Abstract: An object of the present disclosure is to provide a flight management apparatus capable of improving the safety of flying objects. In one example, a flight management apparatus (10) of the present disclosure includes a determination unit (12) configured to determine whether a specific space cell in a space is already reserved based on a reservation state about the specific space cell, when the flight management apparatus receives a request for permission to move to the specific space cell from a flying object; and a permission unit (13) configured to permit the movement to the specific space cell of the flying object when the determination unit determines the specific space cell is not reserved, and not to permit the movement to the specific space cell of the flying object when the determination unit determines the specific space cell is already reserved.

Abstract: Embodiments of the present disclosure set forth techniques for compensating for a roll effect for an optical sensor. The techniques include receiving sensor data from at least one sensor associated with the vehicle, detecting an amount of a roll of the vehicle based on the sensor data, generating a command based on the detected amount of roll, and controlling an orientation of the optical sensor based on the command.

Abstract: A method of checking accuracy of an air data probe system onboard a vehicle is disclosed. An embodiment of the method involves: calculating airspeed measurements from air data provided by the probe system; calculating vehicle speed measurements based on sensor data collected from at least one sensor system onboard the vehicle, wherein the vehicle speed measurements are distinct and independent of the airspeed measurements, and the vehicle speed measurements are calculated without using the air data; comparing a calculated airspeed measurement against a calculated vehicle speed measurement to obtain a speed difference, wherein the calculated airspeed measurement and the calculated vehicle speed measurement correspond to a measurement time during which the vehicle is moving forward; and initiating at least one corrective action onboard the vehicle when magnitude of the speed difference exceeds a threshold value.

Abstract: An aircraft with a unit to transmit information on ability/inability of pilots to fly the aircraft. Guidance avionics include guidance architecture and a flight controller to fly the aircraft. The guidance architecture has two dissimilar guidance chains and a selection unit connected thereto, to the flight controller and to the unit for measuring physical ability/inability, a first guidance chain to compute a main path for the aircraft towards a destination airport based on a current state of the aircraft by following a flight plan and to compute main guidance instructions for following the main path, a second guidance chain to compute an emergency path for the aircraft towards a diversion airport based on an initial portion of the common path with the main path and to compute emergency guidance instructions for following the emergency path. The selection unit receives the main and emergency guidance instructions and transmits either one to the flight controller.

Abstract: Techniques for establishing the sufficiency of a path planner to avoid multiple obstacles in planning a path from a starting location to a destination location is presented. The techniques can include: iterating, until a stopping condition occurs: obtaining, from the path planner, a path from the starting location to the destination location; representing the path from the starting location to the destination location as a disjunction of logical terms; conjoining the disjunction of terms to a conjunction of terms representing previously considered paths; determining a satisfiability condition of the conjunction of terms; and for a positive satisfiability condition, adding at least one corresponding obstacle of the plurality of obstacles to the path planner; and providing an indication of sufficiency of the path planner to avoid the obstacles in planning a path from the starting location to the destination location based on the stopping condition.

Abstract: A method is provided for supporting an aircraft approaching a runway on an airfield. The method includes receiving a sequence of images of the airfield, captured by a camera onboard the aircraft approaching the runway. For at least one image of the sequence of images, the method includes applying the image(s) to a machine learning model trained to predict a pose of the aircraft relative to the runway. The machine learning model is configured to map the image(s) to the pose based on a training set of labeled images with respective ground truth poses of the aircraft relative to the runway. The pose is output as a current pose estimate of the aircraft relative to the runway for use in at least one of monitoring the current pose estimate, generating an alert based on the current pose estimate, or guidance or control of the aircraft on a final approach.

Abstract: A method for detecting and modeling objects in space using LIDAR is disclosed. The method includes transmitting a laser beam to detect at least one object in space. Further, the method includes detecting one or more data related to at least one object. The detection is based upon the principle of reflection of the object in a vacuum. Further, said one or more data related to at least one object obtained from the detection unit is processed. Further, one or more information is determined from the processed data related to at least one object. The one or more information is mapped corresponding to the related at least one object. The method further comprises measuring one or more parameters associated with at least one of the mapped objects and modeling the measurement data related to at least one of the mapped objects.

