• Journal of Astronomy and Space Sciences
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• 제31권3호
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• pp.199-204
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• 2014

This paper intends to highlight the effect of the third-body in an inclined orbit on a spacecraft orbiting the primary mass. To achieve this goal, a new origin of coordinate is introduced in the primary and the X-axis toward the node of the spacecraft. The disturbing function is expanded up to the second order using Legendre polynomials. A double-averaged analytical model is exploited to produce the evolutions of mean orbital elements as smooth curves.

• Journal of Astronomy and Space Sciences
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• 제38권2호
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• pp.93-103
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• 2021

In this work, the problem of resonance caused by some gravitational potentials due to Mercury and a third body, namely the Sun, together with some non-gravitational perturbations, specifically coronal mass ejections and solar wind in addition to radiation pressure, are investigated. Some simplifying assumptions without loss of accuracy are employed. The considered force model is constructed. Then the Delaunay canonical set is introduced. The Hamiltonian of the problem is obtained then it is expressed in terms of the Deluanay canonical set. The Hamiltonian is re-ordered to adopt it to the perturbation technique used to solve the problem. The Lie transform method is surveyed. The Hamiltonian is doubly averaged. The resonance capture is investigated. Finally, some numerical simulations are illustrated and are analyzed. Many resonant inclinations are revealed.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제21회 추계학술대회 논문집
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• pp.65-70
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• 2003

본 연구에서는 섭동가속도의 변화식으로 주어지는 궤도 섭동 방정식으로부터 지구 편원현상과 대기저항에 의해 기인하는 궤도요소들의 변화를 표현하고 궤도 일회전당 변화량을 근거로 하여 대기저항에 의한 속도 보정과 그에 필요한 연료소모량을 효과적으로 예측하는 방법을 제시하고 그 기법을 다목적위성 궤도해석에 적용하였다. 그리고 궤도 해석을 위해 위성에 영향을 미치는 섭동력을 비대칭 중력장, 대기 저항력, 태양과 달의 인력, 태양 복사압에 의한 영향을 계산하여 정량적으로 비교 분석하였다.