Publication Date:
2019-07-13
Description:
The application of forces in multi-body dynamical environments to pennit the transfer of spacecraft from Earth orbit to Sun-Earth weak stability regions and then return to the Earth-Moon libration (L1 and L2) orbits has been successfully accomplished for the first time. This demonstrated transfer is a positive step in the realization of a design process that can be used to transfer spacecraft with minimal Delta-V expenditures. Initialized using gravity assists to overcome fuel constraints; the ARTEMIS trajectory design has successfully placed two spacecraft into EarthMoon libration orbits by means of these applications.
Keywords:
Astrodynamics; Spacecraft Design, Testing and Performance; Astronautics (General)
Type:
LEGNEW-OLDGSFC-GSFC-LN-1022
,
International Astronautical Congress; Sep 27, 2010 - Oct 01, 2010; Prague; Czechoslovakia
Format:
application/pdf
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