On evolution of geostationary satellite orbits

Kiladze, R. I.; Sochilina, A. S.

doi:10.1016/s0273-1177(97)00326-8

Cited by 4 publications

(5 citation statements)

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“…Adding the lunisolar perturbation introduces a subtle modulation of the geopotential curve [16] with a period close to 52 years, as outlined in section 3. In the numerical propagations this variation is not truly periodic, because the third-body positions are derived from ephemerides instead of simple analytical models.…”

Section: Longitudinal Dynamicsmentioning

confidence: 99%

“…The clearest pattern observed in all the simulations was an orbital inclination cycle with a maximum value of 14.5 to 15 degrees and a period of approximately 53 years, which the authors attributed to the precession of the orbital plane discussed above. Kiladze and Sochilina [16] and Kiladze et al [17] observed the orbital evolution of some 360 uncontrolled GS satellites with the purpose of improving the accuracy of the geopotential model parameters. The results of orbital propagations over intervals of a few years disclosed three types of dynamics, the occurrence of which depended on the initial conditions: (i) a simple libration around the nearest stable position (either about 75º E or about 105º W); (ii) a complex ("long") libration around both stable positions; (iii) a circulation with different drift rates.…”

Section: Introductionmentioning

confidence: 99%

“…17 illustrate the first of the ill-behaved scenarios from list (47). Figs.14 and 15show results from the equinoctial elements propagator while data in Figs 16. and 17 come from the Cartesian integrator.…”

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confidence: 99%

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Long-term orbit dynamics of decommissioned geostationary satellites

et al. 2021

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In nominal mission scenarios, geostationary satellites perform end-of-life orbit maneuvers to reach suitable disposal orbits, where they do not interfere with operational satellites. This research investigates the long-term orbit evolution of decommissioned geostationary satellite under the assumption that the disposal maneuver does not occur and the orbit evolves with no control. The dynamical model accounts for all the relevant harmonics of the terrestrial gravity field at the typical altitude of geostationary orbits, as well as solar radiation pressure and third-body perturbations caused by the Moon and the Sun. Orbit propagations are performed using two algorithms based on different equations of motion and numerical integration methods: (i) Gauss planetary equations for modified equinoctial elements with a Runge-Kutta numerical integration scheme based on 8-7 th -order Dorman and Prince formulas; (ii) Cartesian state equations of motion in an Earth-fixed frame with a Runge-Kutta Fehlberg 7/8 integration scheme.The numerical results exhibit excellent agreement over integration times of decades. Some well-known phenomena emerge, such as the longitudinal drift due to the resonance between the orbital motion and Earth's rotation, attributable to the 22 J term of the geopotential. In addition, the third-body perturbation due to Sun and Moon causes two major effects: (a) a precession of the orbital plane, and (b) complex longitudinal dynamics. This study proposes an analytical approach for the prediction of the precessional motion and show its agreement with the (more accurate) orbit evolution obtained numerically. Moreover, long-term orbit propagations show that the above mentioned complex longitudinal dynamics persists over time scales of several decades. Frequent and unpredictable migrations 2 toward different longitude regions occur, in contrast with the known effects due only to the perturbative action of 22 J .

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Section: Longitudinal Dynamicsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Long-term orbit dynamics of decommissioned geostationary satellites

et al. 2021

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“…It has been shown that this limited set of perturbations was not enough to model the EW-well entrapment, however STK has managed to do so. Though J 2 and J 22 alone cannot cover this behavior, it was believed that the tesserals J 21 and J 31 along with sectorial J 33 will provide the missing perturbatory effects to accurately simulate this behavior [1], [20]. Because of the success of the Cowell propagator in the other cases,…”

Section: Comparison Plots -Stk and Custom Propagatorsmentioning

confidence: 99%

“…It has yet to be determined if one of these well collisions has a possibility to achieve EW entrapment, or what conditions specifically allow for fragments originating from a trapped object to leave their well. Additional satellites of interest for this study, as well as discussion on experimental observations on the subject, can be found in [20].…”

Section: Future Workmentioning

confidence: 99%

The Collisional Evolution of Orbital Debris in Geopotential Wells and Disposal Orbits

Polzine¹

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The Collisional Evolution of Orbital Debris in Geopotential Wells and Disposal Orbits Benjamin PolzineThis thesis investigates the orbital debris evolution in the geosynchronous disposal orbit regime and within geosynchronous orbits effected by the geopotential wells. A propagator is developed for the accurate simulation of GEO specific orbits and the required perturbations are determined and described. Collisions are then simulated in the selected regimes using a low velocity breakup model derived from the NASA EVOLVE breakup model. The simulations described in this thesis consider a set of perturbations including the geopotential, solar and lunar gravity, and solar radiation pressure forces. This thesis is based on a prior paper and additionally seeks to address an issue in simulating East-West trapped objects. The results show that this propagator successfully simulates the presence of all wells and the East-West entrapment, and the required perturbations are outlined. Five collision test cases were simulated, one for each type of entrapment and an additional for the disposal orbit.iv ACKNOWLEDGMENTS

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Stochastic motion of geosynchronous satellites

Kuznetsov¹,

Kaiser²

2007

Cosmic Res

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On evolution of geostationary satellite orbits

Cited by 4 publications

References 0 publications

Long-term orbit dynamics of decommissioned geostationary satellites

Long-term orbit dynamics of decommissioned geostationary satellites

The Collisional Evolution of Orbital Debris in Geopotential Wells and Disposal Orbits

Stochastic motion of geosynchronous satellites

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