Calculation of distant retrograde orbits and their use in space weather forecasting
Abstract
There is current renewed interest in using Sun-Earth distant retrograde orbits (DROs) for a space weather forecasting mission, which would temporarily place spacecraft at a position near the Sun-Earth line, but closer to the Sun than the L1 point (such as the ESA HENON mission and ESA SHIELD concept). With in situ observations of the magnetic field on a DRO, the southward (Bz < 0) magnetic field of interplanetary coronal mass ejections (ICMEs), which is not routinely accessible remotely, could be measured several hours in advance. This Bz < 0 field is a decisive factor for forecasting geomagnetic storm intensity. We present an analysis of DROs at different sub-L1 distances for their efficacy for a space weather forecasting mission. An open-source numerical framework to generate DRO trajectories is presented. Our pre-calculated orbits in Heliocentric Earth Ecliptic coordinates can be introduced into numerical or empirical simulations of the ambient solar wind and ICMEs. We then analyze the corresponding forecast lead times, the resulting observational gaps depending on the number of spacecraft and distance of a DRO, and the "cone of acceptance" of the maximum longitudinal separation of a spacecraft to the Sun-Earth line. We define different domains regarding radial evolution and longitudinal CME structure, and show the historical coverage of sub-L1 ICME observations with our ICMECAT catalog. An optimal mission configuration can be selected based on the characteristics of DROs presented here, depending on the requirements of such a mission deemed acceptable with respect to results on CME evolution and coherence.
Related
- Multiviewpoint Tracking of a Coronal Mass Ejection Driven Shock Propagating to Mars: Implications for Space Weather Forecasting
- Validation of Space Weather Forecasting at Leonid Space
- Constraining the orbit of the retrograde planet in the ν Octantis system
- A multi-epoch search for distant Solar System bodies in the Catalina Sky Survey
- Electromagnetic Emission and Orbital Evolution of Eccentric Supermassive Black Hole Binaries in Retrograde Disks
BibTeX
@misc{mostl2026calculation,
title = {{Calculation of distant retrograde orbits and their use in space weather forecasting}},
author = {C. Möstl and E. E. Davies and E. Weiler and E. Palmerio and N. Lugaz and F. Camattari and H. T. Rüdisser and U. V. Amerstorfer},
howpublished = {arXiv},
year = {2026},
month = oct,
doi = {10.48550/arxiv.2610.36315},
eprint = {2610.36315},
archivePrefix = {arXiv},
url = {https://arxiv.org/abs/2610.36315},
note = {CC BY 4.0},
}
RIS
TY - UNPB
TI - Calculation of distant retrograde orbits and their use in space weather forecasting
AU - C. Möstl
AU - E. E. Davies
AU - E. Weiler
AU - E. Palmerio
AU - N. Lugaz
AU - F. Camattari
AU - H. T. Rüdisser
AU - U. V. Amerstorfer
PY - 2026
DA - 2026/10/26
PB - arXiv
DO - 10.48550/arxiv.2610.36315
UR - https://arxiv.org/abs/2610.36315
AB - There is current renewed interest in using Sun-Earth distant retrograde orbits (DROs) for a space weather forecasting mission, which would temporarily place spacecraft at a position near the Sun-Earth line, but closer to the Sun than the L1 point (such as the ESA HENON mission and ESA SHIELD concept). With in situ observations of the magnetic field on a DRO, the southward (B_z < 0) magnetic field of interplanetary coronal mass ejections (ICMEs), which is not routinely accessible remotely, could be measured several hours in advance. This B_z < 0 field is a decisive factor for forecasting geomagnetic storm intensity. We present an analysis of DROs at different sub-L1 distances for their efficacy for a space weather forecasting mission. An open-source numerical framework to generate DRO trajectories is presented. Our pre-calculated orbits in Heliocentric Earth Ecliptic coordinates can be introduced into numerical or empirical simulations of the ambient solar wind and ICMEs. We then analyze the corresponding forecast lead times, the resulting observational gaps depending on the number of spacecraft and distance of a DRO, and the "cone of acceptance" of the maximum longitudinal separation of a spacecraft to the Sun-Earth line. We define different domains regarding radial evolution and longitudinal CME structure, and show the historical coverage of sub-L1 ICME observations with our ICMECAT catalog. An optimal mission configuration can be selected based on the characteristics of DROs presented here, depending on the requirements of such a mission deemed acceptable with respect to results on CME evolution and coherence.
ER -