The effect of the radiation pressure on the orbital evolution of geosynchronous objects

Kuznetsov, E. D.

doi:10.1134/s0038094611050078

Cited by 11 publications

(7 citation statements)

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“…3(b)). The fulfillment of the condition ensures the eccentricity's amplitude limitation depending on the initial value of the eccentricity specified by 0 ≈ 0.01 in (6). Here in cases Figs.…”

Section: Orbital Flipsmentioning

confidence: 92%

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Orbital flips due to solar radiation pressure for space debris in near-circular orbits

Belkin

Kuznetsov

2021

Acta Astronautica

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Orbital plane flips, a transition from prograde to retrograde motion or vice versa, is a phenomenon due to solar radiation pressure that is investigated. We consider initial near-circular orbits with different inclinations, including the vicinity of orbits of the GNSS satellites, GEO, geosynchronous orbits, and super-GEO region. Dynamical evolution of orbits is studied from a numerical simulation. Initial conditions for the objects are chosen in the GNSS orbit regions (GLONASS, GPS, BeiDou, Galileo) as well as 450-1100 km above to nominal semi-major axes of the navigation orbits, and in the vicinity of GEO, geosynchronous orbits, and super-GEO region. Initial data correspond to nearly circular orbits with the eccentricity 0.001. The initial inclination is varied from 55 • to 64.8 • . Initial values of longitude of ascending node are varied from 0 • to 350 • . High area-to-mass ratios are considered, at which orbital plane flips occur. Dynamical evolution covers periods of 24 and 240 years. The maximum inclination of the orbit is achieved when the longitude of the pericenter is sun-synchronous. Flips are possible only for objects with the area-to-mass ratio equal or more than 16 m 2 /kg (the radiation pressure coefficient is 1.44). The flips are caused precisely by solar radiation pressure. The Lidov-Kozai effect is suppressed by solar radiation pressure perturbations, affecting high area-to-mass ratio objects due to a secondary apsidal-nodal secular resonance.

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Section: Orbital Flipsmentioning

confidence: 92%

“…We can mention works focused on the orbital evolution of Geostationary Earth Orbits (GEO) (e.g. [5][6][7][8][9]) and Medium Earth Orbits (MEO) (e.g. [10][11][12][13][14][15]).…”

Section: Introductionmentioning

confidence: 99%

Orbital flips due to solar radiation pressure for space debris in near-circular orbits

Belkin

Kuznetsov

2021

Acta Astronautica

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“…where ≈ 4.56 × 10 −6 Nm −2 is the constant of the SRP, accounts for the mean reflectivity of the surface, A is the spacecraft cross-sectional area assumed constant, m is the mass of the spacecraft, AU is the Astronomical Unit, and the norm of ⊙ /‖ ⊙ ‖ 3 ⋅ AU 2 approximates 1. SRP model in (10) has been widely used in analyzing the effect of SRP on spacecraft absolute orbit and relative motion between two spacecraft [12,39,40]. It is noted that model of differential SRP perturbation in (10) is derived with assumption that the normal vector of spacecraft's surface points in the direction of the Sun [41].…”

Section: Differential 2 Perturbation the Most Important Nonsphericalmentioning

confidence: 99%

Automated Orbital Transfer and Hovering Control Using Artificial Potential

Wang

Zhang

2019

Mathematical Problems in Engineering

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On-orbit servicing for GEO targets has attracted great attention due to particular significance. In this study, the GEO nearby flying is considered, which denotes that the servicing spacecraft approaches GEO targets within tens of meters. Based on the analysis of differential spherical Earth gravity, J2 perturbation, third-body perturbation, and solar radiation pressure (SRP) between two spacecraft, a relative dynamics of GEO nearby flying is built, in which the differential SRP has great influence on relative motion. Therein, considering the differential SRP, an analytical solution to relative dynamics is obtained, which is an extension to CW equation’s solution. Based on the derived relative dynamics, a novel control method utilizing feedback compensation and artificial potential is developed for spacecraft orbital transfer and hovering at the desired position. During orbital transfer, a bounded space is constrained with maximum and minimum relative distance between two spacecraft. An improved repulsive potential based on Gauss function is designed to drive the servicer off the bound and guarantee the potential value converge to zero at the desired position. Meanwhile, a novel attractive potential about relative distance that drives the servicer to the desired position and to hover with high accuracy against perturbations is designed. Besides, a velocity potential with variable gain is designed to ensure that the servicer achieve the desired position without overshoot. The stability of the system is proved with Lyapunov theory, and the feasibility of the proposed control law is verified through numerical simulations with obvious advantages.