Abstract: A device for controlling the movement of a motor vehicle, including a longitudinal controller and a lateral controller which are capable of generating, from first information relating to the road layout and second information relating to the dynamic behaviour of the vehicle, control commands intended for actuators for controlling the longitudinal and lateral movement of the vehicle. The device includes a prediction model which is supplied with the first and second information and is capable of determining future states of the vehicle for future positions of the vehicle over a plurality of iterations defining a future road portion. The model is connected to a module for determining whether driving limit values are violated, which module is capable of determining, for each future state, whether one of the state variables defining the future state reaches or exceeds a driving limit value, and of deducing a future risk situation.

Abstract: The embodiments are a landing control method, an aircraft, and a storage medium. The method is applied to the aircraft, and includes: the current frame template image is subjected to image feature extraction, and the extracted image features are used to train the position filter and the scale filter of the first template image; the position information of the first template image in the next frame image is predicted by using the position filter and the scale filter; and the landing of the aircraft is corrected by using the position information, such that the aircraft can dynamically track the preset takeoff and landing point for landing, so as to realize the accurate landing of the aircraft.

Abstract: An aerial drone is provided with a central passage and a rotating frame. A payload moves within the central passage through the drone body into a deployed position. The payload engages with the rotating frame and can be rotated into a desired orientation below the drone.

Abstract: A ground state determination system for an aircraft includes sensors configured to detect parameters of the aircraft and a flight control system implementing a ground state module. The ground state module includes a ground state monitoring module configured to monitor the parameters and a ground state determination module configured to compare each of the parameters monitored by the ground state monitoring module to a respective parameter threshold to determine whether the aircraft is on a surface.

Abstract: A handheld device and method for entering data and controlling functions of an aerial vehicle are disclosed. The handheld device includes an interface that communicates with a processor and a memory of the aerial vehicle; input devices that receive input from an operator of the handheld device, a display device that displays information related to the input received from the operator via the input devices, and one or more processors. The one or more processors can receive input data from the input devices to modify a field value maintained in the memory of the aerial vehicle. The one or more processors can present, at the display device, an output data corresponding to the input data, and periodically transmit one or more signals to modify the field value maintained in the memory of the aerial vehicle via the interface based on the input data.

Abstract: Systems and methods for navigation with magnetic field sensors are provided. For example, a system includes a magnetic gradient sensor that measures a magnetic gradient. The system also includes one or more inertial sensors that provide inertial measurements. Additionally, the system includes a magnetic field sensor that measures magnetic fields. Further, the system includes one or more processors that execute computer-readable instructions that direct the one or more processors to estimate a magnetic field based on the measured magnetic gradient and a velocity estimate from the inertial measurements. The computer-readable instructions also direct the one or more processors to calculate an error for the magnetic field and other navigation parameters using an additional magnetic field measurement from the magnetic field sensor.

Abstract: A method is provided for supporting one or more ground vehicles on a mission that includes traversal of a ground region. The method includes accessing geospatial data produced from an aerial survey of the ground region, and performing an analysis of the geospatial data to produce terrain data that describes the ground region. The terrain data is weighted based on constraints of the one or more ground vehicles, and an order of priority of criteria of the mission. A map is constructed in which the ground region is expressed as a geospatially-mapped array of the weighted terrain data, and the map is searched for a path that meets the criteria of the mission. The path is described by a series of waypoints that define a route across the ground region, and an indication of the route is output for the one or more ground vehicles to traverse during the mission.

Abstract: Described herein are systems, methods, and apparatuses for performing a user-less payment for an item upon its delivery by an unmanned delivery vehicle. The unmanned delivery vehicle may navigate to a delivery location, receive payment information, initiate a payment transaction with a remote server, and release the item at a specified location upon successful completion of the payment transaction. Upon arrival of the unmanned delivery vehicle, a wireless data transmission device may send payment information to a remote server, and the remote server may provide the unmanned delivery vehicle with an indication of whether the item can be released and a specific location at which the item can be released.

