Abstract: Herein provided is an interface for use in transmitting data from an aircraft including a first connector configured for physically and removably coupling a communication module to a communication system which obtains the data on-board the aircraft from at least one data source within the aircraft, and a second connector for digitally coupling the communication module to a processing unit of the communication module producing at least one message for transmission based on the data, the at least one message comprising information of interest identified based on the data. The interface is configured for conducting the at least one message from the processing unit to at least one radio via the second connector.

Abstract: Methods and apparatus are disclosed for deployable wing portions of an aircraft. An example method of deploying an aircraft includes separating the aircraft from a launch vehicle, the aircraft having a wing pivotably coupled to a fuselage, rotating, about an axis of rotation, the wing relative to the fuselage from a first rotational orientation to a second rotational orientation different from the first rotational orientation, wherein, in the first rotational orientation, the wing extends along a direction that substantially aligns with a longitudinal axis of the fuselage, and extending the wing in a lateral direction away from the fuselage in the second rotational orientation.

Abstract: The disclosure relates to a flight control system comprising at least one hydraulic servo actuator, wherein the servo actuator includes a two-stage electrohydraulic servo valve, wherein the servo valve comprises a pilot stage in which the control current is translated into a hydraulic control pressure, and a power stage in which a valve slide is moved in response to the control pressure in order to adjust the throughflow direction and throughflow cross-section of the valve. The disclosure furthermore relates to an aircraft comprising such a flight control system.

Abstract: A non-rigid airship or hybrid air vehicle has a pressure-stabilised envelope (100) that includes at least one ballonet (102, 103). A system is provided for measuring the geometry of the lifting gas enclosure (101) within the pressure-stabilised envelope (100). The system comprises a plurality of sensors (104, 109) located outside the ballonet(s) but inside the envelope, for measuring the geometry of the enclosure. Some of the sensors (104) are arranged to measure an internal surface of the pressure-stabilised envelope (100), and others of the sensors (109) are arranged to measure an external surface of the at least one ballonet (102, 103).

Abstract: A wing for an aircraft, including a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position. The connection assembly includes a first connection station and a second connection station spaced apart from the first connection station in a wing span direction. The object, to prevent the slat from skewing, is achieved in that the connection assembly includes a sync shaft coupling the first connection station to the second connection station for sync movement of the first and second connection stations.

Abstract: A management system of a work site includes an image data acquisition unit that acquires image data of an unmanned vehicle stopped at the work site due to generation of a trouble, the image data being imaged by an imaging device mounted in a movable body.

Abstract: A wind forecasting system configured to generate forecasted wind conditions for a time interval based on wind data derived from flight log data collected from a plurality of aerial vehicles operating in a first area. The forecasted wind conditions can be used by an aerial route management system to generate a flight plan for an aerial vehicle from a start location to an end location in the first area during the time interval.

Abstract: An attachment assembly for connecting an actuator to a frame, a method for manufacturing this attachment assembly and a method for reducing backlash in an attachment assembly. The attachment assembly comprises: an outer yoke having a first end and an opposite second end and defining an internal cavity at said second end. The outer yoke has an aperture provided at its second end connected to the cavity; and an inner yoke located within the cavity. A tie bar having a ball shaped end extends through said aperture such that the ball shaped end is positioned within the cavity and cannot pass through the aperture. A spring is provided at said first end of said outer yoke that is configured to bias the inner yoke in the direction of the aperture. The attachment also includes shearable means for holding the inner yoke.

Abstract: This disclosure describes systems and methods for a multipoint cable cam (MPCC) of an aerial vehicle. A method includes operations of receiving user input associated with a predetermined path and correlating the received user input with stored global positioning satellite (GPS) data to generate one or more virtual waypoints along the predetermined path. The method includes processing the one or more virtual waypoints to generate a spline-based flight path. The method may include storing the spline-based flight path and transmitting the spline-based flight path to the aerial vehicle.

Abstract: A crank device provided with an upstream lever and with a downstream lever. The crank device includes a phase shifter system connected to the upstream lever and to the downstream lever so that movement in rotation of the upstream lever about an axis of rotation induces movement in rotation of the downstream lever about the axis of rotation, the phase shifter system comprising a linear actuator mechanism carried by the upstream lever, the linear actuator mechanism having an outlet rod, the outlet rod having only one degree of freedom of movement in translation relative to the upstream lever, the outlet rod being connected via an outlet helical connection to the downstream lever so that movement in translation of the outlet rod generates movement in rotation of the downstream lever about the axis of rotation.

