942results about "Aircraft health monitoring devices" patented technology

A wireless engine monitoring system (WEMS) includes an engine monitoring module that is mounted directly on an aircraft engine and records, stores, encrypts and transmits full flight engine data. The system preferably interfaces to the Full Authority Digital Engine Controller / Engine Control Unit (FADEC / ECU) and can record hundreds of engine parameters with a preferred sampling frequency of about one second. The engine monitoring module is preferably formed as a miniaturized module directly mounted on the aircraft engine within its cowling and has a conformal antenna. The engine monitoring module can also upload data for onboard processing.

The disclosed embodiments relate to methods and systems for monitoring sub-systems of an aircraft to detect an abnormal condition, and for identifying one or more sources that are causing the abnormal condition. In response to detecting a trigger event during flight of the aircraft, data for a plurality of relevant parameters is measured and stored in a parameter file. The parameter file is transmitted from the aircraft over a wireless communication link, and relayed to a ground support network. At the ground support network, the measured data for the plurality of the relevant parameters is then used to identify the one or more sources that are causing the abnormal condition.

The disclosed embodiments relate to methods and systems for requesting and retrieving aircraft data during flight of an aircraft. This aircraft data can be used to perform additional monitoring of aircraft sub-systems to detect an abnormal condition, and / or to identify one or more sources that are causing the abnormal condition. In one embodiment, aircraft data for one or more relevant parameters can be requested from the ground, measured on-board the aircraft, and stored in a data file that is then communicated back to personnel on the ground. The real-time aircraft data for one or more relevant parameters can then be analyzed to identify the one or more sources that are causing the abnormal condition.

A system for transmitting aircraft data from an aircraft includes a Data Acquisition Unit (DAU) that records aircraft data. A PC card is interfaced to the DAU and stores the aircraft data from the DAU. A processor retrieves aircraft data from the memory. A first wireless transceiver is controlled by the processor and receives and transmits the aircraft data along a wireless communications signal. A wireless local area network (LAN) communications unit is configured as an access point and positioned within the aircraft and transmits and receives wireless communications signals to and from the PC card. A second wireless transceiver is mounted within the aircraft and receives the wireless communications signal from the wireless LAN communications unit for transmitting the aircraft data from the aircraft.

A system for use in monitoring, measuring, computing and displaying the rate of compression of aircraft landing gear struts experienced while aircraft are executing either normal or hard landing events. A high speed computer attached to high speed cameras, or range-finders, mounted in relation to each of the landing gear struts are used to monitor, measure and record the landing gear compression rates and aircraft touch-down vertical velocities experienced by landing gear struts, as the aircraft landing gear initially comes into contact with the ground. The system also determines through landing gear strut compression rates if aircraft landing limitations have been exceeded.

A system and apparatus for data recording and analyzing operational data and methods for making and using the same are disclosed. The apparatus can monitor and record data generated by a plurality of operational and extended sensors each positioned on a moving platform. The data recording and analysis system can analyze the sensor data during movement and, by performing a statistical analysis of the operational data, can advantageously adjust one or more selected performance capabilities of the platform. For example, the performance envelope of a platform can be increased or decreased according to the experience of an operator. The recorded data can be transmitted at any suitable time, including during and / or after travel. The apparatus provides redundant storage capability and the ability to store information on removable media to enable sharing of data. Thereby, the system, apparatus and method advantageously can optimize the operator's overall experience controlling a platform.

A plurality of wireless engine sensors each includes a sensing circuit that senses an engine parameter as engine data. A radio transceiver receives and transmits the engine data regarding the sensed engine parameters. An engine monitoring module includes a housing configured to be mounted at the aircraft engine. A sensor receiver is mounted within the housing and receives the engine data from the wireless engine sensors. A first wireless transmitter is carried by the housing. A memory is carried by the housing and a processor is carried by the housing and coupled to the memory and the first wireless transmitter and configured to collect and store in the memory engine data related to engine parameters sensed during operation of the aircraft engine by the plurality of wireless engine sensors and transmit the engine data via the first wireless transmitter.

A method and apparatus for operating a sensor system. A first wireless signal is transmitted from a base station to a sensor unit. At least a portion of the first wireless signal is changed into power for the sensor unit using a power harvesting unit in the sensor unit. Information is received from a number of sensors associated with the sensor unit. The information is transmitted to the base station using a second wireless signal.

A system for monitoring physical and environmental conditions of an object can include one or more sensing devices affixed or mounted to the object. The sensing devices produce sensor data (e.g. motion, vibration, impact, temperature, stress and strain) that can be used to anticipate failure or for operation and / or maintenance purposes. The sensing devices can positioned on structures such as a building or an oil rig, on vehicles such as on airplanes, trains, ships and motor vehicles, and on moving devices such as wind turbines and draw bridges.

The different advantageous embodiments provide an apparatus comprising a number of landing gear components for a vehicle, a number of systems, and a number of processor units. The number of systems is configured to generate data about the number of landing gear components and the vehicle. The number of processor units is configured to monitor the data and manage health of the number of landing gear components.

