Starting with Artemis IV, the human lander system (HLS) missions will utilize the Gateway as a staging point in a near rectilinear halo orbit (NRHO) between cislunar space and the lunar surface. The presence of a crew, Orion, and HLS will cause significant perturbations from docking and venting, while attitude requirements on Gateway can cause structural antenna blockage. The HLS mission timeline and perturbations are simulated considering antenna blockage to ground stations. Simulated DSN tracking data is generated and processed to produce a navigation state estimate for orbit maintenance maneuver (OMM) targeting. The starting epoch is varied to adjust tracking availability, and the volume of tracking data processed is reduced. Separately, the observability of perturbations in the NRHO with two-way tracking data is analyzed. The mission is simulated with imperfect knowledge of venting perturbations, and finally the estimation errors from propagating an estimated state from data cutoff (DCO) to maneuvers are investigated.
Navigation Performance Overview of Gateway During a Lunar Lander Mission
2024 AAS/AIAA Astrodynamics Specialist Conference ; 2024 ; Broomfield, CO, US
2024-08-11
Conference paper
No indication
English
LUNAR LANDER INTEGRATION WITH GATEWAY
TIBKAT | 2020
|British Library Conference Proceedings | 2005
|British Library Conference Proceedings | 2011
|Lunar lander mission evaluation lab
IEEE | 2009
|AIAA | 2011
|