Abstract: A leaning vehicle includes a vehicle body, a left front wheel, a right front wheel, a lean mechanism, and a lean brake mechanism. The lean mechanism causes the left front wheel and the right front wheel to lean about a front-rear direction as a rotation center when the vehicle body leans about the front-rear direction as a rotation center. The lean brake mechanism brakes a leaning operation of the lean mechanism. The lean brake mechanism includes a brake caliper and a brake disc. The brake caliper is attached to the lean mechanism and has a brake pad. The brake disc is attached to the lower arm of the upper arm and the lower arm that is farther from the brake pad in the front view, has a contact portion that generates braking force by being pressed by the brake pad.

Abstract: A tilting vehicle includes a frame unit, a tilting mechanism and two front wheels. The frame unit includes a head tube extending generally along an up-down direction, and a main frame detachably connected to the head tube. The tilting mechanism includes one crossbar pivotally connected to the head tube and extending along a left-right direction, and two connecting rods extending along the up-down direction, being opposite to each other along the left-right direction, and being pivotally connected to opposite ends of the one crossbar, respectively, such that the connecting rods are movable along the up-down direction relative to the head tube. The front wheels are rotatably mounted to the connecting rods, respectively.

Abstract: Flat mount brake calipers for bicycles are described herein. An example flat mount brake caliper includes a caliper body defining a first piston cylinder and a second piston cylinder. The caliper body has a flat mount surface with a first threaded bore and a second threaded bore extending into the flat mount surface. The first and second threaded bores are configured to receive threaded fasteners to couple the caliper body to a frame of the bicycle. The first and second piston cylinders are arranged such that projections of the first and second threaded bores do not intersect the first or second piston cylinders. The flat mount brake caliper also includes a brake pad and first and second pistons disposed in the respective first and second piston cylinders to move the brake pad relative to the caliper body.

Abstract: A motor is to be mounted on a vehicle as a drive source. The motor includes a motor shaft extending in an axial direction, a drive gear provided on the motor shaft, a gear shaft extending in the axial direction, a driven gear provided on the gear shaft and coupled to the drive gear, a rotating member, an inner bearing that supports the gear shaft, and an outer bearing that supports the gear shaft. The rotating member is provided on the gear shaft and is configured to be coupled to a power transmission member that transmits power to a wheel of the vehicle. The rotating member is located between the inner bearing and the outer bearing in the axial direction.

Abstract: The present invention relates to electric bicycle speed control device and method. According to the present invention, a torque of a motor for driving a wheel is controlled so that a speed of a pedal driven by a user follows a speed of the wheel, and a torque of the pedal is also controlled by applying an assist level according to the torque of the motor. Therefore, even in an electric bicycle with a chain, it is possible to feel a feeling of the pedal like a bicycle with a chain, and it is possible to adjust the force applied to the pedal according to the assist level.

Abstract: A propulsion device for a two-wheeled vehicle includes a mechanism for providing traction to a rear wheel for manual advancement of the vehicle and a first epicyclic gear reducer coupled with the mechanism and drivable by a first control device configured for varying the geometric configuration of the first epicyclic gear reducer and thus the gear ratio. A motor for assisting pedalling is interposed between the mechanism for the bottom bracket and the rear wheel and is coupled with a second epicyclic gear reducer, drivable by a second control device configured for varying the geometric configuration of the second epicyclic gear reducer and thus the corresponding gear ratio. The second epicyclic gear reducer is coupled and directly in contact with the rear wheel in order to transmit the movement from the propulsion device thereto.

Abstract: A bicycle derailleur comprises a derailleur body, a charging port, a charging-port cover, and a cover connector. The charging port is configured to be detachably connected to a charging cable to charge an electric power source. The charging-port cover is configured to be detachably attached to the charging port. The charging-port cover has a detachment state in which the charging-port cover is detached from the derailleur body to allow connection between the charging port and the charging cable. The cover connector is configured to couple the charging-port cover to the derailleur body in the detachment state.

Abstract: Conventional surfboards enable a rider to catch a wave and ride towards the shoreline while utilizing the power of the ocean to enjoy the ocean waves uniquely. A low-profile motorized surfboard has been developed to assist riders who may have a disability or struggle to get into the position necessary to begin riding the waves. The surfboard may comprise at least one propeller and electromechanical motor, which may provide propulsion for the rider. The surfboard may have an internal power system and supporting circuitry for safe and reliable propulsion. The motorized surfboard may have a low-profile system that is collapsible and allows for the rider to enjoy the surf as if the surfboard were a conventional system. The system may also function to return the rider to the shoreline.

