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 method for determining the distance from a tip of a pointer to a surface using a light source and a single camera, the method comprising detecting in an image captured by the camera a tip of the pointer, determining in the image captured by the camera the intensity of a set of pixels below the tip of the pointer, the intensity defining a reflection by the surface of the tip of the pointer illuminated by the light source, and determining the distance from the tip of the pointer to the surface depending upon the intensity of the set of pixels below the tip of the pointer and an intensity of pixels of the tip of the pointer in the image.

Abstract: A system and method of adaptively managing a plurality of engines in a multi-engine system, where each engine comprises hot gas components and non-hot gas components, and each engine exhibits a performance margin and a remaining useful life, includes continuously, and in real-time, determining a plurality of different degradation mechanisms for each of the plurality of engines, and continuously, and in real-time, determining which of the determined degradation mechanisms is most limiting. The engines are controlled, based on the most limiting degradation mechanism, in a manner that the remaining useful lives of each engine are substantially equal. The plurality of different degradation mechanisms of each engine are determined based on the engine performance margin, modeled failure predictions of the hot gas components, and modeled failure predictions of the non-hot gas components.

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: In accordance with an exemplary embodiment, an operations support system for an engine is provided. A diagnostics unit is configured to receive engine data from the engine and to generate condition indicators based on the engine data using a thermodynamic model, the thermodynamic model being based on component maps associated with the engine. An emissions calculation unit is coupled to the diagnostic unit and configured to calculate emissions information for the engine based on the condition indicators. A graphical user interface is coupled to the emissions calculation unit and configured to display the emissions information.

Abstract: An operations support system is provided for an engine receiving fuel. 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 and the engine data. The engine-specific model unit includes a fuel flow calculation module configured to determine a current fuel flow for the engine and a set point module configured to generate set point information for the engine using a thermodynamic model that reduces the current fuel flow to the engine, the thermodynamic model being based on component maps associated with the engine. The system further includes a data storage unit coupled to the engine-specific model unit and configured to store the set point information.

Abstract: A system and method of adaptively managing a plurality of engines in a multi-engine system, where each engine comprises hot gas components and non-hot gas components, and each engine exhibits a performance margin and a remaining useful life, includes continuously, and in real-time, determining a plurality of different degradation mechanisms for each of the plurality of engines, and continuously, and in real-time, determining which of the determined degradation mechanisms is most limiting. The engines are controlled, based on the most limiting degradation mechanism, in a manner that the remaining useful lives of each engine are substantially equal. The plurality of different degradation mechanisms of each engine are determined based on the engine performance margin, modeled failure predictions of the hot gas components, and modeled failure predictions of the non-hot gas components.

Abstract: A method for determining the distance from a tip of a pointer to a surface using a light source and a single camera, the method comprising detecting in an image captured by the camera a tip of the pointer, determining in the image captured by the camera the intensity of a set of pixels below the tip of the pointer, the intensity defining a reflection by the surface of the tip of the pointer illuminated by the light source, and determining the distance from the tip of the pointer to the surface depending upon the intensity of the set of pixels below the tip of the pointer and an intensity of pixels of the tip of the pointer in the image.

Abstract: An operations support system is provided for an engine receiving fuel. 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 and the engine data. The engine-specific model unit includes a fuel flow calculation module configured to determine a current fuel flow for the engine and a set point module configured to generate set point information for the engine using a thermodynamic model that reduces the current fuel flow to the engine, the thermodynamic model being based on component maps associated with the engine. The system further includes a data storage unit coupled to the engine-specific model unit and configured to store the set point information.

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: 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: 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 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: In accordance with an exemplary embodiment, an operations support system for an engine is provided. A diagnostics unit is configured to receive engine data from the engine and to generate condition indicators based on the engine data using a thermodynamic model, the thermodynamic model being based on component maps associated with the engine. An emissions calculation unit is coupled to the diagnostic unit and configured to calculate emissions information for the engine based on the condition indicators. A graphical user interface is coupled to the emissions calculation unit and configured to display the emissions information.

Abstract: A power management system includes a data fusion unit configured to receive first health indicators from an engine diagnostics module and second health indicators from a power assurance module. The data fusion unit is configured to data fuse the first and second health indicators. A power assessment and decision support unit is coupled to the data fusion unit and configured to generate power available based on the fused first and second health indicators. A system diagnostic reasoner unit is coupled to the data fusion unit, and configured to provide a system level fault diagnosis based on the fused first and second health indicators. A graphical user interface is coupled to the power assessment and decision support unit and the system diagnostic reasoned unit. The graphical user interface is configured to display the system level fault diagnosis and the power available.

Abstract: An operations support system for an engine includes an engine prediction unit configured to receive an engine rating condition and scalars associated with the engine, and to generate condition indicators based on the engine rating condition and the scalars; and a power assurance algorithm unit coupled to the engine prediction unit and configured to generate health indicators based on the condition indicators. The health indicators include a power assurance number.

Abstract: A system and method for controlling the fuel flow rate in a direct metering fuel control system to compensate for actuator flow. The system includes a fuel metering pump that supplies fuel to a fluid-operated actuator and to a gas turbine engine combustor and determines, using a generated model of the fuel metering pump and/or the fluid-operated actuator, fuel flow rate needed by the gas turbine engine and/or the actuator fuel flow rate needed by the fluid-operated actuator. The fuel flow rate of the fuel metering pump is controlled based on the determined actuator fuel flow rate and the determined engine fuel flow rate.

Abstract: Methods and apparatus are provided for operating a gas turbine engine. In a first operational mode, the gas turbine engine generates thrust using the propulsion turbine and not the afterburner when it is commanded to generate a thrust between at least a first thrust magnitude and a second thrust magnitude, and generates thrust using the propulsion turbine and the afterburner when it is commanded to generate thrust greater than the second thrust magnitude. In a second operational mode, the gas turbine engine generates thrust using the propulsion turbine and the afterburner when it is commanded to generate a thrust greater than the first thrust magnitude. The steady state thrust-versus-throttle position response has a substantially constant linear slope that is set to be two times the similar slope of the first operational mode.

Abstract: A system and method of conducting a continuous performance analysis for a system includes collecting transient performance data for a first parameter of the system and a second parameter of the system. Transfer functions are applied to the transient performance data for at least one of the first and second parameters to thereby generate phase compensated performance data representative of a steady state relationship between the first and second parameter. For each phase compensated performance datum, an estimate of the first parameter is calculated at a predetermined value of the second parameter using the phase compensated performance datum and a previously stored performance characteristic curve representative of the steady state relationship between the first and second parameters in a deterioration model extrapolation method.

Abstract: A system and method of phase compensating transient performance data are provided. Transient performance data are collected for a plurality of parameters, and two of the parameters are selected. A transfer function is applied to the transient performance data for at least one of the selected parameters to thereby generate phase compensated performance data that is representative of a steady state relationship between the selected parameters.