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Synergistic Composite Design Data Approaches to Support both Propulsion and Airframe Applications
Navy SBIR 2008.2 - Topic N08-133 NAVAIR - Mrs. Janet McGovern - [email protected] Opens: May 19, 2008 - Closes: June 18, 2008 N08-133 TITLE: Synergistic Composite Design Data Approaches to Support both Propulsion and Airframe Applications TECHNOLOGY AREAS: Air Platform, Materials/Processes ACQUISITION PROGRAM: PEO JSF - Joint Strike Fighter; ACAT I The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), which controls the export and import of defense-related material and services. Offerors must disclose any proposed use of foreign nationals, their country of origin, and what tasks each would accomplish in the statement of work in accordance with section 3.5.b.(7) of the solicitation. OBJECTIVE: Develop innovative methods and analyses that can support both the propulsion and airframe communities' use of organic matrix composites with a single test data set. Experimentally and analytically derived solutions are sought. DESCRIPTION: The generation of organic matrix composite databases necessary to design aircraft structural and propulsion systems has traditionally been a time consuming, expensive endeavor. Furthermore, it has not been possible to develop a single design database that supports the needs of both propulsion systems and airframe structures. This results from the use of disparate approaches to the generation of composite design. Traditionally, propulsion design organizations have used un-notched A-basis design values and airframe design organizations have used notched B-basis allowables. Over time, methods and test matrices tailored to each application have evolved along divergent paths, resulting in data sets that are not translatable from airframe application to propulsion application, and vice versa. In recent years, structural use temperatures on military aircraft have increased, leading to the design of an organic matrix composite structure that operates in the 400-500�F range. This moderate temperature overlap with the needs of propulsion design presents an opportunity to develop and demonstrate methods, approaches and data sets that can satisfy both interests, while reducing the time and cost burden for overall air system design. PHASE I: Develop and demonstrate methods and approaches for the generation of design data that can be utilized by both the propulsion and airframe communities. PHASE II: Develop the design property values and corresponding data analysis to verify the approach. PHASE III: Fully validate methodology and implement on material systems for transition to the F-35. PRIVATE SECTOR COMMERCIAL POTENTIAL/DUAL-USE APPLICATIONS: The use of high temperature capable polymeric materials for structural and propulsion applications continues to grow in civil aerospace, as in the military sector. The methods developed in this work will reduce the cost of dual use development technology in a fashion similar to the overall goals of the program. REFERENCES: 2. http://www.compositesworld.com/hpc/issues/2003/May/100. 3. http://www.grc.nasa.gov/WWW/RT2002/5000/5150sutter.html. 4. http://www.sti.nasa.gov/tto/Spinoff2006/ip_4.html. 5. U.S. Pat. 3,745,148 (July 10, 1973) T. Serafini, P. Delvigs, R. Lightsey, (to The United States of America as represented by the Administrator of the National Aeronautics and Space Administration). 6. U. S. Pat. 4,560,742 (December 24, 1985) R. H. Pater (to The United States of America as represented by the Administrator of the National Aeronautics and Space Administration). 7. U. S. Pat. 5,322,924 (June 21, 1994) C. K. Chuang (to The United States of America as represented by the Administrator of the National Aeronautics and Space Administration). 8. U. S. Pat.5,760,168 (June 2, 1998) P. M. Hergenrother, J. G. Smith (to The United States of America as represented by the Administrator of the National Aeronautics and Space Administration). 9. Salin, I.M. and Seferis, J.C., "Anisotropic Degradation of Polymeric Composites: From Neat Resin to Composite," 17, (3), 430 (1996). 10. Bowles, K.J.; McCorkle, L.; Ingrahm, L., "Comparison of Graphite Fabric Reinforced PMR-15 and Avimid N Composites After Long Term Isothermal Aging at Various Temperatures," NASA TM-107529, 1998.
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