초록 ▼

A device for altering the after body shape of a missile configuration so as to reduce the ballistic flight drag coefficient after booster burnout and including linear shaped charge cutting device for severing a portion of a nozzle exit cone just aft of a fixed boattail configuration on the outer sur

A device for altering the after body shape of a missile configuration so as to reduce the ballistic flight drag coefficient after booster burnout and including linear shaped charge cutting device for severing a portion of a nozzle exit cone just aft of a fixed boattail configuration on the outer surface of the missile to allow boundary layer air flow to flow smoothly over the boattail and thereby reduce the base drag on the missile during the coast phase thereof.

대표청구항 ▼

A missile having a rocket motor structure with a nozzle structure attached thereto, said nozzle structure having an outwardly tapering outer surface, a frustaconical boattail structure mounted over and about an end portion of said rocket motor structure and a forward portion of said rocket nozzle st

A missile having a rocket motor structure with a nozzle structure attached thereto, said nozzle structure having an outwardly tapering outer surface, a frustaconical boattail structure mounted over and about an end portion of said rocket motor structure and a forward portion of said rocket nozzle structure, said boattail structure having an outward surface that tapers inwardly from a forward portion to a point of tangency with the outwardly tapering outer surface of said rocket nozzle, means about said rocket nozzle at said point of tangency and mounted relative to the rocket nozzle, means for causing said portion of said rocket nozzle with said outwardly tapering surface to be separated from the remainder of said rocket nozzle structure by said means about said rocket nozzle at said tangency point to cause a boattail end structure of about 1-caliber in length to be formed on said missile, said rocket motor having a predetermined internal diameter and said rocket motor nozzle having a predetermined internal diameter at an exit end of said rocket nozzle which is substantially equal to said predetermined internal diameter of said rocket motor, said means about said rocket nozzle at said point of tangency being a shaped charge that is spaced a predetermined distance from said rocket motor nozzle and has means for setting off said shaped charge at the appropriate time to sever said nozzle end structure and leave said boattail structure on the missile, and said means for setting off said shaped charge including a power supply and timing means that are inner connected to said shaped charge to cause said shaped charge to be set off at the appropriate time.