Cryogenic Composite Tank Design for Next Generation Launch Technology

Abumen, Galib H.; Kosareo, Daniel N.; Roche, Joseph M.

doi:10.2514/6.2004-3390

Cited by 11 publications

(10 citation statements)

References 2 publications

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“…Several stress analyses for cryogenic fuel tank design have been performed [12][13][14][15][16][17][18][19][20]. Glaessgen et al presented the initial ply level thermal and mechanical stress analyses to determine the causes of the X-33 liquid-hydrogen tank failure [14].…”

Section: Introductionmentioning

confidence: 99%

An Initial and Progressive Failure Analysis for Cryogenic Composite Fuel Tank Design

Pickle

Morgan

et al. 2007

Journal of Composite Materials

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Thermal residual stresses, internal pressure stresses, and acceleration stresses during launch were evaluated and quantified for cryogenic composite fuel tank design. Both failure initiation and progression of graphite/epoxy laminate system (IM7/977-2) [0/90/90/0/0/90] s and graphite/BMI laminate system (IM7/5250-4) [0/90/90/0/0/90] s were investigated using the non-isothermal classical laminate and plate theory (CLPT) and the maximum stress failure criterion. The thermal residual stresses in the transverse direction are the dominant stresses on each ply in the launch stage. After initial ply cracking, through-the-thickness temperature change of a laminate related to fuel leakage as well as a laminate stiffness matrix change was applied to the progressive failure analysis. The fuel leakage-based progressive analysis shows a higher number of initial ply cracking does not necessarily mean a higher chance of matrix cracking in all plies. The graphite/BMI laminate has such an advantage as transverse thermo-mechanical resistance over the graphite/epoxy laminate at an initial exposure to À253 C and 1500 kPa. In terms of complete laminate matrix cracking, however, the graphite/ epoxy laminate is more resistant to transferring stresses to other plies than the graphite/BMI laminate.KEY WORDS: cryogenic composite fuel tank, progressive failure analysis, fuel leakage, IM7/977-2 (graphite/epoxy laminate system), IM7/5250-4 (graphite/ BMI laminate system).

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Section: Introductionmentioning

confidence: 99%

An Initial and Progressive Failure Analysis for Cryogenic Composite Fuel Tank Design

Pickle

Morgan

et al. 2007

Journal of Composite Materials

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“…Numerous studies on the design of composite pressure vessels subjected to internal and external pressure have been conducted at room temperature [4][5][6][7][8][9][10][11]. Several stress analyses for cryogenic fuel tank design have been performed [12][13][14][15][16][17][18][19][20]. Glaessgen et al presented the initial ply level thermal and mechanical stress analyses to determine the causes of the X-33 liquid-hydrogen tank failure [14].…”

Section: Introductionmentioning

confidence: 99%

“…Glaessgen et al presented the initial ply level thermal and mechanical stress analyses to determine the causes of the X-33 liquid-hydrogen tank failure [14]. Abumeri et al performed a finite element stress analysis of IM7/977-2 laminate at À2538C (À4238F) temperature, 207 kPa (30 psi) internal fuel pressure, and 2.5-3 g launch inertia force [15]. However, a detailed computational algorithm was not given in either paper.…”

Section: Introductionmentioning

confidence: 99%

RETRACTION: An Initial and Progressive Failure Analysis for Cryogenic Composite Fuel Tank Design

2008

Journal of Composite Materials

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Thermal residual stresses, internal pressure stresses, and acceleration stresses during launch were evaluated and quantified for cryogenic composite fuel tank design. Both failure initiation and progression of graphite/epoxy laminate system (IM7/977-2) [0/90/90/0/0/90] s and graphite/BMI laminate system (IM7/5250-4) [0/90/90/0/0/90] s were investigated using the non-isothermal classical laminate and plate theory (CLPT) and the maximum stress failure criterion. The thermal residual stresses in the transverse direction are the dominant stresses on each ply in the launch stage. After initial ply cracking, through-the-thickness temperature change of a laminate related to fuel leakage as well as a laminate stiffness matrix change was applied to the progressive failure analysis. The fuel leakage-based progressive analysis shows a higher number of initial ply cracking does not necessarily mean a higher chance of matrix cracking in all plies. The graphite/BMI laminate has such an advantage as transverse thermo-mechanical resistance over the graphite/epoxy laminate at an initial exposure to À2538C and 1500 kPa. In terms of complete laminate matrix cracking, however, the graphite/epoxy laminate is more resistant to transferring stresses to other plies than the graphite/BMI laminate.KEY WORDS: cryogenic composite fuel tank, progressive failure analysis, fuel leakage, IM7/977-2 (graphite/epoxy laminate system), IM7/5250-4(graphite/BMI laminate system).

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“…The most probable cause of the failure was determined to be a combination of the following phenomena [1,[12][13][14]:…”

Section: X-33 Composite Lh2 Cryotankmentioning

confidence: 99%

“…Further tests were performed to fill, apply internal and external loads, and drain the tank repeatedly 40 times, in order to study its structural integrity under cryogenic temperatures and its reusability [14][15][16].…”

Section: Space Launch Initiative (Sli) Composite Cryotank Programmentioning

confidence: 99%

The Application of Carbon Fiber Composites in Cryotank

Zheng¹,

Zeng²,

Zhang³

et al. 2018

Solidification

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To meet the design goal for lightweighting the next-generation launch vehicles, carbon fiber reinforced polymeric-based composites are being explored for cryogenic fuel tank applications. The applications of carbon fiber composites in liquid hydrogen (LH2) and liquid oxygen (LOX) fuel tanks were introduced in this chapter. The materials, processing, and design of DC-XA LH2 tank, X-33 LH2 tank, SLI LH2 tank, and CCTD Program tank were discussed. Lockheed Martin LOX tank and Space X LOX tank were introduced. Technology development, materials development, and development trend of cryogenic fuel tanks were discussed. Thin-ply hybrid laminates and out-of-autoclave tanks are projected for future space missions.

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Cryogenic Composite Tank Design for Next Generation Launch Technology

Cited by 11 publications

References 2 publications

An Initial and Progressive Failure Analysis for Cryogenic Composite Fuel Tank Design

An Initial and Progressive Failure Analysis for Cryogenic Composite Fuel Tank Design

RETRACTION: An Initial and Progressive Failure Analysis for Cryogenic Composite Fuel Tank Design

The Application of Carbon Fiber Composites in Cryotank

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