Provided is a launching apparatus (1) capable of efficiently obtaining water pressure sufficient for launching an underwater payload (2), including a launch tube (3), a conduit (4) including a first end portion (4a) and a communicating portion (4c) communicating with the launch tube (3), a plurality of conduit coils (11 to 15) axially aligned in a first region (R1) between the first end portion (4a) and the communicating portion (4c), a plurality of main circuits (41 to 45) passing an electric current through respective conduit coils (11 to 15), and a main-circuit control section. The main-circuit control section controls operation of the main circuits (41 to 45) to pass electric currents through the conduit coils (11 to 15) to generate an axial first magnetic field (MA) in the conduit (4) and thereby cause an axial second magnetic field (mb) in a moving object (6), thereby moving the moving object (6) in an advance direction toward a second end portion (4b).

An electrical power feed assembly (12) for supplying high current to an electrothermal gun has first and second electrical connectors (38 and 42) with associated contact portions (40 and 44) for engaging and plastically deforming first and second side contacts (20,22) on a cartridge (14) to provide firing while maintaining the electrical contact without any arcing. The first connector (38) has a curved contact portion (40) that provides an interference fit to plastically deform the first contact (20) and establish the electrical contact as the cartridge (14) is inserted into the gun. The second connector (42) has a pair of curved knife edges (48) that engage and plastically deform the second contact (22) of the cartridge to establish and maintain the electrical contact under spring action of the second connector and by operation of a cam mechanism (50) of a breech block (26) of the gun. The cartridge (14) has its first and second contacts (20, 22) made of a relatively soft material, copper and solder preferably, and has the contacts provided with annular shapes that are engaged by the contact portions (40, 44) of the first and second connectors (38, 42).

A high pressure pulsed gas source for accelerating a projectile along a gun barrel comprises a structure including a high voltage electrode for establishing axial electrical discharges in corresponding axial gaps behind an outlet where the projectile is located. Plasma flows at right angles to the discharges into a propellant mass that is converted into a high pressure component of the gas pulse. The gaps are arranged so that after the projectile moves away from its initial position and is in the barrel, power applied to the plasma via gaps close to the outlet is greater than power applied to the plasma via gaps farther from the outlet. To avoid damage to the gun, the gaps are arranged so power applied to the plasma is substantially the same in the discharges when plasma is initially produced. The gaps include walls that are eroded differently by the discharges so gap walls close to the outlet erode faster than gap walls farther from the outlet. The plasma has sufficient pressure so it -tends to flow out of a confining structure for it into contact with the electrode via a secondary flow path other than the flow path through the outlet. The confining structure includes a cavity located in the secondary flow path. A soft, non-electrically conducting material in the cavity expands in a direction at right angles to the secondary flow path and compresses in the direction of the secondary flow path against walls of the cavity to form a seal to overcome a tendency of the plasma to flow into contact with the electrode.

Disclosed is a method and an apparatus for accelerating and shooting a flying body at superhigh speed, consisting of a capacitor (24) in which a high-pressure electric charge can be stored; a primary coil (20) connected to the capacitor (24) via a switching means (22); a conductive cylindrical liner (26) disposed in the primary coil (20); an opening (28) defined on a cylindrical wall of the cylindrical liner (26); and a flying body (30) interposed in the opening (28) and assuming electrical continuity with the liner (26); wherein a high-pressure electric charge stored in the capacitor (24) is momentarily applied to the primary coil (20) so as to compress abruptly the cylindrical liner (26) radially inward and to shoot the flying body (30) interposed in the opening (28) toward the axis of the liner (26).

Beschleunigervorrichtungen, die auf der Wechselwirkung zwischen einem im ruhenden Teil erzeugten magnetischen Feld und elektrischen Strömen einer beweglichen Spulenanordnung beruhen, die mit dem zu beschleunigenden Gegenstand zumindest während des Beschleunigungsvorganges verbunden ist, werden zweckmäßig durch eine Flachspulenanordnung des feststehenden Teiles und eine in gleicher Ebene mit kleinem Abstand liegende Spulenanordnung des beweglichen Teiles ausgeführt.

Besonders günstige Verhältnisse ergibt eine Zweischicht- oder Mehrschicht-Konfiguration für den Stator. Die Verbindung mit dem Nutzlastteil ist zweckmäßig elektrisch aktiv zu gestalten, so daß bei geeigneter Formgebung der Statorspulen auch dieser Teil sich an der Krafteinleitung beteiligt.

Le domaine de l'invention est celui des lanceurs électromagnétiques de projectiles et plus précisément celui des canons électromagnétiques à rails.

Selon l'invention, un canon électromagnétique à rails pour projectile (P) comprenant une armature (A) conductrice d'électricité, comporte une succession de blocs d'alimentation (B1...BK) pour alimenter électriquement une succession de segments (S1...SK) d'une voie de lancement de projectiles formée par deux rails parallèles, lesdits segments (S1...SK) étant isolés les uns des autres sur au moins un desdits rails et chacun desdits blocs d'alimentation (B1...BK) étant relié à l'arrière d'un desdits segments (S1...SK) de voie par deux bornes (BA, BB) pour délivrer un courant propulsif audit projectile lorsque celui-ci pénètre sur le segment (SK) de voie correspondant, le bloc d'alimentation (B1...BK) dudit segment (S1...SK) de voie correspondant appliquant audit segment (S1...SK) de voie, avant la pénétration dudit projectile (P) sur ledit segment (S1...SK) de voie, une tension inférieure à une tension critique à laquelle apparaît un risque de formation d'un arc parasite entre les rails dudit segment (S1...SK) de voie, le courant propulsif étant fourni par le bloc d'alimentation (BK) en raison de la présence de ladite armature (A) dudit projectile (P) entre les rails dudit segment (SK) de rail correspondant.

L'invention s'applique notamment dans le domaine militaire.

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.

Selon l'invention on chauffe par effet Joule une charge conductrice liquide en un temps très bref, le liquide n'ayant pas le temps de se dilater. Le liquide passe directement à l'état de vapeur, ce qui produit une forte pression. Un dispositif conforme à l'invention peut comprendre un banc de condensateurs (10), une ligne plate (12,), un canon (24, 26), une charge conductrice (32) insérée entre un projectile (28) et une culasse (30).

Application à la simulation de micrométéorites, ou à l'étude des collisions entre macroparticules.