Timed missile flight termination system
AssigneeThe United States of America as represented by the Secretary of the Navy
InventorDavid Bruce Franz
Life of this patent
Estimating the term…
Abstract
A pressure activated, timed missile flight termination system for destroy 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.
Claims9
A pressure activated, timed missile flight termination system comprising:
- a. threaded casing means for insertion in a combustion chamber wall of said missile;
- b. a cylindrical piston disposed within a cylinder formed in said threaded casing means;
- c. a primer detachably connected to said threaded casing means;
- d. pin means connected to said cylindrical piston for penetrating said primer and causing said primer to ignite whenever said cylindrical piston is compressed due to a pressure buildup in said combustion chamber;
- e. a pyrotechnic delay fuse connected to said primer;
- f. detonation means connected to said primer for causing a detonation when ignited by said delay fuse;
- g. linear-shaped charge means wrapped around said missile for severing said missile into a plurality of pieces in response to said detonation of said detonation means;
- wherein said pressure buildup in said combustion chamber occurs instantaneously upon ignition of said missile and said pyrotechnic delay fuse provides a predetermined delay before ignition of said detonation means so that said missile is automatically destroyed after a predetermined flight period.
Dependencies are inferred from the claim text.