3.5 Design, Manufacture and Test of Cryotank Components

McCarville, Douglas A.; Guzman, Juan C.; K., Dillon. Alexandra; Jackson, Justin; Birkland, Jordan O.

doi:10.1016/b978-0-12-803581-8.09958-6

Cited by 27 publications

(33 citation statements)

References 5 publications

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“…approaches are now considered based on this non-conventional laminate in applications ranging from cryogenic pressure vessels [1], to airplanes' wings [2], and even reusable space launchers [3].…”

Section: R a F Tmentioning

confidence: 99%

See 1 more Smart Citation

Energy release rate of the fiber/matrix interface crack in UD composites under transverse loading: debond-debond and debond-free boundary interactions

Stasio¹,

Vārna²,

Ayadi³

2019

Preprint

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The effects of crack shielding, finite thickness of the composite and fiber content on fiber/matrix debond growth in thin unidirectional composites are investigated analyzing Representative Volume Elements (RVEs) of different ordered microstructures. Debond growth is characterized by estimation of the Energy Release Rates (ERRs) in Mode I and Mode II using the Virtual Crack Closure Technique (VCCT) and the J-integral. It is found that increasing fiber content, a larger distance between debonds in the loading direction and the presence of a free surface close to the debond have all a strong enhancing effect on the ERR. The presence of fully bonded fibers in the composite thickness direction has instead a constraining effect, and it is shown to be very localized. An explanation of these observations is proposed based on mechanical considerations.

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Section: R a F Tmentioning

confidence: 99%

“…1 Corresponding author: luca.di.stasio@ltu.se .Preprint submitted to Theoretical and Applied Fracture MechanicsJuly 12, 2019…”

mentioning

confidence: 99%

Energy release rate of the fiber/matrix interface crack in UD composites under transverse loading: debond-debond and debond-free boundary interactions

Stasio¹,

Vārna²,

Ayadi³

2019

Preprint

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“…Taking as a reference the number of CCT programs that NASA has sponsored over the last 40 years (McCarville et al, 2017), the European Space Agency (ESA) and industry have decided to apply CCT's technology given the benefits involved in their performance. In comparison to standard cryogenic tanks materials for the space transportation sector, composites offer a reduction of the total weight of a space launcher, an increase in the payload mass performance and cost savings during manufacturing activities.…”

Section: Introductionmentioning

confidence: 99%

“…In addition to PHOEBUS project TRL demonstration objectives, NASA has learned a number of lessons for CCTs (McCarville et al, 2017) over the last 40 years that are a source of risks and/or challenges that push to reinforce the systems engineering perspective through an MBSE approach in order to prevent similar adverse situations. These risks and challenges come from the following sources:…”

Section: Introductionmentioning

confidence: 99%

MBSE Methodology Applied for a Technology Demonstrator in the Space Transportation Sector

Llano¹,

Quappen²

2020

INCOSE International Symp

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Over the last 40 years, NASA has sponsored many technology development programs for composite cryogenic tanks (CCT) in order to improve space launchers’ performance. However, they have learned certain lessons in terms of risk mitigation, design failures, lack of technology maturation and time constraints during development phases that push to reinforce the systems engineering perspective given the number of new functions, components and subsystems involved in these CCTs performance. The present paper suggests a Model‐Based Systems Engineering (MBSE) methodology to reduce the challenges that CCTs entail in a technology demonstrator program currently in a conceptual phase for the Ariane 6 upper stage. Topics such as a strong operational analysis; project instability; a Fully Integrated Operational System (FIOS) model combined with a Manufacturing, Assembly, Integration & Test (MAIT) model; requirements traceability; and model navigability issues are studied throughout the modelling process. Results from this approach show and ease the way to obtain information in a complex and large model intended to simulate our System of Interest (SoI)/CCTs life cycle. Consequently, CCTs can face NASA's aforementioned lessons learned from an early phase of the project in order to prevent similar adverse situations.

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“…The excellent strength-to-weight and stiffness-to-weight ratios, combined with controlled anisotropy of mechanical properties, has ensured a widening application of CFRPs. These characteristics of CFRPs are particularly beneficial in weight-conscious sectors of industry, such as aerospace (see, e.g., [ 1 , 2 ]).…”

Section: Introductionmentioning

confidence: 99%

Robustness of Empirical Vibration Correlation Techniques for Predicting the Instability of Unstiffened Cylindrical Composite Shells in Axial Compression

et al. 2020

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Thin-walled carbon fiber reinforced plastic (CFRP) shells are increasingly used in aerospace industry. Such shells are prone to the loss of stability under compressive loads. Furthermore, the instability onset of monocoque shells exhibits a pronounced imperfection sensitivity. The vibration correlation technique (VCT) is being developed as a nondestructive test method for evaluation of the buckling load of the shells. In this study, accuracy and robustness of an existing and a modified VCT method are evaluated. With this aim, more than 20 thin-walled unstiffened CFRP shells have been produced and tested. The results obtained suggest that the vibration response under loads exceeding 0.25 of the linear buckling load needs to be characterized for a successful application of the VCT. Then the largest unconservative discrepancy of prediction by the modified VCT method amounted to ca. 22% of the critical load. Applying loads exceeding 0.9 of the buckling load reduced the average relative discrepancy to 6.4%.

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3.5 Design, Manufacture and Test of Cryotank Components

Cited by 27 publications

References 5 publications

Energy release rate of the fiber/matrix interface crack in UD composites under transverse loading: debond-debond and debond-free boundary interactions

Energy release rate of the fiber/matrix interface crack in UD composites under transverse loading: debond-debond and debond-free boundary interactions

MBSE Methodology Applied for a Technology Demonstrator in the Space Transportation Sector

Robustness of Empirical Vibration Correlation Techniques for Predicting the Instability of Unstiffened Cylindrical Composite Shells in Axial Compression

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