Abstract: Methods and systems for monitoring operation of hybrid electric engines of aircraft. The methods include monitoring a motor condition of an electrical power system associated with an engine condition using a motor sensor, wherein the electrical power system comprises an electric machine operably coupled to at least one shaft of an engine core, wherein the electric machine is configured to at least one of add power to the at least one shaft and extract power from the at least one shaft, receiving motor data from the motor sensor at a motor controller, wherein the motor controller is configured to control operation of, at least, the electric machine, analyzing the motor data to determine the presence of a fault in the engine core, and, when a fault is detected, performing a fault response action.

Abstract: This invention relates to a curative composition and its use in curing epoxy resins and prepregs, adhesives and moulded materials derived therefrom. The curative composition comprises a clathrate comprising a host component and a guest component, the host comprising a carboxylic acid or ester compounds as defined or phenolphthalin and the guest comprising an imidazole or imidazoline component.

Abstract: A hybrid electric propulsion system includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid electric propulsion system includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to determine hybrid electric propulsion system parameters based on a composite system model and sensor data, determine a prediction based on the hybrid electric propulsion system parameters and the composite system model, determine a model predictive control optimization for a plurality of hybrid electric system control effectors based on the prediction using a plurality of reduced-order partitions of the composite system model, and actuate the hybrid electric system control effectors based on the model predictive control optimization.

Abstract: A system for bleeding air from a core flow path of a gas turbine engine is disclosed. In various embodiments, the system includes a bleed valve having a bleed valve inlet configured to receive a bleed air from a first access point to the core flow path and a bleed valve outlet; and an air motor having a first air motor inlet configured to receive the bleed air from the bleed valve outlet and a first air motor outlet configured to exhaust the bleed air, the air motor configured to pump the bleed air from the core flow path of the gas turbine engine.

Abstract: A system of a hybrid aircraft includes a first gas turbine engine, a second gas turbine engine, and a controller. The first gas turbine engine includes a first low spool electric machine and a first high spool electric machine. The second gas turbine engine includes a second low spool electric machine and a second high spool electric machine. The controller is operable to determine an operating mode of the hybrid aircraft and control power extraction from either or both of the first low spool electric machine and the first high spool electric machine while a single engine descent mode is active. Electric power is provided to either or both of the second low spool electric machine and the second high spool electric machine while the single engine descent mode is active to balance thrust between the first gas turbine engine and the second gas turbine engine.

Abstract: A hybrid-electric aircraft system is provided and includes first and second hybrid-electric engines, each of which includes an electric motor to drive operations thereof, and a supplemental power unit (SPU). The SPU is configured as a thermal engine paired with a generator and is configured to generate electrical power. The first and second hybrid-electric engines are operable normally and off, respectively, with electrical power generated by the SPU being diverted to the electric motor of the second hybrid-electric engine.

Abstract: A system of a hybrid aircraft includes a first gas turbine engine, a second gas turbine engine, a power source, and a controller. The first gas turbine engine includes a first electric machine. The second gas turbine engine includes a second electric machine. The controller is operable to determine an operating condition of the first gas turbine engine and the second gas turbine engine and to detect a change in a thrust command for the hybrid aircraft. The controller is further operable to determine an adjustment to the second electric machine to compensate for the change in the thrust command while the first gas turbine engine is operating in a fuel-driven mode and the second gas turbine engine is operating in an electrically-driven mode. At least a portion of electric power to perform the adjustment to the second electric machine is extracted from the power source.

Abstract: Examples described herein provide a computer-implemented method that includes controlling a high spool motor of an aircraft to cause the high spool motor to drive rotation of a high speed spool of a gas turbine engine of the aircraft to maintain a desired compressor pressure and a desired flow within a combustor of the gas turbine engine. The method further includes commanding fuel flow to the combustor responsive to a trigger event to cause the gas turbine engine to start to a fuel-burning mode.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to optimize projection of big data beyond its footprint. An example apparatus includes memory, instructions, and processor circuitry to access panel audience sizes corresponding to subscribers of a media provider, a subset of the subscribers of the media provider, and corresponding to a media network determine a relative percent difference between the third panel audience size and the fourth panel audience size, when the relative percent absolute difference satisfies a first threshold, determine percentages of demographic groups represented in the panel audience sizes, determine differences associated with the demographic groups, and when at least one of the differences corresponding to at least one of the demographic groups satisfies a second threshold, determine the subscribers, the subset of the subscribers, and the at least one of the demographic groups as useable to determine an audience size of the media network.

Abstract: Systems and methods to semantically compare product configuration models. A method includes receiving a first configuration model and a second configuration model. The method includes generating a first order logic (FOL) representation of the first configuration model and an FOL representation of the second configuration model. The method includes performing a satisfiability modulo theories (SMT) solve for nonequivalence satisfiability on the FOL representation of the first configuration model and the FOL representation of the second configuration model. The method includes storing an indication that the first configuration model is equivalent to the second configuration model when the SMT solve for nonequivalence satisfiability is not satisfied.

