Rotor System Evaluation. Phase 1
Abstract
Flight testing was conducted on a UH-60A Black Hawk helicopter in support of the NASA-Ames Modern Technology Rotors program to provide and validate the technology, acoustics, handling qualities and cost of civil and military rotorcraft. In cooperation with the Rotorcraft Flight Investigations Branch of NASA-Ames Research Center and the U.S. Army Aviation Research and Technology Activity, the U.S. Army Aviation Engineering Flight Activity (AEFA) conducted flight tests totalling 31 productive flight hours between 9 January and 2 June 1987. This report summarizes the flight tests accomplished, test conditions, data, and techniques used to obtain the data. Data measurements included: atmospheric and aircraft state parameters; main rotor blade structural loads, positions and accelerations; flight control positions and structural loads; main rotor hub accelerations and various vibration measurements for the aircraft cabin floor. The handling qualities data in this report, although not representative of a UH-60A in typical operating conditions, were similar to previous AEFA test results in similar configurations. The power required for level flight and hovering out-of-ground effect also agreed with results of previous AEFA test programs.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1988
- Accession Number
- ADA198794
Entities
People
- Christopher J. Young
- David A. Downey
- James L. Webre
- John F. Hagan
- Paul W. Losier
- Randall W. Cason
- Robert M. Buckanin
- Roy Lockwood
- Warren Gould