Abstract
A constant outward radial thrust acceleration can be used to reduce the radius of a circular orbit of specified period. Heliocentric circular orbits are designed to match the orbital period of Earth or Mars for various radial thrust accelerations and are defined as synchronous orbits. Minimum-time solar sail orbit transfers to these synchronous heliocentric orbits are presented.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 523-537 |
| Number of pages | 15 |
| Journal | Advances in the Astronautical Sciences |
| Volume | 103 |
| Issue number | PART 1 |
| State | Published - 2000 |
| Externally published | Yes |
ASJC Scopus subject areas
- Aerospace Engineering
- Space and Planetary Science