Structural Concepts and Aerodynamic Analysis for Low Radar Cross Section (LRCS) Fuselage Configurations.

摘要

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.