Vorgeschlagen wird eine Aktivierungseinheit (1) für Wirkmassen bzw. Wirkkörper (3), gekennzeichnet durch ein Ausstoßrohr (2), sowie um das Ausstoßrohr (2) angebrachte Hochleistungs- Heizelemente (4), bestehend zumindest jeweils aus einem Heizdraht (6), der seinerseits durch eine Regelungseinheit mit elektrischem Strom versorgt wird. Jeder Heizdraht (6) ist in einem Mantel (7) eingefasst und zumindest in einem Wärmeverlust minimierenden Material eingebettet. Beim Durchtreten des Wirkkörpers (3) durch die Aktivierungseinheit (1) kontaktiert der Wirkkörper (3) direkt oder berührungslos an seiner Mantelfläche mit den Einzelelementen (4) der Aktivierungseinheit (1). Durch die Heizdrähte (6) wird die thermische Energie auf den Wirkkörper (3) übertragen, der sich an den Berührungs- bzw. Kontaktpunkten entzündet. Eine weitere Aktivierungseinheit (1 ', 1 ") umfasst im Ausstoßrohr (2', 2") zumindest teilweise durch das Ausstoßrohr (2', 2") längsgeführte Heizelemente (10, 10'), die aus mit CrNi- Stahl ummanteltem (11) Heizdraht (14) bestehen und darauf aufgelötete Kontaktbleche (13) besitzen.

The present invention relates to a power supply device of a small arms fire control system or a similar small arms system. The device includes a first current limit part for limiting a low current when power is supplied from a battery, a second current limit part for limiting a high current when the power is supplied from the battery, a Zener diode and a boost converter connected to the first and second current limit parts, and adapted to charge the supercapacitor up to a final voltage that will be supplied to a load when the supercapacitor is charged to a predetermined voltage, and a microprocessor for checking a power supply state of the system and a voltage of the supercapacitor in real-time and controlling ON/OFF of the first and second current limit parts used in the system. There are advantages in that power of an overall system can be managed stably and efficiently and a use time of a battery can be increased.

A projectile (10) reconfigures in flight from a launch configuration, in which the center of gravity is aft of the center of pressure, to a flight configuration, in which the center of gravity is forward of the center of pressure. The projectile includes a forward portion (12) and an aft portion (14), and the reconfiguration involves movement of at least part of one of the portions relative to the other portion. The projectile may have an overall substantially conical shape when in the launch configuration. The forward portion may include a substantially conical nose (20), and a cylindrical central body (22) attached to the nose. In the launch configuration, at least part of the central body may be located within a hollow (26) in a base (24) of the aft portion. The base may be slidable relative to the central body.

An electromagnetic accelerator system may include a barrel defining a bore through which an acceleration path extends. An electromagnetic coil may be positioned around the barrel such that the acceleration path extends through a core of the electromagnetic coil. A first electrical contact may be positioned along the acceleration path approximately within the core of the electromagnetic coil and electrically coupled to the electromagnetic coil. A second electrical contact may position along the acceleration path approximately within the core of the electromagnetic coil and spaced apart from the first electrical contact. The second electrical contact may be electrically coupleable to the first electrical contact to complete a circuit when a projectile to be accelerated is positioned therebetween.

An explosive device composed of an auxiliary flux compression generator operating to produce a high intensity magnetic field to seed a primary flux compression generator The auxiliary flux compression generator has a first section with a magnetic field supplied by a cylindrical permanent magnet array, the first section is composed of a helical winding having a prescribed pattern configured to convert explosive energy into magnetic energy that will be used as seed magnetic field for the primary flux compression generator.

電機子（５）は、射出対象物である物体（ＰＲ）の射出方向に沿った軸を中心とする。筒状部材（１）は、電機子（５）と少なくとも電気的に接触する。導電ワイヤ（２）は、筒状部材（１）よりも電機子５の中心に近い位置で電機子（５）と機械的かつ電気的に接続される。絶縁板（３）は、筒状部材（１）及び導電ワイヤ（２）を保持する。筒状部材（１）及び導電ワイヤ（２）を介して電機子（５）に電流が流れることで作用する電磁力によって電機子（５）が軸方向に沿って移動することで、物体（ＰＲ）を加速して射出する。

射出装置（１００）及び射出システム（１０００）は、簡易な構成で、安全に物体を射出することができるものとして構成される。導電レール（１１、１２）は、Ｚ方向に延在している。電機子（２）は、導電レール（１１、１２）を介してパルス電流Ｉｄが流れることで作用する電磁力によって、Ｚ方向に移動することで、射出対象物である物体（９）を加速して、射出口（１Ａ）から射出する。制動部（３）は、電磁力によって移動する電機子（２）を制動する。

An electromagnetic launcher with a curved or spiral-shaped, open-ended guideway and conductors for launching a projectile. The projectile, movably retained on or within the guideway, is accelerated along the guideway using electromagnetic forces until it reaches an end of the guideway, then the projectile is launched in a desired direction. The direction of the launch of the projectile is determined by orienting the guideway in the desired direction using an actuator.

The present disclosure relates to a launch system (20), a launch vehicle (200) for use with the launch system (20), and methods of launching a payload utilizing the launch vehicle (200) and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle (200) can comprise a payload (240), a propellant tank (230), an electrical heater (220) wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated, and an exhaust nozzle (210) from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube (100) formed of at least one tube (110, 130), which can be electrically conductive and which can be combined with at least one insulator tube (120). An electrical energy source (300) also can be provided.