Experimental Determination of Material Properties for Inflatable Aeroshell Structures

Hutchings, Allison; Braun, Robert D.; Masuyama, Kento; Welch, Joseph V.

doi:10.2514/6.2009-2949

Cited by 11 publications

(12 citation statements)

References 10 publications

(17 reference statements)

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“…Additionally, the material properties used are those described in Section II, which result in a shear modulus of 150 ksi. In contrast, the actual Kevlar ® material is orthotropic and testing indicates that the material may have a shear modulus closer to 5 ksi 9 , over an order of magnitude lower than the value used in this preliminary tension cone analysis.…”

Section: Tunnel Sting and Support Hardwarementioning

confidence: 75%

Structural Verification and Modeling of a Tension Cone Inflatable Aerodynamic Decelerator

Tanner¹,

Cruz²,

Braun³

2010

51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials ConferenceSelf Cite

9
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16
0

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Verification analyses were conducted on membrane structures pertaining to a tension cone inflatable aerodynamic decelerator using the analysis code LS-DYNA. The responses of three structures -a cylinder, torus, and tension shell -were compared against linear theory for various loading cases. Stress distribution, buckling behavior, and wrinkling behavior were investigated. In general, agreement between theory and LS-DYNA was very good for all cases investigated. These verification cases exposed the important effects of using a linear elastic liner in membrane structures under compression. Finally, a tension cone wind tunnel test article is modeled in LS-DYNA for which preliminary results are presented. Unlike data from supersonic wind tunnel testing, the segmented tension shell and torus experienced oscillatory behavior when subjected to a steady aerodynamic pressure distribution. This work is presented as a work in progress towards development of a fluid-structures interaction mechanism to investigate aeroelastic behavior of inflatable aerodynamic decelerators. Nomenclature

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Section: Tunnel Sting and Support Hardwarementioning
confidence: 75%

Structural Verification and Modeling of a Tension Cone Inflatable Aerodynamic Decelerator
Tanner¹,
Cruz²,
Braun³
2010
51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials ConferenceSelf Cite
9
0
16
0
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“…In addition it is not possible to implement isotropic models such as Comer -Levy as the fabric is a nonlinear orthotropic material. This was observed in the uniaxial UTS tests and has been investigated in detail in previous studies [37] [38]. Further in depth study is required to accurately describe the fabrics material properties in the inflatable boom application and will be conducted in future investigations and applied to numerical models for both inflatable and hybrid booms.…”

Section: Experimental Setup and Developmentmentioning
confidence: 98%

Experimental research on tape spring supported space inflatable structures
Cook
¹
,
Walker
²

2016
Acta Astronautica
12
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3
0
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“…The state‐of‐the‐art in experimentally determining inflatable, braided fabric tube effective mechanical properties for structural modelling was advanced in the following regards compared to prior research in this area : The braided tubes tested here are relatively large diameter and full‐scale for the 6‐m diameter HIAD. Digital image correlation (DIC) was used to provide insight into braid deformation mechanics during inflation and under externally applied stress. This allowed measurement of all parameters needed for input to netting theory calculations, and showed that simple surface averaging of shear strain will not yield the correct gross mechanical properties for these particular test articles. The gas bladder was independently tested to assess its effect on inflated tube properties, and was found to contribute significantly to the longitudinal stiffness of the tubes. Reasonable methods were developed to determine effective lamina constitutive properties from the tension–torsion test data that are suitable for direct input to shell‐based 3D finite‐element models. Individual straight fibre tows extracted from the braid were independently tested to allow comparisons with the stiffness mentioned above as a function of inflation pressure. A close examination of the braid surface during inflation with the DIC system confirmed that the surface flattens with increasing pressure due primarily to braid de‐crimping, a significant driver of the increase in stiffness with inflation pressure. …”

Section: Background and Objectivesmentioning
confidence: 99%

Experimental Determination of Inflatable, Braided Tube Constitutive Properties
Clapp
¹
,
Davids
²
,
Goupee
³

et al. 2015
Strain
5
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0
0
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The primary objective of this study was to conduct constitutive tests of relatively large diameter inflatable, braided fabric tubes at different inflation pressures and braid angles in order to quantify the longitudinal modulus, in-plane shear modulus and effective lamina stiffness properties. The stiffness properties quantified here are of high interest because the same braided fabric tubes have been used in the construction of test articles for a major, multi-year, ground based test campaign led by the United States National Aeronautics and Space Administration. These properties are also input directly into high-fidelity yet computationally intensive 3D shell-based finite-element simulations of the large, inflatable structures. Experimental methods employed during this study included tension-torsion testing, uniaxial tension testing of individual fibre tows, and uniaxial tension testing of gas bladder coupons. Digital image correlation was used to measure all of the geometric information that is necessary to perform netting theory calculations. The test results indicate that fabric in-plane shear modulus is highly dependent on both braid angle and inflation pressure, but that longitudinal stiffness is quite small and relatively unaffected by braid angle and pressure. In addition to advancing the state-of-the art in experimental constitutive property determination of inflatable, braided fabric, this study includes the development of a method to back calculate lamina properties from the experimental results that are suitable for use as input to commonly used finite-element programmes. The digital image correlation data revealed spatial variation of shear strain that was important to consider when computing the gross shear stiffness. Digital image correlation data also captured the braid surface flattening with increasing inflation pressure, which supports the fibre de-crimping theory.

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Experimental Determination of Material Properties for Inflatable Aeroshell Structures

Cited by 11 publications

References 10 publications

Structural Verification and Modeling of a Tension Cone Inflatable Aerodynamic Decelerator

Structural Verification and Modeling of a Tension Cone Inflatable Aerodynamic Decelerator

Experimental research on tape spring supported space inflatable structures

Experimental Determination of Inflatable, Braided Tube Constitutive Properties

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