Abstract: A rotary electric machine arranged as a brushless electric ring motor is described and includes a rotor that is disposed within a stator and arranged to rotate on a guide element. The rotor has a plurality of ferritic elements arranged on an outer surface, and the stator is an annular device having a plurality of electro-magnetic elements arranged on an inner portion between first and second flanges. The first and second flanges both include an annular ring that is fabricated from a non-magnetic material and has a plurality of ferromagnetic elements. The ferromagnetic elements are magnetically coupled to corresponding ones of the electro-magnetic elements to exert magnetic force on the ferritic elements of the rotor when the electro-magnetic elements are activated. The rotary electric machine may operate as a first thrust generating system that is upstream of a second thrust generating system for a turbojet engine.

Abstract: Interlacing equipment may be used to form fabric and to create a gap in the fabric. The fabric may include one or more conductive strands. An insertion tool may be used to align an electrical component with the conductive strands during interlacing operations. A soldering tool may be used to remove insulation from the conductive strands to expose conductive segments on the conductive strands. The soldering tool may be used to solder the conductive segments to the electrical component. The solder connections may be located in grooves in the electrical component. An encapsulation tool may dispense encapsulation material in the grooves to encapsulate the solder connections. After the electrical component is electrically connected to the conductive strands, the insertion tool may position and release the electrical component in the gap. A component retention tool may temporarily be used to retain the electrical component in the gap as interlacing operations continue.

Abstract: Interlacing equipment may be used to form fabric and to create a gap in the fabric. The fabric may include one or more conductive strands. An insertion tool may be used to align an electrical component with the conductive strands during interlacing operations. A soldering tool may be used to remove insulation from the conductive strands to expose conductive segments on the conductive strands. The soldering tool may be used to solder the conductive segments to the electrical component. The solder connections may be located in grooves in the electrical component. An encapsulation tool may dispense encapsulation material in the grooves to encapsulate the solder connections. After the electrical component is electrically connected to the conductive strands, the insertion tool may position and release the electrical component in the gap. A component retention tool may temporarily be used to retain the electrical component in the gap as interlacing operations continue.

Abstract: Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.

Abstract: Disclosed is a method of forming a composite door. A precursor frame sheet, comprising flaps, is formed by cutting a prepreg sheet. The precursor frame sheet is draped over a door-forming tool, comprising a frame face and flap supports, non-parallel to the frame face, such that each of the flaps of the precursor frame sheet is geometrically complementary with a corresponding one of the flap supports. A composite frame is formed by curing the precursor frame sheet, draped over the door-forming tool, wherein the composite frame comprises a first rail and a second rail. The composite frame is separated from the door-forming tool. The composite frame, first composite edge fittings, second composite edge fittings, a first composite side beam, a second composite side beam, and a composite skin are interconnected.

Abstract: Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks includes: an inner outer roller channel; and an outer inner roller channel positioned above the inner outer roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes rollers configured to move within inboard inner roller channels of the plurality of outer tracks; and a plurality of fixed rollers mounted to one or more longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within the outer roller channels of the plurality of outer tracks.

Abstract: A composite door comprises a composite frame, which comprises a first rail, a second rail, and crossbeams, joining the first rail and the second rail. The composite door also comprises a first composite side beam, a second composite side beam, and a composite skin, connected to each of the crossbeams of the composite frame, to the first composite side beam, and to the second composite side beam. The composite door further comprises first composite edge fittings, each connected to a corresponding one of the crossbeams of the composite frame, to the first composite side beam, and to the composite skin, and second composite edge fittings, each connected to a corresponding one of the crossbeams of the composite frame, to the second composite side beam, and to the composite skin.

Abstract: Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks includes: an inner outer roller channel; and an outer inner roller channel positioned above the inner outer roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes rollers configured to move within inboard inner roller channels of the plurality of outer tracks; and a plurality of fixed rollers mounted to one or more longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within the outer roller channels of the plurality of outer tracks.

Abstract: Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.

Abstract: A skin panel configured for attachment to an aircraft structure is constructed of a composite material and has a continuous, smooth outer surface; a continuous, smooth inner surface that is configured for attachment to an aircraft structure; a peripheral edge that extends entirely around the skin panel and has a continuous, smooth surface and a plurality of cavities inside the material of the skin panel. The cavities reduce the weight of the skin panel without significantly detracting from the compression strength and tensile strength of the skin panel.

Abstract: A rotary electric machine arranged as a brushless electric ring motor is described and includes a rotor that is disposed within a stator and arranged to rotate on a guide element. The rotor has a plurality of ferritic elements arranged on an outer surface, and the stator is an annular device having a plurality of electro-magnetic elements arranged on an inner portion between first and second flanges. The first and second flanges both include an annular ring that is fabricated from a non-magnetic material and has a plurality of ferromagnetic elements. The ferromagnetic elements are magnetically coupled to corresponding ones of the electro-magnetic elements to exert magnetic force on the ferritic elements of the rotor when the electro-magnetic elements are activated. The rotary electric machine may operate as a first thrust generating system that is upstream of a second thrust generating system for a turbojet engine.

