Aerodynamic flow, thermal flow, and stress analyses of a proposed 2.5-in braided composite ablative nozzle were conducted. The nozzle was made up of PAN based carbon fiber and Primaset Cyanate Ester resin. The designed thermal and structural layers’ thicknesses were 0.62-in and 0.42-in, respectively. The objective of this paper is to establish the thermal stability and structural integrity of the nozzle. A ballistic profile of 17 seconds burn at 740 psi maximum pressure was used in the analysis. The combustion gas flow was subsonic, sonic, and supersonic, respectively, in the inlet, throat, and exit sections of the nozzle. The exit plane Mach number was 2.32. Three thermochemical states were considered: 100% efficiency, 72% efficiency and no aluminum combustion and 72% efficiency and 100% aluminum combustion. Flow analysis was conducted by NAT92 Code, thermal analysis by CMAFLOW92 Code, and structural analysis by ANSYS. Ablation rates for the three cases were 0.023, 0.047, and 0.01-in/sec, respectively. The recession life of thermal layer was 27, 13, and 62 sec for the three cases. Stress analysis of the nozzle due to aerodynamic pressure and temperature resulted in low strains and presents no concern.
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ASME 2002 Joint U.S.-European Fluids Engineering Division Conference
July 14–18, 2002
Montreal, Quebec, Canada
Conference Sponsors:
- Fluids Engineering Division
ISBN:
0-7918-3616-9
PROCEEDINGS PAPER
Analysis of 3-D Braided Composite Ablative Rocket Nozzle Available to Purchase
Kunigal N. Shivakumar,
Kunigal N. Shivakumar
North Carolina A&T State University, Greensboro, NC
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Aaron Cozart
Aaron Cozart
Aerospace Corporation, Los Angeles, CA
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Kunigal N. Shivakumar
North Carolina A&T State University, Greensboro, NC
Aaron Cozart
Aerospace Corporation, Los Angeles, CA
Paper No:
FEDSM2002-31422, pp. 281-288; 8 pages
Published Online:
February 24, 2009
Citation
Shivakumar, KN, & Cozart, A. "Analysis of 3-D Braided Composite Ablative Rocket Nozzle." Proceedings of the ASME 2002 Joint U.S.-European Fluids Engineering Division Conference. Volume 2: Symposia and General Papers, Parts A and B. Montreal, Quebec, Canada. July 14–18, 2002. pp. 281-288. ASME. https://doi.org/10.1115/FEDSM2002-31422
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