Abstract: An aerial vehicle is provided. The aerial vehicle can include a plurality of sensors mounted thereon, an avionics system configured to operate at least a portion of the aerial vehicle, and a machine vision controller in operative communication with the avionics system and the plurality of sensors. The machine vision controller is configured to perform a method. The method includes obtaining sensor data from at least one sensor of the plurality of sensors, determining performance data from the avionic system or an additional sensor of the plurality of sensors, processing the sensor data based on the performance data to compensate for movement of the unmanned aerial vehicle, identifying at least one geographic indicator based on processing the sensor data, and determining a geographic location of the aerial vehicle based on the at least one geographic indicator.

Abstract: A method for updating a flight plan by an avionics device includes receiving a first flight plan comprising a first set of flight parameters having at least one fuel-related first flight parameter, receiving a second flight plan for a subsequent second flight, the second flight plan based on a fuel remaining in the aircraft without refueling subsequent to the first flight, and receiving an update to the first flight plan. The method further includes, determining, with the avionics device, a set of first updated flight parameters comprising at least one fuel-related first updated flight parameter, determining, whether the fuel-related first updated flight parameter will satisfy predetermined criteria of the second flight plan, and when the fuel-related first updated flight parameter will not satisfy the predetermined criteria, displaying a first notification onboard the aircraft, and receiving a selection of a refueling locations.

Abstract: A method for validating, with a first computing device onboard an aircraft, a flight plan having a set of first flight parameters comprising respective first values, loaded onto the first computing device of an aircraft includes receiving from a second source, by the first computing device, data comprising a set of second flight parameters having respective second values corresponding to the set of first flight parameters. The method includes comparing the first values of the set of first flight parameters to the second values of the corresponding set of second flight parameters by the first computing device, determining, whether an implausible condition exists. When an implausible condition is determined, the method includes automatically displaying a first notification on a display device in the aircraft, requesting a modification to the set of first flight parameters, and receiving a modification to the loaded flight plan based on the notification.

Abstract: Propeller control systems and methods for controlling the pitch of a plurality of propeller blades of a variable pitch propeller assembly operatively coupled with an engine is provided. In one exemplary aspect, the propeller control system includes features for combining overspeed and feathering protective functions in a protective control valve communicatively coupled with a controller. In such an event the controller controls the protective control valve to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted based at least in part on the condition of the engine.

Abstract: A heat sink for a heat-generating component of an electronic device has a backbone panel with opposing upper and lower surfaces. Cooling elements extend away from the upper surface of the heat sink and terminate in upper ends that define a topological surface. Thermally conducting structures extend away from the lower surface of the heat sink and terminate in tips that define a surface that is complementary to the surface of the heat-generating component of the electronic device.

Abstract: A system and method for compiling and monitoring a list of operational aircraft components to determine if a threshold is met. Utilizing the list and the threshold can provide for monitoring the network of aircraft components to monitor both health and security of the aircraft network and components thereof. The system can then indicate or alert when a threshold is met or exceeded. Such an alert can be on a display to a pilot, for example, or to a remote monitoring station.

Abstract: Propeller control systems and methods for controlling the pitch of a plurality of propeller blades of a variable pitch propeller assembly operatively coupled with an engine is provided. In one exemplary aspect, the propeller control system includes features for combining overspeed and feathering protective functions in a protective control valve communicatively coupled with a controller. In such an event the controller controls the protective control valve to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted based at least in part on the condition of the engine.

Abstract: Systems and methods for authenticating data transmissions are provided, such as e.g., analog radio streams received at a vehicle. In one aspect, the vehicle includes features that allow for detection and decryption of an encrypted source identifier embedded or introduced into a data transmission transmitted to the vehicle. The source identifier may be used to determine whether the source is authorized to transmit data transmissions to the vehicle and the data transmission may be authenticated accordingly. In another aspect, the vehicle includes features that determine the location of the transmitting device used to transmit the data transmission to the vehicle. The location is then used to determine whether the data transmission should be authenticated.

Abstract: A contactor apparatus and method for operating the contactor apparatus can include a contactor assembly with a contactor coil operably coupled to a contactor switch. One or more sensors can be provided in the contactor assembly adapted to measure one or more aspects of the contactor assembly. Based upon the measured aspects, a controller can initiate operation of the contactor switch to effectively toggle the contactor switch at a zero-crossing point along an alternating current waveform.

