Shell Buckling Knockdown Factors

Metadata Updated: July 17, 2020

The Shell Buckling Knockdown Factor (SBKF) Project, NASA Engineering and Safety Center[HTML_REMOVED](NESC) Assessment #: 07-010-E, was established in March of 2007 by the NESC in[HTML_REMOVED]collaboration with the former NASA Constellation Program (CxP) and now the Space Launch System (SLS) Program. The SBKF Project has the goal of[HTML_REMOVED]developing and experimentally validating improved (i.e., less-conservative, more robust)[HTML_REMOVED]analysis-based shell buckling design factors (a.k.a., knockdown factors (KDFs)) and developing[HTML_REMOVED]design recommendations for launch vehicle structures. Shell buckling knockdown factors have been historically based on test data from laboratory-scale[HTML_REMOVED]test articles obtained from the 1930s through the 1960s. The knockdown factors are used to account[HTML_REMOVED]for the differences observed between the theoretical buckling load and the buckling load obtained[HTML_REMOVED]from test. However, these test-based KDFs may not be relevant for modern launch- vehicle designs,[HTML_REMOVED]and are likely overly conservative for many designs. Significant advances in structural stability[HTML_REMOVED]theory, high-fidelity analysis methods, manufacturing, and testing are[HTML_REMOVED]enabling the development of new, less conservative, robust analysis-based knockdown factors for[HTML_REMOVED]modern structural concepts. Preliminary design studies indicate that implementation of new[HTML_REMOVED]knockdown factors can enable significant weight savings in these vehicles and will help mitigate[HTML_REMOVED]some of NASA[HTML_REMOVED]s launch-vehicle development and performance risks, by reducing reliance on[HTML_REMOVED]large-scale testing, and providing high-fidelity estimates of as-built structural performance,[HTML_REMOVED]increased payload capability, and improved structural reliability.To achieve its KDF development and implementation goals, the SBKF Project is engaged in several[HTML_REMOVED]work areas including launch-vehicle design trade studies, subcomponent and component level design,[HTML_REMOVED]analysis and structural testing, and shell buckling design technology development including[HTML_REMOVED]analysis-method development, analysis benchmarking and standardization, and analysis-based KDF[HTML_REMOVED]development. Finite-element analysis is used extensively in all these work areas. In particular,[HTML_REMOVED]there are four main categories analyses conducted by SBKF and include:1) high-fidelity structural simulations, 2) imperfection sensitivity studies, 3) test article[HTML_REMOVED]design and analysis and 4) exploratory studies. Each of these types of analysis may have different[HTML_REMOVED]analysis objectives and utilize different modeling approaches that depend on the results required[HTML_REMOVED]to meet the Project needs. A description of the four main categories follows.[HTML_REMOVED]High-fidelity structural simulationsHigh-fidelity structural simulations are defined as simulations that can predict accurately the[HTML_REMOVED]complex behavior of a structural component or an assembly of components (e.g., virtual structural[HTML_REMOVED]test) and often require a significant level of modeling detail and knowledge of the structural[HTML_REMOVED]system (e.g., its physical behavior and expected variability). Models are considered high-fidelity[HTML_REMOVED]if results predicted with these models correlate with[HTML_REMOVED]test data to within a small range of variance and represent accurately the true physical behavior[HTML_REMOVED]of the structure. The permissible amount of variance is determined based on the analysis[HTML_REMOVED]requirements defined by the Project in accordance with the intended end use of the predicted data.[HTML_REMOVED]High-fidelity shell buckling analysis objectives considered by the SBKF Project often require the[HTML_REMOVED]accurate prediction of stiffnesses, local and global deformations, strains, load paths and[HTML_REMOVED]buckling-induced load redistribution, and buckling and failure loads and modes. To achieve these[HTML_REMOVED]analysis goals, the models typically must accurately represent loading and boundary conditions, and[HTML_REMOVED]expected or measured geometric and material varia

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Public: This dataset is intended for public access and use. License: No license information was provided. If this work was prepared by an officer or employee of the United States government as part of that person's official duties it is considered a U.S. Government Work.

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Dates

Metadata Created Date August 1, 2018
Metadata Updated Date July 17, 2020

Metadata Source

Harvested from NASA Data.json

Additional Metadata

Resource Type Dataset
Metadata Created Date August 1, 2018
Metadata Updated Date July 17, 2020
Publisher Space Technology Mission Directorate
Unique Identifier TECHPORT_33077
Maintainer
Public Access Level public
Bureau Code 026:00
Metadata Context https://project-open-data.cio.gov/v1.1/schema/catalog.jsonld
Metadata Catalog ID https://data.nasa.gov/data.json
Schema Version https://project-open-data.cio.gov/v1.1/schema
Catalog Describedby https://project-open-data.cio.gov/v1.1/schema/catalog.json
Harvest Object Id e260a497-0f92-4261-8474-4ed921e7c00b
Harvest Source Id 39e4ad2a-47ca-4507-8258-852babd0fd99
Harvest Source Title NASA Data.json
Data First Published 2018-06-26
Homepage URL https://techport.nasa.gov/view/33077
Data Last Modified 2020-01-29
Program Code 026:027
Source Datajson Identifier True
Source Hash 9f536635c61a7177720c178e89b1d713b6d1aa47
Source Schema Version 1.1

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