Orbit design for Moon-Orbiting-Satellite
- Paper number
IAC-06-C1.P.5.05
- Author
Prof. Lin Liu, Nanjing University, China
- Coauthor
Dr. Hai-hong Wang, Nanjing University, China
- Coauthor
Mr. Hou Xiyun, Nanjing University, China
- Year
2006
- Abstract
More detailed theoretical analysis on the orbital lifetime, orbital inclination of Low-Moon-Orbiting satellite (LMOs) and High-Moon-Orbiting satellite (HMOs), the ’stable areas’ of long orbital lifetime is given in this paper, and numerical simulations under real force model were carried out. Although the absence of atmosphere around the Moon, LMOs and HMOs will impact on the Moon when the perifocus r p = a(1− e)is equal to the Moon’s semimajor axis a e , and the reason is that LMOs and HMOs’ perifocus r p will diminish due to the Moon’s nonspherical gravitational perturbation and the third body(the Earht and the Sun) gravitational perturbation. There are only short period terms with small amplitude in orbital semimajor axis a and they will not lead to obvious variation of r p . Thus, the reason why r p diminish greatly is the large amplitude long period terms Δ e l of the orbital eccentricity e. According to the theoretical analysis, the large amplitude long period terms Δ e l are mainly affected by the odd zonal harmonic terms of the lunar nonspherical gravitational potential, and it is directly related to orbital inclination i. According to our analytical solutions, the ’stable areas’ of orbital lifetime(i.e.|Δ e l |is very small) are given out as below:
i=0 o,27 o,50 o,77 o,85 o According to the character of sin i, there are also ’stable areas’ in90 ∼180 o and they are95 o,103 o,⋯. The mechanics and analytical solutions for the HMOs are also given in this paper.
Numerical simulations under full real force model were carried out: the perifocus altitude h p of LMOs (the mean altitude is h=100 km, e 0=0.001 ) for different inclination are given and the results are coincident with the theoretical analysis. The perifocus altitude doesn’t decrease greatly for LMOs in ’stable areas’ (such as i 0=85 o and95 o )during 10 years and the minimum altitude is still about 60km (the lunar gravity model is JPL’s LG75G). While in the ’unstable areas’ (such as i 0=40 o,90 o ), the lifetime are only 48 days and 172 days.
Numerical results presented in this paper are valuable for the orbit design of LMOs.
- Abstract document
- Manuscript document
IAC-06-C1.P.5.05.pdf (🔒 authorized access only).
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