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“…They find drift rates (in absolute magnitudes) ranging from about 29 mt/yr (9:11 resonance) to about 142 mt/yr (5:4 resonance) with a variation of 33 mt/yr to 75 mt/yr close to the geosynchronous orbit (see Table 2 in Kuznetsov et al (2014)). Secular rates of drift in semi-major axis of about 500 mt/yr have also numerically been estimated in Kuznetsov & Zakharova (2015) for high area-to-mass ratio objects in highly elliptical orbits, the so-called Molniya orbits, close to the 22:45 resonance.As it has been recognized in Kuznetsov (2011), drift rates in the vicinity of the geosynchronous orbit may differ by orders of magnitude. Typical estimates for standard area-to-mass ratios range from -23 km/yr (Smirnov & Mikisha, 1993), -59 mt/yr (Slabinski, 1980), -51 mt/yr (Tueva & Avdyushev, 2006), and -80 mt/yr (all values taken from Kuznetsov, 2011).…”

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confidence: 95%

“…Trapping or escape from the resonance can be used to place the debris in convenient regions of the phase space.keywords Poynting-Robertson effect, Solar wind, Geostationary orbit, Space debris 1 consider several models as well as a different hierarchy of the forces which contribute to shape the dynamics. For example, it was widely shown (see, e.g., , Kuznetsov (2011 and references therein) that the effect of solar radiation pressure on GEO and MEO objects is more relevant for larger area-to-mass ratios. The dissipative contribution due to Poynting-Robertson and solar wind is definitely considered much less important.…”

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confidence: 99%

Poynting–Robertson drag and solar wind in the space debris problem

Lhotka

Celletti

Galeş

2016

Mon. Not. R. Astron. Soc.

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We analyze the combined effect of Poynting-Robertson and solar wind drag on space debris. We derive a model within Cartesian, Gaussian and Hamiltonian frameworks. We focus on the geosynchronous resonance, although the results can be easily generalized to any resonance. By numerical and analytical techniques, we compute the drift in semi-major axis due to Poynting-Robertson and solar wind drag. After a linear stability analysis of the equilibria, we combine a careful investigation of the regular, resonant, chaotic behavior of the phase space with a long-term propagation of a sample of initial conditions. The results strongly depend on the value of the areato-mass ratio of the debris, which might show different dynamical behaviors: temporary capture or escape from the geosynchronous resonance, as well as temporary capture or escape from secondary resonances involving the rate of variation of the longitude of the Sun. Such analysis shows that Poynting-Robertson and solar wind drag must be taken into account, when looking at the long-term behavior of space debris. Trapping or escape from the resonance can be used to place the debris in convenient regions of the phase space.keywords Poynting-Robertson effect, Solar wind, Geostationary orbit, Space debris 1 consider several models as well as a different hierarchy of the forces which contribute to shape the dynamics. For example, it was widely shown (see, e.g., , Kuznetsov (2011 and references therein) that the effect of solar radiation pressure on GEO and MEO objects is more relevant for larger area-to-mass ratios. The dissipative contribution due to Poynting-Robertson and solar wind is definitely considered much less important. However, such dissipative effects might become relevant on micro-meter size particles as well on large area-to-mass ratio space debris (various objects with high area-to-mass ratios are described, e.g., in Früh & Schildknecht (2012)).The aim of the current study is to settle the question of the role of Poynting-Robertson and solar wind (hereafter PR/SW) drag on space debris dynamics. The relevance of this question stems from the consideration that the drag might provoke a drift of the debris towards space regions where operating satellites are placed. To avoid collisions with functional satellites and a consequent possible generation of further debris, it is crucial to have a full control of the dynamics of space debris, including the prediction over long time scales of minor, but still relevant, effects like PR/SW. Our study shows that not only Poynting-Robertson drag, but also solar wind drag, are prominent forces that need to be included in the model to get an accurate estimate of the drift of space debris in the near-Earth environment.The first studies on the Poynting-Robertson effect in the artificial satellite problem date back to Slabinski (1980Slabinski ( , 1983, where the author states that the semi-major axis of a near synchronous satellite with small area-to-mass ratio can decrease at a rate of about 1 mt/yr. The secular evolution of...

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The effect of the radiation pressure on the orbital evolution of geosynchronous objects

Cited by 11 publications

References 11 publications

Orbital flips due to solar radiation pressure for space debris in near-circular orbits

Orbital flips due to solar radiation pressure for space debris in near-circular orbits

Automated Orbital Transfer and Hovering Control Using Artificial Potential

Poynting–Robertson drag and solar wind in the space debris problem

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