A method and device for ascertaining the temperature of a propellant charge (22) and a method and device for joining together propellant charge modules (2) to form a propellant charge (22). The method and device for ascertaining the temperature of a propellant charge (22) includes at least temporarily arranging a sensor head (4) which is movable with respect to the propellant charge (22) in a cavity (7) of the propellant charge (22); and ascertaining the temperature of the propellant charge (22) at least while the sensor head (4) is arranged in the cavity (7) of the propellant charge (22). The propellant charge modules (2) are positioned between stops (9) and are joined together by movement of at least one of the stops toward the other.

A test system is disclosed that has a chassis, a throwing mechanism that is located at an upper part of the chassis onto which at least one weight is attached and which provides throwing the weight attached thereon, a base is located at a lower part of the chassis and onto which a weight is thrown by the throwing mechanism, a control unit for throwing the weight by the throwing mechanism, and at least one pushing member for throwing the weight by pushing which is located on the throwing mechanism and operated by the control unit.

A test system is disclosed that has a chassis, a throwing mechanism that is located at an upper part of the chassis onto which at least one weight is attached and which provides throwing the weight attached thereon, a base is located at a lower part of the chassis and onto which a weight is thrown by the throwing mechanism, a control unit for throwing the weight by the throwing mechanism, and at least one pushing member for throwing the weight by pushing which is located on the throwing mechanism and operated by the control unit.

The present invention includes a device for determining the force necessary for the separation of a bullet from an ammunition cartridge comprising a chamber housing having central bore extending from a lower housing end to an upper housing end and terminating at a upper aperture, wherein the central bore comprises a chamber diameter adapted to accept an ammunition cartridge and that the bullet partially extends from the upper aperture; a frustaconical shape shoulder in the central bore at the upper housing end to reduce the chamber diameter to mate to an ammunition cartridge shoulder; a neck that connects the upper aperture to the frustaconical shape shoulder adapted to accept an ammunition cartridge neck; a cartridge retention lip within the upper aperture adapted to contact an ammunition cartridge bullet aperture; a chamber mount adapted to connect the chamber housing and a testing device; a bullet securing device comprising a bullet securing end to secure the bullet and a bullet securing device mount adapted to connect to the testing device; a moving mechanism to move the bullet securing device away from the chamber housing; a sensor in communication with the moving mechanism to measure a force exerted by the moving mechanism; and a display in communication with the sensor to display and or record the force.

A testing device for study of a magnetized plasma artillery and gunpowder, comprising a pedestal, wherein a top end of the pedestal is provided with a sliding slot for mounting a buffer device, which penetrates through an upper part of the pedestal along a front-rear direction. The sliding slot for mounting the buffer device is internally provided with a buffering slider, which can slide back and forth along the sliding slot for mounting the buffer device. A top end of the buffering slider is provided with a gunpowder combustion chamber fixing groove, which penetrates through an upper part of the buffering slider along the front-rear direction. The gunpowder combustion chamber fixing groove is internally provided with a gunpowder combustion chamber, and an upper part of the gunpowder combustion chamber is provided with a positioning ferrule for fixing the gunpowder combustion chamber.

A shaped charge target apparatus and method for using a target composed of synthetic material, thereby allowing for repeatable testing at a variety of density and hardness values.

A shaped charge target apparatus and method for using a target composed of synthetic material, thereby allowing for repeatable testing at a variety of density and hardness values.

A shaped charge target apparatus and method for using a target composed of synthetic material, thereby allowing for repeatable testing at a variety of density and hardness values.

A shaped charge target apparatus and method for using a target composed of synthetic material, thereby allowing for repeatable testing at a variety of density and hardness values.

Techniques are provided for automated determination of a rocket configuration based on acceleration during rocket motor burn-out and temperature. The rocket configuration is associated with a class of warhead affixed to the rocket. A methodology implementing the techniques according to an embodiment includes measuring the acceleration of the rocket over a period of time associated with the flight of the rocket. The method also includes calculating an acceleration difference between the measured acceleration associated with the start of rocket motor burn-out and the measured acceleration associated with the end of rocket motor burn-out. The method further includes measuring an internal temperature of the rocket and selecting a delta acceleration threshold based on the measured temperature. The method further includes comparing the calculated acceleration difference to the selected delta acceleration threshold, to estimate the rocket configuration. The estimated rocket configuration is used by guidance and control circuitry to select autopilot parameters.