Abstract: A drive train for a wind-up injection device is described. The drive train includes a torsional energy storage adapted to be loaded or unloaded by a rotatable element, a rotatable user handle, a rotationally driveable expelling mechanism adapted to expel the liquid drug, and a clutch element coupled with the torsional energy storage via the rotatable element and including a ratchet for maintaining the rotatable element at one of a number of discrete angular positions against the torque of the torsional energy storage. The clutch element is adapted to transmit the torque from the user handle to the torsional energy storage, or alternatively from the torsional energy storage to the expelling mechanism. The ratchet is switchable from one position to an adjacent position by a torque transmitted from the user handle to the torsional energy storage. The drive train is adapted to dampen torque peaks visco-elastically and/or visco-frictionally.

Abstract: A button for a drug delivery device with a reduced operating loudness includes a plate-like button body forming a touch surface, wherein the plate-like button body is coupled by an axial supporting member to a noise-generating interface of the drug delivery device and movable into a longitudinal direction of the drug delivery device, wherein the plate-like button body includes a material composite with at least one first component consisting of a first material and at least one second component consisting of a second material different from the first material, wherein the at least one first component and the at least one second component are coupled via at least one coupling plane that is at least sectionwise slanted or perpendicular to the longitudinal direction. Further, the disclosure describes a button assembly for a drug delivery device which is shock resistant.

Abstract: One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.

Abstract: An aircraft engine power distribution system for an aircraft engine controller, such as a FADEC, is provided where the power source is independent from the conventional airframe power system, without the need for a back-up battery. The aircraft engine power distribution system includes a magnetic generator operated by an aircraft engine. The aircraft engine power distribution system also includes a power distributor that rectifies the generator output and provides the rectified power to the engine controller as its primary source of power. In this configuration, as long as the aircraft engine is able to operate the magnetic generator, the engine controller receives power. Accordingly, the engine controller operates regardless of the operational status of the airframe power system.

Abstract: A fuel pump includes a bearing element disposed in proximity to an impeller. The bearing element is configured to form a fuel seal with the impeller and to drain fuel leaked from the pump chamber back into the pump chamber. The bearing element minimizes leakage of fuel from the pump chamber into an engine coupled to the impeller. The fuel pump also includes redundant lip seals configured to provide redundant sealing relative to a shaft of the impeller within the fuel pump in order to minimize engine oil from entering the pump chamber and to minimize fuel from entering the engine. Integration of both the bearing element and the redundant lip seals as part of the fuel pump results in the fuel pump having a relatively compact size.

Abstract: A piston aircraft engine assembly includes a piston aircraft engine, a fuel source, and a control system adapted to deliver fuel from the fuel source to the piston aircraft engine. The control system includes a mass airflow sensing apparatus adapted provide a pressure signal, an electronic engine controller coupled to the mass airflow sensing apparatus, and a set of fuel injectors. The electronic engine controller is adapted to (i) receive the pressure signal from the mass airflow sensing apparatus and (ii) generate a set of fuel injector signals based on the pressure signal received from the mass airflow sensing apparatus. The set of fuel injectors is adapted to meter the fuel in response to the set of fuel injector signals generated by the electronic engine controller.

Abstract: One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.

Abstract: A piston aircraft engine assembly includes a piston aircraft engine, a fuel source, and a control system adapted to deliver fuel from the fuel source to the piston aircraft engine. The control system includes a mass airflow sensing apparatus adapted provide a pressure signal, an electronic engine controller coupled to the mass airflow sensing apparatus, and a set of fuel injectors. The electronic engine controller is adapted to (i) receive the pressure signal from the mass airflow sensing apparatus and (ii) generate a set of fuel injector signals based on the pressure signal received from the mass airflow sensing apparatus. The set of fuel injectors is adapted to meter the fuel in response to the set of fuel injector signals generated by the electronic engine controller.

Abstract: An aircraft engine includes a cylinder assembly knock detection and suppression system. The knock detection and control system includes a set of knock detection sensors and an engine controller. Each cylinder assembly of the aircraft engine carries a knock detection sensor and each knock detection sensor is electrically coupled to the engine controller. During operation, each knock detection sensor transmits signals to the engine controller where the signals correspond to detected cylinder assembly vibrations. As the engine controller receives input signals from the sensors, the engine controller filters the input signals to distinguish the input signals as being associated with either knocking or as a non-knock event. In the case where the engine controller detects the occurrence of one or more knock events in a particular cylinder assembly, the engine controller automatically reduces the spark timing for that cylinder assembly and/or increases the volume of fuel delivered to that cylinder assembly.

Abstract: An aircraft engine power distribution system for an aircraft engine controller, such as a FADEC, is provided where the power source is independent from the conventional airframe power system, without the need for a back-up battery. The aircraft engine power distribution system includes a magnetic generator operated by an aircraft engine. The aircraft engine power distribution system also includes a power distributor that rectifies the generator output and provides the rectified power to the engine controller as its primary source of power. In this configuration, as long as the aircraft engine is able to operate the magnetic generator, the engine controller receives power. Accordingly, the engine controller operates regardless of the operational status of the airframe power system.

Abstract: A fuel pump includes a bearing element disposed in proximity to an impeller. The bearing element is configured to form a fuel seal with the impeller and to drain fuel leaked from the pump chamber back into the pump chamber. The bearing element minimizes leakage of fuel from the pump chamber into an engine coupled to the impeller. The fuel pump also includes redundant lip seals configured to provide redundant sealing relative to a shaft of the impeller within the fuel pump in order to minimize engine oil from entering the pump chamber and to minimize fuel from entering the engine. Integration of both the bearing element and the redundant lip seals as part of the fuel pump results in the fuel pump having a relatively compact size.