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Flight-Time Identification of a UH-60A Helicopter and Slung LoadThis paper describes a flight test demonstration of a system for identification of the stability and handling qualities parameters of a helicopter-slung load configuration simultaneously with flight testing, and the results obtained. Tests were conducted with a UH-60A Black Hawk at speeds from hover to 80 kts. The principal test load was an instrumented 8 x 6 x 6 ft cargo container. The identification used frequency domain analysis in the frequency range to 2 Hz, and focussed on the longitudinal and lateral control axes since these are the axes most affected by the load pendulum modes in the frequency range of interest for handling qualities. Results were computed for stability margins, handling qualities parameters and load pendulum stability. The computations took an average of 4 minutes before clearing the aircraft to the next test point. Important reductions in handling qualities were computed in some cases, depending on control axis and load-sling combinations. A database, including load dynamics measurements, was accumulated for subsequent simulation development and validation.
Document ID
19990032457
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Cicolani, Luigi S.
(NASA Ames Research Center Moffett Field, CA United States)
McCoy, Allen H.
(Naval Postgraduate School Monterey, CA United States)
Tischler, Mark B.
(Army Aviation and Missile Command Moffett Field, CA United States)
Tucker, George E.
(NASA Ames Research Center Moffett Field, CA United States)
Gatenio, Pinhas
(Israel Flight Test Center Israel)
Marmar, Dani
(Israel Flight Test Center Israel)
Date Acquired
August 19, 2013
Publication Date
March 1, 1999
Publication Information
Publication: System Identification for Integrated Aircraft Development and Flight Testing
Subject Category
Aircraft Design, Testing And Performance
Distribution Limits
Public
Copyright
Other
Document Inquiry

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