Ultrafast, linearly-deflagration ignition system

Ammunition and explosive-charge making – Miscellaneous

Patent

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Details

60256, 264 3R, F42B 3302

Patent

active

041541413

ABSTRACT:
Disclosed is a method of providing an ingition system for substantially sltaneously and uniformily igniting all the internal burning surfaces of a large propellant grain of the internal burning grain type that is employed in an upper stage advanced missile interceptor. The propellant grain to be ignited is also of the type which requires support for reinforcing the grain during high acceleration loads especially before the interceptor stage motor is pressurized. The means for igniting the large propellant grain is comprised of high-velocity deflagration compositions which are derived from cesium dodecahydrodecaborane and which are extruded or formed in a variety of shapes. These shaped high-velocity deflagration compositions are then bonded to a consumable casting mandrel, or to a grain support tube which also serves as a casting mandrel. The casting mandrel is inserted into the rocket motor case; the propellant formulation is then cast into the rocket motor; and the cast formulation is cured to form a grain for an upper stage rocket motor for an advanced interceptor. The shaped cesium dodecahydrodecaborane can be ignited through a perforation in the grain suppot tube or when used with a consumable mandrel, the shaped cesium dodecahydrodecaborane can be provided with a cavity into which an initiator can be inserted and bonded in place with an adhesive. The initiator when ignited serves to ignite the high-velocity deflagration composition which subseqently ignites the advanced interceptor grain with which the shaped cesium dodecahydrodecaborane is in intimate contact.

REFERENCES:
patent: 2995091 (1961-08-01), Haymes et al.
patent: 3126305 (1964-03-01), Armstrong
patent: 3132475 (1964-05-01), Hopper
patent: 3421325 (1969-01-01), Thibodaux

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