Abstract:
This paper presents the testing and analysis methods used in determination of HH-60G flight loads using data gathered during a series of flight strain surveys. Analysis methods and results are emphasized here as most testing methods and data have been shared in previous forums. This is followed by a discussion of the resulting computed load values and their verification through comparisons to operational parameters such as aircraft weight, engine torque, and G-loads. It is found that computed loads and moments compare very well to flight conditions. For example, main rotor lift force correlates well to the product of aircraft weight and flight G's. When applied to finite element models, the computed loads also lead to strain predictions in good agreement with measured values. Development of these loads will allow the HH-60G program office to better address structural repairs, flight severities, and risk analyses.