Abstract: A system includes a mandrel having an exterior surface configured to receive composite material, a first end, and a second end opposite the first end, an end support coupled to the first end of the mandrel such that the mandrel is rotatable about an axis of rotation, and an intermediate support configured to support the mandrel between the first end and the second end such that at least a portion of the exterior surface is exposed while the mandrel is supported by the intermediate support, a vertical distance between the intermediate support and the axis of rotation defining a support distance, and the intermediate support being adjustable between a first position having a first support distance and a second position having a second support distance greater than the first support distance.

Abstract: A replacement tip section for a rotor blade, from which a legacy tip section was removed, includes a blade tip portion configured to be attached to an intermediate section of the rotor blade after removal of the legacy section. The intermediate section has a connection feature at an end of the intermediate section to which the blade tip portion is attachable. The replacement tip section includes a transition region configured to be attached to a forward end of the connection feature. The transition region is configured to form a leading edge of the rotor blade and extends from the blade tip portion to form an opening into which the intermediate section is attached. The transition region includes a first end having a first airfoil that conforms to the intermediate section airfoil at the connection feature, and a second end having a second airfoil that conforms to the blade tip portion.

Abstract: An electrical conductor assembly for a rotor blade includes a substrate and at least one electrical conductor. The substrate includes an inboard end portion and an outboard end portion. The at least one electrical conductor is attached to the substrate and extends between the inboard end portion and the outboard end portion. The at least one electrical conductor is configured to transmit electricity along a length of the rotor blade. The inboard end portion and the outboard end portion are structured such that when the electrical conductor assembly is installed within the rotor blade, the inboard end portion is securable relative to the rotor blade and the outboard end portion is movable relative to the rotor blade.

Abstract: A system including an apparatus for determining the presence of ice on an external surface of a structure is provided. The apparatus includes a sensor that includes first and second parallel ink or paint conductive traces separated by a gap. The apparatus also includes a circuit configured to measure the impedance or change in impedance between the first and second parallel ink or paint conductive traces.

Abstract: Systems and methods for power and data distribution on an aircraft. One embodiment provides an aircraft comprising a plurality of nodes, a power system controller, and an aircraft controller. Each node is connected to a plurality of LRUs, and each node includes a node controller. The power system controller is configured to control power distribution to each node. The aircraft controller is configured to transmit data to each node and to receive data from each node. The node controller includes an electronic processor and a memory. The node controller is configured to control power to the plurality of LRUs, receive first data from at least one LRU of the plurality of LRUs, and provide the first data to the aircraft controller. The node controller is further configured to receive second data from the aircraft controller and provide the second data to at least one LRU of the plurality of LRUs.

Abstract: Motion steering under kino dynamic constraints is provided. A system can receive an indication to return to a route generated for autonomous navigation by the aircraft to a destination. The system can generate a vector field formed of a plurality of vectors that merge into the route. The vector field can be generated responsive to the indication to return to the route. The system can provide instructions to steer the aircraft toward the destination along the route via one or more vectors of the plurality of vectors in the vector field. The instructions can be based on a cost function applied to the vector field.

Abstract: A multisegment array-fed reflector antenna includes a feed array consisting of a number of subarrays and a multisegment reflector to reflect multiple beams of the feed array into a number of elevation angles. A support structure couples the multisegment reflector to the feed array. The multisegment reflector includes two or more ring-focus parabolic segments, and each ring-focus parabolic segment is a parabolic surface extending along a circle around the support structure.

Abstract: Provided herein are various enhancements for additive manufacturing using titanium and titanium alloy materials. In one example, a method includes inoculating a titanium material with ceramic particles that produce nucleation sites within the titanium material during successive melt and solidification steps of an additive manufacturing process. The nucleation sites promote grain nucleation during solidification of molten titanium material into solid titanium material during the additive manufacturing process.

Abstract: A fastener removal assembly comprises a drive housing operable to receive a drive unit, wherein the drive housing comprises a shaft configured to rotate based on operation of the drive unit, the shaft extending downwards and out of the drive housing. The fastener removal assembly further comprises a set of gripping jaws disposed under the drive housing and around a portion of the shaft and a first pneumatic actuator coupled to the set of gripping jaws configured to actuate the set of gripping jaws to expand and retract. The fastener removal assembly further comprises at least one second pneumatic actuator disposed on top of the first pneumatic actuator. The fastener removal assembly further comprises an intermediate coupler, wherein the intermediate coupler is coupled to a side of the drive housing, and wherein the at least one second pneumatic actuator is coupled to a bottom side of the intermediate coupler.

Abstract: A rotor blade retention assembly includes a central hub, a rotor blade including an upper outer surface, a lower outer surface, a blade hole, and a proximal end coupled to the central hub, a strap member extending along a portion of the rotor blade such that a distal end receiving portion extends into the blade hole, and a retainer assembly disposed within the blade hole and coupled to the strap member. The retainer assembly includes an upper bushing and a lower bushing slidably disposed within the blade hole. The upper bushing includes a counterbored portion. The retainer assembly also includes an outboard blade pin disposed within the distal end receiving portion and includes a blade pin inner cavity.

