Abstract: An insulating glazing unit has at least two glass panes and a circumferential spacer profile between them near their edges, for use in a window, a door, or a façade glazing, and which has in each case a frame, in particular a metallic frame, surrounding the edges of the insulating glazing, wherein at least one RFID transponder is attached to the insulating glazing unit as an identification element, wherein the at least one transponder is arranged on an inner surface of one of the glass panes in the spaced region between the spacer profile and the edge of the glass pane.

Abstract: A flight control apparatus includes an acquisition unit that acquires a flight plan in which first flight conditions are described, and information that indicates a time limit set with respect to a position on a path along which an air vehicle is to fly. An arrival judging unit judges, based on the acquired information, whether or not the air vehicle has arrived at the position within the time limit. A condition determination unit determines a second flight condition if it is judged that the air vehicle has not arrived at the position within the time limit. A flight control unit controls flight of the air vehicle selectively adopts a first flight control method which follows the first flight conditions or a second flight control method which follows the second flight condition based on a result obtained by the arrival judging unit.

Abstract: An example method of performing maintenance on an aircraft includes receiving a vehicle data-signature-map of an interior of an aircraft for at least one parameter of the aircraft, and the vehicle data-signature-map is based on sensor outputs received from sensors of mobile devices positioned at locations in the interior of the aircraft.

Abstract: The present invention comprises: a fatigue estimation unit that estimates the fatigue life of a prescribed area of a fuselage, on the basis of the level of damage in the prescribed area during operation; a determination unit that determines whether the estimated fatigue life will be reached after a prescribed period of time has elapsed; a repair determination unit that determines that repair of the fuselage is unnecessary if a determination is made that the estimated fatigue life will be reached after the prescribed period of time has elapsed, and that determines that the fuselage is to be repaired if a determination is made that the estimated fatigue life will be reached within the prescribed period of time; and a selection unit that, if a determination is made that the fuselage is to be repaired, selects a repair method corresponding to the detected degree of damage in the prescribed area.

Abstract: A wireless communication method, a terminal device, and a network device are provided. The terminal device receives a first indication message sent by the network device, so that the terminal device may select, according to the first indication message, to fly in an appropriate cell. This ensures communication between the terminal device and the network device. The method includes: receiving, by the terminal device, the first indication message sent by the network device. The first indication message includes at least one of: flight zone restriction information of at least one cell, flight altitude information of the at least one cell, flight speed information of the at least one cell, volume information of a flight device, and weight information of the flight device, and/or the first indication message includes information about a flight transmission characteristic supported by the at least one cell.

Abstract: A vehicle fault detection system including a vehicle control module coupled to a plurality of vehicle system sensors configured to detect respective time series of data corresponding to a component parameter, the vehicle control module determines, based on domain knowledge obtained by the vehicle control module from only the respective time series of data, an existence of one or more relationships between the plurality of component parameters, and identifies an anomaly in the respective time series of data and at least a vehicle component to be serviced based only on the domain knowledge and the one or more relationships between the plurality of component parameters. An indication of the anomaly in the respective time series of data and an identification of the vehicle component to be serviced are to be presented as a graphical representation that includes a strength of the one or more relationships between the component parameters.

Abstract: A system and method of evaluating and examining a student pilot in an automated, consistent, unbiased way using a flight data recorder and analyzing the flight data recorded in real time.

Abstract: Some embodiments provide a non-transitory machine-readable medium that stores a program. The program receives from a computing system a plurality of data and a plurality of points associated with the plurality of data for display in a view of a map. Each point in the set of points includes location data specifying a location of the point. The program further determines that a subset of the plurality of points have the same location data. The program also renders in the view of the map a geometry representing the subset of the plurality of points and an indication that the geometry represents the subset of the plurality of points. For points in the plurality of points other than the subset of the plurality of points, the program further renders geometries that represent the points.