Abstract: A method of controlling an aircraft includes tracking, using at least one sensor, one of an input by a pilot or a biometric parameter of a first pilot during flight of the aircraft. The method also includes determining a lack of attention by the pilot or a depth of sleep of the pilot based on the biometric parameter.

Abstract: A modular power distribution apparatus and method includes a frame defined by a first set of parallel supports and a second set of parallel supports, the second set of parallel supports connecting the first set of parallel supports, the frame defining a generally planar assembly, as well as a set of components extending from a side of the frame. The set of components includes a set of power modules.

Abstract: Techniques for employing a smart sensor device that has a primary sensing function for sensing a state of a physical component and can concurrently enable one or more backup functions for sensing one or more states of one or more other physicals components in response to one or more other smart sensor devices not being able to perform their primary function of sensing and/or reporting on the one or more states of the one or more other physical components.

Abstract: A method of adjusting an operator workload during a travel segment including tracking over a time period, using at least one sensor, one of inputs by an operator indicative of an operator workload or image sensor data or a biometric parameter indicative of an operator stress level during the travel segment. Determining, using a controller that is operatively connected to the at least one sensor, a level of one of the operator workload or operator stress level. The method also includes adjusting, using a controller that is operatively connected to the control computer, the operator workload when the level of one of the operator workload or operator stress level exceeds a predetermined threshold.

Abstract: A method and circuit for determining and extinguishing electrical faults includes a power supply, and electrical load, a controller module, and electrical sensors, and when the controller module does not extinguish the electrical fault, another switch blows a fuse.

Abstract: A trunnion-to-disk connection for use on an open fan configuration of a gas turbine engine may include an integral trunnion and blade spar inserted through a trunnion aperture of a fan disk and supported by top bearing and a bottom bearing. A cavity can be provided between a trunnion of the integral trunnion and blade spar and the fan disk, as well as between the top bearing and bottom bearing. Pressurized hydraulic fluid can be supplied to the cavity to urge the integral trunnion and blade spar in a direction to preload the bearings. Prior to pressurization, and prior to installation of the bottom bearing, the trunnion can be inserted into a trunnion aperture of the fan disk such that an end of the trunnion extends past the fan disk to provide sufficient space to insert the bottom bearing from within the open interior of the fan disk.

Abstract: An aircraft and non-transitory computer-readable medium for detecting the spoofing of a signal from a satellite in orbit. A receiver on the aircraft to receive an apparent satellite signal. A computer for determining at least two characteristic signatures of the signal including a power level, and indicating the apparent satellite signal is a spoofed satellite signal.

Abstract: A non-transitory computer-readable medium and apparatus for restoring navigational performance for a navigational system. The apparatus including a receiver for receiving by a first navigational system and a second navigational system a collection of data points to establish a real-time navigational route for the aircraft, and a computer for comparing navigational performance values or drift ranges. The computer capable of establishing a new navigational route based on the collection of data points.

Abstract: An apparatus and method for an aircraft flight management system configured to analyze a takeoff sequence for an aircraft, the aircraft slight management system comprising a memory storing runway information associated with the runway from which the aircraft will depart, one or more inputs configured to receive variables comprising real-time aircraft variables and real-time condition variables that influence an actual velocity of the aircraft, sensors for sensing the actual velocity of the aircraft; and a processor configured to compare a real-time takeoff value to a takeoff requirement value.

Abstract: A method of assessing an operator emotional state and sending an alert based on the emotional state. The method includes tracking during a time period, using at least one sensor, one of an image sensor data, voice data or a biometric parameter of an operator. Determining, using a controller that is operatively connected to at least one sensor, a probability of a likely emotional state from a list of emotional states of an operator based on one of the image sensor data, voice data or the biometric parameter. Comparing, using a processor, the probability of one of the likely emotional states of the operator with a baseline emotional state of the operator. Sending, using the controller, an alert if most likely emotional state deviates from the baseline emotional state by a predetermined threshold.

Abstract: A system and method for acquiring accurate vibration data, time of arrival, or other mechanical state for a mechanical system with rotary elements, such as a planetary gear system with multiple planet gears that rotate relative to a central sun gear, or blades in a turbine engine. Multiple vibration sensors are arranged at spaced intervals along the exterior of the gear system (such as along the ring gear of the system or the exterior housing of the system). Each vibration sensor is so situated as to periodically detect vibrations from each one of the planet gears in succession, as the planet gears rotate around the central sun gear. Using timing and gear-system configuration information, a determination is made as to which gear is being sensed by any one sensor at any time; also determined is which teeth of each gear are being sensed by a particular sensor at any one time.