Abstract: A method for determining a set of output configuration values characterizing a specific configuration of a complex product, includes receiving a set of input configuration parameters, providing at least a part of the input configuration parameters as an input to a solver, using the solver to calculate at least one output value from the provided input configuration parameters, and determining the set of output configuration values from at least the output value calculated by the solver. The solver is configured for solving a first order logic function encoding an algorithm of a trained deep neural network or DNN, wherein the algorithm of the DNN has been trained for modeling a function of an external configuration tool or ECT that is required for determining the specific configuration of the complex product. A system for determining the set of output configuration values, and a training system, are also provided.

Abstract: A hybrid electric propulsion system includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid electric propulsion system includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to determine an estimate of hybrid electric propulsion system parameters based on a composite system model and sensor data, determine a model predictive control state and a prediction based on the hybrid electric propulsion system parameters and the composite system model, determine a model predictive control optimization for a plurality of hybrid electric system control effectors based on the model predictive control state and the prediction using a plurality of reduced-order partitions of the composite system model, and actuate the hybrid electric system control effectors based on the model predictive control optimization.

Abstract: An engine system of an aircraft includes a gas turbine engine comprising at least one spool and at least one electric machine operably coupled with the at least one spool. A controller is configured to detect if the at least one spool of the gas turbine engine is in or is approaching an overspeed condition and apply a load to the at least one spool via the at least one electric machine.

Abstract: An engine system of an aircraft includes an energy storage system, a gas turbine engine, and a controller. The gas turbine engine includes a low spool, a high spool, a low-spool generator operably coupled to the low spool, and a high-spool electric motor operably coupled to the high spool. The controller is configured to detect a braking condition of the aircraft, transfer power from the low-spool generator to the energy storage system based on the storage capacity state of the energy storage system, and transfer power to the high spool through the high-spool electric motor to support combustion in the gas turbine engine while a rotational speed of the low spool is reduced responsive to the low-spool generator extracting energy from the low spool.

Abstract: A system for bleeding air from a core flow path of a gas turbine engine is disclosed. In various embodiments, the system includes a bleed valve having a bleed valve inlet configured to receive a bleed air from a first access point to the core flow path and a bleed valve outlet; and an air motor having a first air motor inlet configured to receive the bleed air from the bleed valve outlet and a first air motor outlet configured to exhaust the bleed air, the air motor configured to pump the bleed air from the core flow path of the gas turbine engine.

Abstract: An amplifier operable with an electric drive signal can amplify signal light having a signal wavelength. A laser diode has an active section with input and output facets. The facets are in optical communication with the signal light and are configured to pass the signal light through the laser diode. The active section is configured to generate pump light in response to injection of the electrical drive signal into the active section. The pump light has a pump wavelength different from the signal wavelength. A doped fiber doped with an active dopant is in optical communication with the signal light and is in optical communication with at least a portion of the pump light from the laser diode. The pump wavelength of the pump light is configured to interact with the active dopant of the fiber and thereby amplify the signal light.

Abstract: A package is disclosed. In one example, the package comprises a carrier, an electronic component mounted on the carrier, an encapsulant encapsulating at least part of the electronic component and at least part of the carrier and having a bottom side at a first vertical level. At least one lead is electrically coupled with the electronic component and comprising a first lead portion being encapsulated in the encapsulant and a second lead portion extending out of the encapsulant at the bottom side of the encapsulant. A functional structure at the bottom side extends up to a second vertical level different from the first vertical level.

Abstract: A package for a size-in-store window covering comprises a box having a first portion that extends for the width of the window covering and a second portion that extends for less than the width of the window covering. The window covering extends beyond an end of a bottom wall a first distance and the head rail extends beyond an end of a first side wall a second distance. A method of cutting a window covering comprises providing a window covering in a box as described above and positioning the box with the exposed portion of the window covering facing down and the exposed portion of the head rail facing a clamp. Methods of packaging a window covering comprise reducing the total number of loops in the window covering, and positioning inserts between adjacent components.

Abstract: The present invention related to compounds of Formula (I): or an agronomically acceptable salt thereof, wherein Q, X, Z, R2 and R3 areas described herein. The inventions further relates to compositions comprising said compounds, to methods of controlling weeds using said compositions, and to the use of Compounds of Formula (I) as a herbicide.

Abstract: A parts assembly, a tank, and a panel discussed, including a first wall; a second wall, a first edge of the first wall facing a second edge of the second wall; a first flange connected to and extending outward from the first wall; a second flange connected to and extending outward from the second wall, the second flange being spaced from and disposed opposite the first flange; at least one fastener extending through and connecting the first flange and the second flange, the at least one fastener being pre-tensioned; and at least one rigid spacing member disposed between the first flange and the second flange, the rigid spacing member being spaced from the at least one fastener, the rigid spacing member being in contact with the first and second flanges, the at least one fastener being disposed between the rigid spacing member and the first and second walls.