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Missile rolling tail brake torque systemApparatus for simulating varying levels of friction in the bearings of a free rolling tail afterbody on a canard-controlled missile to determine friction effects on aerodynamic control characteristics is described. A ring located between the missile body and the afterbody is utilized in a servo system to create varying levels of friction between the missile body and the afterbody to simulate bearing friction.
Document ID
19840008163
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Davis, W. T. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
January 17, 1984
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
Patent Number: NASA-CASE-LAR-12751-1
Patent Number: US-PATENT-4,425,785
Patent Application Number: US-PATENT-APPL-SN-338386
Accession Number
84N16231
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
NASA-CASE-LAR-12751-1|US-PATENT-4,425,785
Patent Application
US-PATENT-APPL-SN-338386

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