Abstract: An apparatus for securing first and second skins to a core in a composite rotor blade includes an elongated member configured to be installed through a passage in the core of the composite rotor blade. The elongated member has a first end configured to be attached to an outer surface of the first skin and a second end configured to be attached to an outer surface of the second skin. The apparatus also includes a first patch configured to adhere the first end to the outer surface of the first skin, and a second patch configured to adhere the second end to the outer surface of the second skin such the elongated member extends from the outer surfaces of the first and second skins through the passage in the core.

Abstract: According to an aspect, a pivoting sail fairing system includes a rotatable fairing, for rotation about a first axis of rotation of an aircraft, that includes a housing that defines a compartment arranged inward from the housing, the housing including a first orifice on a first surface and a second orifice on a second surface of the housing, and a first actuator mounted on a surface of the compartment inward from the housing.

Abstract: An adjustable control link for transferring rotor shaft rotation to a rotating swashplate, the adjustable control link includes an elongate element rotatable with the rotor shaft, the elongate element having a first end. A structure has an opening and a second end. At least one cam component is disposed within the opening and is rotatable relative to the structure about a central axis of the opening. A pin is configured to couple the elongate element to the at least one cam component. The pin is eccentrically rotatable about the central axis to move the first end of the elongate element relative to the second end of the structure.

Abstract: An apparatus comprising a stack of printed circuit board (PCB) layers having a primary longitudinal structure forming a radio frequency (RE) via including a principal tuning section (223) and a constant longitudinal structure (227) along a conductive column support (255) journaled through the layers in the via. The principal section (221) comprising a first tuning sub-assembly (229 A) in a first portion of the RE via above the longitudinal structure (227) and at an entrance of the primary longitudinal structure (221) and comprising a first set of pad, anti-pad pairs (445, 545, 645) tuned to receive an RE band. A second principal tuning sub-assembly (229B) in a second portion of the via below the longitudinal structure (227) and at an exit of the primary longitudinal structure and comprising a second set of pad, anti-pad pairs (445, 545, 645) tuned to receive the band and mirroring the first set of pairs.

Abstract: In an embodiment, a system includes a three-dimensional (3D) printer, a neutral feedstock, a p-doped feedstock, an n-doped feedstock, and a laser. The 3D printer includes a platen and an enclosure. The platen includes an inert metal. The enclosure includes an inert atmosphere. The neutral feedstock is configured to be deposited onto the platen. The neutral feedstock includes a halogenated solution and a nanoparticle having a negative electron affinity. The p-doped feedstock is configured to be deposited onto the platen. The p-doped feedstock includes a boronated compound introduced to the neutral feedstock. The n-doped feedstock is configured to be deposited onto the platen. The n-doped feedstock includes a phosphorous compound introduced to the neutral feedstock. The laser is configured to induce the nanoparticle to emit solvated electrons into the halogenated solution to form, by reduction, layers of a ceramic comprising a neutral layer, a p-doped layer, and an n-doped layer.

Abstract: An aircraft and a control yoke for operating the aircraft. The control yoke includes a base, a handle for manual operation of the aircraft, and a graphical communication device centered at the base for receiving a command from an operator and autonomously operating the aircraft according to the received command.

Abstract: A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.

Abstract: Systems and methods for mission-based path modifications are presented herein. One or more processors may be coupled with memory and housed in a vehicle. The one or more processors may receive data indicative of an issue with at least one function of the vehicle during a mission defined by a type of cargo and a flight path comprising a plurality of segments. The one or more processors may determine, responsive to the issue with the at least one function, an action to perform for the vehicle based on the issue, a current segment of the plurality of segments, and the mission. The one or more processors may execute, during the current segment or a subsequent segment of the plurality of segments, the action on the vehicle.

Abstract: A distributed power amplifier includes radio frequency (RF) input and output terminals. A first field effect transistor (FET) is coupled at a first gate terminal to the RF input terminal and at a first drain terminal to the RF output terminal. The first FET has a first periphery and a first source terminal electrically connected to ground potential. A second FET has a second periphery smaller than the first periphery. The second FET has a second gate terminal electrically coupled to the first gate terminal through a first inductor, a second drain terminal electrically coupled to the first drain terminal through a second inductor, and a second source terminal electrically connected to the ground potential. A drain voltage terminal, which excludes a resistive element, is electrically coupled to a drain bias network through which a drain bias voltage is applied to the first drain terminal and the second drain terminal.

