Abstract: A server apparatus includes a communication unit, and a control unit configured to send an instruction for causing flight vehicles to perform a flight operation, to the flight vehicles. The flight operation includes energizing, by a first flight vehicle, a penetration tool toward a target object in a space, holding a first part, penetrated through the target object, and a second part, not penetrated through the target object, of a cord-shaped member attached to the penetration tool, and flying to outside the space, waiting, by a second flight vehicle, outside the space and receiving any one of the first and second parts from the first flight vehicle, and towing, by the first and second flight vehicles, the target object with the cord-shaped member and transporting the target object to outside the space by flying while respectively holding any one and the other of the first and second parts.

Abstract: Described herein are systems for roof scan using an unmanned aerial vehicle. For example, some methods include capturing, using an unmanned aerial vehicle, an overview image of a roof of a building from above the roof; presenting a suggested bounding polygon overlaid on the overview image to a user; determining a bounding polygon based on the suggested bounding polygon and user edits; based on the bounding polygon, determining a flight path including a sequence of poses of the unmanned aerial vehicle with respective fields of view at a fixed height that collectively cover the bounding polygon; fly the unmanned aerial vehicle to a sequence of scan poses with horizontal positions matching respective poses of the flight path and vertical positions determined to maintain a consistent distance above the roof; and scanning the roof from the sequence of scan poses to generate a three-dimensional map of the roof.

Abstract: A method and apparatus for controlling an Unmanned Aerial Vehicle (UAV) are provided. The method is applied to the UAV, and includes: receiving flight path information transmitted by a UAV controller, wherein the flight path information represents a flight path set by the UAV controller for the UAV controlled by the UAV controller; and transmitting the flight path information to a base station that provides a network service for the UAV, such that the base station determines the flight path based on the flight path information.

Abstract: A system and a method for drone docking are provided. The method includes: setting a moving platform on a vehicle; obtaining, by the moving platform, current environmental data and historical environmental data corresponding to the moving platform; generating, by the moving platform, a recommended flight parameter according to the current environmental data and the historical environmental data, and transmitting the recommended flight parameter to a drone; and adjusting, by the drone, a flight parameter of the drone according to the recommended flight parameter to dock on the moving platform.

Abstract: A storage facilities management device is configured to manage storage facilities such as storage sheds for keeping flight devices. Upon receiving instruction information including a takeoff/landing time of a flight device from a flight management device, the storage facilities management device acquires circumferential information representing circumstances of a storage shed before the takeoff/landing time so as to determine whether or not the flight device is able to take off at the takeoff time of the instruction information or to determine whether or not the flight device is able to land at the landing time of the instruction information according to the circumferential information, thus transmitting the determination result to the flight management device and allowing for takeoff or landing of the flight device according to the instruction information.

Abstract: A method includes obtaining a first test matrix for a first aircraft system and a second test matrix for a second aircraft system. The method also includes, during a first operational test of the first test matrix, obtaining sensor data that includes second sensor data that is not specified by the first test matrix. The method includes evaluating a second operational test of the second test matrix by processing the second sensor data using a second analytic model of the second aircraft system. The method also includes generating second predicted sensor data based on the evaluation of the second operational test. The method includes generating a second error measure by comparing a second subset of the sensor data to the second predicted sensor data. The method includes determining, based at least in part on a range of the second sensor data, a test coverage metric of the second test matrix.

Abstract: The following teachings are of a portable autonomous device and method operating independently of aircraft flight control equipment. The device can be easily moved from one aircraft to another. The device measures the acceleration of the aircraft from the instantaneous speed and the runway distance covered from the start of the acceleration. Once the runway length and take-off speed is input, the device calculates the remaining distance to safely reach the take-off speed. If the remaining runway distance is not enough for the safe take-off, the device provides visual or audible information about the situation and signals to the pilot. In other embodiments, the determination and presentation of the remaining runway length may be implemented in the aircraft flight control equipment.

Abstract: Methods, apparatuses, and systems for predicting radio altimeter failures are provided. An example method may include determining a first plurality of altitude values associated with a first radio altimeter, determining a second plurality of altitude values associated with a second radio altimeter, calculating a first level feature based at least in part on the first plurality of altitude values and the second plurality of altitude values, and determining a radio altimeter failure indicator based at least in part on the first level feature.

