Abstract: Systems and methods for controlling a DC to AC inverter providing a multiphase output at a fundamental frequency are provided. More particularly, a synchronous reference frame control scheme can be employed to regulate a DC to AC inverter to attenuate error at various frequencies of interest for the DC to AC inverter. According to particular example aspects of the present disclosure, the synchronous reference frame control scheme can include control structures to provide for attenuation of the negative sequence and zero sequence currents, leading to reduced total harmonic distortion and voltage unbalance in the output voltage of the inverter.

Abstract: An air agitator assembly for use with a heat-emitting object having a contour, the air agitator assembly including a perforated flexible structure having a thermally absorbing first side confronting and spaced from a portion of the heat-emitting object to define an air space there between and a second side opposite the first side and where at least a portion of the first side of the perforated flexible structure has a contour that matches a contour of a corresponding portion of the heat-emitting object.

Abstract: A method and disconnector for disconnecting a drive shaft of a drive mechanism from rotating equipment, upon a failure of the drive mechanism or rotating equipment, includes a housing, an arm extending from the housing and movable relative to the housing between a first position and a second position, and a parting tool on a distal end of the arm.

Abstract: Systems and methods for recording and communicating engine data are provided. One example aspect of the present disclosure is directed to a method for communicating engine data. The method includes receiving data. The method includes separating the data into categories. For one or more categories, the method includes creating a file including the separated data. For one or more categories, the method includes naming the file, at least in part, based on the category and based on a file naming convention. The method includes prioritizing the created files. The method includes transmitting an identification file comprising identification information for a wireless communication unit and the file naming convention. The method includes transmitting the created files based on the priority.

Abstract: An aircraft starting and generating system includes a starter/generator and an inverter/converter/controller (200) that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/generator after the prime mover have been started, to DC power in a generate mode of the starter/generator. A four leg inverter is coupled with a DC power output (452) of the starter/generator and has an inverter/converter/controller (ICC) (580) with a four leg MOSFET-based bridge configuration that drives the starter/generator in a start mode for starting a prime mover of the aircraft, and converts DC power to AC power in a generate mode of the starter/generator. A four leg bridge gate driver (560) is configured to drive the four leg MOSFET-based bridge (580) during start and generate mode using bi-polar pulse width modulation (PWM).

Abstract: Systems and methods for navigating an aerial vehicle are provided. One example aspect of the present disclosure is directed to a method for navigating an aircraft. The method includes receiving, by one or more processors, one or more first geographic coordinates via an interface configured to receive geographic coordinates from a satellite transmission. The method includes receiving, by the one or more processors, one or more second geographic coordinates via an interface configured to receive geographic coordinates from a ground transmission. The method includes determining, by the one or more processors, that the one or more first geographic coordinates and the one or more second geographic coordinates are inconsistent. The method includes updating, by the one or more processors, a flight plan using the one or more second geographic coordinates when the one or more first geographic coordinates are inconsistent with the one or more second geographic coordinates.

Abstract: An aircraft is disclosed, the aircraft having a fuselage having a centerline, and a wing extending from the fuselage and having a leading edge and a trailing edge. Additionally, the aircraft includes an engine mounted to the wing and having a rotating output shaft, and a propeller operably coupled to the output shaft and generating a rotating flow field to define a propeller wake when the propeller is rotated by the rotating output shaft. The propeller is located forward of the leading edge of the wing, so the propeller wake flows over the wing forming localized areas of effectively increased angle of attack generating a corresponding increased wing loading, with the wing having corresponding localized areas of reduced chord length to neutralize the otherwise increased wing loading. A method of countering the aerodynamic effects of propeller wake acting on a wing is also disclosed.

Abstract: Systems and methods for power generation for an aircraft are provided. In one example embodiment, a power generation system for an aircraft includes a thermionic generator arranged to receive heat from at least one heat source. The thermionic generator is configured to generate electrical power for one or more aircraft systems based at least in part on the heat received from the at least one heat source. The power generation system further includes a thermoelectric generator arranged to receive waste heat from the thermionic generator. The thermoelectric generator is configured to generate electrical power for one or more aircraft systems based at least in part on the waste heat received from the thermionic generator.

Abstract: Systems and methods for providing a synthetic track to observation devices are provided. In one embodiment, a method can include determining a location range and a time range for a synthetic track to be created by a plurality of platforms. The method can further include determining an emission location and an emission time for each of the platforms of the plurality of platforms based, at least in part, on the location range and the time range. The method can include sending a set of data to each of the plurality of platforms, each respective set of data indicating the emission location and the emission time at which the respective platform is to generate the emission to create the synthetic track.

Abstract: An apparatus and method for deicing a surface upon which ice accumulates, on for example an aircraft wing. The apparatus and method for the deicing module include an actuating component, a casing, and a movable member. The movable member breaks ice that has accumulated on a surface of the wing.