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: An embodiment of a communication management unit (CMU) includes emulator and data-mining circuits. The emulator circuit is configured to generate a data request having a same format as a data request from a vehicle communications center, to send the data request to a subsystem disposed on a vehicle, and to receive data sent by the subsystem in response to the data request. The data-mining circuit is configured to provide at least some of the received data to a determining circuit configured to determine information in response to the provided data. For example, such a CMU can request flight-plan data from a flight management subsystem (FMS) by sending, to the FMS, an emulated data-request message having the same format as a data-request message from a ground-based aircraft operations center. That is, the CMU can “fool” the FMS into “thinking” that the data-request message originated from the ground-based aircraft operations center.

Abstract: A computer-implemented method, computer program product and computing system for receiving angle-of-attack information concerning an aircraft; and rendering an angle-of-attack indicator within a flight director of the aircraft based, at least in part, upon the angle-of-attack information.

Abstract: Systems, methods and apparatus for data monitoring are disclosed. A system may include a data acquisition circuit structured to interpret a plurality of detection values, each of the plurality of detection values corresponding to at least one of a plurality of input sensors communicatively coupled to the data acquisition circuit, a data storage circuit structured to store specifications and anticipated state information for a plurality of vehicle types, an analysis circuit structured to analyze the plurality of detection values relative to specifications and anticipated state information to determine a vehicle performance parameter, and a response circuit structured to initiate an action in response to the vehicle performance parameter.

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: Method and system for controlling engine speed in a multi-engine aircraft, comprising monitoring a request for a first engine and a second engine to generate a given thrust and determining a corresponding engine speed for the first engine and the second engine in accordance with the given thrust. When the corresponding engine speed is outside of a selected speed range, a first engine speed and a second engine speed are allowed to track the corresponding engine speed. When the corresponding engine speed is within the selected speed range, a transition of the first engine speed and the second engine speed through the selected speed range is staggered by allowing one of the first engine speed and the second engine speed to transition through the selected speed range while holding the other of the first engine speed and the second engine speed outside of the selected speed range.

Abstract: A method of estimating a parameter of a fluid flowing in a passage includes: having a plurality of instruments operable to measure one or more fluid properties flowing in the passage, the plurality of instruments being disposed in the passage and arranged within a common measurement plane; assigning a stream tube to each instrument, each stream tube represents a region of space in the common measurement plane within the passage and each stream tube surrounds one of the plurality of instruments, the stream tubes together correspond to the cross-sectional shape and area of the passage in the common measurement plane; measuring the one or more fluid properties using the instruments to obtain one or more measured values for each stream tube; using the measured value(s) for each stream tube to calculate a derived value for each stream tube; and summing the derived values across all of the stream tubes.

Abstract: Systems, devices and methods for alerting a crew of an aircraft or other mobile platform of a relevant condition associated with the aircraft are disclosed. One exemplary method comprises receiving data indicative of an existence of the relevant condition associated with the aircraft; receiving data indicative of a substantially real-time value of a dynamic parameter associated with the relevant condition; and displaying an awareness-enhancing indication associated with the relevant condition in a display area of the crew alerting system of the aircraft. The awareness-enhancing indication comprises a textual message and a supplemental indication indicative of the substantially real-time value of the dynamic parameter associated with the relevant condition. In various embodiments, the supplemental indication may be textual or graphical. The supplemental indication may also be indicative of a target value of the dynamic parameter.

Abstract: Methods, systems, and computer program products are provided. Aspects include determining characteristic data associated with a physical environment, based on the characteristic, determining an elastic map for the physical environment, wherein the elastic map comprises a graph comprising a set of nodes and a set of edges, wherein each edge connects two nodes and a set of configurable parameters that define an elastic coupling for each edge, determining an initial physical configuration of the set of nodes in the physical environment based on the elastic map, causing a set of mobile sensors to establish the initial configuration in the physical environment, simulating a mobile sensor elastic coupling between each mobile sensor based on the elastic energy function for each edge, collecting an environmental data point associated with the physical environment, and adjusting a configuration of the set of mobile sensors based on the environmental data point.

Abstract: An aircraft arrival determination system includes an arrival sequence determination unit that is configured to determine a position of an aircraft within a landing queue for a destination airport and an estimated landing time for the aircraft at the destination airport. A landing suggestion unit is configured to provide a landing suggestion for the aircraft. The landing suggestion provides information related to landing at the destination airport or diverting from the destination airport to an alternate airport.