Abstract: An advisory system of a vessel that monitors variables of a vessel system inclusive of systems and subsystems that are used to operate the vessel. The advisory system may use machine-learning to learn from an operator (i) whether or not two variables are related to one another, and (ii) likelihood that a variable will reach a threshold, and, optionally, time until reaching the threshold. The system may receive operator feedback (i) to indicate whether the two variables are related to one another, and (ii) whether a behavior of the variable is normal or not normal. Thereafter, if a determination that the same two variables are related to one another and behaving in a similar manner, provide notification to the operator of the behavior. In response to determining that the variable is behaving (e.g., trending) in a similar manner that is not normal, providing a notification to the operator.

Abstract: An underwater swimming aid includes a power device and a camera instrument fixing device, and the power device includes a propeller for providing power to drive the underwater swimming aid to advance and a connecting plate fixed to the propeller; and the camera instrument fixing device includes a mounting bracket and a fixing bracket, the mounting bracket is fixed to the connecting plate and is fixedly connected to the fixing bracket, and the fixing bracket is used for fixing a camera instrument. According to the underwater swimming aid, the camera instrument fixing device is fixed to an existing underwater swimming aid, and the camera instrument is mounted on the camera instrument fixing device, so that users can photograph underwater scenes while enjoying funs brought by the swimming aid.

Abstract: A diving helmet apparatus includes a diving helmet that is based on a 98th percentile anthropomorphic head form. The helmet is relatively smaller and lighter than convention diving helmets. The center-of-gravity and center-of-buoyancy of the helmet are co-located to reduce diver fatigue. The apparatus has unique neck dam latch devices that use cam mechanisms. The neck dam and the opening in the helmet that receives the diver's head both have a substantially oval shape that contributes to a significant reduction in the volume of the helmet. The apparatus also uses unique face mask latch devices. The neck dam and face mask latch devices allow a diver to easily secure and remove the helmet and face mask without the assistance of dive tenders.

Abstract: The present invention refers to a device for detecting the pressure of compressed gas cylinders in breathing apparatuses for scuba diving which can be powered by means of a battery, provided with a pressure sensor. The device allows the housing of sensors with sufficiently large dimensions, guaranteeing precise gas cylinder pressure readings. Furthermore, the elements that guarantee the watertight seal of the device can be replaced in a practical effective manner.

Abstract: A bottom touching assisting device suitable for deep-sea submersibles and an implementation method thereof are provided. Four support columns are arranged within a mounting box body at a bottom of a deep-sea submersible, the support columns and the mounting box body are connected in a sliding manner through sliders, and the support column is sleeved with a threaded sleeve in a threaded connection manner. In conjunction with a drive component and a pressing mechanism, smooth vertical movement of the support column is achieved when the threaded sleeve rotates. This allows a bottom end of the support column to extend from the mounting box body.

Abstract: A personal watercraft includes a floatation member, a thrust assembly, a steering assembly, and a braking assembly. The assemblies may be actuated either mechanically or electrically. The thrust assembly is human powered, solar powered, or electric powered. The thrust, steering, and braking assemblies can be added after-market to an existing stand-up paddle board (SUP), or built into one or a plurality of SUPs during initial manufacturing. When the thrust assembly is human powered, it is leg or arm powered. When the thrust assembly is leg powered, the legs can move backward and forward in a sliding motion, up and down in a stomping fashion, or move in a loop trajectory. When the thrust assembly is arm powered, the arms can move forward/backward together or separately. The thrust assembly includes one or a plurality of paddles or flippers that are positioned to the side or under the SUP.

Abstract: An underwater propulsion device is disclosed comprising two sleeves for fitting around each of a user's lower legs, with each sleeve mounting a propulsion unit, and the sleeves being connectable by a bar between them during underwater operation of the device by the user.

Abstract: Aspects of the present disclosure are directed to a method for refueling an electric vehicle, the method comprising: detecting, by one or more sensors, a lock signal as a function of installing a battery pack into the electric vehicle; and enabling the battery pack, in response to installing the battery pack, wherein enabling the battery pack comprises a contactor. Aspects of the present disclosure may also be direct to a system for refueling an electric vehicle.

