This report presents the results of a helicopter tiedown test program. The primary purpose of this test was to evaluate a roller gear transmission in an aircraft installation and to conduct a 50-hour tiedown test at a power spectrum equivalent to helicopter military usage. The roller gear transmission transmits 3,000 hp at 203 rpm to a helicopter main rotor head. The transmission is powered by two General Electric axial-flow turboshaft engines, each producing 1,870 hp at 18,966 rpm. A 19.85:1 roller gear unit is the final reduction stage in the transmission.
3000-HP Roller Gear Transmission Development Program. Volume V. Aircraft Tiedown Testing
1975
150 pages
Report
Keine Angabe
Englisch
3000-HP roller gear transmission development program, volume II. Design report
Tema Archiv | 1975
|NTIS | 1972