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1
Periodic, Quasi-Periodic and Chaotic Motions in Celestial ...
A feasible strategy is to consider a spacecraft on a WSB trajectory having the
periselenium distance equal to R. For example, a constellation of satellites of
commune radius R = 1,938km is considered, then nominal WSB trajectory ...
Alessandra Celletti, Sylvio Ferraz-Mello,
2007
2
Fundamentals of Astrodynamics and Applications
... for the Sun, they are aphelion and perihelion; for the Earth, apogee and
perigee; for the Moon, aposelenium, and periselenium, and so forth. Commonly,
we refer to the distance of the closest point in the orbit to the primary focus as the
radius ...
3
Operations Research in Space and Air
The second part of the trajectory depends on the orbital parameters at the Moon,
in particular the eccentricity, the periselenium anomaly and the argument of the
ascending node. The inclination is fixed because the orbit at the Moon must be ...
Tito A. Ciriani, G. Fasano, S. Gliozzi,
2003
4
Technology of Lunar Exploration
Two-impulse transfers are employed if it becomes necessary to change the
periselenium altitude or orientation of the return trajectory, to account for
variations with time in the moon's position relative to Earth.and sun. Indirect
return can be ...
5
Science and Technology Series: An American Astronautical ...
An American Astronautical Society Publication Steve M. Durst. Solid line of
Figure 8 gives selenocentric energy versus the time for the final part of this
trajectory T,. Dashed line Pr corresponds to a passive passage of the
periselenium F. There ...
6
Proceedings of the International Lunar Conference ...
Dashed line Pr corresponds to a passive passage of the periselenium F. There is
an escape in ~ 37 days, here E=0 again (point Es). Hence, the capture is
temporary. For the trajectory Ti, in the XY plane, Figure 9 gives a prolongation of
...
Steve M. Durst, American Astronautical Society,
2004
7
Orbital Motion, Fourth Edition
For satellite orbits of long life, the distance should probably be still further
decreased to 20000km. The required periselenium velocity of the elliptic orbit of
aposelenium 20000 km is then found from equation (12.21) by putting a\ = 1738
km and ...
8
Advances in Astronautical Sciences
the following parameters are considered: • Perigee departure date • Right
ascension of the GTO ascending node • First manoeuvre size • Second
manoeuvre date • Periselenium date • Hyperbolic arrival velocity vector at flyby,
osculating at ...
9
Orbital mechanics and mission design: proceedings of an ...
the following parameters are considered: • Perigee departure date • Right
ascension of the GTO ascending node • First manoeuvre size • Second
manoeuvre date • Periselenium date • Hyperbolic arrival velocity vector at flyby,
osculating at ...
Jerome Teles, American Astronautical Society,
1989
10
The foundations of astrodynamics
(3) Periselenium passage would occur at or near the third quarter lighting of the
Moon. (4) Reentry conditions would be suitable for a manned mission. (5)
Vehicle touchdown would occur in the continental United States. The orbits
chosen ...