Long-term perturbations due to a disturbing body in elliptic inclined orbit |
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Authors: | Xiaodong Liu Hexi Baoyin Xingrui Ma |
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Institution: | (1) School of Aerospace, Tsinghua University, 100084 Beijing, China |
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Abstract: | In the current study, a double-averaged analytical model including the action of the perturbing body’s inclination is developed
to study third-body perturbations. The disturbing function is expanded in the form of Legendre polynomials truncated up to
the second-order term, and then is averaged over the periods of the spacecraft and the perturbing body. The efficiency of
the double-averaged algorithm is verified with the full elliptic restricted three-body model. Comparisons with the previous
study for a lunar satellite perturbed by Earth are presented to measure the effect of the perturbing body’s inclination, and
illustrate that the lunar obliquity with the value 6.68∘ is important for the mean motion of a lunar satellite. The application to the Mars-Sun system is shown to prove the validity
of the double-averaged model. It can be seen that the algorithm is effective to predict the long-term behavior of a high-altitude
Martian spacecraft perturbed by Sun. The double-averaged model presented in this paper is also applicable to other celestial
systems. |
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Keywords: | |
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