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dc.contributor.authorLedsinger, Laura Anneen_US
dc.contributor.authorOlds, John R.en_US
dc.date.accessioned2006-03-17T15:59:12Z
dc.date.available2006-03-17T15:59:12Z
dc.date.issued2000-09
dc.identifier.urihttp://hdl.handle.net/1853/8409
dc.description8th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization Long Beach, CA, September 6-8, 2000.en_US
dc.description.abstractFully reusable two-stage-to-orbit vehicle designs that incorporate 'branching' trajectories during their ascent are of current interest in the advanced launch vehicle design community. Unlike expendable vehicle designs, the booster of a reusable system must fly to a designated landing site after staging. Therefore, both the booster return branch and the orbital upper stage branch along with the lower ascent trajectory are of interest after the staging point and must be simultaneously optimized in order to achieve an overall system objective. Current and notable designs in this class include the U. S. Air Force Space Operations Vehicle designs with their 'pop-up' trajectories, the Kelly Astroliner, the Kistler K-l, the two-stage-to-orbit vehicle Stargazer, and NASA's proposed liquid flyback booster designs (Space Shuttle booster replacement). The solution to this problem using an industrystandard trajectory optimization code (POST) typically requires at least two separate computer jobs — one for the orbital branch, from the ground to orbit, and one for the flyback branch, from the staging point to the landing site. These jobs are coupled and their data requirements are interdependent. These requirements must be taken into consideration when optimizing the entire trajectory. This paper analyzes the results of branching trajectory optimization for the Kistler K-l launch vehicle with respect to computational efficiency and data consistency for various solution methods. In particular, these methods originate from the field of Multidisciplinary Design Optimization (MDO).
dc.format.extent708419 bytes
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.publisherGeorgia Institute of Technologyen_US
dc.relation.ispartofseriesSSDL ; AIAA 2000-4884en_US
dc.subjectReusable launch vehicles
dc.subjectTrajectory analysis
dc.subjectProgram to Optimize Simulated Trajectories (POST)
dc.subjectMultidisciplinary design optimization
dc.subjectTrajectory optimization
dc.titleOptimized Solutions for the Kistler K- 1 Branching Trajectory Using MDO Techniquesen_US
dc.typePaper


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