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Forward bearing reactor mechanism for Titan 3-E/Centaur D-1T space launch vehicleSystem between the Titan/Centaur launch vehicle and its aerodynamic shroud is described. The system provides a precise spring constant and is capable of being inactivated during flight. Design requirements, design details, and the test program are discussed. The conventional English system of units was used during this development program for all principal measurements and calculations.
Document ID
19760012085
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jones, R. A. (General Dynamics/Convair San Diego, CA, United States)
Date Acquired
August 8, 2013
Publication Date
August 1, 1975
Publication Information
Publication: NASA. Kennedy Space Center 9th Aerospace Mech. Symp.
Subject Category
Launch Vehicles And Space Vehicles
Accession Number
76N19173
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19760012084Collected WorksThe 9th Aerospace Mechanisms Symposium19760012084Collected WorksThe 9th Aerospace Mechanisms Symposium
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