Abstract: An improved launch cartridge means for launching a rocket powered round from a spike type launcher wherein the launch cartridge is provided with a probe means extending through the nozzle of the rocket powered round during a first portion of the launch phase thereof to reduce the pressure of the launch gases on the rocket propellant grain of the rocket powered round. The probe means is detachably coupled to the launch cartridge by selectively removable coupling means. For the condition where a pure ballistic trajectory of the rocket powered round is desired, that is, without ignition of the rocket propellant grain in the round, the coupling means is removed and the probe portion of the launch cartridge is driven into gas sealing engagement with the nozzle passage way of the rocket powered round to prevent the launch gases from igniting the rocket propellant grain.

Abstract: A flueric through bulkhead rocket motor ignitor in which a flueric thermal nergy generator is used to set off a pyrotechnic/explosive pickup charge that in turn sets off a donor pyrotechnic/explosive charge that transmits its energy through a thick metallic bulkhead that is utilized to maintain pressure integrity of a rocket motor, and the donor charge transmits its energy to a pyrotechnic/explosive pickup charge that in turn sets off a receptor charge that is utilized to ignite a solid propellant composition.

Abstract: A launcher for a rocket powered round in which the launcher has a launch cartridge coupled thereto and the launch cartridge is insertable into the tailpipe of the round. The launch cartridge has a launch cartridge charge and an initial launch volume intermediate the launch cartridge charge and the round. A probe is coupled to the launch cartridge and extends into the nozzle of the rocket powered round to reduce the gas passage area therethrough during at least a first portion of the launch phase thereof. The probe may be permanently attached to the launch cartridge and thus remain part of the launcher or the probe may be detachably mounted on the launch cartridge and is driven into nozzle sealing relationship to the nozzle when the round is launched to prevent ignition of the rocket propellant grain.

Abstract: A pyrotechnic signal cartridge comprising a cartridge case, a projectile e detachably secured to the cartridge case, a charge in the cartridge case for launching the projectile case, rocket motor thrust means positioned within the projectile case, a rocket motor propellant charge and a pyrotechnic signal charge in the projectile case, ignition means for the pyrotechnic signal charge and the rocket motor propellant charge whereby ignition of the pyrotechnic signal charge and the rocket motor propellant charge after launching of the projectile case provides a self-levitating pyrotechnic display.

Abstract: 1. An igniter adapted to be positioned in the convergent portion of the nozzle of a rocket engine, said igniter comprising, a tapered combustible plastic casing having a small end and a large end, said casing having a stepped recess therein comprising a large cavity formed in the large end of said casing and a relatively small cavity opening into the inner end of said large cavity, a squib including a primer charge positioned in said small cavity, a body of pyrotechnic material positioned in said large cavity adjacent to said primer charge, a closure disc positioned in said large cavity to hold said pyrotechnic material therein, and squib-activating means for igniting said primer charge, said activating means extending from said squib through said casing and out the small end thereof, the inner end of said small cavity and the small end of said casing being substantially spaced from one another to provide a substantial body of combustible plastic therebetween.

Abstract: An igniter mechanism for a rocket motor utilized for towing a load or extting an air crew member from a disabled aircraft. The mechanism operates whenever a sufficient force is exerted on the tow line to shear a pin allowing closure of the switch. Electrical energy coupled to the switch is conducted to a squib which ignites a charge to cause ignition of the rocket motor propellant. The electrical switch mechanism can only be actuated by a predetermined pulling force on the tow line thereby causing the electrical contacts to be brought positively together.