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http://dx.doi.org/10.5139/JKSAS.2021.49.4.321

Derivations of Buckling Knockdown Factors for Composite Cylinders Considering Various Shell Thickness Ratios and Slenderness Ratios  

Kim, Do-Young (Chungnam National University)
Sim, Chang-Hoon (Chungnam National University)
Kim, Han-Il (Chungnam National University)
Park, Jae-Sang (Chungnam National University)
Yoo, Joon-Tae (Korea Aerospace Research Institute)
Yoon, Young-Ha (Korea Aerospace Research Institute)
Lee, Keejoo (Korea Aerospace Research Institute)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.49, no.4, 2021 , pp. 321-328 More about this Journal
Abstract
This paper derives numerically new buckling Knockdown factors for the lightweight design of the composite propellant tanks for space launch vehicles. A nonlinear finite element analysis code, ABAQUS, is used for the present postbuckling analysis of composite cylinders under compressive loads. Various thickness ratios (R/t) and slenderness ratios (L/R) are considered and Single Perturbation Load Approach is applied to represent the geometric initial imperfection of the composite cylinder. For the composite cylinder with thickness ratio of 500 and slenderness ratio of 2.04, the buckling Knockdown factor derived in this work is higher by 84.38% than NASA's previous buckling design criteria. Therefore, it is investigated that a lightweight design is possible when the present Knockdown factors are used for the design of composite propellant tanks. In addition, it is shown that global buckling loads and buckling Knockdown factors decrease as the thickness ratio or slenderness ratio of composite cylinders increases.
Keywords
Buckling Knockdown Factor; Propellant Tank; Composite Cylinder; Postbuckling Analysis;
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