Abstract: A method includes determining a first speed value based on a first signal from a first data source. The method also includes determining a second speed value based on a second signal from a second data source. The method further includes determining a first likelihood of icing value based on a third signal from a third data source. The method also includes determining a second likelihood of icing value based on a fourth signal from a fourth data source. The method further includes performing a first comparison between the first speed value and the second speed value and performing a second comparison between the first likelihood of icing value and the second likelihood of icing value. The method also includes generating sensor reliability data based on the first comparison and the second comparison and displaying situational awareness data based on the sensor reliability data.

Abstract: The present subject matter relates to systems and methods for generating trajectories for a plurality of vehicles in a multi-vehicle system. An optimal motion plan is determined for moving each of the plurality of vehicles between a respective starting position and an assigned goal position, possible collisions are identified among the optimal motion plans of the plurality of vehicles, and, for a subset of the plurality of vehicles identified as being associated with a possible collision, the optimal motion plan of each vehicle in the subset is modified to define modified trajectories that each include a common circular holding pattern such that the possible collision is avoided.

Abstract: Structure inspections are performed with a high resolution by first performing a modeling flight path at a relatively high altitude over the structure. Images are gathered during the modeling flight path and are used to generate a three dimensional model of the structure. From the three dimensional model a lower altitude closer inspection flight path is defined and executed.

Abstract: According to one or more aspects, a control system for managing operational limits associated with two or more actuators includes a controller. The controller may continually monitor a first operational limit associated with a first actuator and a first operational limit associated with a second actuator. The controller may determine a first overall distributed control system operating limit based on the first operational limit associated with the first actuator, the first operational limit associated with the second actuator, and a type of operational limit associated with both operational limits.

Abstract: Typical inventive practice allocates functions between human and robot, interacting in an unmanned system. Analyses are performed of: mission system; function allocation; and, human-robot interaction automation allocation. Mission system analysis includes: identification of mission system needs, mission system integration parameters, and mission capability configuration; and, mission system report creation (at least partially based on these identifications). Function allocation analysis includes: mission activity analysis; functional allocation report creation (at least partially based on the mission activity analysis); unmanned system safety analysis; and, unmanned system safety report creation (at least partially based on the unmanned system safety analysis).

Abstract: A gimbal having a split design, which can be used in an assembly for actuating an aerodynamic high lift device, is described. The gimbal enables a rotating load path when a force is transferred from the actuator to the high lift device via the gimbal. In particular, the split design can include two receivers which can be coupled to posts extending from a nut. The nut can be secured to a shaft which receives a force generated by the actuator. In one embodiment, the actuator can rotate the shaft to cause the gimbal to translate along the shaft. The split design provides a more compact form factor and is lighter in weight than traditional gimbal designs.

Abstract: A gas turbine engine is disclosed having a tip clearance control system. The tip clearance control system has a cabin blower system, a casing arranged in use about a rotor of a gas turbine engine and a fluid delivery passage. The cabin blower system having a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and to compress fluid conducted via the fluid delivery passage into heat exchange with the casing.

Abstract: A method of imaging on a mobile platform includes exposing an imaging device mounted aboard the mobile platform at a plurality of positions of a component of the mobile platform to obtain images, determining, using the images, allowed positions of the component that do not obstruct a field-of-view of the imaging device, and controlling the imaging device according to the allowed positions to avoid imaging the component.

Abstract: The present invention relates to a method and an apparatus for controlling an unmanned aerial vehicle. The method includes: obtaining a flight area control parameter; determining a flight area based on the flight area control parameter; and causing unmanned aerial vehicle to cruise within the flight area, wherein causing unmanned aerial vehicle to cruise within the flight area includes: determining a flight path within the flight area, and causing unmanned aerial vehicle to fly on the flight path periodically in a reciprocating manner, and the flight area is at least one of: a planar flight area, a linear flight area, and a three-dimensional flight area.

Abstract: An aircraft system including an aircraft and an electronic instrument on the aircraft, the electronic instrument including a wireless connectivity interface providing wireless communication over at least one communication channel and a display, wherein the display provides a visual indication of an availability of the communication channel.