Abstract: A method for controlling an unmanned aerial vehicle within a flight operating space. The unmanned aerial vehicle includes one or more sensor arrays on each spar. The method includes determining, using a plurality of sensor arrays, a flight path for the unmanned aerial vehicle. The method also includes receiving, by at least one sensor array of the plurality of sensor arrays, sensor data identifying at least one object in the operating space. The sensor data is transmitted over a communications bus connecting components of the UAV. The method further includes determining, by one or more processors onboard the unmanned aerial vehicle, a flight path around the at least one object. The method also includes generating, by the one or more onboard processors, a first signal to cause the unmanned aerial vehicle to navigate within the operating space around the at least one object.

Abstract: A control device 200 includes at least one memory configured to store a program code, and at least one processor configured to access the program code and operate as instructed by the program code. The program code includes an acquisition code configured to cause the at least one processor to acquire a request for requesting determination as to whether or not a target area is usable for a predetermined purpose, and a control code configured to cause the at least one processor to perform control to cause a first flying object to fly to the target area. The acquisition code is configured to cause the at least one processor to further acquire sensing data that is data obtained by optical sensing of the target area by the first flying object. The program code further comprises a determination code configured to cause the at least one processor to determine, based on the acquired sensing data, whether or not the target area is usable for the predetermined purpose.

Abstract: The aircraft take-off awareness system predicts and informs the pilot about where on the runway certain safety speeds will be achieved. A processor coupled to receive inertial data from the aircraft computes an aircraft weight estimate based at least in part upon the inertial data. The processor then computes a future acceleration prediction based on the computed aircraft weight estimate. Using the future acceleration prediction, the processor then computes the position of various warning reference distances corresponding to predicted positions on the runway at which said certain safety speeds will be achieved. The processor generates a display that it dynamically updates as the reference distances change as the aircraft proceeds down the runway during take-off or aborted take-off.

Abstract: Described herein are systems for roof scan using an unmanned aerial vehicle. For example, some methods include capturing, using an unmanned aerial vehicle, an overview image of a roof of a building from above the roof; presenting a suggested bounding polygon overlaid on the overview image to a user; determining a bounding polygon based on the suggested bounding polygon and user edits; based on the bounding polygon, determining a flight path including a sequence of poses of the unmanned aerial vehicle with respective fields of view at a fixed height that collectively cover the bounding polygon; fly the unmanned aerial vehicle to a sequence of scan poses with horizontal positions matching respective poses of the flight path and vertical positions determined to maintain a consistent distance above the roof; and scanning the roof from the sequence of scan poses to generate a three-dimensional map of the roof.

Abstract: Technologically improved vehicle control systems and methods are described. The provided vehicle control systems and methods embody an inner loop auto-throttle control for causing delta-throttle changes, i.e., servo changes, to achieve desired acceleration targets. The system generates an error on a potential flight path angle using a received thrust acceleration command. The error on the potential flight path angle is converted into an equivalent acceleration. A throttle rate command TLA_ratecmd is generated by converting the equivalent acceleration into the throttle rate command TLA_ratecmd.

Abstract: A method for controlling an unmanned aerial vehicle within a flight operating space. The unmanned aerial vehicle includes one or more sensor arrays on each spar. The method includes determining, using a plurality of sensor arrays, a flight path for the unmanned aerial vehicle. The method also includes receiving, by at least one sensor array of the plurality of sensor arrays, sensor data identifying at least one object in the operating space. The sensor data is transmitted over a communications bus connecting components of the UAV. The method further includes determining, by one or more processors onboard the unmanned aerial vehicle, a flight path around the at least one object. The method also includes generating, by the one or more onboard processors, a first signal to cause the unmanned aerial vehicle to navigate within the operating space around the at least one object.

Abstract: A method of unmanned aerial vehicle (UAV) operation, including: receiving from a customer a first data request, the first data request having: a first geographic coverage area; and a refresh rate for the first geographic coverage area; planning a first plurality of flight missions to accomplish the first data request; uploading flight missions data representing the first plurality of flight missions into a UAV pod; and deploying the UAV pod.

