A pressure activated, timed missile flight termination system is described, for destroying a test missile after a predetermined period of flight to shorten its hazard space so that it can be used is described, on firing ranges having a minimum amount of area. A delayed destruct sequence is initiated by pressure in the missile combustion chamber upon ignition of the missile. A pressure driven piston is compressed by the pressure created in the combustion chamber, causing it to strike a primer which initiates a delay fuse, a detonator, and a linear-shaped charge to destroy the missile. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Timed Missile Flight Termination System


    Contributors:
    D. B. Franz (author)

    Publication date :

    1976


    Size :

    5 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    UpSTAGE Missile Flight Control System

    Pearson, John L. | SAE Technical Papers | 1970




    Peacekeeper flight termination ordnance system

    Ramsey, James / Sessler, Donald / Yang, Lien | AIAA | 1995