A hybrid gun for launching a projectile (19) by a combined propulsion effect of a chemical propellant and electrothermal energy. The gun comprises a breech-associated electrothermal propulsion energy injector (14) having a plasma beam generator (15) and a tubular chamber (17) holding a light working fluid (18) that during the travel of the projectile in the barrel (12) produces at the rear of the projectile (19) a light gaseous buffer zone. Optionally the gun may have in addition one or more electrothermal propulsion energy injectors mounted on the barrel.

There is also provided ammunition for use with a hybrid gun having a chemical propellant holding cartridge designed for ignition by working fluid injected by the breech associated electrothermal propulsion energy injector.

Le lanceur se compose de deux tubes (1 et 16) isolés électriquement. Un projectile (40) propulsé par un premier étage de lancement crée un court-circuit quand il chevauche les deux tubes (1 et 16). Un signal est produit sur une ligne de sortie (29) qui permet de fermer un interrupteur (21) et de décharger un condensateur (22), qui crée une étincelle dans une charge (44) contenue dans le projectile (40). La partie avant (42) du projectile (40) est projetée à une vitesse accrue.

An electronically controlled multi-pulse ignitor ignites a cartridge used to launch a projectile (50). An electronics module (9) is programmed with a temperature performance profile for the cartridge. A temperature sensor is coupled to supply current cartridge temperature data to the electronics module (9). A first event ignitor is coupled to the electronics module (9) and initiates a ballistic cycle upon command from the electronics module (9). A translation mechanism (64), including a first charge coupled to the first event ignitor, moves the projectile (50) forward to increase the free volume in the cartridge. A second event ignitor (70), coupled to receive a second event ignition signal from the electronics module (9), ignites the main propellant charge on receiving the second event ignition signal from the electronics module (9), where the timing of ignition of the second event ignitor (70) is determined by the temperature performance profile and the current cartridge temperature data.

A tube launched rocket system which uses a plurality of small propellant charges located within the tube 20 to propel the projectile 40. The charges 30 form part of the outer wall of a travelling propulsion chamber. The chamber is substantially defined by a propulsion housing 50, which includes a forward plate 60 that abuts the projectile, and an aft nozzle 62 for venting gases from the interior 56 of the chamber. The system can include baffles for directing the flow of combustion gases, and can employ an electronic ignition system for igniting the propellant charges in sequence. As charges adjoining the propulsion chamber are ignited, the resulting combustion gases thrust into the interior of the chamber, forcing the housing forward as they flow backwards through the nozzle. As the propulsion housing travels through the tube, additional propellant charges are ignited as they effectively become part of the outer wall of the propulsion chamber. The housing pushes the projectile ahead of it through the tube.

A hybrid gun for launching a projectile (19) by a combined propulsion effect of a chemical propellant and electrothermal energy. The gun comprises a breech-associated electrothermal propulsion energy injector (14) having a plasma beam generator (15) and a tubular chamber (17) holding a light working fluid (18) that during the travel of the projectile in the barrel (12) produces at the rear of the projectile (19) a light gaseous buffer zone. Optionally the gun may have in addition one or more electrothermal propulsion energy injectors mounted on the barrel.

There is also provided ammunition for use with a hybrid gun having a chemical propellant holding cartridge designed for ignition by working fluid injected by the breech associated electrothermal propulsion energy injector.

A method and apparatus for accelerating a projectile in a launching tube at a rate determined by the rate of combustion of a propellant charge (3-6, 34) disposed within the tube at the rear of the projectile. The method includes the steps of:

    generating an electrical discharge for producing hot gases, and

    injecting the hot gases into a region of the launching tube in the rear of said projectile so as to interact with said propellant charge, thereby increasing its rate of combustion.

Lanceur de projectile à grande vitesse.

Il comprend une chambre (1, 2) remplie d'explosif détonant (20) accélérant le projectile (10). Le canon (5) est entaillé de rainures (16) qui filtrent l'onde de choc et empêchent le tube (6) d'imploser. Un accélérateur (11) peut être prévu.

Application à la simulation des impacts d'éclats.