Abstract: An example method of limiting an aircraft to a pitch axis envelope includes determining aircraft state limits associated with multiple pitch axis variables of an aircraft, determining predicted aircraft states, comparing the predicted aircraft states to the aircraft state limits to produce aircraft state errors, translating the aircraft state errors into a set of positive and negative limit elevator commands, selecting a highest priority positive limit elevator command, selecting a highest priority negative limit elevator command, limiting a primary pitch axis control law elevator command of the aircraft to a value that is less than or equal to the highest priority positive limit elevator command and greater than or equal to the highest priority negative limit elevator command, and controlling the aircraft according to the primary pitch axis control law elevator command limited to the value.

Abstract: A drone charging station configured to receive at least one drone, the docking station including an elongated docking shaft sized to engage with the at least one drone, the docking shaft having a drone entrance end and a drone exit end opposite the drone entrance end; and a drone guiding thread helically disposed along the elongated docking shaft, the drone guiding thread configured to engage with a corresponding guiding region on the at least one drone to allow the at least drone to move along the drone guiding thread from the drone entrance end to the drone exit end.

Abstract: A delivery container assembly for receiving a package. The delivery container assembly includes a container having at least one wall and an open top end defining a storage space. The container includes a lid hingedly coupled to the container and is movable between an open position and a closed position. The container includes an elevator assembly disposed within the container and including an elevator floor movable between a lowered position and a raised position. The lid is movable from the closed position to the open position upon movement of the elevator floor from the lowered position to the raised position.

Abstract: Methodologies, systems, and computer-readable media are provided for in-field authentication of autonomous electronic devices. A first mobile autonomous electronic device wirelessly communicates with a second mobile autonomous electronic device and receives a set of identification information associated with the second mobile autonomous electronic device. The first electronic device autonomously travels to a specified location and transmits a first authentication signal to the second electronic device upon arrival at the specified location. The second electronic device confirms the identity of the first electronic device based on the first authentication signal and transmits a second authentication signal to the first electronic device. Once the first electronic device has confirmed that the identity of the second electronic device corresponds to an expected identity, the first electronic device transfers the object to the second electronic device.

Abstract: A no/low visibility automatic takeoff system for an aircraft obtains a runway reference centerline and aircraft pointing direction (via the aircraft's sensors) and automatically controls the aircraft pointing direction to track the runway reference centerline. An initial vector is obtained based on the initial position of the aircraft the first piloted initiation of the takeoff roll. After the system obtains a centerline, it automatically tracks the centerline and corrects aircraft trajectory so the aircraft heading closely matches the runway centerline as the aircraft proceeds down the runway.

Abstract: A flight control system for an aircraft is disclosed. The flight control system includes one or more processors and a memory coupled to the processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive as input a plurality of first operating parameters that each represent an operating condition of the aircraft. The flight control system is further caused to determine a drag coefficient and a lift coefficient based on the plurality of first operating parameters. The flight control system is also caused to determine an estimated dynamic pressure based on both the drag coefficient and the lift coefficient.

Abstract: A small cell base station adapted to be secured to a strand cable is provided with a flywheel and an electric motor to rotate the flywheel in an axis of rotation substantially perpendicular to the strand cable. The rotating flywheel acts as a gyrostabilizer to prevent swinging of the small cell base station due to wind.

Abstract: A system having components coupled to an aircraft and components remote from the aircraft processes sensor-derived data, transmits information between aircraft system components and remote system components, and dynamically generates updated analyses of position and orientation of the aircraft relative to a desired landing site, while the aircraft is in flight toward the desired landing site. Based on the position and orientation information, the system generates instructions for flight control of the aircraft toward a flight path to the landing site, and can update flight control instructions as new data is received and processed.

Abstract: A method includes transmitting a first electromagnetic signal from a first node to a second node through free space. The method also includes transmitting a second electromagnetic signal from the first node to the second node through a communication link, where the communication link physically couples the first and second nodes. The method further includes identifying a distance between the first and second nodes based on a time-difference-of-arrival between reception of the first electromagnetic signal at the second node and reception of the second electromagnetic signal at the second node.