Abstract: An apparatus includes an aperture layer coupled to a polarizer layer. The aperture layer includes an antenna and a filter. A circuit layer is mechanically and thermally coupled to the aperture layer. The antenna includes a square horn antenna made of a polymer material. The filter includes a waveguide filter having a first and a second piece separately molded. The waveguide filter includes a folded-back waveguide coupled to the horn antenna at one end and to the circuit layer at another end.

Abstract: Provided herein are various leptonic power sources, leptonic control systems, and leptonic-powered engines. An apparatus includes a leptonic source configured to emit beam electrons to ionize a material into a plasma according to a selectable ionization degree and deposit charge onto a plurality of cathodes in a progressively more negatively charged arrangement to establish an electric field of a selectable intensity in the plasma.

Abstract: A monolithic attitude control motor frame includes a monolithic structure including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. Adjacent cavities of the plurality of cavities share a side wall or side wall portion therebetween. Each of the cavities is configured to receive an attitude control motor. A monolithic attitude control motor system includes a monolithic frame including an outer surface of revolution and a plurality of side walls defining a plurality of cavities extending radially from the outer surface of revolution. The system further includes a plurality of attitude control motors corresponding to the plurality of cavities, such that an attitude control motor of the plurality of attitude control motors is disposed in each cavity of the plurality of cavities.

Abstract: A structural member for use in a rotor system which rotates about a rotational axis includes a pin which extends substantially perpendicular to the rotational axis, a filler component positioned adjacent the pin, and a plurality of layers of composite material having fibers oriented lengthwise along a central axis which is perpendicular to the rotational axis. The plurality of fibers in the layers of composite material is wrapped about the pin and the filler component such that the fibers extend along the central axis and the plurality of layers form an opening filled by the filler component and which decreases as a function of distance from the pin along the central axis.

Abstract: A flight control system for a rotary-wing aircraft includes a shape sensor and a controller. The shape sensor is configured to measure a shape of a rotor blade during movement of the rotor blade. The controller is communicably coupled to the shape sensor and is configured to (i) receive, from the shape sensor, a first signal indicative of a first blade shape; (ii) receive a blade characteristic regarding the rotor blade; and (iii) determine at least one of a moment or force associated with the rotor blade based on the first signal and the blade characteristic.

Abstract: A heat exchange device comprising phase change material-impregnated heat conductive foam disposed between fluid stream channels in a heat exchanger element.

Abstract: Disclosed are optical systems that vary the refractive index of at least one relatively angled transmissive surface to reduce reflections. Embodiments include at least one optical component with relatively angled surface portions that are transmissive to electromagnetic radiation (EMR). In certain embodiments, an electrically conductive layer reflective to EMR and an anti-reflective coating are proximate the optical component. The anti-reflective coating includes a gradient-index (GRIN) layer with an index of refraction that varies across a length to increase propagation of EMR at a predetermined angle of incidence to prevent reflection of the EMR between the angled transmissive surfaces.

Abstract: A system comprising a scanner to scan the airman or soldier (subject), a processor to receive, from the scanner, a non-manifold three-dimensional (3D) digital surface model (DSM) scan data representative of the subject, and a computer-aided manufacturing (CAM) device. The processor recognizes anatomical features on the 3D surface model including the cephalic (head) region of the scanned subject; stores each sub region defined by anatomical features as a non-manifold 3D surface model; creates a surface offset from the DSM sub region; creates a closed volume within and between the DSM sub region and the offset surface representative of a solid 3D pilot flight equipment; and causes a computer-aided manufacturing (CAM) device to manufacture the solid 3D pilot flight equipment.

Abstract: A rotatable swashplate is rotatable relative to a stationary swashplate around a shaft and connects to a pitch control rod assembly. The rotatable swashplate includes an upper portion and a lower portion. The upper portion is extendable outside of a stationary swashplate and includes a plurality of lugs each configured to attach to a pitch control rod assembly, an innermost wall configured to receive a shaft, and a membrane. The lower portion is positionable within the stationary swashplate and has an outermost wall and at least one extension extending radially between the outermost wall and the innermost wall. The membrane extends radially over the at least one extension.

Abstract: A rotating steering mirror assembly comprising a first wedge rotatable relative to a base and a second wedge rotatable relative to the first wedge to controllably tilt a mirror on an outward- or forward-facing surface of the second wedge. Respective motors can independently rotate the first and second wedges.