Abstract: The method can include performing inference using the system; and can optionally include training the system components. The method functions to automatically interpret flight commands from a stream of air traffic control (ATC) radio communications. The method can additionally or alternatively function to train and/or update a natural language processing system based on ATC communications. Additionally, the method can include or be used in conjunction with collision avoidance and/or directed perception for traffic detection associated therewith.

Abstract: A system for maintaining attitude control under degraded or depleted energy source conditions using multiple electric propulsors includes a plurality of propulsors, at least an energy source providing electric power to the plurality of propulsors and a vehicle controller communicatively coupled to each propulsor and configured to calculate initial power levels for the plurality of propulsors, the initial power levels including an initial power level for each propulsor, determine an energy output capacity of the least an energy source under load, calculate, by the vehicle controller, an aggregate potential demand of the plurality of propulsors as a function of the initial power levels, determine that electric potential is insufficient to match the aggregate potential demand, and for each initial power level generate a reduced power level, the reduced power level less than the initial power level and direct a corresponding propulsor to consume electrical power at the reduced power level.

Abstract: There are approximately 35,000 abandoned and unplugged oil and gas wells in New York with no known location. Unplugged wells emit methane, a strong greenhouse gas, which has the potential to significantly contribute to global climate change and act as a pollutant chemical. A long-range UAV equipped with methane sensors, MagPike (atomic magnetometer), and LiDAR sensors successfully detected unmarked well sites using characteristic magnetic signals generated by vertical metal piping preserved in the ground. The optimal flight altitude and transect spacing was determined for detection driven by the total field strength of the Earth's magnetic field and the height of tree canopies determined by LiDAR. Traditional methods of identifying oil and gas wells are costly and less powerful in acquisition of data such as using large magnetometers attached to helicopters.

Abstract: A cotton topping unmanned aerial vehicle having cutter discs and front grain lifting baffle plates is provided, the unmanned aerial vehicle includes an unmanned aerial vehicle body, a carrying component, a grain lifting component, and a cutting component. The carrying component includes a suspension, an electric push rod mounting base, an electric push rod, a motor mounting base, and motors. An upper end of the electric push rod is bolted to the electric push rod mounting base. The motor mounting base is welded to a lower end of the electric push rod. The grain lifting component is grain lifting baffle plates which include a left baffle plate and a right baffle plate, and both the left baffle plate and the right baffle plate are welded to guard plates.

Abstract: A Rapid Aero Modeling program and process may be applied to computational experiments such as computational fluid dynamics (CFD) programs to obtain aerodynamic models which may be in the form of polynomial equations. The program and process may be utilized to estimate (develop) aerodynamic models appropriate for flight dynamics studies, simulations, and the like. Feedback loops are provided around computational codes to rapidly guide testing toward aerodynamic models that meet user-defined fidelity criteria. A user has the freedom to choose a specific level of fidelity in terms of prediction error, in advance of a CFD test (computation).

Abstract: Introduced here computer programs and associated computer-implemented techniques for establishing the dimensions of interior spaces. These computer programs are able to accomplish this by combining knowledge of these interior spaces with spatial information that is output by an augmented reality (AR) framework. Such an approach allows two-dimensional (2D) layouts to be seamlessly created through guided corner-to-corner measurement of interior spaces.

Abstract: A method is provided for detecting and avoiding conflict along a current route of a robot. The method includes accessing or determining trajectories of the robot and a nearby moving object forward in time from their respective current positions, and detecting a conflict from a comparison of the trajectories. The method includes selecting a maneuver to avoid the conflict, and outputting an indication of the maneuver for use in at least one of guidance, navigation or control of the robot to avoid the conflict. Selection of the maneuver includes determining a plurality of angles that describe the conflict such as those at which the robot and moving object observe one another, and/or an angle between their trajectories, and evaluating the plurality of angles to select the maneuver.

Abstract: According to the present invention there is provided a method of taking a measurement using a sensor mounted on an aerial vehicle, the aerial vehicle having one or more propellers and one or more motors which are selectively operable to drive the one or more propellers to rotate to cause the vehicle to fly, and a sensor mounted on the aerial vehicle, the method comprising the steps of, operating the one or more motors to drive the one or more propellers to cause the vehicle to fly; at a first time instant, slowing down or turning off said one or more motors; while the one or more motors are slowed down or turned off, taking a measurement using said sensor; at a second time instant, which is after the measurement has been taken using the sensor, operating the one or more motors again to drive the one or more propellers to cause the vehicle to fly. There is further provided a corresponding aerial vehicle.