Abstract: The present disclosure is directed generally toward sailing vessels. One example is a catamaran with one or more pivoting masts per hull member, which may pivot from a generally perpendicular upright position, to a generally flat stowed position toward the bow of the hulls. The masts are capable of sustaining a plurality of sails, which may travel 180 degrees with respect to the hulls.

Abstract: A system for providing raw water for cooling of one or more Auxiliary Systems of a Luxury Boat, when the Luxury Boat is in Temporary Dry Storage involves a pump, external to the Luxury Boat, a controller coupled to the external pump and a sensor coupled to a boat-based pump controller on the Luxury Boat. The sensor is configured to sense a trigger signal from the boat-based pump controller indicating that raw water is to be pumped to the one or more Auxiliary Systems and send a signal to the controller that will cause the controller to start the external pump pumping raw water to the Luxury Boat. A related method for controlling raw water supply to one or more Auxiliary Systems of a Luxury Boat, when the Luxury Boat is in Temporary Dry Storage is also described.

Abstract: A hatch locking device for an aircraft hatch includes an eccentric bush which can be connected to a hatch bulkhead of the aircraft hatch panel, an inner lining which is introduced into the eccentric bush and has a bolt receptacle which is oriented centrally along a bolt receptacle axis for receiving a locking bolt, a conical pressing sleeve in the inner lining, a conical clamping sleeve, the outer conical shell face of which is in displaceable engagement with an inner conical shell face of the conical pressing sleeve, and the inner cylindrical shell face of which is flush with the outer wall of the bolt receptacle, and linear actuators which are mounted on in each case two opposite sides of the conical pressing sleeve in the inner lining and are designed to displace the conical pressing sleeve along the bolt receptacle axis with respect to the conical clamping sleeve.

Abstract: Various flight control components can be operated through gearbox driven rotary actuators. In the event of a jam occurring the gearbox, the gearbox can be decoupled from a surrounding support housing to enable free-trailing or limited motion relative to the support housing. The motion may or may not be damped. Decoupling the gearbox enables the flight control component to move to a neutral or non-interfering position even when user control over the component has been lost.

Abstract: A failsafe vale provides “Hole-In-The-Wall” failsafe functionality for thin-wing aircraft control surface actuation systems having a geared rotary actuator powered by a hydraulic rotary motor. The failsafe valve is associated with the hydraulic rotary motor and mechanically connected to the control surface, and enables the flight control surface to return to an aerodynamically neutral failsafe position if electrical control and/or hydraulic pressure is lost. When the failsafe valve receives a normal command pressure from the hydraulic system, the valve is inactive and the actuation system operates normally. However, if there is a loss of electrical command capacity to control hydraulic valves and/or a loss of hydraulic pressure, the failsafe valve is activated and connects one of the motor hydraulic control lines to the case return line for the motor if the control surface is away from its failsafe position.

Abstract: A propulsive assembly, in particular for an aircraft, comprising a mast and a propulsion device comprising an engine and a nacelle, the engine comprising a propeller, the propulsive assembly comprising: A standby protection device comprising a first connecting member fixedly mounted to the mast and a second connecting member fixedly mounted to the propulsion device, the second connecting member being rotatably hinged with respect to the first connecting member in at least one degree of freedom, and at least one retaining member keeping the second connecting member fixed with respect to the first connecting member, and configured, in the presence of a predetermined unbalance force on the propeller, to release the standby protection device in order to protect the mast.

Abstract: Technologies are described herein for a drag recovery scheme. In various examples, a recovery engine is placed within a vortex flow of air caused by the impingement of air upon a nacelle of a main engine. The propeller of the recovery engine can use the vortex flow of air to provide additional thrust the aircraft, thus reducing the load on the main engines or providing an increased velocity.

Abstract: A leg mechanism includes an articulated leg system, a passive device and a cable. The articulated leg system has a leg portion. The passive device is coupled to the articulated leg system and is configured to apply a first force to a portion thereof. The cable is coupled to the articulated leg system and is configured to apply a second force, in opposition to the first force, to a portion thereof. When the cable is drawn away from the articulated leg system, the second force moves the leg portion in a first direction. When tension is released from the cable, the passive device exerts the first force so as to move the leg portion a second direction that is opposite the first direction.

Abstract: A transmit charging coil is driven to wirelessly transfer energy to a receiving charging coil. The wireless energy transfer can be adjusted in response to detecting the receive charging coil. Navigation of an un-manned vehicle may be adjusted in response to the wireless energy transfer.