Abstract: Systems and methods for mapping trip trajectories include identifying one or more vehicle trips (e.g., aircraft flights). One or more trajectory configurations associated with at least a portion of each vehicle trip can be identified, and location data associated with the one or more vehicle trips can be requested. Trip trajectory data based at least in part from the location data associated with the one or more vehicle trips and the one or more trajectory configurations associated with at least a portion of each vehicle trip can be generated. The trip trajectory data can be provided for display on a map of a geographic area including one or more locations defined by the location data associated with the one or more vehicle trips.

Abstract: Methods provide for guidance without sensing data about an ownship, the method includes: pre-loading, from an airport mapping database to an lateral guidance computer within a cockpit, airport mapping data for use in guidance of the ownship from a lateral guidance computer; executing airport moving map applications to process the airport mapping data to form a synthesized view for displaying on a display within the cockpit; receiving by the electronic information device within the cockpit at least one of a 3D spatial representation of the ownship; overlaying the 3D spatial representation of the ownship onto the synthesized view for providing a visual 3D representation of the ownship; and providing, without using the sensing data about the ownship, one or more cues, by a digital taxi application based on only airport mapping data and dimensions associated with the 3D spatial representation of the ownship, on the display within the cockpit.

Abstract: Disclosed is an automatic climbing and gliding method of a high altitude unmanned aerial vehicle (UAV). The disclosed method includes setting a cylindrical virtual flight region so that the high altitude UAV climbs and glides, setting a first target point on an end of a first flight radius which is vertically arranged to form the virtual flight region, setting second to Nth target points at arbitrary second to Nth flight radii sequentially arranged above or below the first flight radius, having the target points have a predetermined plane slope angle, and allowing the UAV to climb along a straight path line sequentially connecting each of the target points.

Abstract: A computerized method performed by an unmanned aerial vehicle (UAV), comprising: receiving, by the UAV, a flight plan comprising a plurality of inspection locations for a structure, wherein the plurality of inspection locations each comprise a waypoint having a geospatial reference; navigating to ascend to a first altitude above the structure; conducting an inspection for an object of interest in at least one of the plurality of inspection locations according to the flight plan, the inspection comprising: navigating to a position above a surface of the structure associated with the object of interest based on monitoring an active sensor, and obtaining, while within a particular distance from the surface of the structure, information from one or more sensors describing the structure such that obtained information includes at least a particular level of detail; navigating to another inspection location of the plurality of inspection locations; and navigating to a landing location.

Abstract: Systems and methods for controlling an unmanned aerial vehicle within an environment are provided. In one aspect, a system comprises one or more sensors carried by the unmanned aerial vehicle and configured to provide sensor data and one or more processors. The one or more processors can be individually or collectively configured to: determine, based on the sensor data, an environment type for the environment; select a flight mode from a plurality of different flight modes based on the environment type, wherein each of the plurality of different flight mode is associated with a different set of operating rules for the unmanned aerial vehicle; and cause the unmanned aerial vehicle to operate within the environment while conforming to the set of operating rules of the selected flight mode.

Abstract: A display system for an aircraft includes a controller in communication with a display. The controller receives a category associated with a phase of flight of the aircraft. Information related to operation of the aircraft and associated with the received category is displayed on the display.

Abstract: The present disclosure provides an autonomous navigation method and system, and a map modeling method and system. The autonomous navigation method comprises: controlling an unmanned aerial vehicle to take off, and collecting videos of a scene corresponding to the unmanned aerial vehicle at each collection time point; obtaining feature points in the videos of the scene corresponding to each collection time point; generating a flight path of the unmanned aerial vehicle according to the feature points in the videos of the scene corresponding to each collection time point; generating a first map model according to the flight path of the unmanned aerial vehicle and the videos of the scene corresponding to each collection time point; and carrying out autonomous navigation on the unmanned aerial vehicle according to the first map model.

Abstract: An unmanned aerial vehicle (UAV) assessment and reporting system may conduct micro scans of a wide variety of property types. A risk zone within which the UAV may navigate during the micro scan may include a plurality of virtual tags that identify navigational hazards relevant to the navigation of the UAV at a specific location or specify scan actions to be implemented while the UAV is at the specific location. Scan data from any of a wide variety of sensor types may be compared with profile data using computer vision techniques to identify characteristics, defects, damage, construction materials, and the like. A rule set evaluator may evaluate tags and/or matched profile data to determine adaptive actions to modify the navigation or scanning process of the UAV.