Abstract: A composite door comprises a composite frame, which comprises a first rail, a second rail, and crossbeams, joining the first rail and the second rail. The composite door also comprises a first composite side beam, a second composite side beam, and a composite skin, connected to each of the crossbeams of the composite frame, to the first composite side beam, and to the second composite side beam. The composite door further comprises first composite edge fittings, each connected to a corresponding one of the crossbeams of the composite frame, to the first composite side beam, and to the composite skin, and second composite edge fittings, each connected to a corresponding one of the crossbeams of the composite frame, to the second composite side beam, and to the composite skin.

Abstract: An aircraft flap is constructed of nested layers of composite material in the aircraft flap that include an inner layer, a middle layer and an outer layer. The aircraft flap is constructed with the inner layer laid up around a central mandrel, the middle layer laid up around the middle layer and the outer layer laid up around the middle layer. The inner layer, the middle layer and the outer layer are co-cured on the mandrel, removed from the mandrel and then assembled together with the inner layer formed in a folded over configuration around a hollow interior volume of the aircraft flap, the middle layer formed in a folded over configuration over the inner layer, and the outer layer formed in a folded over configuration around the middle layer.

Abstract: An aircraft flap is constructed of nested layers of composite material in the aircraft flap that include an inner layer, a middle layer and an outer layer. The aircraft flap is constructed with the inner layer laid up around a central mandrel, the middle layer laid up around the middle layer and the outer layer laid up around the middle layer. The inner layer, the middle layer and the outer layer are co-cured on the mandrel, removed from the mandrel and then assembled together with the inner layer formed in a folded over configuration around a hollow interior volume of the aircraft flap, the middle layer formed in a folded over configuration over the inner layer, and the outer layer formed in a folded over configuration around the middle layer.

Abstract: Aircraft wings and aircraft including such aircraft wings are disclosed. An example apparatus includes an aircraft wing having a first panel; a second panel; ribs coupled between the first and second panels; and stiffeners coupled between the ribs in a spanwise direction and to the first panel, the coupling between the stiffeners and the first panel to deter axial loads from being received by the stiffeners, the stiffeners to increase a compressional stability of the first panel, wherein the coupling between the stiffeners and the first panel are indirect couplings formed via clips, the couplings formed via the clips deter the axial loads from being received by the stiffeners while increasing the compressional stability of the first panel.

Abstract: A structural assembly including a first member having an external side and an internal side, the first member defining a first member through-bore, a second member having an external side and an internal side, the second member defining a second member through-bore aligned with the first member through-bore, and a mechanical fastening system including a bushing at least partially received in the first member through-bore, the bushing defining a bushing through-bore and including a flange, wherein the flange is positioned in a gap between the internal side of the first member and the external side of the second member, a nut plate connected to the internal side of the second member, the nut plate defining a clearance bore aligned with the second member through-bore and the bushing through-bore, the nut plate including a nut, and a bolt extending through the bushing through-bore and into threaded engagement with the nut.

Abstract: A skin panel configured for attachment to an aircraft structure is constructed of a composite material and has a continuous, smooth outer surface; a continuous, smooth inner surface that is configured for attachment to an aircraft structure; a peripheral edge that extends entirely around the skin panel and has a continuous, smooth surface and a plurality of cavities inside the material of the skin panel. The cavities reduce the weight of the skin panel without significantly detracting from the compression strength and tensile strength of the skin panel.

Abstract: Systems, methods, and devices are configured to implement hydraulic actuators. Devices may include a housing having an internal surface defining an internal cavity that may have a substantially circular cross sectional curvature. The devices may include a rotor that includes a first slot having a substantially circular curvature. The devices may include a first vane disk partially disposed within the first slot of the rotor, where the first vane disk has a substantially circular external geometry. The first vane disk may be mechanically coupled to the rotor via the first slot, and the first vane disk may be configured to form a first seal with the internal surface of the housing. The devices may include a first separator device that may be configured to form a second seal with the internal surface of the housing and a third seal with an external surface of the rotor.

Abstract: Aircraft wings and aircraft including such aircraft wings are disclosed. An example apparatus includes an aircraft wing having a first panel; a second panel; ribs coupled between the first and second panels; and stiffeners coupled between the ribs in a spanwise direction and to the first panel, the coupling between the stiffeners and the first panel to deter axial loads from being received by the stiffeners, the stiffeners to increase a compressional stability of the first panel, wherein the coupling between the stiffeners and the first panel are indirect couplings formed via clips, the couplings formed via the clips deter the axial loads from being received by the stiffeners while increasing the compressional stability of the first panel.

Abstract: A structural assembly including a first member having an external side and an internal side, the first member defining a first member through-bore, a second member having an external side and an internal side, the second member defining a second member through-bore aligned with the first member through-bore, and a mechanical fastening system including a bushing at least partially received in the first member through-bore, the bushing defining a bushing through-bore and including a flange, wherein the flange is positioned in a gap between the internal side of the first member and the external side of the second member, a nut plate connected to the internal side of the second member, the nut plate defining a clearance bore aligned with the second member through-bore and the bushing through-bore, the nut plate including a nut, and a bolt extending through the bushing through-bore and into threaded engagement with the nut.