Abstract: An assembly for an aircraft propulsion system includes a propeller, a blade position sensor, and a controller. The propeller is configured for rotation about a rotational axis. The propeller includes a plurality of propeller blades. The plurality of propeller blades have a pitch. Each propeller blade of the plurality of propeller blades is configured for rotation about a respective lengthwise axis to selectively vary the pitch. The blade position sensor is configured to measure the pitch. The blade position sensor is configured to generate a pitch output signal representative of the measured pitch. The controller is in signal communication with the blade position sensor. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to: detect a presence or an absence of an erroneous propeller blade pitch measurement using at least the pitch output signal.

Abstract: A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control system, which issues commands for controlling engine parameters comprising an acceleration reference signal, load shedding, variable geometry positioning, and fuel flow. The control system may further issue commands for controlling the amount of power drawn. The control system may further use the reading to monitor the engine's condition.

Abstract: A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control system, which issues commands for controlling engine parameters comprising an acceleration reference signal, load shedding, variable geometry positioning, and fuel flow. The control system may further issue commands for controlling the amount of power drawn. The control system may further use the reading to monitor the engine's condition.

Abstract: A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control system, which issues commands for controlling engine parameters comprising an acceleration reference signal, load shedding, variable geometry positioning, and fuel flow. The control system may further issue commands for controlling the amount of power drawn. The control system may further use the reading to monitor the engine's condition.

Abstract: Systems and processes are provided for verifying ownership of a network identifier or domain name. A content provider can verify that a first entity owns the network identifier by instructing the first entity to modify data associated with the network identifier in a defined manner. The content provider can verify that the first entity owns the network identifier by confirming that the data associated with the network identifier has been modified in the defined manner.

Abstract: An expanding error correction architecture groups the output data of a data end to several parts, and each grouped output data of the data end is connected to one of a plurality of error correction circuit to be processed for a check sum. One part of the output data of the data end is arranged in a successive form, and another part of the output data of the data end is arrange in a non-successive form. The architecture of the present invention increases the error detection ability for check sums of different data sizes in the data end.

Abstract: A memory circuit is designed for a Universal Serial Bus (USB) 2.0 circuit architecture. An analog front end unit is connected to a high-speed delay phase lock loop unit. A full-speed delay phase lock loop and data recovery unit is connected to the analog front end unit. A receiver unit is connected to the high-speed delay phase lock loop unit and the full-speed delay phase lock loop and data recovery unit. A transceiver unit is connected to the analog front end unit and the receiver unit. A control unit is connected to the transceiver unit, the receiver unit, the high-speed delay phase lock loop unit and the full-speed delay phase lock loop and data recovery unit. An external oscillator unit is connected to the control unit.