The patent application relates to a pressure activated, timed missile flight termination system for destroying a test missile after a predetermined period of flight to shorten its hazard space so that it can be used 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.
Timed Missile Flight Termination System
1976
12 pages
Report
Keine Angabe
Englisch
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