Abstract: An energy-load assembly includes an accommodating box, a power source, a load and an undercarriage. The accommodating box can be connected to a body of an unmanned aerial vehicle; the power source is arranged in the accommodating box, and can provide electric energy to the unmanned aerial vehicle; the load is arranged at the bottom of the accommodating box; and the undercarriage is connected to the accommodating box. The energy-load assembly provided integrates the power source, the load and the undercarriage. The corresponding power source and the load can be integrated according to different tasks performed.

Abstract: An underwater and aerial vehicle includes a fixing frame, a core navigation system and an energy supply system. The fixing frame has a circular ring configuration in a middle part thereof, and the waterproof sealing cabin is fixed in the circular ring configuration, and multiple cantilever arms extend around the circular ring configuration. An underwater navigation control module and a relay are provided on an auxiliary fixing platform. A second brushless motor is provided on each of the cantilever arms. Each second brushless motor is provided with a marine propeller. A flight control module, a remote control receiver and a power management module are provided on a fixing platform. A first brushless motor is provided on each of the cantilever arms. Each first brushless motor is provided with a rotor via a coupling. The energy supply system is arranged in a lower part of the waterproof sealing cabin.

Abstract: Physical and logical components of a long line loiter control system address control of a long line loiter maneuver conducted beneath a carrier, such as a fixed-wing aircraft. Control may comprise identifying, predicting, and reacting to estimated states and predicted states of the carrier, a suspended load control system, and a long line. Identifying, predicting, and reacting to estimated states and predicted states may comprise determining characteristics of state conditions over time as well as response time between state conditions. Reacting may comprise controlling a hoist of the carrier, controlling thrusters of the suspended load control system, and or controlling or issuing flight control instructions to the carrier so as not to increase the response time and or to avoid a hazard.

Abstract: Methods comprise flying an aircraft at cruise which results in an aerodynamic lift force on a flight control surface of the aircraft that urges the flight control surface away from a stowed position. Concurrently with the flying, the methods include counteracting the aerodynamic lift force with a magnetic force that urges the flight control surface towards the stowed position and that results in the flight control surface being maintained in the stowed position during the flying. Flight control systems comprise a flight control surface and an adjacent structure. The flight control surface or the adjacent structure comprises a magnet and the other of the flight control surface or the adjacent structure comprises a ferromagnetic structure. A magnetic force urges the flight control surface toward a stowed position.

Abstract: A flight vehicle capable of improving the accuracy of the arrival position of baggage. The flight vehicle according to the present disclosure includes a mounting unit that holds a mounted object, holds the mounting unit via a string member, and has a moving means including a rotor blade provided between the upper end and the lower end of the mounting unit, when the mounting unit is viewed from the side.

Abstract: The present specification provides a device and method for controlling a winch parcel delivery system through an uncrewed aerial vehicle (UAV) or drone. The example apparatus contemplates the use of a winch that will attach to a hook with active and passive release mechanisms through a winch line. The apparatus is enabled to attach to a parachute recovery system. The apparatus can detect when the ground has been reached to enable safe delivery of parcels. The apparatus can removably attach to various types of drones.

Abstract: An aircraft light includes a support board and a supporting profile. The support board supports at least one electric light source, in particular at least one LED. The support board has two lateral edges, which extend in a longitudinal direction of the support board and which are spaced apart from each other in a transverse direction (T) of the support board. The supporting profile comprises a receiving space for receiving and supporting the support board. The receiving space is defined by a base, extending in a longitudinal direction (L) of the supporting profile and in a transverse direction (T) of the supporting profile, and two opposing side walls protruding from the base. The supporting profile further comprises two undercut sections, forming opposing slots in the two opposing side walls that are dimensioned for accommodating a lateral edge of the support board, respectively.

Abstract: An aircraft cabin partition system may include at least a first partition with a partition cut-out and a first flange with a first flange cut-out. The aircraft cabin partition system may include a first coupling assembly configured to be inserted within the first flange cut-out, configured to be inserted within an opening of a seat rail within a floor of an aircraft cabin, and configured to couple the at least the first partition to the seat rail when engaged. The aircraft cabin partition system may include at least a second partition with a second flange with a second flange cut-out. The aircraft cabin partition system may include a second coupling assembly configured to be inserted within the partition cut-out, configured to be inserted within the second flange cut-out, and configured to couple the at least the second partition to the at least the first partition when engaged.

