Abstract
Developing a modern low thrust trajectory planning tool for applications to picosatellites poses a number of unique challenges. This work discusses the development of a propellant-minimum trajectory planning tool, that combines a higher order integrator, algebraic differentiation techniques, adaptive step size control, a non-linear programming problem solver, and analysis of cumulative density functions of the control profile to generate a robust, extendable solution framework. Discussions of the lessons learned in merging these techniques, as well as a few demonstrated case studies will be included. The work will be shown to be extendable in the future towards cooperative formation flying.
Original language | English (US) |
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Pages (from-to) | 1413-1432 |
Number of pages | 20 |
Journal | Advances in the Astronautical Sciences |
Volume | 148 |
State | Published - Jan 1 2013 |
Externally published | Yes |
Event | 23rd AAS/AIAA Space Flight Mechanics Meeting, Spaceflight Mechanics 2013 - Kauai, HI, United States Duration: Feb 10 2013 → Feb 14 2013 |
ASJC Scopus subject areas
- Aerospace Engineering
- Space and Planetary Science