Abstract: A method for estimating the pressure measurement bias of a barometric sensor in a wireless terminal. A location engine using the method generates an enhanced estimate of the measurement bias. The location engine generates the enhanced estimate based in part on Global Navigation Satellite System (GNSS)-based estimates of the elevation of the wireless terminal, which the terminal generates as it concurrently makes barometric pressure measurements. Each GNSS-based estimate of elevation is often generated from noisy measurements and has an associated uncertainty. The location engine accounts for the uncertainty in the GNSS estimates of elevation by applying an optimal estimation technique, such as Kalman filtering, on the biased pressure measurements and the GNSS-based estimates.

Abstract: A method of controlling an aircraft having multiple configurations is provided, wherein each configuration is controlled by a different control law implemented by a flight control device and transition from one configuration to another configuration is achieved by gradually blending out a control law for one configuration and by gradually increasing an impact of a control law for another configuration in the flight control device based on an estimated flight condition of the aircraft by dynamically adjusting, in the flight control device, respective maximum and minimum limit values of control volumes, which control volumes are defined by parameter ranges of control parameters in connection with a corresponding control law for the one configuration and for the other configuration, respectively.

Abstract: Systems and methods are provided for coordinating an Unmanned Vehicle (UV) to perform authenticated delivery of goods. A method for coordinating a delivery may include instructing, via a communication network, a user device to collect user preferences on delivery logistics. The method may also include receiving the user preferences from the user device. The method may also include receiving user financial data from a financial service provider server. The method may also include receiving real-time information comprising location information of a UV and a user device. The method may also include authorizing the delivery of the package if an authentication process is satisfied based on the user preferences, the user financial data, and the real-time information. The method may also include transmitting to the UV a command to complete the delivery, if the delivery is authorized. The method may also include transmitting to the UV an abort command, if the delivery is not authorized.

Abstract: The aircraft threat envelope protection system employs a threat envelope data structure in a computer-readable medium that stores at least one trigger condition for each of a plurality of different types of threats associated with the aircraft, and modeled using a common schema. A processor computes plural different projected trajectories representing different possible aircraft paths through spacetime. The processor associates at least some of the plurality of the threats to specific trigger points in spacetime along each of the projected trajectories. The processor will deprecate ones of the projected trajectories when they are deemed not viable to recover from a threat. The processor initiates an aircraft protective response when all projected trajectories but one have been deprecated and the aircraft is within a predetermined proximity to the closest trigger point in spacetime along the non-deprecated trajectory.

Abstract: Techniques described are related to determining when a discrepancy between data of multiple sensors (e.g., IMUs) might be attributable to a sensor error, as opposed to operating conditions, such as sensor bias or noise. For example, the sensor data is passed through one or more filters (e.g., bandpass filter) that model the bias or noise, and the filtered data may then be compared for consistency. In some examples, consistency may be based on residuals or some other metric describing discrepancy among the filtered sensor data.

Abstract: An aerial vehicle comprises one or more sensors to environmental data, a communication system to receive control inputs from a user, two or more actuators, with each actuator coupled to a rotary wing. The aerial vehicle also comprises a controller to determine a mode of the aerial vehicle based on the environmental data and the control inputs, each mode indicating a set of flight characteristics for the aerial vehicle, generate a gain value based on the mode, the gain value, when used to modify power signals transmitted to actuators of the aerial vehicle, causes the aerial vehicle to conform within the indicated flight characteristics of the determined mode, generate an output signal modified by the gain value based on the input signal, and transmit a power signal based on the output signal to each actuator of the aerial vehicle.

