Third-order secular Solution of the variational equations of motion of a satellite in orbit around a non-spherical planet

Ammar, M. K.; Shaboury, Samy M. El; Amin, M. R.

doi:10.1007/s10509-012-1038-1

Cited by 13 publications

(7 citation statements)

References 8 publications

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“…As only the zonal perturbation terms of geopotentials are considered in the design of reference repeat-groundtrack orbit, the Earth gravity field is axially symmetric (Kozai 1959;Ammar et al 2012). 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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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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“…+β 3 cos (4i) + β 4 cos (6i)) + J 3 2 R 6 n t a 6 (︀ 1 − e 2 )︀ 19/2 (β5 where the subscript (ob) stands for oblateness, µ is the Newtonian constant times mass of Earth, R the mean equatorial radius of the Earth, ω the argument of the perigee, J k the zonal harmonics, given by J 2 = 1.08263 × 10 −3 , J 3 = − 2.5322 × 10 −6 , J 4 = −1.6110 × 10 −6 , D 4 = J 2 2 + J 4 = −0.4389122 × 10 −6 , and α i and β j , i = 1, . .…”

Section: The Perturbation Due To Oblatenessmentioning

confidence: 99%

“…A semi-analytic theory for a low Earth orbit satellite, taking into account the perturbations due to Earth's oblateness and atmospheric drag *Corresponding Author: Mohamed R. Amin: Mathematics Department., College of Sciences and Arts, Qassim University, AlRass, Saudi Arabia; Theoretical Physics Dept., National Research Centre, Dokki, Giza, Egypt; Email: m.abdelhameid@qu.edu.sa was considered by Bezdek (2004) [5]. Ammar et al (2012) [6] studied the satellite motion under the Earth's oblateness up to the third order. They showed that the Earth's oblateness had a secular perturbation on the semi-major axis and on the eccentricity of the satellite orbit.…”

Section: Introductionmentioning

confidence: 99%

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Self-Maintenance Orbits Using The perturbations Due to Air Drag and Due to Earth's Oblateness

Amin

2020

Mechanics and Mechanical Engineering

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The focus of this paper is the design of a self-maintenance orbit using two natural forces against each other. The effect of perturbations due to Earth's oblateness up to the third order on both the semi-major axis and eccentricity for a low Earth orbit satellite together with the perturbation due to air drag on the same orbital parameters were used, in order to create self-maintenance orbits. Numerical results were simulated for a low earth orbit satellite, which substantiates the applicability of the results.

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“…They found that, these points are stable for 0 C µ µ < < and unstable for 1 2 C µ µ < < , and C µ depends on the radiating and oblateness coefficients. The influence of the eccentricity of the orbits of the primary bodies with or without radiation pressures on the existence of the equilibrium points and their stability was touched upon to an extent by [16], [19] and [20].…”

Section: µ µmentioning

confidence: 99%

Effect on L<sub>4,5</sub> in the ER3BP when Both Primaries are Radiating with Oblateness up to Zonal Harmonic J<sub>4</sub>

Singh

Ashagwu

2019

ILCPA

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This study examines the triangular points in the elliptic restricted three-body problem when both primaries are sources of radiation as well as oblate spheroids with oblateness up to zonal harmonic J4. The positions of triangular points and their critical mass ratio are seen to be affected by the eccentricity, semi major axis, radiation and oblateness of both primaries up to zonal harmonic J4. We highlight the effects of the said parameters on the locations of the triangular points of 61 CYGNI and STRUVE 2398. The triangular points of these systems are found to be unstable.

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Third-order secular Solution of the variational equations of motion of a satellite in orbit around a non-spherical planet

Cited by 13 publications

References 8 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

Self-Maintenance Orbits Using The perturbations Due to Air Drag and Due to Earth's Oblateness

Effect on L<sub>4,5</sub> in the ER3BP when Both Primaries are Radiating with Oblateness up to Zonal Harmonic J<sub>4</sub>

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