Exhaust nozzle firing guide for sea-launched missile

摘要

A temporary tubular insert (20) is located in the interior of the divergent portion (12b) of the missile engine exhaust nozzle, defining a cylindrical outlet passage for the driving exhaust gas flow. The insert extends over at least half of the length of the divergent portion of the nozzle. The insert is constructed of material of low resistance to the temperature and pressure of the exhaust combustion gases, such that it is destroyed shortly after firing the missile engine. Alternatively the insert may be constructed of stronger material and attached to the interior of the nozzle by connectors ruptured at a predetermined interval after firing.