The objectives of this study were: (1) to develop structural concepts for three low radar cross section (LRCS) fuselage configurations constructed of conventional materials; (2) to determine the effects of these concepts on the weight, cost, fail-safety, and maintainability of the three configurations; (3) to compare these findings with those of a baseline UH-60A helicopter, and thus select the structural concept that is the lowest in weight and cost and the easiest to maintain; (4) to assess the application of advanced materials for each configuration; (5) to identify high technical risk areas; (6) to develop overall design tranding data for helicopters, using the three fuselage configurations of conventional and advanced materials; (7) to conduct an analytical investigation of the aerodynamic loads, vertical drag and mission performance of the three low radar cross section (LRCS) configurations; and (8) to compare these findings with those of the baseline UH-60 helicopter. Structural concepts developed for the three LRCS configurations showed that extensive reshaping, as exemplified by Configuration 2, would increase fuselage weight from that of the baseline UH-60A fuselage by 223 pounds and cost by 3.65 percent. When advanced materials were used, Configuration 2 decreased from the baseline fuselage weight and cost by 118 pounds and 3.98 percent respectively.
Structural Concepts and Aerodynamic Analysis for Low Radar Cross Section (LRCS) Fuselage Configurations
1978
141 pages
Report
No indication
English
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