Show simple item record

dc.contributor.authorWibben, D.R.
dc.contributor.authorLevine, A.
dc.contributor.authorMcAdams, J.V.
dc.contributor.authorAntreasian, P.G.
dc.contributor.authorRieger, S.
dc.contributor.authorGetzandanner, K.M.
dc.contributor.authorMoreau, M.C.
dc.contributor.authorLauretta, D.S.
dc.date.accessioned2022-03-17T01:57:25Z
dc.date.available2022-03-17T01:57:25Z
dc.date.issued2022
dc.identifier.citationWibben, D. R., Levine, A., McAdams, J. V., Antreasian, P. G., Rieger, S., Getzandanner, K. M., Moreau, M. C., & Lauretta, D. S. (2022). OSIRIS-REx Orbit Trim Strategy. AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022.
dc.identifier.isbn9781624106316
dc.identifier.doi10.2514/6.2022-2471
dc.identifier.urihttp://hdl.handle.net/10150/663627
dc.description.abstractOne of the more challenging aspects of the trajectory design for the OSIRIS-REx (Origins, Spectral Interpretation, Resource Identification, and Security-Regolith Explorer) mission at asteroid Bennu was maneuvering while in orbit. The orbital dynamics were highly perturbed by various sources, most notably solar radiation pressure, which degraded accuracy of long term predictions of the spacecraft’s location in orbit. Generally, the Navigation team had to solve three separate issues: correcting a perturbed orbit, changing to a different orbit, or phasing the orbit to place the spacecraft at a specific location at a specific time. The team composed a common framework using up to two maneuvers that could solve all of these problems using an identical schedule that allowed for consistent planning long before the final trajectory could be designed. This orbit trim strategy was successfully used for the first time in the Orbital B phase of the mission to maximize the duration of usable observing geometry in a time-variable orbit with strict operational limits. It was used an additional 3 times throughout the mission to adjust and/or change the orbit, most notably altering the orbit in the weeks prior to the successful Touch-And-Go (TAG) sample collection attempt. This same strategy was used to phase the orbit a total 10 times in preparation for each of the science sorties over potential sample sites, the TAG Rehearsals, and TAG. The trim strategy was demonstrated to be robust and performed exceptionally well in all aspects, which proved critical to a successful sample collection.
dc.language.isoen
dc.publisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
dc.rightsThis material is declared a work of the U.S. Government and is not subject to copyright protection in the United States.
dc.rights.urihttps://creativecommons.org/publicdomain/mark/1.0/
dc.titleOSIRIS-REx Orbit Trim Strategy
dc.typeProceedings
dc.typetext
dc.contributor.departmentUniversity of Arizona
dc.identifier.journalAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
dc.description.notePublic domain article
dc.description.collectioninformationThis item from the UA Faculty Publications collection is made available by the University of Arizona with support from the University of Arizona Libraries. If you have questions, please contact us at repository@u.library.arizona.edu.
dc.eprint.versionFinal published version
dc.source.journaltitleAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
refterms.dateFOA2022-03-17T01:57:25Z


Files in this item

Thumbnail
Name:
6.2022-2471.pdf
Size:
1.633Mb
Format:
PDF
Description:
Final Published Version

This item appears in the following Collection(s)

Show simple item record

This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States.
Except where otherwise noted, this item's license is described as This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States.