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An electrorheologically controlled semi-active landing gearThis study is to explore the application of electrorheology (ER) to the real-time control of damping forces that are transmitted through the nose landing gear for an F-106B aircraft. The main part of the landing gear is a strut that consists of a pneumatic spring and an ER controlled damper that is situatted on the strut centerline and applies a force directly opposing the vertical displacement of the nose wheel. The damping element rotates in response to strut displacement, employing a co-axial arrangement of stator and rotor plates connected to the opposing electrodes in the control circuit. The vertical displacement is conveted into rotation of the damper through a screw-nut mechanism. The ER fluid between the electrodes is thus engaged in shear along circumferential lines of action. This design results in a fast time response and a high ratio of strut forces achieved under Er-vs. zero-field control. Compact size and simplicity in fabrication are also attained. The analysis shows that when using an ER fluid of a yield stress of 7kPa, the energy absorption efficiency of the landing gear can reach almost 100% at various sink rates.
Document ID
19950062074
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lou, Zheng
(University of Michigan MI, United States)
Ervin, Robert D.
(University of Michigan MI, United States)
Winkler, Christopher B.
(University of Michigan MI, United States)
Filisko, Frank E.
(University of Michigan MI, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Publication Information
ISSN: 0148-7191
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
SAE PAPER 931403
Meeting Information
Meeting: SAE, Aerospace Atlantic Conference & Exposition
Location: Dayton, OH
Country: United States
Start Date: April 20, 1993
End Date: April 23, 1993
Accession Number
95A93673
Funding Number(s)
CONTRACT_GRANT: NAG1-1410
Distribution Limits
Public
Copyright
Other

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