Abstract: A gas turbine engine and methods of operation are disclosed including a low pressure motor-generator and flutter control system.

Abstract: A gas turbine engine and methods of operation include a low pressure electric motor-generator arranged for selective operation in a generator mode to generate electrical power or a drive mode to assist rotation of a low pressure drive shaft of the engine.

Abstract: A device, system, and method. The device includes a memory and a processor communicatively coupled to the memory. The processor may be configured to receive synthetic image data corresponding to a determined current location and orientation of a user's eye and a determined current location of a vergence point corresponding to the user's gaze. The processor may be configured to generate a left stream of left synthetic images based on the synthetic image data, the determined current location and orientation of the user's left eye, and the determined current location of the vergence point. The processor may be configured to generate a right stream of right synthetic images based on the synthetic image data, the determined current location and orientation of the user's right eye, and the determined current location of the vergence point. The processor may be configured to output the left and right streams.

Abstract: A turbofan gas turbine engine includes low pressure (LP) motor-generator operable in either a generation mode or a drive mode, an high pressure (HP) motor-generator operable in a either a generation mode or a drive mode, and a power control module for selectively operating the LP and HP motor-generators according to operational conditions of the engine.

Abstract: A structure for use in an energy storage device, the structure comprising a backbone system extending generally perpendicularly from a reference plane, and a population of microstructured anodically active material layers supported by the lateral surfaces of the backbones, each of the microstructured anodically active material layers having a void volume fraction of at least 0.1 and a thickness of at least 1 micrometer.

Abstract: Apparatuses, systems, and methods are disclosed for drone interdiction. A projectile is capable of being launched to intercept a drone. The projectile may include a set of tethers that deploy from the projectile for securing the drone. The projectile may include a recovery device that deploys from the projectile for controlling a descent of the drone.

Abstract: A system is disclosed which utilizes a three-dimensional (3D) display system, in combination with an avionics Synthetic Vision System (SVIS), to provide 3D synthetic images of scenes around an aircraft where the systems are dynamically modified to meet particular needs of a flight crew, depending upon variable characteristics of the aircraft and environment including: phase of flight of the aircraft; attitude of the aircraft; proximity of the aircraft to Degraded Visual Environment (DVE) conditions; whether the 3D display system is an head-down display (HDD) or an immersive head-mounted display (HMD); and whether the 3D display system is an head-up display (HUD) or an HMD with a transparent visor.

Abstract: An electrically conductive contact element can include a first base and a second base with elongate, spaced apart leaves between the bases. A first end of each leaf can be coupled to the first base and an opposite second end of the leaf can be coupled to the second base. A body of the leaf between the first end and the second end can be sufficiently elongate to respond to a force through said contact element substantially parallel with the first axis and the second axis by first compressing axially while said force is less than a buckling force and then bending while said force is greater than the buckling force.

Abstract: An aviation display system includes an input source configured to provide a left eye input channel including a first band and an input source configured to provide a right eye input channel having a second band different from the first band. A processor is coupled with the input sources and with a non-transitory processor readable medium storing processor executable code, which causes the processor to receive data indicative of the left eye and right eye input channels from the input sources and to generate a left eye output channel and a right eye output channel. A display is configured to receive the left and right eye output channels from the processor and to provide an image indicative of the left eye output channel to a left eye of a user, and an image indicative of the right eye output channel to a right eye of the user.

Abstract: An aircraft power and propulsion system includes an air compressor, a heat rejection heat exchanger, a combustor positioned to receive compressed air from the air compressor as a core stream and provide thrust to the aircraft, and a closed-loop s-CO2 system. The closed-loop s-CO2 system includes carbon dioxide as a working fluid, receives power from the combustor, and rejects heat via the heat rejection heat exchanger to a cooling stream. The closed-loop system s-CO2 configured to provide power to a fan that provides the cooling stream and thrust, and power to the air compressor and at least one auxiliary load.

