Computer Science – Performance
Scientific paper
Jul 1992
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992jpnt.confrq...b&link_type=abstract
AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 28th, Nashville, TN, July 6-8, 1992. 8 p.
Computer Science
Performance
Combustion Chambers, Liquid Propellant Rocket Engines, Nozzle Design, Performance Prediction, Titan Launch Vehicles, Bumpers, Computer Aided Design, Optimization, Thermal Protection
Scientific paper
The use of a concurrent engineering team is described in the context of a nozzle-contour optimization study and the related redesign of the exit closure on the Titan IV stage-one engine. The design tasks included: (1) payload increase of 300 lbs; (2) ordnance reduction; (3) development of integrated external thermal insulation; and (4) the improvement of subassembly reliability. The design changes are detailed and illustrated with references to the inputs of members of the concurrent engineering team from all affected disciplines. The nozzle extension has an optimized area ratio of 16.7:1 and an ablative skirt and bumper designed for the configuration. The revised design is shown to be effective in terms of reaching design goals such as reduced life-cycle costs and enhanced reliability, and the concurrent engineering approach facilitates the accelerated development of the product.
Beaudette B. P.
Higgins W. Jr. E.
Meland L. C.
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