TY - GEN
T1 - OSIRIS-REx Extended Mission Trajectory Design & Target Search
AU - Sutter, Brian
AU - Hatten, Noble
AU - Hughes, Kyle
AU - Getzandanner, Kenneth M.
AU - Englander, Jacob
AU - Mudek, Alec
AU - Wibben, Daniel
AU - Williams, Kenneth
AU - Penas, Miguel Benayas
AU - Moreau, Michael
AU - Lauretta, Dante S.
AU - Dellagiustina, Daniella N.
AU - Nolan, Michael
AU - Polit, Anjani T.
N1 - Funding Information:
This material is based upon work supported by NASA under Contracts NNM10AA11C and NNG13FC02C. OSIRIS-REx is the third mission in NASA’s New Frontiers Program. Dante Lauretta of the University of Arizona, Tucson, is the principal investigator, and the University of Arizona also leads the science team and the science observation planning and data processing. Daniella DellaGuistina of the University of Arizona is the OSIRIS-REx deputy principal investigator and the principal investigator for the extended mission. Lockheed Martin Space Systems in Denver built the spacecraft and is providing flight operations. Goddard Space Flight Center and KinetX Aerospace are responsible for navigating the OSIRIS-REx spacecraft.
Funding Information:
The authors acknowledge members of the OSIRIS-REx and extended mission teams including Flight Dynamics System (FDS), the University of Arizona science planning team, the Lockheed Martin flight operations team, and overall project management. This material is based upon work supported by NASA under Contracts NNM10AA11C and NNG13FC02C. OSIRIS-REx is the third mission in NASA?s New Frontiers Program. Dante Lauretta of the University of Arizona, Tucson, is the principal investigator, and the University of Arizona also leads the science team and the science observation planning and data processing. Daniella DellaGuistina of the University of Arizona is the OSIRIS-REx deputy principal investigator and the principal investigator for the extended mission. Lockheed Martin Space Systems in Denver built the spacecraft and is providing flight operations. Goddard Space Flight Center and KinetX Aerospace are responsible for navigating the OSIRIS-REx spacecraft.
Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.
PY - 2022
Y1 - 2022
N2 - After jettisoning its Sample Return Capsule (SRC) containing regolith samples from the near-Earth asteroid (101955) Bennu to Earth in September 2023, the Origins, Spectral Interpretation, Resource Identification, and Security–Regolith Explorer (OSIRIS-REx) spacecraft will perform a divert maneuver and safely fly by Earth at an altitude of 250 km. SRC return and the divert maneuver officially mark the completion of the spacecraft’s primary mission; however, it will continue on in heliocentric orbit with a nearly fully-functional instrument suite and enough propellant for nearly 600 m/s Delta-V. The post-Earth flyby trajectory fortuitously enables an exciting extended mission opportunity: rendezvous with the near-Earth asteroid (99942) Apophis immediately following its historic Earth close approach in April 2029. In this paper, we detail the discovery, optimization, and analysis of the Apophis rendezvous trajectory for an extended OSIRIS-REx mission. We also present the technical approach for an alternate target search and corresponding results, assessing the alternate trajectories compared to the baseline Apophis rendezvous from a trajectory design standpoint.
AB - After jettisoning its Sample Return Capsule (SRC) containing regolith samples from the near-Earth asteroid (101955) Bennu to Earth in September 2023, the Origins, Spectral Interpretation, Resource Identification, and Security–Regolith Explorer (OSIRIS-REx) spacecraft will perform a divert maneuver and safely fly by Earth at an altitude of 250 km. SRC return and the divert maneuver officially mark the completion of the spacecraft’s primary mission; however, it will continue on in heliocentric orbit with a nearly fully-functional instrument suite and enough propellant for nearly 600 m/s Delta-V. The post-Earth flyby trajectory fortuitously enables an exciting extended mission opportunity: rendezvous with the near-Earth asteroid (99942) Apophis immediately following its historic Earth close approach in April 2029. In this paper, we detail the discovery, optimization, and analysis of the Apophis rendezvous trajectory for an extended OSIRIS-REx mission. We also present the technical approach for an alternate target search and corresponding results, assessing the alternate trajectories compared to the baseline Apophis rendezvous from a trajectory design standpoint.
UR - http://www.scopus.com/inward/record.url?scp=85123893216&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85123893216&partnerID=8YFLogxK
U2 - 10.2514/6.2022-2469
DO - 10.2514/6.2022-2469
M3 - Conference contribution
AN - SCOPUS:85123893216
SN - 9781624106316
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
BT - AIAA SciTech Forum 2022
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
Y2 - 3 January 2022 through 7 January 2022
ER -