Abstract: An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.

Abstract: A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.

Abstract: An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.

Abstract: A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.

Abstract: An electric machine having an electrically insulative manifold is disclosed. In one example aspect, an electric machine includes a non-electrically conductive manifold. The manifold defines a chamber operable to receive a cooling fluid. The electric machine includes a prime winding in fluid communication with the chamber and one or more secondary windings in electrical communication with the prime winding and in fluid communication with the chamber. Further, the electric machine includes an electric machine terminal extending through the non-electrically conductive manifold and coupled with the prime winding. The electric machine terminal can provide or collect cooling fluid from the chamber of the manifold and can act as the electrical connection point for directing electrical power to or from the windings of the electric machine.

Abstract: An electric machine having a hybrid insulative-conductive manifold is disclosed. In one aspect, an electric machine includes a manifold that includes an insulative plate and a conductive backplate positioned adjacent to the insulative plate. The insulative plate and the backplate define a first channel and a second channel therebetween. The electric machine also includes a prime winding and a secondary winding electrically isolated from the prime winding. The prime winding and the secondary winding are both in fluid communication with the first channel and the second channel. A terminal conductor extends through the backplate and insulative plate and is electrically coupled with the prime winding. The terminal conductor is electrically isolated from the backplate and provides cooling fluid to the prime winding and the first channel so that cooling fluid flows between the terminal conductor and the prime winding and between the terminal conductor and the first channel.

Abstract: A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.

Abstract: An aircraft equipped with a distributed unducted fan propulsion system is provided. In one aspect, an aircraft includes a body defining a lateral centerline that separates the body into a first side and a second side. One or more first unducted fans are mounted to the first side of the body. The one or more first unducted fans are rotatable in a first direction. One or more second unducted fans are mounted to the second side of the body. The one or more second unducted fans are rotatable in a second direction that is opposite the first direction.

Abstract: An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.

Abstract: An electric machine having an electrically insulative manifold is disclosed. In one example aspect, an electric machine includes a non-electrically conductive manifold. The manifold defines a chamber operable to receive a cooling fluid. The electric machine includes a prime winding in fluid communication with the chamber and one or more secondary windings in electrical communication with the prime winding and in fluid communication with the chamber. Further, the electric machine includes an electric machine terminal extending through the non-electrically conductive manifold and coupled with the prime winding. The electric machine terminal can provide or collect cooling fluid from the chamber of the manifold and can act as the electrical connection point for directing electrical power to or from the windings of the electric machine.

Abstract: Systems, computer-implemented methods and/or computer program products that facilitate selecting components for aviation engines. In one embodiment, a computer-implemented method comprises: calculating, by a system operatively coupled to a processor, standard deviation between components for aviation engines based on a statistical distribution of measured manufacturing characteristics; selecting, by the system, a subset of components based on the calculated standard deviation; and analyzing, by the system, the subset of components at respective standard deviation to determine a standard deviation and period of time for trading that maximizes durability performance.

Abstract: A system for selecting components for an engine includes an electronic control unit comprising a processor and a memory component and a machine-readable instruction set. The machine-readable instruction set is stored in the memory component of the electronic control unit and causes the system to perform at least the following when executed by the processor: receive a catalog of a plurality of components, where the plurality of components include a measured manufacturing characteristic, receive at least one operating environment characteristic of a plurality of operating environment characteristics, and select one or more components from the catalog of the plurality of components for a bill of materials based on the measured manufacturing characteristic and the at least one operating environment characteristic.

Abstract: Systems, computer-implemented methods and/or computer program products that facilitate selecting components for aviation engines. In one embodiment, a computer-implemented method comprises: calculating, by a system operatively coupled to a processor, standard deviation between components for aviation engines based on a statistical distribution of measured manufacturing characteristics; selecting, by the system, a subset of components based on the calculated standard deviation; and analyzing, by the system, the subset of components at respective standard deviation to determine a standard deviation and period of time for trading that maximizes durability performance.