Abstract: A method of controlling a vehicle, which is configured to be autonomously driven, includes determining a learned route based on a driving route that the vehicle has driven in a manual mode from a starting location to an ending location, driving the vehicle along the learned route in an autonomous mode, detecting a parking space based on driving the vehicle along the learned route in the autonomous mode, and based on a detection of the parking space in the learned route, parking the vehicle in the detected parking space.

Abstract: The disclosed non-limiting embodiment provides important improvements in aircraft performance in short rejected takeoff systems by automatically detecting whether the speed of the aircraft does not exceed Vshort, where Vshort>V1; automatically detecting whether one of said plural engines has failed during takeoff while the aircraft is still in contact with the ground; and if the aircraft speed does not exceed vshort and an engine has failed, automatically performing an autonomous abort takeoff sequence to allow an improved takeoff weight in case of a single engine failure autonomously rejected takeoff. The aircraft's take off weight increase leads to increased payload or fuel quantity. The Payload increase allows for increased passenger and/or cargo capability. The fuel quantity increased allows the aircraft to achieve greater ranges. An aircraft provided with the proposed system, which reduces accelerate-stop distance, may then operate in shorter runways as compared to the prior art.

Abstract: Aspects include a system for transferring a payload between drones. The system includes a first aerial drone having a first transfer member and a first controller. The first controller including a processor configured to change a first altitude and first orientation of the first aerial drone. A second aerial drone is provided having a second transfer member and a second controller, the second transfer member having a cone member on one end, the second transfer member being configured to receive the payload. The second controller including a processor configured to change a second altitude and a second orientation of the second aerial drone. The controllers cooperate to dispose the first transfer member within the cone member and transfer the payload from the first aerial drone to the second aerial drone.

Abstract: An aircrew automation system and method for use in an aircraft. The aircrew automation system comprises one or more processors, an optical perception system, an actuation system, and a human-machine interface. The optical perception system monitors, in real-time, one or more cockpit instruments of the aircraft visually to generate flight situation data. The actuation system mechanically engages at least one flight control of the aircraft in response to the one or more flight commands. The human-machine interface provides an interface between a human pilot and the aircrew automation system. The human-machine interface comprises a display device to display a status of the aircraft and the actuation system.

Abstract: Disclosed are various embodiments involving use of a multi-scale fiducial by an autonomously controlled aerial vehicle. A first image at a first location is captured, and a first fiducial at a first scale of a multi-scale fiducial is recognized within the first image. The autonomously controlled aerial vehicle is piloted relative to the multi-scale fiducial based at least in part on information contained within the first fiducial. A second image at a second location is captured, and a second fiducial at a second scale of the multi-scale fiducial is recognized within the second image. An action is then performed based at least in part on information contained within the second fiducial.

Abstract: Embodiments for managing drones by one or more processors are described. A first aerial drone having a payload coupled thereto is controlled such that the first aerial drone travels from a first location to a second location. A second aerial drone is controlled such that the second aerial drone travels to the second location. While the first aerial drone and the second aerial drone are in flight at the second location, the payload is detached from the first aerial drone and coupled to the second aerial drone. After the payload is detached from the first aerial drone and while the payload is coupled to the second aerial drone, the second aerial drone is controlled such that the second aerial drone travels from the second location to a third location.

Abstract: A method of unmanned aerial vehicle (UAV) operation, including: receiving from a customer a first data request, the first data request having: a first geographic coverage area; and a refresh rate for the first geographic coverage area; planning a first plurality of flight missions to accomplish the first data request; uploading flight missions data representing the first plurality of flight missions into a UAV pod; and deploying the UAV pod.

Abstract: Automated throttle control is described herein. One disclosed example method includes calculating, using a processor, a thrust resolver angle based on a flight condition of an aircraft, and controlling a throttle from moving past at least one of the thrust resolver angle or a range defined by the thrust resolver angle to maintain the aircraft in a preferred flight mode.

Abstract: An aircraft includes a safe takeoff system that automatically and autonomously rejects a takeoff if actual measured acceleration deviates from calculations based on pre-flight parameters and the speed of the aircraft traveling down the runway is within a safe speed range to guarantee a successful low inertia rejected takeoff.