Abstract: A system and method are provided and include a light source projector mounted on a subject vehicle, a controller that controls the light source projector to project a bounding box on a roadway upon which the subject vehicle is traveling in a destination lane of a lane change of the subject vehicle; and a sensor that detects a response image projected by a secondary vehicle on the roadway in the adjacent lane, the response image indicating either agreement or disagreement with the lane change of the subject vehicle. The controller generates an alert in the subject vehicle based on the detected response.

Abstract: [Object] To provide an information processing device for enabling a user to easily carry out effective photography depending on a subject or location. [Solution] Provided is an information processing device including: a flight route generation unit that presents a template of flight route information showing a flight route of a flying object, and generates flight route information of the flying object, associating the flight route information of the selected template with a flight range of the flying object, on the basis of an operation performed by a user.

Abstract: A command and control system is provided which links users and platforms in real time and with touch screen ease, delivering a highly intuitive, integrated user experience with minimal infrastructure. Capitalizing on a cloud based architecture, from the cloud, to the touch table, to a hand held device, the command and control system creates seamless connections between sensors, leaders and users for up-to-the-minute information clarity.

Abstract: Embodiments described herein may help to provide support via a fleet of unmanned aerial vehicles (UAVs). An illustrative medical-support system may include multiple UAVs, which are configured to provide support for a number of different situations. Further, the medical-support system may be configured to: (a) identify a remote situation, (b) determine a target location corresponding to the situation, (c) select a UAV from the fleet of UAVs, where the selection of the UAV is based on a determination that the selected UAV is configured for the identified situation, and (d) cause the selected UAV to travel to the target location to provide support.

Abstract: A method to determine a risk of failure for a machine including: generating a first value for a risk of failure of the machine, wherein the first value is determined by a first model receiving as an input a condition of the machine and the first model includes a relationship derived from historical machine failures and correlating the input condition of the machine to a value for the risk of failure; generating a second value of the risk of failure of the machine, wherein the second value is determined by a second model receiving as an input information regarding wear or degradation of the machine and the second model includes a relationship correlating the input information regarding wear or degradation to a value for the risk of failure, and determining a total risk of failure based on the first and second values of the risk of failure.

Abstract: The drone (10) comprises an onboard video camera (14) picking up a sequence of images to be transmitted to a remote control. The user selects an exposure mode such as forward or sideways, panoramic or boom plane, tracking, defining a trajectory to be transmitted to the drone. Corresponding setpoint values are generated and applied to a processing subsystem controlling the motors of the drone. Once the drone is stabilized on the prescribed trajectory (38), the exposure by the video camera (14) is activated and the trajectory is stabilized by an open loop control avoiding the oscillations inherent in a servocontrol with feedback loop.

Abstract: Methods, systems, and process-readable media include an autonomous vehicle override control system that receives override commands from a pilot qualified on a first type of unmanned autonomous vehicle (UAV) and translates the inputs into suitable commands transmitted to a target UAV of a second UAV type. A pilot's certification for a first UAV type may be determined from the pilot's login credentials. The system may obtain a first control model for the first UAV type and a second control model for the target UAV. Pilot input commands processed through the first control model may be used to calculate movements of a virtual UAV of the type. The system may estimate physical movement of the target UAV similar to the first physical movement, and generate an override command for the target UAV using the second control model and the second physical movement. Control models may accommodate current conditions and pilot experience.

Abstract: A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.

Abstract: Systems and methods are provided for docking an unmanned aerial vehicle (UAV) with a vehicle. The UAV may be able to distinguish a companion vehicle from other vehicles in the area and vice versa. The UAV may take off and/or land on the vehicle. The UAV may be used to capture images and stream the images live to a display within the vehicle. The vehicle may control the UAV. The UAV may be in communication with the companion vehicle while in flight.

Abstract: Embodiments described herein may help to provide support via a fleet of unmanned aerial vehicles (UAVs). An illustrative medical-support system may include multiple UAVs, which are configured to provide support for a number of different situations. Further, the medical-support system may be configured to: (a) identify a remote situation, (b) determine a target location corresponding to the situation, (c) select a UAV from the fleet of UAVs, where the selection of the UAV is based on a determination that the selected UAV is configured for the identified situation, and (d) cause the selected UAV to travel to the target location to provide support.

Abstract: Systems and methods for configuring a direct lift control system of a vehicle are disclosed. An example system provided herein includes a spoiler coupled to an aircraft, a direct lift control schedule to generate a plurality of spoiler deflection commands and a controller to control an actuator coupled to the spoiler to actuate the spoiler based on the spoiler deflection commands to modulate lift of the aircraft without using a short-period pitch control.

