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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

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


    Beteiligte:
    Jones, R. A. (Autor:in)


    Erscheinungsdatum :

    01.08.1975


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch





    FIRST TITAN IV-CENTAUR LAUNCH PUTS MILSTAR INTO ORBIT

    Guillemette, Roger G. | Online Contents | 1994



    Atlas/Centaur Launch Vehicle Operation Experience

    Newton, K. E. | SAE Technical Papers | 1968


    Atlas/Centaur launch vehicle operation experience

    Newton, K.E. | Engineering Index Backfile | 1968