Abstract: Systems and methods of refining trajectories for aircraft include a trajectory prediction module for predicting a set of four-dimensional trajectories for aircraft; and a constraint selector module for determining a set of constraints based on the set of four-dimensional trajectories. The trajectory can be refined by mapping values for a goal associated with the set of four-dimensional trajectories based on the determined set of constraints and estimating additional values for the goal based on the mapped values.

Abstract: An apparatus and method for operating an avionics data network includes a network switch core configured for a time-sensitive networking (TSN) schema, a set of TSN networking end nodes communicatively connected with the network switch core, a set of ARINC 664 part 7 (A664p7) networking end nodes communicatively connected with the network switch core, and an A664p7 legacy module connected with, or incorporated into, the network switch core and configured to receive a set of A664p7 networking data from the set of A664p7 networking end nodes.

Abstract: An apparatus and method of operating a set of generators supplying power to a common power bus, includes obtaining a first generator speed signal and a second generator speed signal, determining a common mode torsional oscillation value and a differential mode torsional oscillation value, determining a first generator share command and a second generator share command based on the common mode torsional oscillation value and the differential mode torsional oscillation value, and applying the first and second generator share commands.

Abstract: Systems and methods for configuring a cryptographic system, such as an avionic data transfer system associated with an aircraft, are provided. More particularly, systems and methods can be used to assemble a cryptographic key configuration (CKC) for use in a cryptographic system. A CKC can include various components for configuration of a cryptographic system. An administrator can generate CKCs for multiple host systems via a user interface (e.g., a graphical user interface) at a terminal and can deliver the CKCs to the host systems via an automated process by way of, for instance, a removable data cartridge.

Abstract: A method of assembling a rotating rectifier having multiple radially spaced bus bars with a corresponding fastener to an electrical machine having at least one machine with a stator and a rotor mounted on a rotating shaft, the method includes inserting the rotating rectifier into a hollow portion of the rotating shaft, axially aligning the fasteners with a corresponding radial opening in the rotating shaft, inhibiting an inward radial movement of the fasteners by inserting an inhibiting tool into an interior defined by the multiple radially spaced bus bars, and at least partially securing the fasteners to a corresponding fastener on at least one of the rotor and rotating shaft while the inhibiting tool resides in the interior.

Abstract: A fastener assembly for aircraft cockpit electronics can include a spring locking quarter turn fastener, where a head of the fastener can be positioned on a non-display side of the assembly, and a thread of the fastener can extend to a display side of the assembly. The fastener assembly can additionally include a spring assembly and mounting hardware.

Abstract: An impeller fan assembly that includes a housing, a stator, a rotor having a hub and an annular array of non-stationary blades extending from the hub, at least two spaced apart bearings mounted to the stator, and a pump in fluid communication with the bearings to provide fluid to the bearings. A screw pump is provided within the hollow portion of the shaft. Inlet of the screw pump is fluidly coupled to the sump and outlet is in fluid communication with the bearings. Rotation of the screw pump pumps fluid from the sump to the bearings. A de-swirler is provided within the sump to reduce rotational movement of the fluid within the sump. The de-swirler has a hub with fixed curved vanes extending from the centerline of the hub. The curved vanes have curvature in a direction opposite from a rotational direction of the screw pump.

Abstract: A turbofan engine includes a turbine engine having a rotatable fan and a generator. The generator further includes a main machine, an exciter, and a generator control unit for controlling the excitation of the main machine. A rotor assembly is located within one of the blades, and a stator assembly that is along a rotational path of the rotor assembly whereby the operation of the turbine engine rotates the fan, which rotates the rotor assembly along its rotational path past the stator assembly to generate electricity.

Abstract: Provided is a valve assembly system including a flowbody including a channel formed at an inner surface thereof, a butterfly plate disposed within the channel and rotatably mounted within the flowbody. The system also includes a pair of dual-sided pistons that receive differential pressure at an input side and an output side of the valve assembly system. A spring is controlled for biasing against at least one of the dual-sided pistons based on the differential pressure, and to rotate the butterfly plate to regulate the differential pressure and the valve assembly system to a predetermined output pressure.

Abstract: Systems and methods for determining a flight path of an aircraft are provided. In one embodiment, a method can include identifying one or more parameter(s) associated with a moving target. The method can include determining a moving circular flight path associated with the moving target based at least in part on the parameter(s) associated with the moving target. The method can include identifying one or more condition(s) associated with at least one of the aircraft and the moving circular flight path. The method can include determining a flight path of the aircraft from a location of the aircraft to the moving circular flight path based at least in part on the parameter(s) associated with the moving target and the condition(s) associated with at least one of the aircraft and the moving circular flight path.