Abstract: A thin-skin support member is provided. The thin-skin support member may include a semi-circular edge and a flat edge that define a hollow cavity. A cylindrical cavity may be adjacent the hollow cavity and at least partially defined by the semi-circular edge. The cylindrical cavity may be configured to retain a strut assembly. A mounting interface may be coupled to the semi-circular edge and the flat edge. A torsion interface may be disposed adjacent the cylindrical cavity and configured to receive a torsion link. The thin-skin support member may be made using additive manufacturing and thus may have a grain structure grown in the direction of material being added.

Abstract: An onboard inert gas system has an electrochemical and a membrane gas separator. The electrochemical separator includes an electrochemical cell including a cathode and anode separated by an electrolyte separator. An electrical power source provides power to the electrical circuit at a voltage that electrolyzes water at the anode and forms water at the cathode, or reduces oxygen at the cathode and forms oxygen at the anode. Oxygen is consumed at the cathode, providing nitrogen-enriched air. Nitrogen-enriched air from the cathode is connected by a flow path to the membrane gas separator, which comprises a membrane having a greater permeability to oxygen or water than to nitrogen. Nitrogen-enriched air from the membrane gas separator that is further enriched in nitrogen, reduced in water content, or both, is connected by a flow path to a fuel tank, a fire suppression system, or both a fuel tank and a fire suppression system.

Abstract: A hybrid-electric propulsion system includes a gas turbine engine, an electric machine coupled to and rotatably driven by the gas turbine engine to produce AC electric power, an energy storage system, and a propulsion unit. The gas turbine engine includes a combustor and a recuperator that places an exhaust air flow that is downstream from the combustor in a heat exchange relationship with a compressed air flow that is upstream from the combustor to transfer thermal energy from the exhaust flow to the compressed flow. The propulsion unit includes a fan and an electric motor rotably coupled to the fan, the electric motor being driven by electric power from one of the electric machine or the energy storage system.

Abstract: A propulsion system includes a gas turbine engine, an electric motor system having a motor drive electrically connected to the electric machine and an electric motor electrically connected to the motor drive where the electric motor drives a propulsion unit, an electric machine rotatably attached to the gas turbine engine and electrically connected to the electric motor system, an energy storage system having bi-directional electrical connections with the electric motor system and the electric machine, and an Rankine cycle system in communication with the gas turbine engine for recovering waste heat from the gas turbine engine.

Abstract: Systems and methods for operating a hoist and hook assembly may determine a position of a target using a position sensor. A hook assembly may be positioned in response to the position of the target as detected by the position sensor. Positioning the hook assembly may include articulating a boom coupled to a hoist, using one or more local thrust sources on the hook assembly, and/or moving an airframe relative to the position of the target.

Abstract: A taxi tug includes a chassis, a motive power source, and an auxiliary power services system. The chassis has at least one drive wheel. The motive power source is operatively connected to the at least one drive wheel. The auxiliary power services system is disposed on the chassis and is configured to provide at least one of electric power, pneumatic power, and low pressure conditioned air to an aircraft.

Abstract: An air inert gas generating system consists of heat exchangers, a heating element, and a plurality of solid oxide electrochemical gas separator (SOEGS) cells. The SOEGS cells are interconnected in series to create a stack. A voltage is applied to the stack causing oxygen ions to be transported from the air flowing through the cathode through the electrolyte to the anode side of the SOEGS, resulting in oxygen-depleted gas. The oxygen-depleted gas can be used to inert the ullage of aircraft fuel tank or support the fire suppression system in the cargo hold. The oxygen-enriched gas can be used for other purposes.

Abstract: A cargo management system is provided comprising a slide bushing supported cargo shuttle, an actuator coupled to a bushing slide plate; an aft shuttle drive belt coupled to the slide bushing supported cargo shuttle; and a forward shuttle drive belt coupled to the slide bushing supported cargo shuttle. Also disclosed is a slide bushing supported cargo shuttle comprising a housing, a bushing slide plate extendable from the housing via an actuator and a top surface of the bushing supported cargo shuttle and a power drive unit coupled to the top surface.

Abstract: A propulsion system and related methods are disclosed. A propulsion system may have a propulsor, an energy conversion system, an energy storage system that stores electrical energy, and a turbine. The propulsor may be in electrical communication with the energy conversion system, and the energy conversion system may receive electrical energy from the turbine or the energy storage system and deliver it to the propulsor. In this manner, a vehicle may be propelled by the propulsor even when the turbine is not operating.

Abstract: A cargo management system is provided comprising a slide bushing supported cargo shuttle, an actuator coupled to a bushing slide plate; an aft shuttle drive belt coupled to the slide bushing supported cargo shuttle; and a forward shuttle drive belt coupled to the slide bushing supported cargo shuttle. Also disclosed is a slide bushing supported cargo shuttle comprising a housing, a bushing slide plate extendable from the housing via an actuator and a top surface of the bushing supported cargo shuttle and a power drive unit coupled to the top surface.

