Accession Number:

ADA014267

Title:

3000-HP Roller Gear Transmission Development Program. Volume 5. Aircraft Tiedown Testing

Descriptive Note:

Final rept.

Corporate Author:

UNITED TECHNOLOGIES CORP STRATFORD CT SIKORSKY AIRCRAFT DIV

Personal Author(s):

Report Date:

1975-07-01

Pagination or Media Count:

150.0

Abstract:

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 19.851 roller gear unit is the final reduction stage in the transmission.

Subject Categories:

  • Helicopters
  • Machinery and Tools

Distribution Statement:

APPROVED FOR PUBLIC RELEASE