Abstract: A tachometer for supplying a signal representative of the rotational rate of a rotatable device includes a plurality of detection magnets, an index feature, and one or more non-rotationally mounted magnetic circuits. The detection magnets are coupled to, and spaced around, the device, to thereby rotate with the device when the device is rotated. The index feature is associated with the rotatable device, to thereby rotate with the device when the device is rotated. The index feature and the plurality of detection magnets are spaced evenly around the device. The magnetic circuits are spaced evenly around the device, and each magnetic circuit is configured to supply a first electrical signal each time one of the detection magnets rotates past the magnetic circuit and a second electrical signal each time the index feature rotates.

Abstract: A tachometer for supplying a signal representative of the rotational rate of a rotatable device includes a plurality of detection magnets, an index feature, and one or more non-rotationally mounted magnetic circuits. The detection magnets are coupled to, and spaced around, the device, to thereby rotate with the device when the device is rotated. The index feature is associated with the rotatable device, to thereby rotate with the device when the device is rotated. The index feature and the plurality of detection magnets are spaced evenly around the device. The magnetic circuits are spaced evenly around the device, and each magnetic circuit is configured to supply a first electrical signal each time one of the detection magnets rotates past the magnetic circuit and a second electrical signal each time the index feature rotates.

Abstract: A starter-generator system supplies a controllable torque to a gas turbine engine, to thereby assist in starting the gas turbine engine, by independently controlling excitation frequency and/or voltage magnitude. The starter-generator includes a multi-phase exciter stator, a rotationally mounted multi-phase exciter rotor, a multi-phase main stator, a rotationally mounted multi-phase main rotor, and an exciter controller. The rotationally mounted multi-phase exciter rotor has a plurality of exciter rotor windings wound thereon that, upon excitation thereof with a rotating electromagnetic exciter flux generated by the exciter stator, have non-rectified excitation currents induced therein.

Abstract: A flight control surface actuator assembly includes a pair of flight control surface actuators and a pivot arm. One of the flight control surface actuators is coupled to a flight control surface and a static airframe structure, the other flight control surface actuator is coupled to the flight control surface and the pivot arm. The pivot arm coupled to the static airframe structure and is configured to pivot relative to the second flight control surface actuator and the static airframe structure.

Abstract: A turbofan gas turbine propulsion engine includes a system to transfer power from the low pressure turbine to the high pressure turbine and/or extract additional load from the low pressure turbine during certain turbofan engine operational conditions. The systems include a hydrostatic power transfer system that includes a hydraulic pump and a hydraulic motor coupled to the low pressure and high pressure turbine, respectively. The systems additionally include a mechanical and electrical load shifting/loading sharing systems that use clutches and gear assemblies to share and/or shift load between the turbines.

Abstract: A flight control surface actuator assembly includes a plurality of flight control surface actuators, and a pivot arm. Each flight control surface actuator is adapted to couple to a flight control surface, and each is further adapted to receive a drive force and is operable, upon receipt thereof, to move between at least an extended position and a retracted position. The pivot arm is rotationally coupled to, and is configured to pivot relative to, each of the flight control surface actuators, the pivot arm is also adapted to be rotationally coupled to, and configured to pivot relative to, a static airframe structure.

Abstract: A generator system is configured to supply relatively constant frequency AC power when driven by a variable speed prime mover, by independently controlling the main rotor flux rotational speed. The generator system includes an exciter stator that induces current in the exciter rotor windings at a desired frequency and phasing. The exciter rotor windings are electrically connected to the main rotor windings, and are thus electrically excited at the same frequency and phasing. Excitation is supplied to the exciter stator from an exciter controller, which controls the frequency and phasing of the exciter excitation, based on the rotational speed of the generator, to maintain a constant output frequency.

Abstract: A flight control surface actuation system includes a plurality of smart actuators to move aircraft flight control surfaces between extended and retracted positions. The system includes a high availability network between the flight control avionics and the smart actuators, and between each of the smart actuators. The system configuration allows network nodes associated with each smart actuator to monitor and control one another, under higher level control of the aircraft flight control avionics, to provide multiple levels of health monitoring, control, and shutdown capability.

Abstract: A wireless communication module is used to implement an ad-hoc wireless sensor network. The wireless communication module is configured to interface with numerous and varied types of sensors and, in one particular embodiment, is used to implement an ad-hoc wireless sensor network for an aircraft engine. The modules are also configured to implement various functions to optimize ad-hoc network functionality and to minimize the electrical power dissipated by each module in the ad-hoc network.

Abstract: Improved drying, binder evaporation, and sintering processes which may be used in conjunction with specialized sintering tools to provide for the geometrically stable sintering of large, complex, metal injection molded preform parts or flowbodies. The improved process includes a three-stage drying process, a single stage binder evaporation process, and a two-stage sintering process.