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Impact studies of a 1/3-scale model of an air cushion vehicleAn experimental investigation was conducted to determine the effects of various parameters of the impact performance of a 1/3-scale dynamic model of an air cushion vehicle. Impact response was determined by measuring the maximum values of variables, including sidelobe, front lobe, and cavity pressures, normal acceleration, pitch and roll angles, and vertical displacement during impact, for various combinations of drop height, initial pitch and roll angles, and forward speed. Increasing initial pitch angle increased the maximum values of the front lobe pressure, normal acceleration, nose down pitch angle, and to some extent, vertical displacement, but it inversely affected the maximum cavity pressure. Increasing the drop height of the model increased the potential energy of the system and generally produced larger responses over the entire range of variables measured, except for the roll angle after impact, which remained constant. Forward speed had no effect on the impact performance of the model, except for essentially doubling the maximum nose down pitch angle after impact at the maximum speed tested.
Document ID
19850015446
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Daugherty, R. H.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
April 1, 1985
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-TM-86360
L-15916
NAS 1.15:86360
Accession Number
85N23757
Funding Number(s)
PROJECT: RTOP 505-45-14
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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