Abstract: Printable high-strength alloys, including aluminum alloys can be produced in an additive manufacturing process. Such alloys can include aluminum-silver (“Al—Ag”) alloys that are produced by a laser melting process using a powder bed fusion. The results of the process and the characteristics of the produced alloy can be determined by controlling at least an energy beam power, an energy beam speed, and/or an energy beam size. The operational parameters can be controlled with high precision to produce a printable, high-strength aluminum alloy.

Abstract: A lens installation system that includes a tool for a keyhole in an imaging system housing. The tool includes a base having a first diameter dimensioned to fit below a lens housing cavity of an imaging system housing. The base has a top end forming a shoulder to seat the shoulder below the lens housing cavity. The tool includes a lens centering seat integrated with the base. The seat includes a ring and a recessed cavity within the ring. The ring is defined by an outer surface dimensioned to contact an inner diameter of an inner surface of the keyhole below the lens housing cavity, a first sloped surface providing a chamfered edge that is inclined for a distance above the outer surface, and a second sloped surface descending from an upper edge of the first sloped surface by a predetermined distance.

Abstract: Localized measurement of turbulent airflows is provided using enhanced techniques of digital holography with computed tomography. In an implementation, an optical beam is diffracted to produce an array of signal beams which propagate at different angles through a test volume that includes a test article. A reference beam is optically interfered with the array of signal beams after propagating through the test volume, producing a corresponding array of holograms simultaneously detected by a single digital holographic sensor. Digitized versions of the holograms are processed to produce a signal field for each test beam. Computed tomography is then applied to the signal fields to determine path-resolved turbulence measurements.

Abstract: According to some embodiments, a system includes a three-dimensional (3D) printer, a hydraulic press, and a kiln. The three-dimensional printer includes a print bed, a first printhead, and a second printhead. The first printhead is configured to deposit a layer of a first powder on the print bed. The second printhead is configured to deposit a layer of a second powder on the print bed. The hydraulic press is configured to compress a greenware to form a compressed greenware. The kiln is configured to heat the compressed greenware to a reaction temperature to form an object. The object is surrounded by an excess of the first powder. The kiln is also configured to heat the object surrounded by the excess of the first powder to a melting temperature. The melting temperature is at least the melting point of the first powder and less than the melting point of the object.

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: According to certain embodiments, a device comprises a body, a mechanical propulsion system affixed to the body to cause the body to traverse a multi-oriented surface and to prevent contact between the body and the multi-oriented surface, a thrust system to apply a thrust force to the device that opposes a gravitational force acting on the device, and a payload with at least one sensor to detect a characteristics of the multi-oriented surface.

Abstract: A method includes determining a target acoustic profile based on acoustic conditions at an exterior surface exposed to weather. The method further includes determining a plurality of foam layer characteristics based on the target acoustic profile. The method further includes determining one or more of elastomer characteristics based on the target acoustic profile and the plurality of foam layer characteristics. The method further includes providing a foam layer comprising the plurality of foam layer characteristics. The method further includes depositing an elastomer into the provided foam layer according to the one or more elastomer characteristics. The method further includes coupling the foam layer comprising the deposited elastomer onto the exterior surface exposed to weather. The foam layer including the deposited elastomer absorbs acoustic energy corresponding to the target acoustic profile.

Abstract: A rotor blade configured to be installed on a rotary wing aircraft includes a spar including an inboard portion extending from a root of the rotor blade to a first spanwise position of the rotor blade and an outboard portion meeting the inboard portion at the first spanwise position. The rotor blade further includes an upper skin and a lower skin coupled the outboard portion of the spar. The first spanwise position is defined by a most inboard point at which the upper and lower skins are coupled to the spar. The inboard portion includes a top layer, a bottom layer, and an inner cavity. The top layer has a substantially constant first thickness and the bottom layer has a substantially constant second thickness, and the distance between an outer surface of the top layer and an outer surface of the bottom layer is substantially constant.

Abstract: A gear box includes a housing, an actuator coupled to the housing, and a bearing assembly pivotably coupled to the actuator. The bearing assembly including an outer raceway, a cylindrical housing positioned within the outer raceway, and an annular bearing positioned between the outer raceway and the housing. The cylindrical housing has a first end and a second end opposite the first end. A sensor is coupled to the first end of the cylindrical housing and configured to monitor an operating condition of the annular bearing. A linkage couples the actuator to the second end of the cylindrical housing and an output shaft is rotatably coupled to the bearing assembly.

Abstract: A circuit assembly includes a sealable enclosure and at least one electronic circuit element contained within the sealable enclosure. The at least one electronic circuit element includes a control circuit, a garnet, and a first polymer material applied on a surface of the control circuit and on a surface of the garnet. A second polymer material fills a remaining space defined within the enclosure, the second polymer material applied on an exposed surface of the first material.