Abstract: An armrest assembly comprising a secondary armrest assembly is disclosed that can be deployed from a stowed and nested position beneath a primary armrest, with the secondary armrest assembly comprising a plurality of articulable and pivotable components, a seating assembly comprising the present armrest assembly, and vehicles configured to comprise the present armrest and seating assembly.

Abstract: An environmental control system of a vehicle includes a first compression device including a compressor, a first turbine, and a power turbine operably coupled by a shaft. The first turbine is configured to receive a first medium, the compressor is configured to receive a second medium, and the power turbine is configured to receive a third medium. A second compression device, separate from the first compression device, includes a second turbine. The environmental control system is operable in a first mode and a second mode. In the first mode, the second medium is provided to the compressor and the second turbine sequentially. In the second mode, the second medium bypasses the second turbine. In in both the first mode and the second mode, only the second medium is provided to an outlet of the environmental control system.

Abstract: An air duct system for an aircraft provides passengers with light, data, electrical power, and sanitized air. The air duct system includes an air duct having a main body and a visible light source configured to generate visible light, where the visible light is modulated by one or more controllers based on a visible light communication protocol. The air duct system simultaneously achieves four functions for improving passengers' flying experience. First, a portion of the visible light transmitted by the air duct illuminates the interior cabin of the aircraft. Second, by modulating the visible light, the air duct system transmits and distributes data that is received by the passengers' electronic devices. Third, a portion of the visible light is converted into electrical power at each passenger seat to power passengers' electronic devices. Fourth, in embodiments, the visible light is emitted at a germicidal wavelength spectrum to create sanitized air.

Abstract: Thermoelectric cooling assemblies, and systems and methods employing such assemblies integrated within an aircraft antennae radome, with the cooling assemblies operating exclusively via electrical power provided by scavenging waste heat from an adjoining antennae array provide thermal protection to heat-sensitive structural components adjoining the antennae array.

Abstract: An electrothermal ice protection system (IPS) installed on an aircraft includes a sensor, a parting strip assembly, and a controller. The sensor monitors a direction of a local incident airflow that is imparted on the sensor. The parting strip assembly is coupled to the critical surface and includes a plurality of heating sections. The controller is in signal communication with the sensor and the parting strip assembly. The controller determines a direction of surface airflow incident on a critical surface of the aircraft based on the local incident airflow and selectively concentrates power to at least one targeted heating section among the plurality of heating sections with respect to non-targeted heating sections among the plurality of heating sections based on the direction of the surface airflow.

Abstract: An aircraft power system comprises a turbocharger, the turbocharger including a compressor for supplying combustion air to an internal combustion engine, a turbine operatively connected to an internal combustion engine to receive an exhaust flow from the internal combustion engine and convert energy of the exhaust flow into rotational power and, a turbo shaft operatively connecting the turbine to the compressor to transfer at least some of the rotational power to the compressor. A generator is operatively connected to the turbo shaft to receive at least some of the rotational power from the turbo shaft for generating electrical power. At least one electrically powered air-mover is electrically connected to the generator to receive at least some of the electrical power to produce thrust.

Abstract: A lightweight, high power density, fault-tolerant fuel cell system, method, and apparatus for full-scale clean fuel electric-powered aircraft having a fuel cell module including a plurality of fuel cells working together to process gaseous oxygen from air compressed by turbochargers, superchargers, blowers or local oxygen supply and gaseous hydrogen from liquid hydrogen transformed by heat exchangers, with an electrical circuit configured to collect electrons from the plurality of hydrogen fuel cells to supply voltage and current to motor controllers commanded by autopilot control units configured to select and control an amount and distribution of electrical voltage and torque or current for each of the plurality of motor and propeller assemblies, wherein electrons returning from the electrical circuit combine with oxygen in the compressed air to form oxygen ions, then the protons combine with oxygen ions to form H2O molecules and heat.

Abstract: The disclosure describes an automated aerial vehicle (AAV) and system for automatically detecting a contact or an imminent contact between a propeller of the AAV and an object (e.g., human, pet, or other animal). When a contact or an imminent contact is detected, a safety profile may be executed to reduce or avoid any potential harm to the object and/or the AAV. For example, if a contact with a propeller of the AAV by an object is detected, the rotation of the propeller may be stopped to avoid harming the object. Likewise, an object detection component may be used to detect an object that is nearing a propeller, stop the rotation of the propeller, and/or navigate the AAV away from the detected object.

Abstract: An aircraft includes electrical components and a ducted fan with a cooling coil. The aircraft is designed to discharge heat from the electrical components to the cooling coil.

