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Experimental investigation of active loads control for aircraft landing gearAircraft dynamic loads and vibrations resulting from landing impact and from runway and taxiway unevenness are recognized as significant in causing fatigue damage, dynamic stress on the airframe, crew and passenger discomfort, and reduction of the pilot's ability to control the aircraft during ground operations. One potential method for improving operational characteistics of aircraft on the ground is the application of active control technology to the landing gears to reduce ground loads applied to the airframe. An experimental investigation was conducted which simulated the landing dynamics of a light airplane to determine the feasibility and potential of a series hydraulic active control main landing gear. The experiments involved a passive gear and an active control gear. Results of this investigation show that a series hydraulically controlled gear is feasible and that such a gear is very effective in reducing the loads transmitted by the gear to the airframe during ground operations.
Document ID
19820023445
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Mcgehee, J. R. (NASA Langley Research Center Hampton, VA, United States)
Dreher, R. C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
August 1, 1982
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
L-15224
NASA-TP-2042
NAS 1.60:2042
Accession Number
82N31321
Funding Number(s)
PROJECT: RTOP 505-44-33-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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