Abstract: A method and electronic device for providing an optimal quantity of aircraft fuel. The method comprises collecting recorded flight data from past flights of an aircraft; determining aircraft specific performance correction parameters per flight phase, using the recorded flight data; collecting a flight plan of the aircraft; determining the total fuel required for the given flight plan, using the aircraft specific performance correction parameters; determining a single synthetic drag factor (?DFMS) and a single synthetic fuel factor (?FFFMS) that, when used by the aircraft FMS, yield the said total fuel required for the given flight plan; receiving an estimated total fuel required determined by the aircraft FMS based on the flight plan, the single synthetic drag factor (?DFMS) and the single synthetic fuel factor (?FFFMS). The method allows reducing the fuel weight and total flight cost, and is particularly advantageous for FMS which only admit one single drag factor and one single fuel factor.

Abstract: A system and method is provided for commanding a payload of an aircraft. A plurality of flight segments, which comprise trajectory information of the aircraft, are received. A plurality of payload commands are generated using statements of payload intents. Each one of the payload commands are synchronized with at least one of the plurality of flight segments. The system and method express the operations to be performed by the payload onboard in order to achieve the established mission goals of the aircraft.

Abstract: A system includes a sensor configured to be located on an exterior of a vehicle, a processing circuit, and a display device. The sensor is configured to detect a surface condition of a surface and output an indication of the surface condition. The processing circuit is configured to receive the indication from the sensor and generate a visualization based on the indication. The display device is configured to display the visualization.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a control unit to command the gas turbine engine to perform one of a rolling takeoff procedure and an unrestricted takeoff procedure. The control unit is configured command the gas turbine engine to perform the rolling takeoff procedure when information required to determine whether the unrestricted takeoff procedure can be performed is unavailable to the control unit.

Abstract: An example method for predictive take-off rejection (TOR) of an aircraft includes receiving, at a computing device on the aircraft and at a time before the aircraft takes off for a current flight, outputs from a plurality of sensors positioned on the aircraft, comparing the outputs received from the plurality of sensors for the current flight to reference flight data, based on comparing the outputs received from the plurality of sensors for the current flight to the reference flight data the computing device making a determination of whether to initiate a TOR procedure before the aircraft reaches a takeoff speed on a runway, and based on determining to initiate the TOR procedure, the computing device sending a signal to a control device on the aircraft to initiate the TOR procedure.

Abstract: The present disclosure relates to a method of controlling the braking of an aircraft equipped with a landing gear bearing braked wheels, the aircraft being propelled by jet engines and equipped with a thrust reversal system, the method involving the steps of estimating the grip/adhesion of the braked wheels and activating the thrust-reversal system or modulating the reverse-thrust generated by the thrust-reversal system if this system is already activated, based on the estimated grip/adhesion.

Abstract: A system and method for determining the distance between at least one point on a vehicle and at least one projected area off of the vehicle includes receiving, with a processor, sensor signals indicative of LIDAR data for the projected area off the vehicle; applying, with the processor, a linear estimation algorithm to filter out noise within the LIDAR data and define a surface plane for the projected area; evaluating, with the processor, the LIDAR data against a vehicle state model; determining, with the processor, the distance between the at least one point on the vehicle and the at least one projected area off the vehicle; and commanding a response in the vehicle controls.

Abstract: An onboard system for controlling flight of an unmanned aerial vehicle. The system comprises: a flight management system configured for controlling flight of the unmanned aerial vehicle; a mission control module configured to send commands to the flight management system for guiding the unmanned aerial vehicle to perform a mission; a safety module configured to communicate commands to the flight management system for guiding the unmanned aerial vehicle to fly in a safe mode; a communication control component which is switchable between a mission state in which the flight management system receives commands from the mission control module and a safety state in which the flight management system receives commands from the safety module; and a monitor module configured to determine whether a trigger condition warranting a change in mode is present or not and to cause the communication control component to switch from the mission state to the safety state when the trigger condition is present.