Abstract: A power and propulsion system includes an air compressor, a combustor positioned to receive compressed air from the air compressor as a core stream, and a closed-loop system having carbon dioxide as a working fluid that receives heat from the combustor and rejects heat to a cooling stream. The closed-loop system configured to provide power to a fan that provides the cooling stream, and to one or more distributed propulsors that provide thrust to an aircraft.

Abstract: An apparatus, system, and method for a gas turbine engine may include a sectioned heat exchanger. A heat exchanger may include an inlet manifold configured to receive a working fluid. A plurality of circuits including at least first and second circuits configured to transfer heat with respect to the working fluid. Each of the circuits may have a circuit inlet valve, a circuit heat exchange channel, and a circuit outlet valve. The heat exchanger may further include an outlet manifold configured to pass the working fluid to an outlet. The heat exchanger may include a first sensor configured to measure of first parameter of the first circuit and a second sensor configured to measure a second parameter of at least one of the outlet and the second circuit. A controller may be configured to selectively isolate at least one of the plurality of circuits based on a pressure difference between the first and second parameters.

Abstract: A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.

Abstract: An electrochemical stack comprising carrier ions, an anode comprising an anode active material layer, a cathode comprising a cathode active material layer, a separator between the anode and the cathode comprising a porous dielectric material and a non-aqueous electrolyte, and an ionically permeable conductor layer located between the separator and an electrode active material layer.

Abstract: A magnetic gearbox for use in a gas turbine engine includes an inner rotor assembly, a stator assembly, and an outer rotor assembly. The inner rotor assembly includes a first plurality of permanent magnets and an inner rotor. The outer rotor assembly includes an outer rotor and a second plurality of permanent magnets. Each of the inner and outer rotors include a plurality of slots to receive an attachment portion of each of the first and second plurality of permanent magnets to secure the plurality of magnets relative to the rotors during rotation.

Abstract: A structure for use in an energy storage device, the structure comprising a backbone system extending generally perpendicularly from a reference plane, and a population of microstructured anodically active material layers supported by the lateral surfaces of the backbones, each of the microstructured anodically active material layers having a void volume fraction of at least 0.1 and a thickness of at least 1 micrometer.

Abstract: A structure for use in an energy storage device, the structure comprising a backbone system extending generally perpendicularly from a reference plane, and a population of microstructured anodically active material layers supported by the lateral surfaces of the backbones, each of the microstructured anodically active material layers having a void volume fraction of at least 0.1 and a thickness of at least 1 micrometer.

Abstract: An electrochemical stack comprising carrier ions, an anode comprising an anode active material layer, a cathode comprising a cathode active material layer, a separator between the anode and the cathode comprising a porous dielectric material and a non-aqueous electrolyte, and an ionically permeable conductor layer located between the separator and an electrode active material layer.

Abstract: An integrated gas turbine engine, electrical power subsystem and thermal management subsystem for aerospace application includes a first motor/generator coupled to a low pressure (LP) shaft of the gas turbine engine, a second motor/generator coupled to a high pressure (HP) shaft of the gas turbine engine, and a system controller coupled to each of the gas turbine engine, a first motor generator and a second motor/generator, wherein the controller receives engine thrust demand and electrical power demand and is programmed to determine total system power demand and the amount of power sharing between the first motor/generator and the second motor/generator to meet thrust and electrical power demand.

Abstract: An aircraft includes first and second gas turbine engines having a first component and a second component that is redundant with the first component, and an engine health monitoring system (EHMS) coupled to the first and second gas turbine engines. The EHMS is configured to calculate a remaining useful life (RUL) of the first component and of the second component, calculate a rate-of-life consumption of the first component and of the second component, predict when failure of the first component and failure of the second component will occur based on the RUL of each and based on the respective rate-of-life consumption of each, and provide instructions for altering operation of the aircraft that affects the RUL of the first or second component.