Abstract: Muzzleloader systems include a pre-packaged propellant charge and primer for providing efficient loading and unloading of the muzzleloader. The muzzleloader accepts in the breech end the propellant containment vessel that abuts against a constriction portion with a reduced diameter portion. The propellant containment vessel having an end portion with a tapered surface that conforms to the constriction portion surface. A projectile is inserted in the muzzle end and seats against the constriction portion. The propellant containment vessel may be received in a removable breech plug. The constriction portion may be part of the breech plug or a separate component secured in the barrel by way of the breech plug. The containment vessel further comprises a primer mechanism that may be integrated into the proximal end of the containment vessel.

Abstract: A gas generator comprises a casing forming a ring or a ring portion and housing a pyrotechnic charge, the casing including at least one vent for ejecting the gas produced during combustion of the charge. Because of its ring design, the gas generator is easy to integrate in the structure of a rotary machine. In particular, it can constitute a starter device for a turbojet.

Abstract: The invention relates to an actuator comprising an actuator element movably supported at an actuator housing, a pyrotechnic pressure element to move the actuator element and a control means to control a force exerted onto the actuator element by the pressure element to move the actuator element.

Abstract: Fuel ignition system for jet engine starting contains pyrocartridges, connected by tubes to nozzles. The nozzles enter in a heat pipe so that the plumes hot pyrogases are in a zone of backflows of composite fuel. The pyrocartridges are connected to the electronic unit, control pyrocartridges and fuel supply.

Abstract: A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section.

Abstract: A gas turbine engine comprising a combustion chamber section, a turbine section, and a compressor section. The turbine section surrounds the combustion chamber and the compressor section surrounds the turbine section.

Abstract: A microelectrical mechanical system (MEMS) microthruster array is disclosed. The MEMS microthruster array of the present invention can be used for maintaining inter satellite distance in small satellites. One microthruster array includes numerous microthruster propulsion cells, each having a vacuum enclosed explosive igniter disposed on one side by a breakable diaphragm and having a propellant-filled chamber on the opposite side of the diaphragm. Upon explosion of the explosive igniter, the first diaphragm breaks, which, together with the explosion of the explosive igniter, causes the propellant to expand rapidly, thereby providing exhaust gases which are ejected from an exterior face of the microthruster propulsion array, thereby providing a small unit of thrust.