Abstract: A system and method for automatic splicing of rolls of sleeve material used in various packaging markets is provided. The system will automatically splice the prepared end of a new roll onto the expiring end of the prior roll. The system performs an automatic cut and splice operation resulting in a butt splice of the two rolls with tape applied to both sides of the splice joint. The splice can be done in-registration to provide a consistent product repeat length between expiring and new rolls.

Abstract: A hydrostatic pressure testing system for hydrostatic pressure testing of pipe or other vessels. A control center may include a computer program that monitors, records, and controls the system during testing. A test fluid assembly may include a fill conduit capable of providing a test fluid to an inlet section of a vessel to be tested in response to a command from the computer program. A pressure-release safety assembly may have a vent conduit in fluid communication between an outlet section of the vessel and a safety valve. The safety valve may be in fluid communication with a bleed tank for storing an outlet flow of test fluid from the vessel. The safety valve is actuated to relieve fluid pressure in the vessel in response to a selective condition. A method of using the system to conduct hydrostatic pressure testing is also described.

Abstract: A hydrostatic pressure testing system for hydrostatic pressure testing of pipe or other vessels. A control center may include a computer program that monitors, records, and controls the system during testing. A test fluid assembly may include a fill conduit capable of providing a test fluid to an inlet section of a vessel to be tested in response to a command from the computer program. A pressure-release safety assembly may have a vent conduit in fluid communication between an outlet section of the vessel and a safety valve. The safety valve may be in fluid communication with a bleed tank for storing an outlet flow of test fluid from the vessel. The safety valve is actuated to relieve fluid pressure in the vessel in response to a selective condition. A method of using the system to conduct hydrostatic pressure testing is also described.

Abstract: Air induction control systems and methods for aircraft are provided. A particular aircraft includes a fuselage, a pair of wings and an engine. The aircraft also includes an inlet defining an aperture to receive air for delivery to the engine. The inlet has a longitudinal axis generally aligned with a direction of flow of the air as the air approaches the inlet. The aircraft also includes at least one first dielectric barrier discharge generator positioned to apply a first force to the air prior to the air being received by the engine. The first force acts in a first direction. The aircraft further includes at least one second dielectric barrier discharge generator positioned to apply a second force to the air prior to the air being received by the engine. The second force acts in a second direction that is non-parallel to the first direction.

Abstract: Air induction control systems and methods for aircraft are provided. A particular aircraft includes a fuselage, a pair of wings and an engine. The aircraft also includes an inlet defining an aperture to receive air for delivery to the engine. The inlet has a longitudinal axis generally aligned with a direction of flow of the air as the air approaches the inlet. The aircraft also includes at least one first dielectric barrier discharge generator positioned to apply a first force to the air prior to the air being received by the engine. The first force acts in a first direction. The aircraft further includes at least one second dielectric barrier discharge generator positioned to apply a second force to the air prior to the air being received by the engine. The second force acts in a second direction that is non-parallel to the first direction.

Abstract: An air induction system for an aircraft to control distortion and pressure recovery for improved aerodynamic performance. The system includes an inlet and at least one dielectric barrier discharge generator positioned upstream of the engine for imparting momentum to a low-energy boundary layer of air. A plurality of spaced dielectric barrier discharge generators may be activated in selected combinations to optimize performance at respective flight conditions. In one embodiment, one or more generators may be oriented generally transverse relative to the flow of intake air to eject the boundary layer in a lateral direction and prevent its ingestion by the engine. In another embodiment, one or more generators may be oriented along the direction of flow to accelerate the boundary layer air.