NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsDevelopment of Constraint Force Equation Methodology for Application to Multi-Body Dynamics Including Launch Vehicle Stage SeperationThe objective of this report is to develop and implement a physics based method for analysis and simulation of multi-body dynamics including launch vehicle stage separation. The constraint force equation (CFE) methodology discussed in this report provides such a framework for modeling constraint forces and moments acting at joints when the vehicles are still connected. Several stand-alone test cases involving various types of joints were developed to validate the CFE methodology. The results were compared with ADAMS(Registered Trademark) and Autolev, two different industry standard benchmark codes for multi-body dynamic analysis and simulations. However, these two codes are not designed for aerospace flight trajectory simulations. After this validation exercise, the CFE algorithm was implemented in Program to Optimize Simulated Trajectories II (POST2) to provide a capability to simulate end-to-end trajectories of launch vehicles including stage separation. The POST2/CFE methodology was applied to the STS-1 Space Shuttle solid rocket booster (SRB) separation and Hyper-X Research Vehicle (HXRV) separation from the Pegasus booster as a further test and validation for its application to launch vehicle stage separation problems. Finally, to demonstrate end-to-end simulation capability, POST2/CFE was applied to the ascent, orbit insertion, and booster return of a reusable two-stage-to-orbit (TSTO) vehicle concept. With these validation exercises, POST2/CFE software can be used for performing conceptual level end-to-end simulations, including launch vehicle stage separation, for problems similar to those discussed in this report.Document ID20160010566Acquisition SourceLangley Research CenterDocument TypeTechnical Publication (TP)AuthorsPamadi, Bandu N.*(NASA Langley Research Center Hampton, VA, United States)*Toniolo, Matthew D.*(NASA Langley Research Center Hampton, VA, United States)*Tartabini, Paul V.*(NASA Langley Research Center Hampton, VA, United States)*Roithmayr, Carlos M.*(NASA Langley Research Center Hampton, VA, United States)*Albertson, Cindy W.*(NASA Langley Research Center Hampton, VA, United States)*Karlgaard, Christopher D.*(Analytical Mechanics Associates, Inc. Hampton, VA, United States)*Date AcquiredAugust 24, 2016Publication DateJuly 1, 2016Subject CategorySpacecraft Design, Testing And PerformanceReport/Patent NumberL-20644NASA/TP-2016-219326NF1676L-23195Funding Number(s)WBS: WBS 869021.05.07.09.05Distribution LimitsPublicCopyrightPublic Use Permitted.Available DownloadsNameType20160010566.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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