Forward bearing reactor mechanism for Titan 3-E/Centaur D-1T space launch vehicle

Details Forward bearing reactor mechanism for Titan 3-E/Centaur D-1T space launch vehicle Forward bearing reactor mechanism for Titan 3-E/Centaur D-1T space launch vehicle

Aug 1975

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1975aeme.symp....1j&link_type=abstract

In NASA. Kennedy Space Center 9th Aerospace Mech. Symp. p 1-18 (SEE N76-19172 10-12)

Physics

Aerodynamic Loads, Bearings, Centaur Launch Vehicle, Titan 3 Launch Vehicle, Design Analysis, Mechanical Devices, Shrouds, Supports

Scientific paper

System 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.

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