Abstract
The basic mechanical performances of carbon fiber reinforced plastics (CFRP) material systems are experimentally and analytically evaluated to discuss their applicability to the cryogenic propellant tanks of planned future reusable launch vehicles. The materials are based on different types of epoxy matrices, bismaleimide matrix and PEEK. The temperature dependent anisotropic elastic constants and thermal expansion coefficients are experimentally obtained and used in the analytical predictions of delamination propagation, matrix crack onset, and propellant leakage. The use of temperature dependent material constants is essential for analysis with higher accuracy. Static tensile tests revealed that the matrix cracks tend to take place at drastically lower mechanical load under cryogenic environment, posing the possibility of propellant leakage through the chain of these matrix cracks. Interlaminar fracture toughness of epoxy based composite increased at cryogenic condition. Numerical predictions of delaminations and matrix cracks based on the simple energy release rate calculations are shown to be in good agreement with the experimental results. Simple conductance model of thicknesswise propellant leakage through the chain of matrix cracks is developed and successfully compared with the gas helium leakage test.
| Original language | English |
|---|---|
| Title of host publication | 41st Structures, Structural Dynamics, and Materials Conference and Exhibit |
| Publication status | Published - 2000 |
| Externally published | Yes |
| Event | 41st Structures, Structural Dynamics, and Materials Conference and Exhibit 2000 - Atlanta, GA Duration: 2000 Apr 3 → 2000 Apr 6 |
Other
| Other | 41st Structures, Structural Dynamics, and Materials Conference and Exhibit 2000 |
|---|---|
| City | Atlanta, GA |
| Period | 00/4/3 → 00/4/6 |
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ASJC Scopus subject areas
- Civil and Structural Engineering
- Mechanics of Materials
- Building and Construction
- Architecture
Cite this
Mechanical performance of CF/polymer composite laminates under cryogenic conditions. / Aoki, Takahira; Ishikawa, Takashi; Kumazawa, Hisashi; Morino, Yoshiki.
41st Structures, Structural Dynamics, and Materials Conference and Exhibit. 2000.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Mechanical performance of CF/polymer composite laminates under cryogenic conditions
AU - Aoki, Takahira
AU - Ishikawa, Takashi
AU - Kumazawa, Hisashi
AU - Morino, Yoshiki
PY - 2000
Y1 - 2000
N2 - The basic mechanical performances of carbon fiber reinforced plastics (CFRP) material systems are experimentally and analytically evaluated to discuss their applicability to the cryogenic propellant tanks of planned future reusable launch vehicles. The materials are based on different types of epoxy matrices, bismaleimide matrix and PEEK. The temperature dependent anisotropic elastic constants and thermal expansion coefficients are experimentally obtained and used in the analytical predictions of delamination propagation, matrix crack onset, and propellant leakage. The use of temperature dependent material constants is essential for analysis with higher accuracy. Static tensile tests revealed that the matrix cracks tend to take place at drastically lower mechanical load under cryogenic environment, posing the possibility of propellant leakage through the chain of these matrix cracks. Interlaminar fracture toughness of epoxy based composite increased at cryogenic condition. Numerical predictions of delaminations and matrix cracks based on the simple energy release rate calculations are shown to be in good agreement with the experimental results. Simple conductance model of thicknesswise propellant leakage through the chain of matrix cracks is developed and successfully compared with the gas helium leakage test.
AB - The basic mechanical performances of carbon fiber reinforced plastics (CFRP) material systems are experimentally and analytically evaluated to discuss their applicability to the cryogenic propellant tanks of planned future reusable launch vehicles. The materials are based on different types of epoxy matrices, bismaleimide matrix and PEEK. The temperature dependent anisotropic elastic constants and thermal expansion coefficients are experimentally obtained and used in the analytical predictions of delamination propagation, matrix crack onset, and propellant leakage. The use of temperature dependent material constants is essential for analysis with higher accuracy. Static tensile tests revealed that the matrix cracks tend to take place at drastically lower mechanical load under cryogenic environment, posing the possibility of propellant leakage through the chain of these matrix cracks. Interlaminar fracture toughness of epoxy based composite increased at cryogenic condition. Numerical predictions of delaminations and matrix cracks based on the simple energy release rate calculations are shown to be in good agreement with the experimental results. Simple conductance model of thicknesswise propellant leakage through the chain of matrix cracks is developed and successfully compared with the gas helium leakage test.
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M3 - Conference contribution
AN - SCOPUS:84896884746
BT - 41st Structures, Structural Dynamics, and Materials Conference and Exhibit
ER -