Analytical formulae are summarized to approximate the evolution of the semi major axis, the maneuver time, and the final mass fraction for low thrust orbital transfers with circular initial orbit, circular target orbit, and constant thrust directed either always along or always opposite the velocity vector. For comparison, the associated results for high-thrust transfers, i.e. the two-impulse Hohmann transfer, are summarized. All results are implemented in a computer code designed to analyze planar planetary and interplanetary space missions. As a numerical example, a mission from Low-Earth Orbit (LEO) to Jupiter's moon Europa is analyzed.
|Number of pages||21|
|Journal||Advances in the Astronautical Sciences|
|Publication status||Published - 2003 Dec 1|
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Space and Planetary Science