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Analytical micromechanics modeling technique developed for ceramic matrix composites analysis
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Min, James B. |
| Copyright Year | 2005 |
| Description | Ceramic matrix composites (CMCs) promise many advantages for next-generation aerospace propulsion systems. Specifically, carbon-reinforced silicon carbide (C/SiC) CMCs enable higher operational temperatures and provide potential component weight savings by virtue of their high specific strength. These attributes may provide systemwide benefits. Higher operating temperatures lessen or eliminate the need for cooling, thereby reducing both fuel consumption and the complex hardware and plumbing required for heat management. This, in turn, lowers system weight, size, and complexity, while improving efficiency, reliability, and service life, resulting in overall lower operating costs. |
| File Size | 126110 |
| Page Count | 3 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20050217295 |
| Archival Resource Key | ark:/13960/t75t8m28s |
| Language | English |
| Publisher Date | 2005-06-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Ceramic Matrix Composites Propulsion System Performance Mathematical Models Carbon Fiber Reinforced Plastics High Strength Propulsion System Configurations Operating Temperature Spacecraft Propulsion Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
