ReDSHIFT: A Global Approach to Space Debris Mitigation

Rossi, Alessandro; Colombo, Camilla; Tsiganis, K.; Beck, J. B.; Rodríguez, J. Becedas; Walker, Scott J.I.; Letterio, Federico; Vedova, Florio Dalla; Schaus, Volker; Popova, Rada; Francesconi, Alessandro; Stokes, H.; Schleutker, Thorn; Alessi, Elisa Maria; Schettino, Giulia; Gkolias, Ioannis; Skoulidou, Despoina K.; Holbrough, Ian; Bernelli‐Zazzera, Franco; Stoll, Enrico; Kim, Youngkyu

doi:10.3390/aerospace5020064

Cited by 28 publications

(13 citation statements)

References 5 publications

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“…One of the goals of the ReDSHIFT is the development of a software toolkit that would enable an informed design of "debris compliant" missions, including the design of an appropriate passive removal strategy, given an operational orbit and ∆V budget. We refer the reader to Rossi et al (2018) for a in-depth discussion about the software toolkit. The results presented in this paper have been collected in the form of a database of pre-computed solutions, to be used as input in the software toolkit.…”

Section: Gnss-graveyard Studymentioning

confidence: 99%

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Medium Earth Orbit dynamical survey and its use in passive debris removal

Skoulidou

Rosengren

Tsiganis

et al. 2019

Advances in Space Research

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The Medium Earth Orbit (MEO) region hosts satellites for navigation, communication, and geodetic/space environmental science, among which are the Global Navigation Satellites Systems (GNSS). Safe and efficient removal of debris from MEO is problematic due to the high cost for maneuvers needed to directly reach the Earth (reentry orbits) and the relatively crowded GNSS neighborhood (graveyard orbits). Recent studies have highlighted the complicated secular dynamics in the MEO region, but also the possibility of exploiting these dynamics, for designing removal strategies. In this paper, we present our numerical exploration of the long-term dynamics in MEO, performed with the purpose of unveiling the set of reentry and graveyard solutions that could be reached with maneuvers of reasonable ∆V cost. We simulated the dynamics over 120-200 years for an extended grid of millions of fictitious MEO satellites that covered all inclinations from 0 to 90 • , using non-averaged equations of motion and a suitable dynamical model that accounted for the principal geopotential terms, 3rd-body perturbations and solar radiation pressure (SRP). We found a sizeable set of usable solutions with reentry times that exceed ∼ 40 years, mainly around three specific inclination values: 46 • , 56 • , and 68 • ; a result compatible with our understanding of MEO secular dynamics. For ∆V ≤ 300 m/s (i.e., achieved if you start from a typical GNSS orbit and target a disposal orbit with e < 0.3), reentry times from GNSS altitudes exceed ∼ 70 years, while low-cost (∆V 5 − 35 m/s) graveyard orbits, stable for at lest 200 years, are found for eccentricities up to e ≈ 0.018. This investigation was carried out in the framework of the * Corresponding author

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Section: Gnss-graveyard Studymentioning

confidence: 99%

“…Our study is part of the EC-funded "ReDSHIFT" project 1 (Rossi et al, 2018). The main goal of this project is to introduce a holistic approach in the design of passive debris removal strategies.…”

Section: Introductionmentioning

confidence: 99%

Medium Earth Orbit dynamical survey and its use in passive debris removal

Skoulidou

Rosengren

Tsiganis

et al. 2019

Advances in Space Research

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“…In particular, it is demonstrated that there exists an integral of motion, corresponding to (β cos i − α) µa(1 − e 2 ) = constant, (6) where α, β are as defined in Eq. (2). In other words, assuming that the motion of the spacecraft is governed only by the Earth's monopole, the Earth's oblateness and the solar radiation pressure, at any instant we can recover the inclination value from…”

Section: Analysis In the Frequency Domainmentioning

confidence: 99%

A frequency portrait of Low Earth Orbits

Schettino

Alessi

Rossi

et al. 2019

Celest Mech Dyn Astr

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In this work we deepen and complement the analysis on the dynamics of Low Earth Orbits (LEO), carried out by the authors within the H2020 ReD-SHIFT project, by characterising the evolution of the eccentricity of a large set of orbits in terms of the main frequency components. Decomposing the quasi-periodic time series of eccentricity of a given orbit by means of a numerical computation of Fourier transform, we link each frequency signature to the dynamical perturbation which originated it in order to build a frequency chart of the LEO region. We analyse and compare the effects on the eccentricity due to solar radiation pressure, lunisolar perturbations and high degree zonal harmonics of the geopotential both in the time and frequency domains. In particular, we identify the frequency signatures due to the dynamical resonances found in LEO and we discuss the opportunity to exploit the corresponding growth of eccentricity in order to outline decommissioning strategies.1 All the papers related to the project are available on the ReDSHIFT website at http://redshift-h2020.eu/documents/.2 http://redshift-h2020.eu/results/leo . 3 The oblateness of the Earth, J 2 , does not affect the evolution of the eccentricity over long term (e.g. [16]).

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“…Past numerical simulations have shown that some geostationary transfer orbits (GTOs) are dynamically shortlived (Janin 1991;Siebold and Reynolds 1995;Morand et al 2012), and recent works have demonstrated that this problem still presents a number of interesting and hitherto unknown features Gurfil 2016, 2017). Motivated by our preceding dynamical survey of orbital stability and associated lifetimes in circumterrestrial spacefrom low-Earth orbit (LEO) to beyond the geostationary ring (GEO) (Rosengren et al 2018) -conducted in the framework of the ReDSHIFT project (Rossi et al 2017(Rossi et al , 2018, we revisit the problem of GTO long-term stability. In fact, we extend our previous results, based solely on the long-term conservative evolution, by adding the effect of atmospheric drag at high altitudes.…”

Section: Introductionmentioning

confidence: 99%

Dynamical lifetime survey of geostationary transfer orbits

Skoulidou

Rosengren

Tsiganis

et al. 2018

Celest Mech Dyn Astr

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In this paper, we study the long-term dynamical evolution of highly-elliptical orbits (HEOs) in the medium-Earth orbit (MEO) region around the Earth. The real population consists primarily of Geosynchronous Transfer Orbits (GTOs), launched at specific inclinations, Molniya-type satellites and related debris. We performed a suite of long-term numerical integrations (up to 200 years) within a realistic dynamical model, aimed primarily at recording the dynamical lifetime of such orbits (defined as the time needed for atmospheric reentry) and understanding its dependence on initial conditions and other parameters, such as the area-to-mass ratio (A/m). Our results are presented in the form of 2-D lifetime maps, for different values of inclination, A/m, and drag coefficient. We find that the majority of small debris (> 70%, depending on the inclination) can naturally reenter within 25-90 years, but these numbers are significantly less optimistic for large debris (e.g., upper stages), with the notable exception of those launched from high latitude (Baikonur). We estimate the reentry probability and mean dynamical lifetime for different classes of GTOs and we find that both quantities depend primarily and strongly on initial perigee altitude. Atmospheric drag and higher A/m values extend the reentry zones, especially at low inclinations. For high inclinations, this dependence is weakened, as the primary mechanisms leading to reentry are overlapping lunisolar resonances. This study forms part of the EC-funded (H2020) "ReDSHIFT" project.

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ReDSHIFT: A Global Approach to Space Debris Mitigation

Cited by 28 publications

References 5 publications

Medium Earth Orbit dynamical survey and its use in passive debris removal

Medium Earth Orbit dynamical survey and its use in passive debris removal

A frequency portrait of Low Earth Orbits

Dynamical lifetime survey of geostationary transfer orbits

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