NASA Technical Reports Server (NTRS) 20030003790: Buckling Design Studies of Inverted, Oblate Bulkheads for a Propellant TankReport as inadecuate




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An investigation of the deformation and buckling characteristics of a composite, oblate bulkhead that has an inverted geometry and is subjected to pressure-only loading is presented for three bulkhead geometries and thicknesses. The effects of a stiffening support ring at the bulkhead to cylinder interface are also evaluated. Buckling analyses cond

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AIAA 2002-1525 BUCKLING DESIGN STUDIES OF INVERTED, OBLATE BULKHEADS FOR A PROPELLANT TANK Stanley S.
Smeltzer III* NASA Langley Research Center Hampton, VA 23681-2199 and Lockheed Lynn M.
Bowman* Martin Engineering and Sciences Corporation Hampton, VA 23681-2199 Abstract An investigation of the deformation and buckling characteristics of a composite, oblate bulkhead that has an inverted geometry and is subjected to pressure-only loading is presented for three bulkhead geometries and thicknesses. The effects of a stiffening support ring at the bulkhead to cylinder interface are also evaluated. Buckling analyses conducted using the axisymmetric shell code BOSOR4 are discussed for several bulkhead ellipsoidal ellipsoidal * Aerospace Engineer, Mechanics Aeronautical Engineer. maj or axis (in.) minor axis (in.) Branch. Copyright © 2001 by the American Institute of Aeronautics U.S.
Code.
The U.S.
Government has a royalty-free license All other rights are reserved by the copyright owner. American Member, AIAA P r s z internal tank pressure (psi.) tank radius (in.) arc length tank longitudinal axis The past decade has provided numerous studies that have identified various reusable launch vehicle (RLV) configurations 1-3as well as strategies intended to optimize their performance, a-6 An important component in each one of these vehicle optimization strategies is the willingness to trade increased structural component weight for an overall reduction in vehicle weight or vehicle performance. All of these endeavors have been conducted with one goal in mind: to develop a RLV capable of providing cost-eftbctive ($1000-lbm) access to low-earth-orbit by reducing launch and operations costs.
One of the important areas related to the development of a future reusable launch vehicle is the capability for accurately predicting optimum vehicle weight based on a variety of component configurations; such as tanks, intertanks, or thrust structures. The current strategy for th...






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