An aircrew automation system that provides a pilot with high-fidelity knowledge of the aircraft's physical state, and notifies that pilot of any deviations in expected state based on predictive models. The aircrew automation may be provided as a non-invasive ride-along aircrew automation system that perceives the state of the aircraft through visual techniques, derives the aircraft state vector and other aircraft information, and communicates any deviations from expected aircraft state to the pilot.

A method and apparatus are provided for operating a network data processing system on an aircraft. A number of operations are performed in a virtual machine on the aircraft. The virtual machine runs on a processor unit in the network data processing system on the aircraft to create a simulated computer environment. The virtual machine accesses resources of the processor unit for performing the number of operations using a host operating system on the processor unit. A current state of the aircraft is identified by the network data processing system. Running of the virtual machine is managed based on the current state of the aircraft and a policy for managing the virtual machine for different states of the aircraft.

Systems (224, 222, 700) and methods (800) for providing wireless health monitoring for a locator beacon (216). The methods involve: coupling a Transponder and Sensor Module (TSM) to the locator beacon such that at least one condition of the locator beacon or a battery (230) of the locator beacon can be remotely monitored; periodically detecting the condition by the TSM (224); and periodically and wirelessly transmitting, from the TSM to a wireless device (222, 700) located in proximity to the TSM, a signal including information describing the condition detected by the TSM. The TSM can include, but is not limited to a transponder (e.g., an RFID tag) and sensor. The wireless device, can include, but is not limited to a transponder interrogator.

An unmanned aerial vehicle is provided. The unmanned aerial vehicle includes: a battery; a battery residual quantity detector configured to detect a residual quantity of the battery; a communicator configured to perform communication with a rechargeable unmanned aerial vehicle used in charging or replacement of the battery; and a processor configured to control the communicator to transmit its operation information to the rechargeable unmanned aerial vehicle detected within a predetermined distance when the detected residual quantity of the battery is less than the predetermined reference quantity and control to wirelessly charge the battery by the power supplied from the rechargeable unmanned aerial vehicle to maintain an operable state of the unmanned aerial vehicle or replace the battery to a new battery provided from the rechargeable unmanned aerial vehicle when being close to the rechargeable unmanned aerial vehicle receiving the operation information.

An aircraft control system including transducers connected by interface units to an avionics network, such as an AFDX network. Each transducer is directly connected to an interface unit local to the transducer. Each interface unit is a configurable unit and has a signal processing module converting data to a format suitable for transmission over the network. Each interface unit may be configurable, via software commands, to operate in an application session mode, a data-loading mode, or a maintenance mode. Each interface unit may be directly associated with one of the software applications of the aircraft control system. The network may include a lower bandwidth part where data communication is conducted over sampling ports only. Interface units may be configured or installed using a plug and play method.

A maintenance system is provided for an environmental conditioning element of an environmental control system of a vehicle. The maintenance system includes a data acquisition module configured to determine an ambient temperature, an altitude of the vehicle, and a measured ECS compressor temperature; a fouling module coupled to receive the ambient temperature, the altitude, and the measured ECS compressor temperature from the data acquisition module and configured to generate a fouling condition of the environmental conditioning element based on at least the ambient temperature, the altitude, and the measured ECS compressor temperature; and a reporting module coupled to receive the fouling condition from the fouling module and configured to generate a report for a user that includes the fouling condition.

An engine monitoring module includes a housing configured to be mounted at the aircraft engine and a first wireless transmitter carried by the housing. A memory is carried by the housing and a processor is carried by the housing and coupled to the memory and the first wireless transmitter and configured to collect and store in the memory engine data relating to at least one engine parameter sensed during operation of the aircraft engine by a plurality of engine sensors that transmit the engine data via the first wireless transmitter. A wireless receiver is located within the aircraft and configured to receive the engine data transmitted from the first wireless transmitter. A second wireless transmitter is located within the aircraft and operatively connected to the wireless receiver and configured to receive and transmit the engine data.

In one embodiment, a method for health and trend monitoring for aircraft systems includes receiving, by a processor on the aircraft, a plurality of sensor signals from a respective plurality of sensors onboard the aircraft and determining a reference signal from a subset of the plurality of sensor signals. Next, each of the plurality of sensor signals is individually compared to the reference signal to provide a plurality of difference signals. Each of the plurality of difference signals is compared to a threshold value, and a maintenance message is provided for any respective sensor associated with any of the plurality of difference signals exceeding the threshold value. An aircraft employing the health and trend monitoring system is also disclosed.

A system for transmitting aircraft data from an aircraft includes a Data Acquisition Unit (DAU) that records aircraft data. A PC card is interfaced to the DAU and stores the aircraft data from the DAU. A processor retrieves aircraft data from the memory. A first wireless transceiver is controlled by the processor and receives and transmits the aircraft data along a wireless communications signal. A wireless local area network (LAN) communications unit is configured as an access point and positioned within the aircraft and transmits and receives wireless communications signals to and from the PC card. A second wireless transceiver is mounted within the aircraft and receives the wireless communications signal from the wireless LAN communications unit for transmitting the aircraft data from the aircraft.

