Characteristics of aircraft with integrated regenerative engine propulsion systems and aircraft with nonregenerative turboshaft engines were determined in order to assess the relative advantages and disadvantages of the engines in a utility transport helicopter application. Conceptual designs of aircraft, powered by regenerative engines and nonregenerative engines of approximately 1000 shp, were based on existing and future Army mission requirements for a typical utility transport helicopter. Comparative weight and performance parameters, reliability aspects, maintenance requirements, life-cycle cost and cost effectiveness for various missions, and overall mission effectiveness and system cost were assessed for these aircraft. (Author)
Regenerative Engline Powered Aircraft Design Study
1972
213 pages
Report
Keine Angabe
Englisch
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