Simulation Prediction and Flight Validation of UH-60A Black Hawk Slung-Load Characteristics

This paper describes the development and validation of a slung-load simulation model obtained by integrating the GenHel blade-element and components-type simulation of the UH-60A with the slung-load equations of motion. The load aerodynamics model accounts for rotor downwash effects and static aerodynamics. The downwash model is based on momentum theory and empirical wake velocity data. Static aerodynamics for the CONEX cargo container were obtained from wind tunnel tests. The simulation validation is based primarily on comparison with flight test frequency response data. Frequency sweep flight test data, including load motion data, have been obtained at Ames in recent years for test loads which included an aerodynamically inert steel block and the aerodynamically active CONEX. It is shown that the simulation, validated for on-axis response dynamics over the frequency range of interest in handling qualities, [0.05, 2] Hz, can predict some of the key handling qualities and system stability parameters of interest in evaluating and certifying helicopter slung-load configurations.