Abstract: A band includes a latch body that is movable by pulling a tab. The latch body extends through an opening of the band and secures with a pin located on a head-mountable device. The band can detach from the head-mountable device by pulling the tab, which actuates the latch body and removes the latch body from the pin. A spring (or springs) can bias the latch body toward the opening, causing the latch body to enter the pin. An applied force to the tab can overcome the biasing force provided by the spring(s), and move the latch body away from, and out of, the pin.

Abstract: A multivariate predictive system processes usage based data that includes a database engine that provides access to a plurality of database management systems that mine diverse sources of usage based data. A digital filter selectively filters data streams that include usage based data. A sampler automatically divides the filtered data into sample groups and stores the sample groups in a memory. The sampler divides the filtered data according to insurance rating variables processed by a processor programmed to underwrite an insurance product and rate that insurance product. Some samplers store the divided filter data in a local memory. A multiplier multiples rating factors preprogrammed with the insurance rating variables with a base rate of insurance to determine an insured's insurance premium.

Abstract: A method for self-generating an engine-specific model in an engine health monitoring system is provided. The method comprises generating a generic engine model including a generic physics-based model for each of a plurality of engine components in the specific engine; capturing a plurality of observed engine component parameters for each of the plurality of engine components and a plurality of observed environmental parameters during one or more pre-planned training missions; and training an engine-specific model using the plurality of observed engine component parameters and the plurality of environmental parameters captured during the one or more pre-planned training missions, wherein the engine-specific model includes an engine-specific physics-based model for each of the plurality of engine components in the specific engine.

Abstract: During operation, a computer obtains information specifying a lighting configuration of one or more lights in an environment, where the lighting configuration includes the one or more lights at predefined or predetermined locations in the environment. Then, the computer receives sensor data associated with the environment. Moreover, the computer analyzes the sensor data to determine a context associated with the environment. Then, based at least in part on the lighting configuration, a layout of the environment, and the determined context, the computer automatically determines the dynamic lighting states of the one or more lights, where a dynamic lighting state of a given light includes an intensity and a color of the given light. Next, the computer provides instructions corresponding to the dynamic lighting states to the one or more lights. Note that the dynamic lighting states may be based at least in part on a transferrable profile of the individual.

Abstract: During operation, a computer generates, based at least in part on an initial lighting configuration in an environment and a layout of the environment, and provides a simulation of the environment with the initial lighting configuration. Note that the initial lighting configuration includes one or more lights at predefined or predetermined locations in the environment, dynamic lighting states of the one or more lights, and a dynamic lighting state of the given light includes an intensity and a color of the given light. Moreover, based at least in part on the initial lighting configuration, the layout of the environment, and a determined context of the environment, the computer modifies the initial lighting configuration to obtain an updated lighting configuration. Next, based at least in part on the updated lighting configuration and the layout, the computer generates and selectively provides an updated simulation of the environment with the updated lighting configuration.

Abstract: A system and method for providing bleed air compensation for a continuous power assurance analysis of a gas turbine engine includes estimating bleed air flow rate from the gas turbine engine, estimating a shift in power turbine inlet temperature based on the estimated bleed air flow rate, and applying the estimated shift in power turbine inlet temperature to the continuous power assurance analysis of the gas turbine engine.

Abstract: A system and method for translating performance characteristics of a system from one system condition to another system condition includes sensing, at a current system condition, a first system performance parameter and a second system performance parameter. The first and second system performance parameters correspond to a measured performance characteristic value of the system. A first reference performance datum associated with the first and second system performance parameters at the current system condition, and a second reference performance datum associated with the first and second system performance parameters at a selected reference system condition are both retrieved from a memory. A difference between the first and second reference performance data is calculated to generate a translation value.

Abstract: During operation, a computer obtains information specifying a lighting configuration of one or more lights in an environment, where the lighting configuration includes the one or more lights at predefined or predetermined locations in the environment. Then, the computer receives sensor data associated with the environment. Moreover, the computer analyzes the sensor data to determine a context associated with the environment. Then, based at least in part on the lighting configuration, a layout of the environment, and the determined context, the computer automatically determines the dynamic lighting states of the one or more lights, where a dynamic lighting state of a given light includes an intensity and a color of the given light. Next, the computer provides instructions corresponding to the dynamic lighting states to the one or more lights. Note that the dynamic lighting states may be based at least in part on a transferrable profile of the individual.