Abstract: A graphical depiction of insufficient system integrity for low-visibility synthetic vision system taxi mode is disclosed. The graphical depiction may be configured to be displayed on a display device of an aircraft. The graphical depiction may include an aircraft ownship symbol. The aircraft ownship symbol may be modified following a receipt of one or more signals related to a location of the aircraft relative to an aircraft movement surface and a comparison to the one or more signals to one or more thresholds. The comparison may be configured to determine whether there is insufficient system integrity in a degree of confidence in the location of the aircraft relative to the airport movement surface.

Abstract: A regime recognition system for an aircraft has a regime engine configured to identify a sub-regime performance of the aircraft only after having identified a top tier or top level regime performance that can include the sub-regime performance.

Abstract: A three-dimensional wind vector field measurement system employs convergent beams for localised velocity measurement enabling mapping of the wind field across an extended spatial region. This enables characterisation of complex field signatures. This enables advanced control and protective systems for wind turbines. This also enables improved wind harvesting. This also enables improved prospecting. This also enables improved equipment selection. Buoy mounted systems enable measurement in an offshore environment.

Abstract: An apparatus for guiding an aircraft includes: an air velocity sensor disposed on the aircraft and configured to sense a speed and direction of a wind remote to the aircraft to provide remote wind speed and direction data; a flight control actuator coupled to a flight control device; and a flight controller communicably coupled to the air velocity sensor, the flight controller having an input section that receives the remote wind speed and direction data from the air velocity sensor, a processor configured to determine a magnitude and direction of the wind with respect to a planned flight route and to predict an influence acting on the aircraft due to the magnitude and direction of the wind with respect to the planned flight route, and an output section communicably coupled to the flight control actuator to provide a control signal that results in the aircraft counteracting the predicted influence.

Abstract: A significant weather advisory system for an aircraft is disclosed. The system is configured to identify, from strategic weather data, current significant weather events from weather impacted areas projected to be intersected by a geographical corridor around a projected flight path and projected to occur during determined time intervals during which the airborne vehicle is expected to pass through the weather impacted areas; compare the current significant weather events to previously identified significant weather events and detect significant changes between the current significant weather events and the previously identified significant weather events; and generate a notification for display to the flight crew via an onboard notification system that identifies the detected significant change when a significant change is detected.

Abstract: A pressure measuring probe, in particular for use in an aircraft is disclosed. In one aspect, the pressure measuring probe includes at least one acquisition tube, including a capability for discharging water and captured crystals contained in the atmosphere, where the discharge capability includes a drainage hole arranged in a rear partition of the tube, in the axis of symmetry thereof and in the flow direction of the flow of air.

Abstract: An in-flight entertainment and communications (IFEC) system is configured to interconnect an avionics data bus to a local area network. An avionics interface is connectable to the avionics data bus, and receptive to avionics data transmitted on the avionics data bus by one or more avionics nodes over a predetermined protocol. A local network interface establishes the local area network, and portable electronic devices may be connectable to the local network interface over the local area network to establish a data communications link thereon. A data processor is connected to the avionics interface and the local network interface, and relays the avionics data from the avionics interface to the local network interface for transmission to the one or more portable electronics devices. This transmission is according to the predetermined protocol over the data communications link established on the local area network.

Abstract: A computer-implemented method for real-time streaming of flight data includes receiving flight data from one or more aircraft data sensors, evaluating the received flight data according to data evaluation rules, and upon determining that the received flight data matches one or more conditions specified in the data evaluation rules, starting or stopping a transmission of the received flight data to a ground station.

Abstract: A computer-implemented method for prioritized flight data transmission includes receiving a frame of flight data from one or more aircraft data sensors, the frame of flight data comprising a plurality of parameters collected from one or more avionics systems, associating each parameter of the plurality of parameters with a respective priority level, decomposing the frame of flight data into a plurality of flight data frame layers, wherein each flight data frame layer of the plurality of flight data frame layers comprises a subset of the plurality of parameters having respective priority levels that are equivalent, and transmitting, to a ground station, a first flight data frame layer of the plurality of flight data frame layers comprising parameters having a highest respective priority level.

