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

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 19.85:1 roller gear unit is the final reduction stage in the transmission.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1975
Accession Number
ADA014267

Entities

People

  • D. O. Adams
  • G. F. Gardner

Organizations

  • United Technologies Corporation

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Acquisition
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Data Acquisition
  • Fabrication
  • Fuselages
  • Helicopters
  • Horsepower
  • Measurement
  • Power Levels
  • Power Spectra
  • Resonant Frequency
  • Static Tests
  • Test And Evaluation
  • Test Facilities
  • Turboshaft Engines

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Electrical Engineering