论文信息 - Flight-Time Identification of a UH-60A Helicopter and Slung Load

Flight-Time Identification of a UH-60A Helicopter and Slung Load

Abstract This paper describes a flight test demonstration of a system for identification of the stabilityand handling qualities parameters of a helicopter-slung load configuration simultaneouslywith flight testing, and the results obtained. Tests were conducted with a UH-60A Black Hawkat speeds from hover to 80kts. The principal test load was an instrumented 8x6x6ft cargocontainer. The identification used frequency domain analysis in the frequency range to 2Hz,and focussed on the longitudinal and lateral control axes since these are the axes most affectedby the load pendulum modes in the frequency range of interest for handling qualities. Resultswere computed for stability margins, handling qualities parameters and load pendulumstability. The computations took an average of 4 minutes before clearing the aircraft to the nexttest point. Important reductions in handling qualities were computed in some cases, dependingon control axis and load-sling combination. A database, including load dynamicsmeasurements, was accumulated for subsequent simulation development and validation.

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