<i>Theory of Satellite Geodesy: Applications of Satellites to Geodesy</i>

Kaula, W. M.

doi:10.1063/1.3033941

Cited by 235 publications

(327 citation statements)

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“…Thus, the disturbing potential acting on the satellite can be formulized as the series of zonal harmonics from Kaula (1963Kaula ( , 1966 …”

Section: -24mentioning

confidence: 99%

High-precision repeat-groundtrack orbit design and maintenance for Earth observation missions

Jia

et al. 2017

Celest Mech Dyn Astr

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The focus of this paper is the design and station keeping of repeat-groundtrack orbits for Sun-synchronous satellite. A method to compute the semimajor axis of the orbit is presented together with a station-keeping strategy to compensate for the perturbation due to the atmospheric drag. The results show that the nodal period converges gradually with the increase of the order used in the zonal perturbations up to J15. A differential correction algorithm is performed to obtain the nominal semimajor axis of the reference orbit from the inputs of the desired nodal period, eccentricity, inclination and argument of perigee. To keep the satellite in the proximity of the repeat-groundtrack condition, a practical orbit maintenance strategy is proposed in the presence of errors in the orbital measurements and control, as well as in the estimation of the semimajor axis decay rate. The performance of the maintenance strategy is assessed via the Monte Carlo simulation and the validation in a high fidelity model. Numerical simulations substantiate the validity of proposed mean-elements-based orbit maintenance strategy for repeat-groundtrack orbits.

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“…Thus, the disturbing potential acting on the satellite can be formulized as the series of zonal harmonics from Kaula (1963Kaula ( , 1966 …”

Section: -24mentioning

confidence: 99%

High-precision repeat-groundtrack orbit design and maintenance for Earth observation missions

Jia

et al. 2017

Celest Mech Dyn Astr

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“…Using the formulae given by [11] for the functions F nmp and G npq , the explicit expression of the above terms can be found in Appendix A. of the resonances when the eccentricity is in the range e ∈ [0, 0.5]. However, for the 1:3 resonance, there is a term of order four in the eccentricity, precisely T 2204 , which plays a very important rôle for moderate and large eccentricities (see Section 5.3).…”

Section: Secular and Resonant Hamiltonianmentioning

confidence: 99%

“…where the inclination and eccentricity functions F nmp , G npq can be computed by wellknown recursive formulae (see, e.g., [11]). The angle S nmpq is defined as…”

Section: Introductionmentioning

confidence: 99%

A study of the main resonances outside the geostationary ring

Celletti

Galeş

2015

Advances in Space Research

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Abstract. We investigate the dynamics of satellites and space debris in external resonances, namely in the region outside the geostationary ring. Precisely, we focus on the 1:2, 1:3, 2:3 resonances, which are located at about 66 931.4 km, 87 705.0 km, 55 250.7 km, respectively. Some of these resonances have been already exploited in space missions, like XMM-Newton and Integral.Our study is mainly based on a Hamiltonian approach, which allows us to get fast and reliable information on the dynamics in the resonant regions. Significative results are obtained even by considering just the effect of the geopotential in the Hamiltonian formulation. For objects (typically space debris) with high area-to-mass ratio the Hamiltonian includes also the effect of the solar radiation pressure. In addition, we perform a comparison with the numerical integration in Cartesian variables, including the geopotential, the gravitational attraction of Sun and Moon, and the solar radiation pressure.We implement some simple mathematical tools that allows us to get information on the terms which are dominant in the Fourier series expansion of the Hamiltonian around a given resonance, on the amplitude of the resonant islands and on the location of the equilibrium points. We also compute the Fast Lyapunov Indicators, which provide a cartography of the resonant regions, yielding the main dynamical features associated to the external resonances. We apply these techniques to analyze the 1:2, 1:3, 2:3 resonances; we consider also the case of objects with large area-to-mass ratio and we provide an application to the case studies given by XMM-Newton and Integral.

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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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Theory of Satellite Geodesy: Applications of Satellites to Geodesy

Cited by 235 publications

References 0 publications

High-precision repeat-groundtrack orbit design and maintenance for Earth observation missions

High-precision repeat-groundtrack orbit design and maintenance for Earth observation missions

A study of the main resonances outside the geostationary ring

The Stability of Disposal Orbits At Super-synchronous Altitudes

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