A jewelry display includes a ferromagnetic planar substrate and a bracket configured to be attached to a wall. The bracket has at least one wall engagement surface disposed along an inner surface and at least one ferromagnetic planar substrate engagement surface disposed along an outer surface. An adhesive backed non-slip covering adhesively attaches to the substrate engagement surface. At least one bracket magnet is disposed on the inner surface of the bracket. A plurality of jewelry fixtures are configured to be removably attached to the front surface of the ferromagnetic planar substrate, each jewelry fixture having at least one permanent fixture magnet and a jewelry holding structure, where the at least one permanent fixture magnet of each jewelry fixture is magnetically attracted to the ferromagnetic planar substrate.

According to a first aspect of the present invention, there is provided a method of slowing down a moving projectile, the projectile moving within an electromagnetic railgun, the method comprising: using an electromagnetic field generated by the railgun to slow down the projectile, wherein the projectile is a munitions projectile, and/or a carrier for catching the munitions projectile.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle 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 can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle 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 formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle 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 can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle 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 formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

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.

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.

An exhaust system for a combustion engine vehicle includes an exhaust pipe extending between an exhaust inlet disposed opposite an exhaust outlet. The exhaust inlet and exhaust outlet are in fluidic communication with one another. The exhaust inlet is configured to receive an exhaust gas produced by an internal combustion engine of the combustion engine vehicle. A second pipe has an air inlet extending from and connected to the exhaust pipe. The second pipe is configured to be in fluidic communication with the exhaust outlet. The air inlet is configured to receive an outside flow of air. The exhaust gas from the combustion engine vehicle and the outside flow of air captured by the air inlet when the combustion engine vehicle is moving forward are configured to be combined and to cooperatively exit out the exhaust outlet.

An electromagnetic levitation force type propulsion device includes an integrated electromagnet structure, an auxiliary propulsion structure and a power supply control structure. The integrated electromagnet structure includes a mounting frame, a propulsion outputting shaft capable of moving back and forth relative to the mounting frame and extending out of the mounting frame, and two electromagnets opposite to each other. One of the electromagnets is assembled to the mounting frame to form a stationary electromagnet and the other electromagnet is fastened to the propulsion outputting shaft to form a movable electromagnet. The movable electromagnet is provided at the other side of the mounting frame and can move back and forth relative to the stationary electromagnet. The auxiliary propulsion structure drives the movable electromagnet back and forth relative to the stationary electromagnet. The power supply control structure provides a power supply for the integrated electromagnet structure and/or the auxiliary propulsion structure.

An electromagnetic levitation force type propulsion device includes an integrated electromagnet structure, an auxiliary propulsion structure and a power supply control structure. The integrated electromagnet structure includes a mounting frame, a propulsion outputting shaft capable of moving back and forth relative to the mounting frame and extending out of the mounting frame, and two electromagnets opposite to each other. One of the electromagnets is assembled to the mounting frame to form a stationary electromagnet and the other electromagnet is fastened to the propulsion outputting shaft to form a movable electromagnet. The movable electromagnet is provided at the other side of the mounting frame and can move back and forth relative to the stationary electromagnet. The auxiliary propulsion structure drives the movable electromagnet back and forth relative to the stationary electromagnet. The power supply control structure provides a power supply for the integrated electromagnet structure and/or the auxiliary propulsion structure.

The Hyper-Magnetic Matter Accelerator comprises an apparatus and method of a plurality of basin-formed electromagnetic field generators as well as rotational electromagnetic field generators mounted in series to a conduit; energized in sequence for ferrous matter or projectile acceleration to, but not limited to or by high-hypersonic velocity and rotation for trajectory stabilization accuracy. Velocity control may be implemented through the use of various power levels as well as configuration by one skilled in the art based on said artisan's intended velocity objective.