Titanium alloy foil-inserted carbon fiber/epoxy composites for cryogenic propellant tank application

Ogasawara, Toshio; Arai, Norio; Fukumoto, R; Ogawa, Teiichiro; Yokozeki, Tomohiro; Yoshimura, Akinori

doi:10.1080/09243046.2013.844756

Cited by 21 publications

(3 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Metal liners can be used (type III COPV) instead of all-composite structures (type IV COPV), but the metal-composite interface generates further difficulties in manufacturing and increases weight [257]. Therefore, research was carried out on replacing the solid metal liners with lighter, composite-compatible and non-permeable films [258][259][260][261][262][263][264].…”

Section: Permeabilitymentioning

confidence: 99%

Properties of cryogenic and low temperature composite materials – A review

2020

View full text Add to dashboard Cite

Section: Permeabilitymentioning

confidence: 99%

Properties of cryogenic and low temperature composite materials – A review

2020

View full text Add to dashboard Cite

“…Such tanks possess high strength and low weight compared to conventional metal tanks. [1][2][3][4][5] However, one of the most crucial issues for this type of tank is polymer compatibility with the contents.…”

Section: Introductionmentioning

confidence: 99%

Study on the compatibility of modified cyanate ester resin in liquid oxygen

Wang

Gao

et al. 2020

SPE Polymers

View full text Add to dashboard Cite

A cyanate ester (CE) resin co-modified with epoxy (EP) and bismaleimide (BMI) as the continuous phase, and phenolphthalein poly (ether sulfone) (PES-C) as the dispersed phase were used for developing liquid oxygen (LOX) composite tanks. Gaseous oxygen (GOX) anti-oxidation, LOX impact sensitivity, ductility, and cycle durability is a critical index for materials in LOX applications. Added components significantly improved material ductility at low temperature versus neat CE resin because of microstructure changes. However, improvement in thermal resistance was not achieved without tradeoffs; the addition of BMI improved thermal resistance but decreased durability. The failure mechanism of a tank containing GOX was related to reaction with oxygen. LOX impact sensitivity (IRS) is associated with anti-oxidation and flaming retardance of the samples. Micro-domains tended to separate from the continuous phase more during the LOX impact test versus the GOX test and was accompanied by increasing ductility and anti-oxidation. Cycle durability was affected more by the difference in coefficient of thermal expansion between the continuous and PES-C phases rather than immersion time. In summary, CE resin (CYEP6BM5) co-modified with PES-C, EP, and BMI showed good LOX compatibility including IRS value of 2%, 19 cycles durability, and flaming retardance of UL94V0 and may be applied for LOX composite tanks.

show abstract

“…The three first developed FMLs continue to be used extensively across the aerospace market with GLass Laminate Aluminium Reinforced Epoxy (GLARE) being selected for the A380 upper fuselage and Boeing 777 [48,63], Aramid Reinforced ALluminium Laminates (ARALL) which continues to be utilised in supersonic aircraft wings and tails [59] and CArbon Reinforced ALluminium Laminates (CARALL) in aircraft carrier cargo doors [56]. Furthermore, additional hybrid laminate structures have been further implemented over the past two decades with a Carbon Fibre Reinforced Polymer (GFRP)-titanium FMLs being used to improve gas barrier properties in propellent tank applications [40] and graphite-titanium FMLs in the biomedical industry [16].…”

Section: Fibre Metal Laminatesmentioning

confidence: 99%

Investigating mode I and mixed mode fracture toughness values in fibre metal laminates

Evans¹

View full text Add to dashboard Cite

The military, bio-medical and particularly aerospace industries are continually motivated to produce materials which inhibit increased mechanical properties. This has led to advanced material design stemming from combining materials in hopes of producing a more established hybrid material which exceeds the limitations of each individual material constituent. Over the past 70 years and substantially over the last twenty years, this has led to the development of Fibre Metal Laminates (FMLs) which consist of thin layered composite/metal alloy sheets. Particularly, FMLs offer; increased impact tolerances, fatigue resistance and a higher modulus of elasticity albeit at lower densities. First and foremost, I would like to thank my advisor throughout this Thesis topic, A/Prof. Martin Veidt for his endless guidance, support and encouragement. You have provided me with the resources and knowledge to make this Thesis possible and I appreciate you giving me the opportunity to experience hybrid composite structures. In addition, I would like to also thank Kurt Mills for his time in manufacturing the hybrid samples. Furthermore, for his abilities in calibrating the measurement techniques and microscopy images. Finally, I would like to thank all other members that made the time to discuss ideas and provide clarity to tasks and results. These people include; Dr. Juan P. Torres who demonstrated the measurement techniques, Mitch Dunn who arranged the composite samples being water-jet cut and Dr. Michael Heitzmann who provided the FEM knowledge. v

show abstract

Titanium alloy foil-inserted carbon fiber/epoxy composites for cryogenic propellant tank application

Cited by 21 publications

References 22 publications

Properties of cryogenic and low temperature composite materials – A review

Properties of cryogenic and low temperature composite materials – A review

Study on the compatibility of modified cyanate ester resin in liquid oxygen

Investigating mode I and mixed mode fracture toughness values in fibre metal laminates

Contact Info

Product

Resources

About