-Based Approximation Methods for Initial Conditions for Low-Thrust Spacecraft Trajectory Optimization
ERAU - Prescott, AZ; AC1-Atrium, 11 am - 3 pm | Eagle Gym, 7 - 9 pm
In the realm of low-thrust spacecraft trajectories, there are many different ways to solve for optimal trajectories. Given a set of boundary conditions, such as the initial position, final position, and time of flight (Lambert’s problem), there is no trivial solution to finding the optimal route. There are currently several solutions to the boundary conditions problem of low-thrust spacecraft trajectories used as a starting point for optimization methods. These methods facilitate the ability to look through the large sample sizes of options that are inherent in low-thrust trajectory problems and make an accurate, near-optimal initial guess. The initial guess can then be processed using an optimization model such that the ideal solution may be acquired. Shaped-based approximation methods used to find a viable initial guess use the method of defining a curve and then designing a control for the thrust such that a spacecraft follows that shape. One can then simulate the trajectory and use the results in an optimization algorithm. During the course of this research, a variety of shape-based approximation methods will be tested against different sets of initial conditions. The shapes used will come from different literature that defines different available shapes as well as a new shape that will developed during the course of this research.
- POSTER PRESENTATION