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<p>Advancements in the development of an Atmosphere-Breathing Electric Propulsion (ABEP) system at the University of Stuttgart’s Institute of Space Systems (IRS) highlight the need to focus not only on technical development but also on the operational aspects of ABEP in very low-Earth orbit (VLEO). The present work gives a summary of the analysis performed with the ESA-funded project ram-CLEP on the expected atmospheric conditions and eclipsing times using the <i>ASTOS</i> software and the NRLMSISE-00 atmospheric model, identifying worst-case scenarios—such as maximum atmospheric density and longest eclipse duration—that the satellite system must withstand. This includes the consideration of elliptical Sun-synchronous orbits, which, although unconventional, offer unique advantages such as allowing for lower perigee altitudes and increased system robustness during thruster outages. These analyses establish foundational conditions under which the satellite shall sustain payload operation and use the ABEP system to compensate for altitude loss due to atmospheric drag. In a proprietary multi-disciplinary design optimization approach, which takes into account the drag dependent on geometry and atmospheric conditions as well as performance models of the ABEP system, the most suitable satellite design is identified for further investigations. This contribution next implements a simulation-based approach to analyze the performance and feasibility of the system in its intended orbit. Beyond single-orbit performance under worst-case conditions, long-term simulations covering the entire eclipse season provide a more comprehensive review of the mission concept’s feasibility. This analysis also defines a performance envelope for the ABEP system, outlining operational conditions and power levels for efficient functioning. Moreover, varying the assumed margins and ABEP efficiencies enables a sensitivity study, which demonstrates the robustness of the proposed solution. From the simulation-based analysis, certain limiting factors for performance are identified, such as significant fluctuations in mass flow rates, the specific impulse required for the thrusters, and energy availability through solar panels and battery storage. Preliminary mitigation strategies, including adjustments to attitude control, are discussed. Finally, this paper outlines key priorities for the future development of ABEP systems, specifically focusing on preparing them for operational feasibility in very low-Earth orbit.</p>

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Operational aspects of an ABEP system for drag compensation in VLEO

  • 期刊论文

  • 发表日期：

    2025年7月25日

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  • Maximilian Walther,
  • Konstantinos Papavramidis,
  • Jonathan Skalden,
  • Philipp Maier,
  • Elizabeth Gutierrez,
  • Georg Herdrich,
  • Andreas Wiegand,
  • Louis Walpot,
  • Berthyl Duesmann

摘要

Advancements in the development of an Atmosphere-Breathing Electric Propulsion (ABEP) system at the University of Stuttgart’s Institute of Space Systems (IRS) highlight the need to focus not only on technical development but also on the operational aspects of ABEP in very low-Earth orbit (VLEO). The present work gives a summary of the analysis performed with the ESA-funded project ram-CLEP on the expected atmospheric conditions and eclipsing times using the ASTOS software and the NRLMSISE-00 atmospheric model, identifying worst-case scenarios—such as maximum atmospheric density and longest eclipse duration—that the satellite system must withstand. This includes the consideration of elliptical Sun-synchronous orbits, which, although unconventional, offer unique advantages such as allowing for lower perigee altitudes and increased system robustness during thruster outages. These analyses establish foundational conditions under which the satellite shall sustain payload operation and use the ABEP system to compensate for altitude loss due to atmospheric drag. In a proprietary multi-disciplinary design optimization approach, which takes into account the drag dependent on geometry and atmospheric conditions as well as performance models of the ABEP system, the most suitable satellite design is identified for further investigations. This contribution next implements a simulation-based approach to analyze the performance and feasibility of the system in its intended orbit. Beyond single-orbit performance under worst-case conditions, long-term simulations covering the entire eclipse season provide a more comprehensive review of the mission concept’s feasibility. This analysis also defines a performance envelope for the ABEP system, outlining operational conditions and power levels for efficient functioning. Moreover, varying the assumed margins and ABEP efficiencies enables a sensitivity study, which demonstrates the robustness of the proposed solution. From the simulation-based analysis, certain limiting factors for performance are identified, such as significant fluctuations in mass flow rates, the specific impulse required for the thrusters, and energy availability through solar panels and battery storage. Preliminary mitigation strategies, including adjustments to attitude control, are discussed. Finally, this paper outlines key priorities for the future development of ABEP systems, specifically focusing on preparing them for operational feasibility in very low-Earth orbit.