Short-period and long-period perturbations of a spherical satellite due to direct solar radiation

Aksnes, K.

doi:10.1007/bf01228536

Cited by 65 publications

(20 citation statements)

References 5 publications

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“…Moreover, some authors have pointed out that Earth's shadowing effects should not be neglected and that these phenomena could lead to significant short-periodic perturbations (see Kozai 1961, Ferraz-Mello 1972, Aksnes 1976). Recent observations (Schildknecht et al, 2010) have made it possible to identify the area-to-mass ratio of 274 uncorrelated objects.…”

Section: Introductionmentioning

confidence: 99%

Symplectic integration of space debris motion considering several Earth’s shadowing models

Hubaux

Lemaître

Delsate

et al. 2012

Advances in Space Research

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In this work, we present a symplectic integration scheme to numerically compute space debris motion. Such an integrator is particularly suitable to obtain reliable trajectories of objects lying on high orbits, especially geostationary ones. Indeed, it has already been demonstrated that such objects could stay there for hundreds of years. Our model takes into account the Earth's gravitational potential, luni-solar and planetary gravitational perturbations and direct solar radiation pressure. Based on the analysis of the energy conservation and on a comparison with a high order non-symplectic integrator, we show that our algorithm allows us to use large time steps and keep accurate results. We also propose an innovative method to model Earth's shadow crossings by means of a smooth shadow function. In the particular framework of symplectic integration, such a function needs to be included analytically in the equations of motion in order to prevent numerical drifts of the energy. For the sake of completeness, both cylindrical shadows and penumbra transitions models are considered. We show that both models are not equivalent and that big discrepancies actually appear between associated orbits, especially for high area-to-mass ratios.

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Section: Introductionmentioning

confidence: 99%

Symplectic integration of space debris motion considering several Earth’s shadowing models

Hubaux

Lemaître

Delsate

et al. 2012

Advances in Space Research

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“…where є is the small parameter of the expansion which represents the second zonal harmonic 2 J of the Earth's potential, and …”

Section: The Formulationmentioning

confidence: 99%

“…If the sun-synchronous orbit is high enough and the sub satellite point is initiated outside the Earth's shadow, then the illumination of the sub satellite point will be remain conti-nuously throughout the year. Since a sun-synchronous orbits follows the Sun, so the solar pressure perturbations cannot be neglected, if the orbit is un-shadowed, long period occur in all the orbital elements except semi-major axis [1] [2]. It is well known that Earth oblateness causes the orbital angular momentum vector of earth satellite to process about the Earth's polar axis.…”

Section: Introductionmentioning

confidence: 99%

Solar Radiation Pressure and Gravitational Waves Effects on Sun-Synchronous Orbits

Youssef¹

2018

WJM

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For certain values of semi-major axis and eccentricity, orbit plane precession caused by Earth oblate is synchronous with the mean orbital motion of the apparent Sun (a sun-synchronism). Many forces cause slow changes in the inclination and ascending node of sun-synchronous orbits. In this work, we investigate the analytical perturbations due to the direct solar radiation pressure and gravitational waves effects. A full analytical solution is obtained using technique of canonical Lie-transformation up to the order three in 2 J (the oblateness of the Earth). The solar radiation pressure and gravitational waves perturbations cause second order effects on all the elements of the elliptic orbit (the eccentricity, inclination, ascending node, argument of perigee, and semi-major axis) consequently these perturbations will cause disturbance in the sun-synchronism. Also we found that the perturbation or the behavior of gravitational waves almost the same as the perturbation or the behavior of solar radiation pressure and their coupling will incorporate the sun-synchronism through the secular rate of the ascending node precession.

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“…DAMAGE incorporates a semi-analytical orbital propagator that determines the rates of change in the classical orbital elements a, e, i, ω, Ω arising from perturbations induced by the Earth gravitational harmonics 6 , SRP 7 and lunisolar gravitational attraction 8 . Of particular interest to this study were changes in semi-major axis and eccentricity, as these values define the perigee.…”

Section: Long-term Orbital Propagationmentioning

confidence: 99%

The Stability of Disposal Orbits At Super-synchronous Altitudes

Lewis

2003

54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronaut

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An investigation of the stability of super-synchronous disposal orbits using University of Southampton's DAMAGE (Debris Analysis and Monitoring Architecture for the Geosynchronous Environment) is presented. The DAMAGE orbital propagator was used to analyse the influence of the initial perigee, eccentricity, right ascension of ascending node (RAAN) and argument of perigee, and the initial lunar RAAN, on the evolution of disposal orbit perigee over a 200-year period. This propagator includes perturbations arising from low-order gravitational harmonics, third-body influences and solar radiation pressure (SRP). The results of two sensitivity studies are presented. The first evolved 14,112 disposal orbits with initial perigees at the minimum altitude suggested by the IADC guideline, whilst the second study evolved 17,920 disposal orbits with initial perigees from 42,374 km to 42,464 km. The studies show that the initial perigee and eccentricity of the disposal orbit are the most important factors for maintaining the orbit above the protected region. Some sensitivity to the initial lunar RAAN, disposal orbit RAAN and argument of perigee was also found. These findings suggest that the IADC guideline specifying a preferred initial perigee is appropriate if it accompanies a guideline for the initial eccentricity of the disposal orbit.

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Short-period and long-period perturbations of a spherical satellite due to direct solar radiation

Cited by 65 publications

References 5 publications

Symplectic integration of space debris motion considering several Earth’s shadowing models

Symplectic integration of space debris motion considering several Earth’s shadowing models

Solar Radiation Pressure and Gravitational Waves Effects on Sun-Synchronous Orbits

The Stability of Disposal Orbits At Super-synchronous Altitudes

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