Abstract: During operation, a computer generates, based at least in part on an initial lighting configuration in an environment and a layout of the environment, and provides a simulation of the environment with the initial lighting configuration. Note that the initial lighting configuration includes one or more lights at predefined or predetermined locations in the environment, dynamic lighting states of the one or more lights, and a dynamic lighting state of the given light includes an intensity and a color of the given light. Moreover, based at least in part on the initial lighting configuration, the layout of the environment, and a determined context of the environment, the computer modifies the initial lighting configuration to obtain an updated lighting configuration. Next, based at least in part on the updated lighting configuration and the layout, the computer generates and selectively provides an updated simulation of the environment with the updated lighting configuration.

Abstract: A method for self-generating an engine-specific model in an engine health monitoring system is provided. The method comprises generating a generic engine model including a generic physics-based model for each of a plurality of engine components in the specific engine; capturing a plurality of observed engine component parameters for each of the plurality of engine components and a plurality of observed environmental parameters during one or more pre-planned training missions; and training an engine-specific model using the plurality of observed engine component parameters and the plurality of environmental parameters captured during the one or more pre-planned training missions, wherein the engine-specific model includes an engine-specific physics-based model for each of the plurality of engine components in the specific engine.

Abstract: An embodiment of the invention provides a wireless ear-borne audio device that may be configured in a variety of ways, including, but in no way limited to a device for recording audio information and storing the audio information for later replay, and/or forwarding the audio information to another device. The audio information may be analyzed to perform further functions. An embodiment of the invention also provides a method for compressing audio data and transmitting the audio information to the ear-borne audio device in a manner that reduces the power consumption of the ear-borne audio device in receiving data via a Bluetooth® connection.

Abstract: A system and method for providing bleed air compensation for a continuous power assurance analysis of a gas turbine engine includes estimating bleed air flow rate from the gas turbine engine, estimating a shift in power turbine inlet temperature based on the estimated bleed air flow rate, and applying the estimated shift in power turbine inlet temperature to the continuous power assurance analysis of the gas turbine engine.

Abstract: An embodiment of the invention provides a wireless ear-borne audio device that may be configured in a variety of ways, including, but in no way limited to a device for recording audio information and storing the audio information for later replay, and/or forwarding the audio information to another device. The audio information may be analyzed to perform further functions. An embodiment of the invention also provides a method for compressing audio data and transmitting the audio information to the ear-borne audio device in a manner that reduces the power consumption of the ear-borne audio device in receiving data via a Bluetooth® connection.

Abstract: A compressor surge avoidance control system and method for a gas turbine engine includes sensing a plurality of engine inlet parameters, and receiving a fuel command value. The sensed parameters are processed to determine a surge fuel value that is representative of a fuel flow above which, for the sensed engine inlet parameters, a compressor surge will likely occur. The surge fuel value and the fuel command value are compared, and a protective action signal is generated if the fuel command value exceeds the surge fuel value.

Abstract: A system method for predicting vehicle mission capability for a vehicle that is propelled by an engine includes collecting engine degradation data for the engine. Location independent engine degradation data are generated from the collected engine degradation data. The location independent engine degradation data are representative of engine degradation that is independent of locations associated with the mission. Predictions of location dependent engine degradation are calculated from the collected engine degradation data and the location independent engine degradation data. The location dependent engine degradation is representative of engine degradation due to movement through locations associated with the mission.

Abstract: 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.

Abstract: A system and method of adaptively synchronizing the performance margin of a multi-engine system includes continuously, and in real-time, determining the performance margin of a first engine and the performance margin of the second engine. A difference between the performance margins of the first and second engines is calculated, and the first and second engines are controlled to attain a predetermined difference between the performance margins of the first and second engines.

Abstract: An operations support system is provided for an engine. The system includes a diagnostics module configured to receive engine data from the engine and to generate diagnostics data based on the engine data using a thermodynamic model, the thermodynamic model being based on component maps associated with the engine; an acoustics module coupled to the diagnostics module and comprising an acoustics calculation unit, the acoustics calculation unit configured to receive the diagnostics data and to determine an acoustics level for the engine based on the diagnostics data; and a graphical user interface coupled to the acoustics module and configured to display the acoustics level.

Abstract: An operations support system is provided for an engine with a turbine having a turbine inlet. The system includes a diagnostic engine model unit configured to receive engine data from the engine and to generate diagnostics data based on the engine data, the diagnostics data including scalars. The system further includes an engine-specific model unit coupled to the diagnostic engine model unit and configured to receive the scalars from the diagnostic engine model unit and configured to generate turbine inlet temperature information for the engine using a thermodynamic model. The thermodynamic model is based on component maps associated with the engine. The system further includes a storage unit coupled to the engine-specific model unit and configured to store the turbine inlet temperature information.

Abstract: 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.