Abstract: Systems and methods are disclosed for evidence-based training of aircraft operators. For example, a computer-implemented method may include: analyzing aircraft flight data indicative of actions performed by an aircraft operator in operating aircraft, to thereby determine an assessment of a performance of the aircraft operator in operating aircraft; based on the assessment, determining a training scenario to be presented to the aircraft operator via a training simulator as part of training for the aircraft operator; providing, to the training simulator, information indicative of the determined training scenario; receiving, from the training simulator, training flight data indicative of actions performed by the aircraft operator during a simulation of the scenario using the training simulator; and based on the training flight data and the assessment, determining an evaluation of the training for the aircraft operator.

Abstract: To bring an aircraft in flight to a runway, an automatic trajectory generation system obtains a procedure, called STARI procedure, which provides a final trajectory flyable by the aircraft to land on the runway, such that from the entry point of the final trajectory or from any point above it, a holding loop pattern of a predefined shape is flyable in order to dissipate energy if necessary. The automatic trajectory generation system then computes a lateral trajectory, avoiding any terrain relief, meteorological obstacles and military zones, between the current position of the aircraft and the entry point or a point above it, based on performance adapted to an operational state of the aircraft. An overall trajectory is thus obtained, by linking the computed lateral trajectory and the final trajectory of the STARI procedure, including iterations of the holding loop pattern if necessary.

Abstract: Methods, systems, and program products of inspecting solar panels using unmanned aerial vehicles (UAVs) are disclosed. A UAV can obtain a position of the Sun in a reference frame, a location of a solar panel in the reference frame, and an orientation of the solar panel in the reference frame. The UAV can determine a viewing position of the UAV in the reference frame based on at least one of the position of the Sun, the location of the solar panel, and the orientation of the solar panel. The UAV can maneuver to the viewing position and point a thermal sensor onboard the UAV at the solar panel. The UAV can capture, by the thermal sensor, a thermal image of at least a portion of the solar panel. A server onboard the UAV or connected to the UAV can detect panel failures based on the thermal image.

Abstract: The invention relates to a method for controlling aircraft. A specified flight position of the aircraft is compared with a piece of geographical height information corresponding to the provided flight position. The piece of geographical height information is obtained from a set of pieces of height information, said set corresponding to a geographical area, wherein for a first part of the geographical area, the set of pieces of height information indicates a piece of relevant geographical height information and for a second part of the geographical area, the set indicates a piece of height information deviating from the actual geographical height. The second part of the geographical area comprises a first special area, in which the aircraft is only permitted to operate to a limited degree.

Abstract: A method and system for controlling movement of a vehicle. Movement, orientation, and position data of the vehicle is collected. A model of kinematics of the vehicle and its environment is created and a Theory of World model is produced and updated. The model includes geometric algebra multivectors. Errors and noise are stored as geometrically meaningful first-class objects within the multivectors. Geometric algebra operations are used to manipulate the model during operation. Error and noise data are propagated and manipulated using geometric algebra operations to reflect measurement and processing errors or noise. The models are used in generation of control data with a primary intent of ensuring stability. Operations such as intersections are used to compare position, orientation, and movement of the vehicle against position, orientation, and movement of objects in its environment. System tasks include, but are not limited to, kinematics, inverse kinematics, collision avoidance, and dynamics.

Abstract: A method includes, in response to a determination that one or more authenticated delivery locations includes a first delivery location, identifying, using an unmanned aerial vehicle registry, one or more unmanned aerial vehicles based on at least one unmanned aerial vehicle characteristic associated with a medication delivery request. The method also includes determining, for each unmanned aerial vehicle of the one or more unmanned aerial vehicles, an availability status, selecting an unmanned aerial vehicle based on at least a corresponding availability status and at least one selection criteria, and instructing the unmanned aerial vehicle to transport the medication package from a starting location to the first delivery location.

Abstract: In an illustrative embodiment, systems and methods for automatically identifying positions of objects of interest using a vehicle-mounted sensor apparatus include obtaining images captured by imaging sensor(s) of the sensor apparatus during a time interval and analyzing the images to detect objects of interest. On detecting an object of interest, the systems and methods may calculate a geographic position corresponding to the object of interest and store a data record including an identifier of the object of interest, the geographic position, and a timestamp. The objects of interest may include urban fixtures, advertising materials, and/or vehicles. The systems and methods may be applied to identifying parking violations.