Abstract: A method and system for diagnosing a condition of an air-breathing aircraft engine are described. The method comprises obtaining a sample of lubricating fluid from the engine, filtering the sample to obtain a plurality of particles from the lubricating fluid, obtaining chemical composition data for the plurality of particles, determining a quantity of volcanic ash in the lubricating fluid by considering each one of the particles as composed partially of volcanic ash and partially of at least one other material and analyzing the chemical composition data, the volcanic ash having associated thereto a predetermined chemical composition, and diagnosing a condition of the engine based on the quantity of volcanic ash found in the lubricating fluid.

Abstract: A pilot headset and system for automatically generating turbulence reports is provided. The turbulence reporting pilot headset includes a headset body having a motion sensor positioned therein that is adapted to collect motion data representative of changes in motion experienced by the headset body, and a motion data correlation module which is programmed, structured and/or configured to correlate the collected motion data to turbulence level data.

Abstract: A cloud-based computing system for providing a maintenance message associated with a unique maintenance action for fault rectification is disclosed. The system includes a diagnostic module including one or more processors configured by instructions stored in non-transient computer readable media. The diagnostic module is configured to: identify, for each potential CAS message in an aircraft, a set of inputs that are evaluated to trigger the potential CAS message; identify, for each of the potential CAS messages, each unique combination of input conditions for the set of inputs that triggers the potential CAS message; and identify, for each of the potential CAS messages, a unique maintenance message associated with each unique combination of input conditions that triggers the potential CAS message, wherein each unique maintenance message is associated with a unique maintenance action for fault rectification.

Abstract: Systems and methods are provided that include features for determining a hover time remaining for an aircraft performing a hover maneuver. In some exemplary embodiments, the hover time remaining can be communicated to a pilot or aircrew member.

Abstract: A system comprises a vehicle communication application hosted on a portable device. The application generates a traffic control log on screen; generates a free text screen accessible by a user; generates standard traffic control message screens; generates a connectivity services and status screen; provides a regulatory standard communication protocol converter that formats messages to a regulatory standard communication compliant protocol; and provides for regulatory standard communication over Internet protocol processing for communication of regulatory standard communication protocol messages to a datalink device. The system also comprises a ground data center that receives and transmits messages from and to a vehicle, through the application. The data center communicates with a traffic control center, and processes messages received from the vehicle to meet protocol requirements prior to transmitting messages to the traffic control center.

Abstract: A system may include a display and a processor. The processor may be configured to: receive aircraft traffic data and ownship data; generate and update a linear map based on the aircraft traffic data and the ownship data; and output the linear map as graphical data to the display. The display may be configured to display the linear map to a user. The linear map may depict a one-dimensional relationship between an ownship and designated traffic. The linear map may convey a range between the ownship and the designated traffic and may convey a closure rate between the ownship and the designated traffic. The linear map may include: a graphical threshold indicator; a graphical ownship indicator; a graphical scale; and a graphical designated traffic indicator.

Abstract: A monitoring method, the purpose of which is, when a loss of power is detected in an aircraft engine, to generate an alarm in the form of a single message displayed on a display screen in the cockpit, in order to indicate if the level of damage suffered by the engine is critical or not. The steps implemented are based on alarm signals transmitted by a central processing unit of the engine and also on alarm signals transmitted by a diagnostic device for the onboard systems of the aircraft, in order to take account of both the situation of the engine and also the situation of the systems surrounding the engine which can be affected by damage to an engine.

Abstract: Improved mechanisms for collecting information from a diverse suite of sensors and systems, calculating the current precipitation, atmospheric water vapor, atmospheric liquid water content, or precipitable water and other atmospheric-based phenomena, for example presence and intensity of fog, based upon these sensor readings, predicting future precipitation and atmospheric-based phenomena, and estimating effects of the atmospheric-based phenomena on visibility, for example by calculating runway visible range (RVR) estimates and forecasts based on the atmospheric-based phenomena.