A control system for an in-flight engine restart system of a rotorcraft includes an engine control unit that controls and detects status of an engine. The control system also includes a flight control computer that communicates with the engine control unit, an engine operation control system, and a pilot interface including pilot controls. The engine operation control system includes a processor that initiates a health check of the in-flight engine restart system to determine an in-flight engine restart system status. The engine operation control system processes engine mode of operation commands to establish an engine mode of operation, and delivers commands to aspects of the in-flight engine restart system including the engine control unit based on processing of the engine mode of operation commands. The engine operation control system reports the in-flight engine restart system status and results of the engine mode of operation commands to the flight control computer.

An engine monitoring module includes a housing configured to be mounted at the aircraft engine and a first wireless transmitter carried by the housing. A memory is carried by the housing and a processor is carried by the housing and coupled to the memory and the first wireless transmitter and configured to collect and store in the memory engine data relating to at least one engine parameter sensed during operation of the aircraft engine by a plurality of engine sensors that transmit the engine data via the first wireless transmitter. A wireless receiver is located within the aircraft and configured to receive the engine data transmitted from the first wireless transmitter. A second wireless transmitter is located within the aircraft and operatively connected to the wireless receiver and configured to receive and transmit the engine data.

The disclosed embodiments relate to methods and systems for monitoring sub-systems of an aircraft to detect an abnormal condition, and for identifying one or more sources that are causing the abnormal condition. In response to detecting a trigger event during flight of the aircraft, data for a plurality of relevant parameters is measured and stored in a parameter file. The parameter file is transmitted from the aircraft over a wireless communication link, and relayed to a ground support network. At the ground support network, the measured data for the plurality of the relevant parameters is then used to identify the one or more sources that are causing the abnormal condition.

A method of transmitting aircraft flight data for an aircraft from the aircraft to a destination server via a wireless communication link with the method including determining an operational status of the aircraft, determining flight data to be transmitted, and transmitting the determined flight data to be transmitted to the destination server.

Method and apparatus for monitoring a vehicle. An apparatus comprises a sensor system and a computer system. The sensor system is associated with a number of human operators of a vehicle and a number of components in the vehicle. The sensor system is configured to generate physiological data for the number of human operators. The computer system is configured to receive the physiological data; determine whether the physiological data is within a level for a desired level of performance for operating the vehicle based on a policy; and perform a number of actions to maintain the desired level of performance for operating the vehicle in response to the physiological data not being within the level for the desired level of performance.

A method for testing an airplane maintenance system, which comprises the steps of: testing communications and data transmission between an aircraft operator and a management service provider; testing general communications and data transmission between internal systems of the management service provider; and testing communications and data transmission between the internal systems of the management service provider during for predetermined procedures.

A method is provided for wirelessly monitoring an aircraft propulsion system having a plurality of rotor blades, at least some of which rotor blades have an internal compartment. The method includes: providing a primary transducer having a primary coil, and one or more secondary transducers, each secondary transducer having a secondary coil connected to a sensor, wherein the secondary transducers are respectively disposed within the internal compartments; wirelessly powering the secondary transducers using a magnetic field generated by the primary transducer; monitoring at least one operational parameter from within each internal compartment using a respective sensor; and transmitting output signals from the secondary transducers to the primary transducer through the magnetic field, wherein the output signals are indicative of the monitored parameters.

Systems (224, 222, 700) and methods (800) for providing wireless health monitoring for a locator beacon (216). The methods involve: coupling a Transponder and Sensor Module (TSM) to the locator beacon such that at least one condition of the locator beacon or a battery (230) of the locator beacon can be remotely monitored; periodically detecting the condition by the TSM (224); and periodically and wirelessly transmitting, from the TSM to a wireless device (222, 700) located in proximity to the TSM, a signal including information describing the condition detected by the TSM. The TSM can include, but is not limited to a transponder (e.g., an RFID tag) and sensor. The wireless device, can include, but is not limited to a transponder interrogator.

A geometry-based flight control system is disclosed. The geometry-based flight control system receives a set of inputs associated with a requested set of forces and moments to be applied to the aircraft and computes an optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments. Computing the optimal mix of actuators and associated actuator parameters includes taking into consideration dynamically varying effectiveness of one or more actuators based on a dynamic state of the aircraft. For example, the dynamic state may comprise an angle of a tiltwing of the aircraft or an angle of a tilt rotor of the aircraft.

An emergency landing control system for an aircraft includes a landing site data source, a performance margin data source, an engine health data source, an aircraft health data source, and a processor. The landing site data source determines, continuously and in real-time, available landing sites. The performance margin data source conducts, continuously and in real-time, continuous performance analysis of an engine. The engine health data source determines, continuously and in real-time, available engine power as a function of time. The aircraft health data source determines, continuously and in real-time, available aircraft life as a function of time. The processor receives data from these data sources and, based on these data, continuously generates landing paths to one or more of the available landing sites, and selectively and continuously adjusts maximum available engine power up to emergency power limits, as needed, during execution of a landing maneuver to a landing site.