Abstract: Disclosed implementations describe systems and methods for stabilizing vertical takeoff and landing (“VTOL”) or hover flight of a degraded canted-hex aerial vehicle so that the degraded canted-hex aerial vehicle can safely navigate to a landing area. For example, upon detection of a motor-out event, the disclosed implementations may cause an opposing propulsion mechanism of the aerial vehicle to terminate operation, the prioritization of the flight controller to change, and for a feedback loop of the flight controller to provide a preferred thrust to counteract yaw torques acting on the canted-hex aerial vehicle.

Abstract: A system for autonomous flight of an electric vertical takeoff and landing (eVTOL) aircraft. The system may include a pusher component, a lift component, a flight controller, and a pilot override switch. The pusher component is mechanically coupled to the eVTOL aircraft. The lift component is mechanically coupled to the eVTOL aircraft. The flight controller is communicatively connected to the pilot override switch. The flight controller is configured to identify a transition point, initiate operation of the pusher component, and terminate operation of the lift component. A method for flight control of an eVTOL aircraft is also provided.

Abstract: A set of commands for each of a plurality of actuators to alter an aircraft's state responsive to one or more inputs is produced. The set of commands is provided to fewer than all actuators comprising the plurality of actuators.

Abstract: In an aspect an apparatus for determining a most limiting parameter of an electric aircraft is presented. An apparatus includes at least a processor and a memory communicatively connected to the at least a processor. A memory contains instructions configuring at least a processor to receive aircraft data from a sensing device. A sensing device is configured to measure a parameter of an electric aircraft and generate aircraft data. At least a processor is configured to determine a most limiting parameter of an electric aircraft as a function of aircraft data. At least a processor is configured to communicate a most limiting parameter to a pilot indicator in communication with the at least a processor and memory communicatively connected to the at least a processor. A pilot indicator is configured to display a most limiting parameter to a user.

Abstract: An emergency collective actuator includes an actuator motor to produce an actuation force and an actuator linkage that directly engages a friction control lever that is pivotally supported on the collective stick of a helicopter to apply the actuation force directly to the friction control lever such that the actuation force initially disengages the friction control and then reduces the adjustable pitch toward a minimum collective pitch position. The actuator can include a clutch that slips to allow the pilot to overcome the actuation force and that slips responsive to an engagement of the friction control by the pilot, but otherwise the clutch co-rotates with the motor shaft to bias the adjustable pitch toward a minimum collective pitch position.

Abstract: Autonomous underwater vehicles and systems are provided with fast stabilization and fine attitude control with a constant and high rotational speed flying wheel to rotate the vehicle's body with respect to its core and optionally a combination of reaction masses used in three perpendicular axes. The gimbal and the reaction mass inertial systems are used for fast response to any angular or linear disturbance coming from the ocean current or waves. When equipped for optical communications, the vehicle has an optical receiver and transmitter and controller that provides three levels of attitude stabilization: gimbal and the reaction mass inertial systems; isolated movable platform and fine optical beam steering for targeting the laser beam from the transmitter. The ability to maintain precise positioning allows multiple vehicles to be optically linked.

Abstract: An aerial robot system may include an aerial robot having an airframe, a piezo actuator, a wing connected to the piezo actuator, and a photovoltaic cell. The system may further include a laser source configured to emit a laser beam oriented toward the photovoltaic cell for conversion by the photovoltaic cell into electrical energy. The aerial robot may further include a boost converter connected to the photovoltaic cell and configured to raise a voltage level of the electrical energy, and a signal generator connected to the boost converter and configured to generate an alternating signal. The piezo actuator is connected to the signal generator to move according to the alternating signal to cause the wing to move in a flapping motion to generate aerodynamic force that moves the robot. Methods for manufacturing aerial robots and corresponding electronics are also disclosed herein.

Abstract: The invention relates to a system and process for generating digital images of a site having a structure with superimposed intersecting grid lines and annotations. The process includes acquiring a plurality of digital images, still frames and/or video images of the site, the structure, or both, with each of the digital images. The structure, the site, and points of interest within the digital images are identified, and then the system and process photogrammetrically generates a three-dimensional point cloud from the digital images. The identified structures, objects and features are then used to calculate measurements and provide masking and annotations in order to generate the two-dimensional stitched and annotated digital image of the site and/or the structure.