Abstract: A multi-mode aircraft power-split-transmission system includes a rotational power input and a power-split transmission. The power-split transmission includes a sun gear, a planetary carrier, a ring gear, a first rotational power output, and a second rotational power output. The multi-mode aircraft power-split-transmission system also includes a first resistance device coupled to the first rotational power output and fixed to an airframe of the multi-mode aircraft and a second resistance device coupled to the second rotational power output and fixed to the airframe. Operation of the first resistance device causes power received from the rotational power input to be directed to the second rotational power output.

Abstract: Coupler assemblies are described that removably couple sides of an auxiliary fuel tank in a cargo area of an aircraft. In one embodiment, a first coupler of the coupler assemblies includes a first attachment member that supports a body with a hollow channel having a centerline disposed longitudinally in the fuselage between a first end and a second end, and a slot between an outer surface of the body and the hollow channel. A second coupler of the coupler assemblies includes an engagement member, a second attachment member, and an arm extending between the engagement member and the second attachment member. The engagement member is slidably received within the hollow channel from the first end, and fits slidably within the hollow channel to engage with the body of the first coupler, with the arm extending through the slot.

Abstract: This fuel tank dam closes a gap between a first structural component fixed to the inside surface of the outer plate of a fuel tank and a second structural component provided with a cutout part into which the first structural component is inserted. This fuel tank dam includes: a first portion that can be fixed to the first structural component; a second portion that has a surface extending in a direction intersecting with the first portion and can be fixed to the second structural component; and a third portion that has a bellows and is disposed between the first portion and the second portion. This fuel tank dam is configured such that the first portion, the second portion, and the third portion are integrated, the bellows has a thickness of 0.381 to 1.524 mm, and the second portion has a thickness of 0.762 to 7.620 mm.

Abstract: A time-delay latch for securing a structure in a specified position includes a housing, a fluid chamber contained within the housing for holding fluid, a pin that extends through the fluid chamber and is axially movable within and through the fluid chamber, and a release frame movably secured within the housing. When the pin is in a latched position, the release frame engages with the pin to prevent axial movement of the pin. When the pin is in an unlatched position, the release frame disengages from the pin to allow axial movement of the pin. The axial movement of the pin between the latched position and the unlatched position requires a prescribed duration of time to elapse. During operation, the axial movement of the pin between the unlatched position and the latched position can occur faster than the prescribed duration of time.

Abstract: A fixed-wing cargo aircraft having a kinked fuselage to extend the useable length of a continuous interior cargo bay while still meeting a tailstrike requirement is disclosed. The fuselage defines a continuous interior cargo bay along a majority of its length and a pitch axis about which the cargo aircraft rotates during takeoff while still on the ground. The fuselage includes a forward portion defining longitudinal-lateral plane of the cargo aircraft an aft portion extending aft from the pitch axis to the aft end and containing an aft region of the continuous interior cargo bay that extends along a majority of a length of the aft portion. The aft portion has a centerline extending above the forward upper surface of the aircraft.

Abstract: Systems and methods are provided for assembling a structure. The systems and method including micro pulsing a structure along a track in a process direction by less than a length of the structure. The structure is indexed to one or more work stations by mating indexing features in a manufacturing excess of the structure to complementary features at the work stations. The work stations would the perform work on the structure at the work stations while the structure is indexed to the work stations. Iteratively repeating the micro pulsing and indexing and working upon the structure until it is ready to advance to the next assembly process.

Abstract: Systems and methods for fusing and analyzing multiple sources of data from a plurality of aircraft-related data sources for fault determination and other integrated vehicle health management (IVHM) diagnostics are provided. More particularly, one or more portions of data from a plurality of aircraft-related data sources for one or more aircraft are accessed. One or more alerts indicative of a data anomaly within the one or more portions of aircraft-related data sources can be detected, wherein a type of alert and originating data source associated with each alert as well as optional related confidence scores can be identified. One or more aircraft faults can be determined based at least in part on a correlation of identified types and data sources for detected alerts. An output indicative of the determined one or more aircraft faults can be provided.

Abstract: Methods and apparatus to measure multiple control surfaces with a sensor are disclosed. A disclosed example apparatus for determining a condition associated with first and second control surfaces includes a sensor to measure a rotation of a shaft operatively coupled thereto. The apparatus also includes a first differential operatively coupled between the shaft and a first pivot of the first control surface, and a second differential operatively coupled between the first differential and a second pivot of the second control surface.