Abstract: A method for automatically delivering a physical mail includes receiving, by an unmanned aerial vehicle from an unmanned aerial vehicle management system, a delivery information, the delivery information includes information about a first secure mailbox and information about a second secure mailbox, the first secure mailbox being related to a first target user, delivering the physical mail to the first secure mailbox, and rerouting the unmanned aerial vehicle carrying the physical mail from the first secure mailbox to the second secure mailbox in response to the physical mail being delivered to the first secure mailbox.

Abstract: There is provided a control device including an image display unit configured to acquire, from a flying body, an image captured by an imaging device provided in the flying body and to display the image, and a flight instruction generation unit configured to generate a flight instruction for the flying body based on content of an operation performed with respect to the image captured by the imaging device and displayed by the image display unit.

Abstract: Visual landing aids including a series of contrasting circles and polygons for unmanned aerial vehicles that are capable of being accurately detected over a wide range of angles and distances by an unmanned aerial vehicle equipped with a camera and shape detection capabilities. The visual landing said may be implemented using contrasting colors for the pattern which reflect visible and/or UV or infrared light, or by light emitting elements. In some examples, the landing aids includes a secondary smaller version of the landing aid shape pattern that is embedded within the larger pattern, to enable greater detection range while facilitating close-in precision guidance. In still further examples, light emitting elements may be pulsed at a rate that is synchronized with the camera shutter on the unmanned aerial vehicle to further enhance accurate detection.

Abstract: A method of determining the speed of the wind to be taken into account for determining a maximum authorized takeoff weight of an aircraft. A measured speed TASmes of the local wind is calculated from at least one current speed TASinst of the local wind and an observed speed TASobs of the local wind on the basis of weather observations and on the basis of a heading value. The measured speed TASmes is compared with the observed speed TASobs in order to determine a calculated speed TASperfo of the local wind while also making use of at least one instability criterion of the local wind as supplied by the weather observations and weather forecasts. The calculated speed TASperfo is then for taking into account in order to optimize the maximize authorized takeoff weight of the aircraft.

Abstract: A system and method for controlling a tail-sitter aircraft, includes determining a mode of operation for the aircraft; operating each of a large turbine engine and a small turbine engine to provide total aircraft power during hover or high-power mode of operation; and selectively providing aircraft power from the small turbine engine to a plurality of rotors during a long-range endurance cruise mode of operation.

Abstract: Systems and methods for processing aircraft flight information and flight plan information are described. Specific techniques are described for managing flight data in real time, sharing flight data between a plurality of systems, dynamically managing flight information, generating flight plan information, providing flight plan information to a user, and closing flight plan discontinuities.

Abstract: A method for sensing a takeoff of an aircraft includes receiving a rate of change in vertical motion of the aircraft, determining whether the rate of change in vertical motion of the aircraft exceeds a first threshold, integrating the rate of change in vertical motion of the aircraft and outputting a virtual altitude signal, responsive to receiving the indication that a portion of the aircraft is contacting a surface, delaying the virtual altitude signal through a discrete low pass filter and outputting a delayed virtual altitude signal, subtracting the delayed virtual altitude signal from the virtual altitude signal to output an altitude perturbation signal, determining whether the altitude perturbation signal exceeds a second threshold value, and outputting an indication that the portion of the aircraft is not contacting the surface responsive to the rate of change in the vertical motion of the aircraft and the altitude perturbation signal.

Abstract: Methods, systems, and computer readable media are disclosed for direct arming aircraft runway approach guidance modes, for example and without limitation, for aircraft operational. In some aspects, a method for directly arming a runway approach guidance mode of an aircraft includes displaying on a display unit an airport, selecting the airport and selecting an active runway for final approach, displaying an path toward the selected final approach runway, selecting the final approach runway, displaying on the display unit at least one symbol associated with at least one runway approach guidance mode, and arming at least one of the at least one runway approach guidance mode.

Abstract: To provide a warning system that can issue a stall warning taking a flight environment into account. The warning system according to the present invention is a warning system for an aircraft, for issuing a warning in the case where there is a possibility of the aircraft stalling, and includes a selecting section for selecting one of two or more calculation criteria based on an icing state of the aircraft, a calculating section for calculating a stall angle based on the selected calculation criterion, and a warning section for comparing the calculated stall angle with a current angle of attack of the aircraft and issuing a stall warning if the current angle of attack exceeds the stall angle.