|
Abstract
|
|
|---|---|
| In this work the solution to the 8th Global Trajectory Optimization Competition proposed from the PoliMi-UPM team is presented. With the aim of maximizing the objective function, a two-stage strategy has been devised. First, two spacecraft target selenoflybys to significantly modify their orbital parameters, in particular increasing the semi-major axis. Later, the formation is steered with low-thrust propulsion to point radio sources within the assigned tolerance. The latter is achieved by means of a geometrical method that minimizes the orbital parameters variation, and that provides boundary condition for an indirect method solution of the Two-point Boundary Value Problem. No constraints on the number of seen radio sources have been applied. On a higher level, a genetic algorithm is used to identify the optimal flyby parameters. | |
|
International
|
Si |
|
Congress
|
26th AAS/AIAA Space Flight Mechanics Meeting |
|
|
960 |
|
Place
|
Napa, California (EEUU) |
|
Reviewers
|
Si |
|
ISBN/ISSN
|
1081-6003 |
|
|
|
|
Start Date
|
14/02/2016 |
|
End Date
|
18/02/2016 |
|
From page
|
4301 |
|
To page
|
4308 |
|
|
Advances in the Astronautical Sciences Volume 158, Spaceflight Mechanics 2016 |