TY - GEN
T1 - Application of ZEM/ZEV guidance for closed-loop transfer in the earth-moon system
AU - Drozd, Kristofer
AU - Furfaro, Roberto
AU - Topputo, Francesco
N1 - Publisher Copyright:
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - The vision for advanced missions to the lunar far-side brings many challenges to the forefront of the space community. This paper focuses on two subjects pertaining to lunar far-side operations: utilization of a feedback guidance algorithm and the ability to exploit invariant manifolds for reaching desired states in a fuel efficient manner. The performance of the δr/δv form of the ZEM/ZEV (Zero-Effort-Miss/Zero-Effort-Velocity) feedback guidance algorithm is evaluated through scenarios in the Circular Restricted Three-Body Problem. All scenarios include the use of invariant manifolds to complete transfers. A grid search is implemented to find invariant manifolds and δr/δv trajectories that minimize the fuel used during the transfer. Overall, the use of the δr/δv guidance algorithm for targeting manifolds is successful when thrust is not saturated, but becomes problematic when thrust saturation exists. Conclusions were drawn by exploring halo to halo transfers, descending from, and ascending to the lunar far-side.
AB - The vision for advanced missions to the lunar far-side brings many challenges to the forefront of the space community. This paper focuses on two subjects pertaining to lunar far-side operations: utilization of a feedback guidance algorithm and the ability to exploit invariant manifolds for reaching desired states in a fuel efficient manner. The performance of the δr/δv form of the ZEM/ZEV (Zero-Effort-Miss/Zero-Effort-Velocity) feedback guidance algorithm is evaluated through scenarios in the Circular Restricted Three-Body Problem. All scenarios include the use of invariant manifolds to complete transfers. A grid search is implemented to find invariant manifolds and δr/δv trajectories that minimize the fuel used during the transfer. Overall, the use of the δr/δv guidance algorithm for targeting manifolds is successful when thrust is not saturated, but becomes problematic when thrust saturation exists. Conclusions were drawn by exploring halo to halo transfers, descending from, and ascending to the lunar far-side.
UR - http://www.scopus.com/inward/record.url?scp=85141610043&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85141610043&partnerID=8YFLogxK
U2 - 10.2514/6.2018-0958
DO - 10.2514/6.2018-0958
M3 - Conference contribution
AN - SCOPUS:85141610043
SN - 9781624105333
T3 - Space Flight Mechanics Meeting, 2018
BT - Space Flight Mechanics Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - Space Flight Mechanics Meeting, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -