IA
I. Ariño Monsec
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Very Low Earth Orbit (VLEO) enhances payload capabilities but suffers from high aerodynamic drag, limiting satellite lifetime. This thesis presents the preliminary design of a satellite using Air-Breathing Electric Propulsion (ABEP) for continuous drag compensation. Mission analysis defined a viable altitude range of 260–380km, selecting a 268 km sun-synchronous orbit (14:00 LTAN) to balance drag, power generation, and ground track repetition. Through configuration trade-offs, a compact design was chosen to maximize ABEP performance, minimize risk, and fit standard launcher envelopes. To sustain this orbit, the ABEP system requires a specific impulse of 4200s, well within Gridded Ion Thruster margins. Comprising 25% of spacecraft mass, it outperforms conventional propulsion and reduces total mass relative to historical VHR earth observation missions (<1m GSD). Extended solar arrays are explored to enhance passive aerodynamic stability. Beyond propulsion performance, this study concludes VLEO feasibility relies heavily on surface accommodation coefficients and solar activity variations.
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Very Low Earth Orbit (VLEO) enhances payload capabilities but suffers from high aerodynamic drag, limiting satellite lifetime. This thesis presents the preliminary design of a satellite using Air-Breathing Electric Propulsion (ABEP) for continuous drag compensation. Mission analysis defined a viable altitude range of 260–380km, selecting a 268 km sun-synchronous orbit (14:00 LTAN) to balance drag, power generation, and ground track repetition. Through configuration trade-offs, a compact design was chosen to maximize ABEP performance, minimize risk, and fit standard launcher envelopes. To sustain this orbit, the ABEP system requires a specific impulse of 4200s, well within Gridded Ion Thruster margins. Comprising 25% of spacecraft mass, it outperforms conventional propulsion and reduces total mass relative to historical VHR earth observation missions (<1m GSD). Extended solar arrays are explored to enhance passive aerodynamic stability. Beyond propulsion performance, this study concludes VLEO feasibility relies heavily on surface accommodation coefficients and solar activity variations.