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Effect of Altitude, Right Ascension of Ascending Node and Inclination on Lifetime of Circular Lunar Orbits

International Journal of Astronomy and Astrophysics 2011年第3期1卷 155-163页

作者： shraddha gupta Ram Krishan Sharma 不详

The lifetime of a lunar satellite orbit is constrained by the non-spherical nature of the Moon’s gravity field. The orbital lifetime of lunar orbits depends significantly on the initial conditions of the orbit. Right ascension of ascending node (Ω) is one of the important orbital parameter affecting the orbital lifetime. In the present work we have analyzed the effect of Ω on the variation of lifetime with altitude for circular lunar orbits. It is found that at a particular initial altitude, a small increase in the altitude results in substantial increase in the orbital lifetime due to effect of the long periodic terms of Earth’s gravity on eccentricity and this transition altitude is different for different Ω. Further, it is observed that the variation of transition altitude with Ω follows a definite, but different trend for orbits with different inclinations. The transition altitude for polar orbits is found to be higher without the effect of Sun and Earth gravity. Variation of transition altitude with orbital inclination is also analyzed. Lifetimes of high altitude circular lunar orbits are analyzed and it is observed that at high altitudes lifetime decreases with altitude.

关键词： Lifetime of Lunar Orbits Transition Altitude Right Ascension of Ascending Node Polar Orbits Long-Periodic Effects of Earth’s Gravity

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Short-Term Orbit Prediction with J<sub>2</sub>and Mean Orbital Elements

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International Journal of Astronomy and Astrophysics 2011年第3期1卷 135-146页

作者： shraddha gupta M. Xavier James Raj R. K. Sharma 不详

An analytical theory for calculating perturbations of the orbital elements of a satellite due to J2 to accuracy up to fourth power in eccentricity is developed. It is observed that there is significant improvement in all the orbital elements with the present theory over second-order theory. The theory is used for computing the mean orbital elements, which are found to be more accurate than provided by Bhatnagar and taqvi’s theory (up to second power in eccentricity). Mean elements have a large number of practical applications.

关键词： Perturbation Due to J2 Mean Orbital Elements Short-Periodic Terms Osculating Orbital Elements Fourth Power in Eccentricit

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