Publication Date:
2019-07-13
Description:
The application of forces in multi-body dynamical environments to permit 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 that 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 spacecrafts into Earth-Moon libration orbits by means of these applications.
Keywords:
Astrodynamics
Type:
GSFC-E-DAA-TN15167
,
Acta Astronautica (ISSN 0094-5765); 73; 237-249
Format:
text