Abstract: A tail cone integrated ram air turbine (RAT) includes a rotatable segment of an aircraft tail cone configured to deploy a set of RAT blades. The tail cone integrated RAT also includes a power transfer shaft connected between the rotatable segment and configured to transfer power to from the rotatable segment to an auxiliary power unit (APU). The tail cone integrated RAT further includes a controller connected to the APU and configured to control power output from the APU. When emergency power for an aircraft is needed, the set of RAT blades is deployed from the rotatable segment of an aircraft tail cone. Mechanical power from the rotatable segment is transferred to an APU generator to produce emergency electrical power.

Abstract: A propulsion system has a gas turbine engine optimized to operate at a single operating condition corresponding to a maximum continuous power output of the gas turbine engine, an electric motor system, an electric machine rotatably attached to the gas turbine engine and electrically connected to the electric motor system, and an energy storage system having bi-directional electrical connections with the electric motor system and the electric machine. A method of operating the propulsion system including operating the gas turbine engine for a first period of time to provide electric power to the electric motor system and to recharge the energy storage system, turning off the gas turbine for a second period of time, and discharging the energy storage system to operate the electric motor system during the second period of time.

Abstract: A runway traction estimation and reporting method and computer readable medium is provided. Upon detection of a landing event, a runway traction estimation and reporting method provides for various measurements and calculations to estimate the traction of the runway and create a traction map of the runway. A computer readable medium may contain instructions for a runway traction estimation and reporting processor directing the processor to perform various measurements and calculations to estimate the traction of the runway. The processor may communicate with a ground station or with other aircraft to produce collaborative results.

Abstract: A runway traction estimation and reporting method and computer readable medium is provided. Upon detection of a landing event, a runway traction estimation and reporting method provides for various measurements and calculations to estimate the traction of the runway and create a traction map of the runway. A computer readable medium may contain instructions for a runway traction estimation and reporting processor directing the processor to perform various measurements and calculations to estimate the traction of the runway. The processor may communicate with a ground station or with other aircraft to produce collaborative results.

Abstract: A tail cone integrated ram air turbine (RAT) includes a rotatable segment of an aircraft tail cone configured to deploy a set of RAT blades. The tail cone integrated RAT also includes a power transfer shaft connected between the rotatable segment and configured to transfer power to from the rotatable segment to an auxiliary power unit (APU). The tail cone integrated RAT further includes a controller connected to the APU and configured to control power output from the APU. When emergency power for an aircraft is needed, the set of RAT blades is deployed from the rotatable segment of an aircraft tail cone. Mechanical power from the rotatable segment is transferred to an APU generator to produce emergency electrical power.

Abstract: A variable speed ratio speed increaser drive train for a wind turbine is disclosed. The drive train may include at least one drive wheel adapted to receive mechanical energy from a main shaft of the wind turbine and capable of rotating at a variable input rotational speed and at least one driven wheel in at least indirect contact with the at least one drive wheel, the at least one driven wheel capable of at least indirectly translating against the at least one drive wheel to vary a speed ratio of the drive train to provide a constant output rotational speed.

Abstract: A constant speed ratio speed increaser friction wheel drive train for a wind turbine is disclosed. The drive train may include at least one drive wheel adapted to receive mechanical energy from a main shaft of a wind turbine and capable of rotating at an input rotational speed, the at least one drive wheel constructed of a plurality of drive wheel segments and at least one driven wheel in contact with and rotating against a surface of the at least one drive wheel at an output rotational speed, the output rotational speed varying with the input rotational speed.

Abstract: A wind turbine includes a vertically standing hybrid tower adapted to support a horizontally oriented rotor. The tower includes a fixed base portion and a separate rotatable upper rotor swept portion adapted to be secured to the base portion and rotatably yawed into the wind. The interface between the base and upper tower portions includes a bearing system defined by a pair of vertically spaced ring bearings adapted to encase and secure a downwardly depending spindle of the upper tower portion for rotatable support thereof within a vertically oriented cup-shaped opening in the base portion. Pluralities of contact rollers situated between inner and outer races of the ring bearings are each mounted on a single spindle and preloaded in angular orientation relative to the vertical axis of the tower.

Abstract: A wind turbine includes a vertically standing non-uniform tower adapted to support a horizontally oriented rotor. A fixed base portion of the turbine is adapted to support a separate rotatable tower having an upper rotor swept portion along the main body of the tower. The tower is adapted to be secured to the base for being rotatably yawed into the wind. A bearing system is housed between the base and lower tower extremity includes a pair of vertically spaced tracks situated on an annular support rail adapted to be fixed to a ground structure, for example a reinforced concrete foundation. The bearing system is further defined by pluralities of yaw bearing cartridge assemblies adapted to extend through flanged apertures of a skirt portion in the lower extremity of the tower.