The method of osculating parameters is used to obtain the integral orbit restrictedness condition around the colinear libration center in the restricted elliptical three body problem. It is shown that, if a restricted orbit exists, it can be found by solving the equations of spacecraft motion under the above mentioned conditions.
Limitation of Spacecraft Orbit Near Colinear Libration Center of Limited Elliptical Three Body Problem (Abstract Only)
1987
1 pages
Report
No indication
English
Satellite Libration on a Elliptical Orbit
NTIS | 1965
|Attitude pointing schemes and spacecraft configurations for libration-point-orbit spacecraft
Online Contents | 2017
|Attitude pointing schemes and spacecraft configurations for libration-point-orbit spacecraft
Online Contents | 2017
|End-of-life disposal concepts for Libration Point Orbit and Highly Elliptical Orbit missions
Online Contents | 2014
|Orbit Design of Spacecraft on Elliptical Orbit
Springer Verlag | 2018
|