Abstract: A method for controlling an aerial vehicle includes obtaining flight indication data containing a position region associated with the flight indication data, determining whether a current position of the aerial vehicle is within the position region associated with the flight indication data, and, in response to the current position being within the position region, generating a flight control instruction according to the flight indication data, and controlling a flight of the aerial vehicle according to the flight control instruction.

Abstract: A method for determining airspeed of an aircraft that includes determining a rotor model relating a power coefficient of a propeller of the aircraft to an axial inflow velocity through the propeller as a function of a set of rotor operating parameters; determining the set of rotor operating parameters by sampling an electronic control signal associated with an electric motor actuating the propeller; computing the axial inflow velocity through the propeller based on the set of rotor operating parameters using the rotor model; and determining the airspeed based on the axial inflow velocity.

Abstract: A technology is described for a wireless sensor network. An example method may include detecting an aircraft takeoff preparation event using cabin air pressure data and accelerometer data indicating that an aircraft is preparing for takeoff. Transmitting a listen command to sensor nodes included in a sensor network, the listen command instructing the sensor nodes to disable the wireless network transmissions and listen for commands transmitted by the gateway. Disabling gateway wireless transmissions to the sensor nodes and a computing network. Detecting a landing event using the cabin air pressure data and the accelerometer data indicating that the aircraft has landed. Enabling the gateway wireless transmissions to the sensor nodes and the computing network, and transmitting an enable command to the sensor nodes included in the sensor network, the enable command instructing the sensor nodes to enable the wireless network transmissions and resume sending sensor data to the gateway.

Abstract: A manually activated communications system is provided. The manually activated communications system includes a manually activated switch, a monitoring system configured to store operational and performance data of a vehicle, and a radio, coupled to the monitoring system and the manually activated switch, which may be located within or outside the monitoring system. The manually activated switch, monitoring system and radio are contained within the vehicle. The radio is configured to wirelessly transmit the operational and performance data of the vehicle to a portable processing system, proximate to the vehicle, when the vehicle is parked and the manually activated switch is actuated.

Abstract: A system for monitoring lubrication of a drive train, including a lubricant pressure sensor to detect a pressure of the lubricant in the drive train and to provide a lubricant pressure signal; lubricant volume sensor to detect a volume of the lubricant in the drive train and to provide a lubricant volume signal; non-contact temperature sensor to detect a temperature of the drive train and to provide a non-contact temperature signal; and logic management system in communication with the lubricant pressure sensor, the lubricant volume sensor, and the non-contact temperature sensor; the logic management system configured to receive and process the lubricant pressure signal, the lubricant volume signal, and the non-contact temperature signal; wherein when the lubricant pressure signal reaches a predetermined minimum pressure level and the lubricant volume signal reaches a predetermined minimum volume level, the logic management system displays non-contact temperature measurement data to a display device.

Abstract: A method for using an airfield Light Fidelity (LiFi) system in an airfield to exchange optical wireless data communications with an aircraft. The method (i) detects aircraft exterior lights including aircraft LED lamps, via a plurality of airfield photo detectors, wherein the airfield LiFi system comprises the plurality of airfield photo detectors positioned at intervals along a runway of the airfield; (ii) in response to detecting the aircraft exterior lights, establishes a communication connection to an aircraft LiFi system comprising the aircraft LED lamps and aircraft photo detectors, by the airfield LiFi system; and (iii) exchanges the optical wireless data communications via the communication connection, by the airfield LiFi system, by: receiving communications from aircraft LED lamps, via airfield photo detectors; transmitting communications to aircraft photo detectors, via airfield LED lamps; and presenting ground station notifications.

Abstract: A vehicle fault detection system including a plurality of sensors coupled to a vehicle system and configured to detect respective time series of data, where each time series of data corresponds to a component parameter of a plurality of component parameters, a vehicle control module coupled to the plurality of sensors, the vehicle control module being configured to determine an existence of one or more relationships between the plurality of component parameters, and identify anomalies in the respective time series of data based on the one or more relationships between the plurality of component parameters, and a user interface coupled to the vehicle control module, the user interface being configured to present to an operator an indication of the anomalies in the respective time series of data.

