Abstract
In this paper, we consider the problem of orbit-raising of all-electric satellites. In order to minimize the impact of radiation during the electric orbit-raising maneuver, we formulate an optimization problem that minimizes radiation fluence along the trajectory. We use a direct optimization approach to solve the resulting optimal control problem for a variety of mission scenarios. We identify combinations of electric thrusters and starting orbits that deploy a satellite in GEO in 6 months, and identify the mass and power requirements of the solar arrays for small and large classes of telecommunication satellites.
Original language | English (US) |
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Pages (from-to) | 765-782 |
Number of pages | 18 |
Journal | Advances in the Astronautical Sciences |
Volume | 148 |
State | Published - 2013 |
Event | 23rd AAS/AIAA Space Flight Mechanics Meeting, Spaceflight Mechanics 2013 - Kauai, HI, United States Duration: Feb 10 2013 → Feb 14 2013 |
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Space and Planetary Science