Abstract: Implantable medical systems enter an exposure mode of operation, either manually via a down linked programming instruction or by automatic detection by the implantable system of exposure to a magnetic disturbance. A controller then determines the appropriate exposure mode by considering various pieces of information including the device type including whether the device has defibrillation capability, pre-exposure mode of therapy including which chambers have been paced, and pre-exposure cardiac activity that is either intrinsic or paced rates. Additional considerations may include determining whether a sensed rate during the exposure mode is physiologic or artificially produced by the magnetic disturbance. When the sensed rate is physiologic, then the controller uses the sensed rate to trigger pacing and otherwise uses asynchronous pacing at a fixed rate.

Abstract: An artillery shell is fired out of a gun towards a fire. A trigger releases a fire-retarding material from the artillery shell to retard the fire.

Abstract: An artillery shell is fired out of a gun towards a fire. A trigger releases a fire-retarding material from the artillery shell to retard the fire.

Abstract: An artillery shell is fired out of a gun towards a fire. A trigger releases a fire-retarding material from the artillery shell to retard the fire.

Abstract: A propulsion unit having reduced noise employs a rotor having a plurality of variable pitch blades. A tensioning joint mechanism is carried within each blade and a tension element is engaged by the tension joint mechanism. The tension element is configured to maintain tension between the blades in the rotor and the tensioning joint mechanism adapted to allow variation of pitch of the blades without altering tension in the tension element.

Abstract: An artillery shell is fired out of a gun towards a fire. A trigger releases a fire-retarding material from the artillery shell to retard the fire.

Abstract: An aircraft propulsion system includes a fan, a primary powerplant, an augmenting powerplant and a controller. The primary powerplant is coupled to the fan and configured to rotate the fan during a first flight stage and during a second flight stage. The augmenting powerplant is coupleable with the fan. The controller is configured to cause the augmenting powerplant to drive the fan during the first flight stage, and to cause the augmenting powerplant to cease driving the fan based on an indication of a transition from the first flight stage to the second flight stage.

Abstract: A propulsion system for a transport aircraft employs a gas turbine core coupled to a wing. A ducted fan is coupled to the core gas turbine extending downstream from and integrated in a trailing edge of the airplane wing.

Abstract: In one aspect a propulsion system comprises an engine and a drive assembly coupled to the engine, comprising a first driveshaft rotatable in a first direction about a first axis, a first fan coupled to the first driveshaft to rotate in the first direction, and a clutch assembly to selectively disengage the first fan from the first driveshaft. Other aspects may be described.

Abstract: Systems and methods provide for the mitigation of vibrational forces acting on a horizontal stabilizer of an aircraft. According to one aspect, a damper is coupled to a front portion of a horizontal stabilizer to dampen vibrations in a first degree of freedom, with another damper coupled to a mounting point of the horizontal stabilizer to dampen vibrations in a second degree of freedom. The dampers may be passive, operating independently to mitigate vibrational forces, or active, applying a mitigating force to the horizontal stabilizer based on real-time or estimated vibration states.

Abstract: An artillery shell is fired out of a gun towards a fire. A trigger releases a fire-retarding material from the artillery shell to retard the fire.

Abstract: A propulsion unit having reduced noise employs a rotor having a plurality of variable pitch blades. A tensioning joint mechanism is carried within each blade and a tension element is engaged by the tension joint mechanism. The tension element is configured to maintain tension between the blades in the rotor and the tensioning joint mechanism adapted to allow variation of pitch of the blades without altering tension in the tension element.

Abstract: Systems and methods provide for the mitigation of vibrational forces acting on a horizontal stabilizer of an aircraft. According to one aspect, a damper is coupled to a front portion of a horizontal stabilizer to dampen vibrations in a first degree of freedom, with another damper coupled to a mounting point of the horizontal stabilizer to dampen vibrations in a second degree of freedom. The dampers may be passive, operating independently to mitigate vibrational forces, or active, applying a mitigating force to the horizontal stabilizer based on real-time or estimated vibration states.

Abstract: An artillery shell is fired out of a gun towards a fire. A trigger releases a fire-retarding material from the artillery shell to retard the fire.

Abstract: A propulsion system for a transport aircraft employs a gas turbine core coupled to a wing. A ducted fan is coupled to the core gas turbine extending downstream from and integrated in a trailing edge of the airplane wing.