Abstract: A method for determining airspeed of an aircraft that includes determining a rotor model relating a power coefficient of a propeller of the aircraft to an axial inflow velocity through the propeller as a function of a set of rotor operating parameters; determining the set of rotor operating parameters by sampling an electronic control signal associated with an electric motor actuating the propeller; computing the axial inflow velocity through the propeller based on the set of rotor operating parameters using the rotor model; and determining the airspeed based on the axial inflow velocity.

Abstract: A system includes display equipment and a processor coupled to the display equipment. The processor is configured to cause the display equipment to display an electronic checklist associated with an aircraft. The processor is configured determine whether the electronic checklist includes a checklist item associated with a particular control page of a plurality of control pages. The processor is configured to, based on determining that the electronic checklist includes the checklist item associated with the particular control page, cause the display equipment to display the particular control page that includes a control element that is selectable to cause a control command to be sent to one or more components.

Abstract: Methods and systems are provided for displaying non-compliance with expected performance values for flight parameters of an aircraft. The method comprises collecting flight parameter data from the aircraft during aircraft operations and generating a graphical display of a flight path of the aircraft. The flight parameter data is compared with the expected performance values for the flight parameters of the aircraft and points of noncompliance by the aircraft are identified along its flight path. A graphical display icon is superimposed on each point of noncompliance on a graphical display of the flight path of the aircraft. The graphical display icon is a unique iconographic representation of the flight parameter. The flight path and the display icons are displayed on a graphical display device for review after completion of aircraft operations.

Abstract: A ground weather center may transmit information requests that carry at least one meteorological specific triggering command. An airborne system may translate the triggering command into detectable meteorological conditions and may arm the trigger(s) for specific weather sensors accordingly and downlink information upon the airborne system detects the triggering conditions. By using such a triggering command, the airborne system may be able transmit the same amount of valuable information with less bandwidth by reducing the number of redundant downlinked packets.

Abstract: Provided are a facility management system and method using an Internet of things (IoT) based sensor and an unmanned aerial vehicle (UAV). The facility management system and method may determine a current status and an abnormal behavior of a facility by primarily measuring the abnormal behavior of the facility in real time by a plurality of IoT based sensors included in the facility and secondarily precisely measuring the abnormal behavior of the facility by capturing an image through a UAV when necessary or when the abnormal behavior is detected, and may prevent a false alarm due to an error of a measurement sensor by performing two inspections through the IoT based sensor unit and the UAV.

Abstract: The present general inventive concept relates to methods and systems to select and display information on an avionics display screen. The systems and methods allow for the selection and display of information using knobs to highlight and select the desired information for display, eliminating the need for a cursor function. The systems and methods also provide for multiple pages and/or multiple windows or “tiles” within these pages and/or windows simultaneously on a single screen of a display, with each window, page, and/or tile being fully controlled independently when selected. The present general inventive concept also relates to systems and methods to provide multiple cues on an electronic display system altitude tape to a pilot in advance and impending approach to a predefined altitude. The present general inventive concept also relates to systems and methods to employ variable resolution topographical data based on display range for an avionics navigation display.

Abstract: A system for acceptance testing includes a data acquisition system operable to receive a plurality of sensor inputs from a component under test. The system also includes a health and usage monitoring system (HUMS) interface operable to receive data from a HUMS coupled to the sensor inputs. The system further includes a data processing system operable to determine a plurality of condition indicators based on the sensor inputs acquired by the data acquisition system, receive a plurality of HUMS data from the HUMS interface based on the sensor inputs, compare the condition indicators to the HUMS data, and output a test result based on results of the comparison.

Abstract: A condition of an unmanned aerial vehicle (UAV) is detected using one or more sensors of the UAV and signaled according to an alert definition associated with the condition. For example, an alert definition can indicate to signal the condition by using a motor of the UAV to produce an audible tone. A tonal signal having a frequency within an audible spectrum can be generated according to the alert definition. The tonal signal and a drive signal used for supplying current to the motor can be combined to produce a combined signal. The combined signal can then be transmitted to the motor to cause the motor to produce the audible tone. In some cases, an amplitude of the tonal signal can be modulated, such as where the amplitude of the combined signal exceeds a threshold associated with an operating margin of the UAV.