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Measurement of the UH-60A Hub Large Rotor Test Apparatus Control System StiffnessThis purpose of this report is to provides details of the measurement of the control system stiffness of the UH-60A rotor hub mounted on the Large Rotor Test Apparatus (UH-60A/LRTA). The UH-60A/LRTA was used in the 40- by 80-Foot Wind Tunnel to complete the full-scale wind tunnel test portion of the NASA / ARMY UH-60A Airloads Program. This report describes the LRTA control system and highlights the differences between the LRTA and UH-60A aircraft. The test hardware, test setup, and test procedures are also described. Sample results are shown, including the azimuthal variation of the measured control system stiffness for three different loadings and two different dynamic actuator settings. Finally, the azimuthal stiffness is converted to fixed system values using multi-blade transformations for input to comprehensive rotorcraft prediction codes.
Document ID
20140016747
Acquisition Source
Ames Research Center
Document Type
Technical Memorandum (TM)
Authors
Kufeld, Robert M. (NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
November 26, 2014
Publication Date
February 1, 2014
Subject Category
Aeronautics (General)
Report/Patent Number
Log No. 1041
NASA/TM-2014-216649
ARC-E-DAA-TN13233
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
Large Rotor Test Apparatus
Control System Stiffness
Measurement of the UH-60A Hub

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