Class / Patent application number | Description | Number of patent applications / Date published |
102202000 | Propellant ignitors | 8 |
20110072996 | PROPELLANT CHARGE - A propellant charge for use for ammunition, in which the propellant charge is separate from the projectile, has a propellant charge substance which can be initiated by a fuse. In order to solve the problem of providing a propellant charge for use in a two-part munition, which on the one hand can be produced easily and at low cost and on the other hand does not present any risk of damage when mechanically loaded before use, it is proposed that a propellant charge casing be provided which surrounds the propellant charge substance, with the propellant charge casing being in the form of a plastic part which is composed of a non-combustible, temperature-stable plastic material. | 03-31-2011 |
20110155011 | PLASMA JET IGNITER USED FOR AN ELECTRO-THEREMAL-CHEMICAL (ETC) GUN, MACHINE GUN OR OTHER BARRELED WEAPON OR EQUIVALENT TYPE. - A method is provided for an electric activation of a plasma jet igniter for firing Electro-Thermal-Chemical (ETC) guns, machine guns and other equivalent ETC barreled weapons, without complete consumption of any of the components necessary for its activation upon activating the igniter. Each activation of the igniter by means of one or several voltage pulses, which from an electric pulse generator ( | 06-30-2011 |
20110259225 | PROPELLANT CHARGE IGNITER - The invention relates to producing a propellant charge igniter tube ( | 10-27-2011 |
20120067240 | RING-SHAPED OR PLATE-LIKE ELEMENT AND METHOD FOR PRODUCING SAME - A ring-shaped or plate-like element, in particular for a metal-sealing material-feedthrough, for example for devices which are subjected to high pressures, such as igniters for airbags or belt tensioning devices, includes a feedthrough opening, whereby the feedthrough opening is located substantially in the center of the ring-shaped or plate-like element and whereby the ring-shaped or plate-like element has a thickness. The ring-shaped or plate-like element has a relief region in the area of the feedthrough opening. Further, the ring-shaped or plate-like element in the relief region has at least one thickness which is reduced by the height of the relief region and which is selected so that the feedthrough opening can be punched out of the ring-shaped or plate like element having the reducing thickness. | 03-22-2012 |
20120137912 | CONTROLLABLE DIGITAL SOLID STATE CLUSTER THRUSTERS FOR ROCKET PROPULSION AND GAS GENERATION - A thruster stack assembly and method for manufacturing the same is provided. The thruster stack assembly includes a plurality of grain elements having a common core region (e.g., a channel or passageway), where each grain element comprises a volume of electrically ignitable propellant. The thruster stack assembly further includes electrodes associated with the plurality of grain elements, the electrodes adapted for selectively igniting the plurality of grain elements. In one example, one or more of the grain elements may be ignited and combusted without igniting or damaging adjacent grain elements of the stack. The core region serves to channel combustion gases and exhaust from the thruster stack. Multiple stacks may be assembled together to form three-dimensional thruster arrays. | 06-07-2012 |
20140069289 | DISTRIBUTED ORDNANCE SYSTEM, MULTIPLE STAGE ORDNANCE SYSTEM, AND RELATED METHODS - A distributed ordnance system comprises a plurality of ordnance controllers and a plurality of firing units. Each ordnance controller of the plurality of ordnance controllers may be operably coupled with at least one firing unit of the plurality of firing units. Each ordnance controller may be configured to provide power signals to the at least one firing unit coupled therewith, and communicate with the at least one firing unit for initiation of an ordnance event. A multiple-stage ordnance system may comprise a first stage and a second stage that each include an ordnance controller configured to control operation of an ordnance event, and at least one firing unit to initiate the ordnance event. Related methods for constructing a multiple-stage ordnance control system and controlling initiation of an energetic material are also disclosed. | 03-13-2014 |
20140083317 | REPEATABLE PLASMA GENERATOR AND A METHOD THEREFOR - The invention concerns a method for repeatable ignition of propellant charges in a weapon system, e.g. for firing shells from a barrel weapon, through electrical discharge in a combustion chamber duct ( | 03-27-2014 |
20140230678 | ROCKET DELAY APPARATUSES, SYSTEMS AND METHODS - Delay tools, systems and methods for achieving a selection of alternative delay times, a tool of which including a body, a drill bit operable relative to the body and a knob operably connected to the drill bit, and operably disposed relative to the body for engagement of the body with a rocket motor bulkhead and the drill both relative to a delay to provide for achieving a selection of alternative delay times. | 08-21-2014 |