Are mercury emissions from satellite electric propulsion an environmental concern?*

Fourie, Dan; Hedgecock, Ian M.; Simone, Francesco De; Sunderland, Elsie M.; Pirrone, Nicola

doi:10.1088/1748-9326/ab4b75

Cited by 6 publications

(5 citation statements)

References 36 publications

(37 reference statements)

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“…The present study of ion trajectories investigates the interactions between ionsreleased with energies and altitudes consistent with xenon electric thruster operation on an orbiting spacecraft -and the geomagnetic field. The methodology is amenable to other electric propulsion propellants such as argon, krypton, iodine, hydrazine and its derivatives, cesium and ionic liquids, as well as those which may be of greater environmental concern such as mercury [24]. In fact, such questions of environmental effects due to electric propulsion emissions have been raised since the 1970s with investigation of cesium [25].…”

Section: The Magnetospherementioning

confidence: 99%

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Simulations of xenon beam ions emitted from electric thrusters in Earth’s magnetosphere

Sampson,

Crofton

2023

J Electr Propuls

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This study sought to characterize the behavior of exhausted electric thruster xenon ions in the near-Earth magnetospheric environment as functions of various trajectory and particle attributes, neglecting effects of electric fields, plasma waves and particle collisions. This was done via simulation using the AeroTracer program, a software tool which computes ion trajectories within the magnetosphere by applying an adaptive step-size Runge-Kutta technique to the fully relativistic Lorentz equation. Over 3,800 independent simulations were performed, with variables including release position, release energy and direction, ion charge, and orbital phase. Initial release altitude was a major driver in determining whether the ion eventually fell to Earth (“Below Minimum Altitude” or BMA), remained trapped by the simulation’s end (“Maximum Number of Steps” or MNS), or traveled beyond the magnetosphere (“Lost to Space” or LTS). Ions expelled at the highest altitudes investigated - 60,000 km and above - almost invariably were lost to space. Like altitude, increasing inclination and energy were important factors that reduced trapping, affecting the outcome probabilities. Higher charge state produced strong improvement of trapping capability. Effects of orbital phase, day of year and solar cycle phase were also apparent. A transition region was found in the 20,000 km to 60,000 km altitude range, within which the sensitivity of outcomes to parameter variation increased. The ordered sequence MNS> BMA> LTS was found to be consistent with decreasing confinement capability, and it was manifested consistently as parameters were varied.

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Section: The Magnetospherementioning

confidence: 99%

“…Fig 24. Results for solar maximum and solar minimum ion release (including both orbit raising and lowering cases)…”

mentioning

confidence: 99%

Simulations of xenon beam ions emitted from electric thrusters in Earth’s magnetosphere

Sampson,

Crofton

2023

J Electr Propuls

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“…This may prove challenging to implement at a global scale and may benefit from discussion about incentivizing the development or transfer of alternative designs, as the entire launch industry in some countries relies heavily on specific engine technologies and propellants. On a related issue concerning in-space propulsion, in 2022, the UN adopted a provision to phase out mercury (heavy metal highly toxic to humans) out of concern that it would then return to Earth's surface [47].…”

Section: Policy Alternatives and Perspectivesmentioning

confidence: 99%

Space sustainability isn’t just about space debris: On the atmospheric impact of space launches

Sirieys

Gentgen

Milton

et al. 2022

MIT Science Policy Review

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Throughout their life cycle, space launch vehicles impact their local and global environments on Earth and in space. Given the space industry’s projected growth, recent literature suggests that the atmospheric consequences of these activities are understudied and insufficiently addressed. Rockets uniquely emit combustion gases and particles into distinct layers of the atmosphere, inducing effects that include perturbations of ozone chemistry and of Earth’s energy balance through radiative forcing. International environmental regulations do not presently address rocket emissions and only scarce, isolated policies exist at the national level. Additional research on the impact of space launches, including new in situ measurements coupled with global atmospheric models, is required to inform policymaking and future mitigation. The development of an actionable and collaborative sustainability index for launch vehicles could serve as a basis for future regulations or incentivize the sector towards more sustainable designs by making emissions reduction a competitive advantage.

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“…The present study of ion trajectories investigates the interactions between ions Ð released with energies and altitudes consistent with xenon electric thruster operation on an orbiting spacecraft Ð and the geomagnetic őeld. The methodology is amenable to other electric propulsion propellants (such as argon, krypton and iodine) as well as those which may be of greater environmental concern [12]. In fact, such questions of environmental effects due to electric propulsion emissions have been raised since the 1970s with investigation of cesium [13].…”

Section: A the Magnetospherementioning

confidence: 99%

Simulations of Xenon Beam Ions Emitted from Electric Thrusters in Earth's Magnetosphere

Sampson

Crofton

2022

Preprint

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This study sought to characterize the behavior of exhausted electric thruster xenon ions in the near-Earth magnetospheric environment as functions of various trajectory and particle attributes. This was done via simulation using the AeroTracer program, a software tool which computes ion trajectories within the magnetosphere by applying an adaptive step-size Runge-Kutta technique to the fully relativistic Lorentz equation. Over 3,800 independent simulations were performed, with variables including release position, release energy and direction, ion charge, and orbital phase. Initial release altitude was a major driver in determining whether the ion eventually fell to Earth (BMA), remained trapped by the simulation's end (MNS), or traveled beyond the magnetosphere (LTS). Ions expelled at the highest altitudes investigated -60,000 km and above -almost invariably were lost to space. Like altitude, increasing inclination and energy were important factors that reduced trapping, affecting the outcome probabilities. Higher charge state produced strong improvement of trapping capability. Effects of orbital phase, day of year and solar cycle phase were also apparent. A transition region was found in the 20,000 km to 60,000 km altitude range, within which the sensitivity of outcomes to parameter variation increased. The ordered sequence MNS > BMA > LTS was found to be consistent with decreasing confinement capability, and it was manifested consistently as parameters were varied.

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Are mercury emissions from satellite electric propulsion an environmental concern?*

Cited by 6 publications

References 36 publications

Simulations of xenon beam ions emitted from electric thrusters in Earth’s magnetosphere

Simulations of xenon beam ions emitted from electric thrusters in Earth’s magnetosphere

Space sustainability isn’t just about space debris: On the atmospheric impact of space launches

Simulations of Xenon Beam Ions Emitted from Electric Thrusters in Earth's Magnetosphere

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