Abstract: Systems and methods for UAV safety are provided. An authentication system may be used to confirm UAV and/or user identity and provide secured communications between users and UAVs. The UAVs may operate in accordance with a set of flight regulations. The set of flight regulations may be associated with a geo-fencing device in the vicinity of the UAV.

Abstract: Technologies are generally described for controlling a flight path of a UAV based image capture system for solid modeling. Upon determining an initial movement path based on an estimate of a structure to be modeled, images of the structure to be modeled may be captured and surface hypotheses formed for unobserved surfaces based on the captured images. A normal vector and a viewing cone may be computed for each hypothesized surface. A set of desired locations may be determined based on the viewing cones for the entire structure to be modeled and a least impact path for the UAV determined based on the desired locations and desired flight parameters.

Abstract: A system and method of monitoring received instrument landing system (ILS) signals onboard an aircraft includes performing a pre-approach sampling of the received ILS signals to thereby generate pre-approach phase ILS data. A statistical approach course of the aircraft is determined based at least in part on the pre-approach phase ILS data. A determination is made as to when the aircraft is below a predetermined activation altitude and, when it is, approach sampling of the received ILS signals is performed to generate approach phase ILS data. The approach phase ILS data is compared to the statistical approach course to determine a course deviation. An alert signal is selectively generated when the course deviation exceeds a predetermined magnitude.

Abstract: A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and/or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types.

Abstract: Said system (1) comprises as least the following principal functions, a flight path management function (2), a navigation function (3) which makes it possible to calculate the position of the aircraft, a function (5) for calculation of deviations between the position of the aircraft and a flight path to be followed, a management function (6) of at least one navigation database, a management function (7) of performance calculations of the aircraft, and a function (8) of management of interfaces and of display, each of said principal functions being allocated to a specific device of the aircraft, said flight path management function (2) being linked to each of said other principal functions.

Abstract: A system for enhancing movement of a multi-engine flight vehicle about either of pitch or yaw axes. The engines are oriented relative the centerline of the flight vehicle and a portion of the engines have a positive tangential cant and the remaining engines have a negative tangential cant. The attitude of the flight vehicle about the pitch, yaw and roll axes is controlled by differentially throttling the multi-engine flight vehicle.

Abstract: An aerodynamic wing load distribution control apparatus for increasing flight performance of an aircraft. The apparatus may include an aileron uprigger connectable to left and right ailerons of an aircraft and configured to uprig the left and the right wing ailerons of such aircraft. An operator interface communicates operator command inputs to the aileron uprigger. The aileron uprigger includes left and right actuators actuable in response to command inputs received from an operator through the operator interface and are connectable into respective left and right aileron control linkages of an aileron actuator assembly.

Abstract: A system for enhancing movement of a multi-engine flight vehicle about either of pitch or yaw axes. The engines are oriented relative the centerline of the flight vehicle and a portion of the engines have a positive tangential cant and the remaining engines have a negative tangential cant. The attitude of the flight vehicle about the pitch, yaw and roll axes is controlled by differentially throttling the multi-engine flight vehicle.

Abstract: The invention relates to a device aboard an aircraft comprising output means configured to restore information relating to the aircraft status from aircraft systems, the device including a module providing interface between said output means and said aircraft systems, said module being configured to synthesize information from aircraft systems depending on predetermined behavior rules and to transmit said information thus synthesized to said output means.

Abstract: In one or more embodiments, an apparatus and method for operating an unmanned and autonomous vehicle includes a sensor management module configured to direct sensors as to what function they are to provide; a mission management module configured to provide execute function capabilities; an effects management module configured to provide launching and directing weapons to their target capabilities; a vehicle management module; a situation awareness management module configured to provide correlate sensor data of objects, threats, targets, geographic points of interest that the pilot requires in the immediate environment; a communications management module; an information management module configured to provide a database of intelligence-related data; a middleware module configured to interface with the sensor management module, the mission management module, the effects management module, the vehicle management module, the situation awareness management module, the communications management module, and the inf

Abstract: A system and method for multiple vehicles to be dispatched and routed to multiple destinations, with or without constraints, containing a software core, which uses bounded geographic regions (“BGRs”) and Node Pairs to explicitly optimize, in two dimensions, for user desired dependent variables, by analyzing variance due to standard and user-defined independent variables. The invention stores Node Pair data, and can use error function, feedback, and ANOVA/MANOVA to create a tightly convergent dispatching and navigation solution.