Abstract: Unmanned aerial vehicles (UAVs) and control thereof to assemble into flexible, dynamic structures. A UAV includes a flexible screen retractable between extended and retracted positions, connector(s) for coupling to another UAV that can pull the flexible screen from a retracted position to an extended position, and a coupling portion for coupling to connector(s) of yet another UAV to connect to and extend a flexible screen thereof. Chain(s) of coupled UAVs with extended flexible screens thereof form a structure that can change shape and size based on UAV movement. Local wireless communication with a group control UAV facilitates coordinated positioning and control of a UAV group. A group control UAV with a power supply and an electrical conducting lead can power UAVs of a group while it and they are in-flight, and can perform real-time management of the group UAVs in forming and maintaining a desired shape of the structure.

Abstract: A vehicle is electrically connected to one or more accessories. The vehicle includes at least one controller that may be configured to identify the accessory based on accessory identification information. The controller may also be configured to provide one or more commands to control an operation of the accessory.

Abstract: An up-down flapping wingtip is provided for a ground effect vehicle. The wingtip is positionable at an anhedral angle to control the wingtip clearance from ground. Variable wingtip clearance reduces the risk of damage due to collision with the ground or water, thereby permitting more efficient flight at lower altitude with an equivalent safety. The wingtip is positioned by a wingtip flap and an actuator. The wingtip anhedral angle is controlled by a flight control system. A sensor is included for determining whether an object lies in the path of the wingtip. The sensor communicates with the flight control system in order to vary the flapping angle of the wingtip to increase clearance from the ground or water, thus avoiding impact with the object. The wingtip anhedral angle is reduced to increase the wingspan for flight out of ground effect.

Abstract: A system network and methods supported by a constellation of GNSS satellites orbiting around the Earth, and deployed for precise remote monitoring of the spatial displacement, distortion and/or deformation of stationary and/or mobile systems, including buildings, bridges, and roadways. The methods involve (i) embodying multiple GNSS rovers within the boundary of the stationary and/or mobile system being monitored by the GNSS system network, (ii) receiving GNSS signals transmitted from GNSS satellites orbiting the Earth, and (iii) determining the geo-location and time-stamp of each GNSS rover while the stationary and/or mobile system is being monitored for spatial displacement, distortion and/or deformation, using GNSS-based rover data processing methods practiced aboard the system, or remotely within the application and database servers of the data center of the GNSS system network.

Abstract: Methods and associated systems for autonomous package delivery utilize a UAS/UAV, an infrared positioning senor, and a docking station integrated with a package delivery vehicle. The UAS/UAV accepts a package for delivery from the docking station on the delivery vehicle and uploads the delivery destination. The UAS/UAV autonomously launches from its docked position on the delivery vehicle. The UAS/UAV autonomously flies to the delivery destination by means of GPS navigation. The UAS/UAV is guided in final delivery by means of a human supervised live video feed from the UAS/UAV. The UAS/UAV is assisted in the descent and delivery of the parcel by precision sensors and if necessary by means of remote human control. The UAS/UAV autonomously returns to the delivery vehicle by means of GPS navigation and precision sensors. The UAS/UAV autonomously docks with the delivery vehicle for recharging and preparation for the next delivery sequence.

Abstract: A method and system for controlling movement of a vehicle. Movement, orientation, and position data of the vehicle is collected. A model of kinematics of the vehicle and its environment is created and a Theory of World model is produced and updated. The model includes geometric algebra multivectors. Errors and noise are stored as geometrically meaningful first-class objects within the multivectors. Geometric algebra operations are used to manipulate the model during operation. Error and noise data are propagated and manipulated using geometric algebra operations to reflect measurement and processing errors or noise. The models are used in generation of control data with a primary intent of ensuring stability. Operations such as intersections are used to compare position, orientation, and movement of the vehicle against position, orientation, and movement of objects in its environment. System tasks include, but are not limited to, kinematics, inverse kinematics, collision avoidance, and dynamics.