Abstract: A landing gear assembly for rotorcraft includes a shock absorber, a ground support assembly and an airframe linkage assembly. The shock absorber includes a force sensor to detect a pressure of an incompressible fluid within the shock absorber and a temperature sensor to detect a temperature of the fluid. The ground support assembly is linked to the shock absorber and includes an axle and a ground contact element movable in relation to the axle. The linkage assembly is linked to the shock absorber and/or the ground support assembly and includes a position sensor to detect movement of the axle between compressed and uncompressed conditions of the shock absorber. Various rotorcraft include one, two, three or more landing gear assemblies and an attitude control system. Various rotorcraft methods process sensor signals from one, two, three or more landing gear assemblies at the attitude control system to provide various rotorcraft functions.

Abstract: A pilot seat assembly includes a track, a support base, a seat pan, and a seat. The track is mounted on a floor of a vehicle and defines a travel path from a forward end of the track to an aft end of the track. The support base is coupled to the track and is selectively moveable along the travel path. The seat pan is mounted to the support base and is selectively movable in an outboard direction and an inboard direction relative to the support base. The seat is mounted on the seat pan such that the seat pan is between the seat and the support base. A seat back section of the seat is selectively reclinable relative to a seat bottom section of the seat to transition the pilot seat assembly between a control position and a rest position.

Abstract: A distributed adaptive coding and modulation network includes multiple network hubs that move relative to Earth, communicate among each other using intra-hub links, communicate with endpoint devices via wireless links, and elect one network hub to operate as a leader hub. A remainder of the network hubs operate as follower hubs. The leader hub is operational to negotiate a current modulation and coding scheme with the follower hubs based on a session management protocol, communicate with a first endpoint device, relay data between the endpoint devices using the current modulation and coding scheme, and dynamically renegotiate the current modulation and coding scheme in response to a change in link conditions based on the session management protocol. An edge follower hub is operational to communicate with a second endpoint device, and relay the data between the endpoint devices through the inter-hub links using the current modulation and coding scheme.

Abstract: Certain aspects of the present disclosure provide techniques for a method, including: receiving multi-dimensional event data associated with a vehicle event; determining, based on the multi-dimensional event data, an inspection classification for the vehicle event; receiving multi-dimensional analysis data associated with the inspection classification for the vehicle event; determining, based on the multi-dimensional analysis data, a repair classification for the vehicle event; receiving multi-dimensional action data associated with the repair classification for the vehicle event; and determining, based on the multi-dimensional action data, a monitoring classification for the vehicle event.

Abstract: An amplifier with stacked transconducting cells in “current mode combining” is disclosed herein. In one or more embodiments, a method for operation of a high-voltage signal amplifier comprises inputting, into each transconducting cell of a plurality of transconducting cells, a direct current (DC) supply current (Idc), an alternating current (AC) radio frequency (RF) input current (IRF_IN), and an RF input signal (RFIN). The method further comprises outputting, by each of the transconducting cells of the plurality of transconducting cells, the DC supply current (Idc) and an AC RF output current (IRF_OUT). In one or more embodiments, the transconducting cells are connected together in cascode for the DC supply current, and are connected together in cascade for the AC RF input and output currents.

Abstract: Described is a method for extraction of a region of interest (ROI) from a composite synthetic aperture radar (SAR) phase history data. The method comprising receiving, with a system comprising a processor, the composite SAR phase history data of a plurality of backscattered return signals produced by a SAR system illuminating a scene with a SAR beam. The method also comprises obtaining a location of a first ROI within the scene and extracting from the composite SAR phase history data a first component SAR phase history data corresponding to the ROI at the location of the ROI.

Abstract: Sound-attenuating heat exchangers and methods of exchanging heat and attenuating sound within sound-attenuating heat exchangers. The sound-attenuating heat exchangers include a base region, which defines a first base side and a second base side, and a plurality of elongate fluid conduits, which are at least partially defined by the base region and configured to contain a cooled fluid stream. The sound-attenuating heat exchangers also include a plurality of heat transfer-enhancing structures, which extend from the first base side and are configured to exchange thermal energy with a cooling fluid stream, and a sound-attenuating region, which extends from the second base side. The sound-attenuating region includes a plurality of resonator cells configured to attenuate sound and a plurality of resonator cell openings. Each resonator cell opening opens from a corresponding resonator cell toward the plurality of heat transfer-enhancing structures.

Abstract: Systems and methods are provided for inspecting aircraft fuselages. Non-Destructive Inspection (NDI) stations inspect sections of a fuselage via pulsed-line assembly techniques. After each pulse, a section of fuselage is moved by less than its length, and one or more NDI stations disposed at different portions of the section to inspect the section of fuselage for out-of-tolerance conditions. A method for inspecting a structure for inconsistencies which includes advancing a structure along a track in a process direction through a Non-Destructive Inspection (NDI) station, indexing the structure to the NDI station and inspecting the structure with the NDI station.

Abstract: A method of fabricating of an object includes causing a first heat source to heat a feed material to form a melt pool of the feed material on a surface. The method further includes causing a second heat source to heat the melt pool on the surface to regulate grain formation of the feed material in the melt pool as the melt pool cools and solidifies on the surface to form at least a portion of the object. The method also includes causing the first heat source and the second heat source to move relative to the surface as the melt pool is formed and cooled.

Abstract: A headrest ventilation assembly is configured to secure to a headrest of a seat assembly, and includes an air conduit including one or more air inlets and one or more air outlets, and an air filter disposed within the air conduit between the one or more air inlets and the one or more air outlets. The air filter is configured to remove contaminants from the air that is drawn into the air conduit before being delivered out of the one or more air outlets. The assembly can also include a fan disposed on or within the air conduit. The fan is configured to draw the air into the one or more air inlets and provide airflow to deliver the air out of the one or more air outlets. The assembly can also include one or more ultraviolet (UV) light emitters disposed on or within the air conduit. The UV light emitter(s) are configured to emit UV light into the air to sanitize the air before the air is delivered out of the one or more air outlets.

Abstract: A hinge assembly for connecting a door to a fuselage of an aircraft includes a hinge arm having a fuselage fitting pivotably coupled to a fuselage rotatable interface and a door fitting pivotably coupled to a door rotatable interface. The hinge assembly includes a programmable gear assembly coupled to the hinge arm allowing the hinge arm to pivot around the fuselage fitting when the door is moved from a door closed position to a door open position and causing the door to maintain in a generally parallel orientation relative to the fuselage between the door closed position to the door open position. The programmable gear assembly includes a fuselage gear coupled to the fuselage fitting, a door gear coupled to the door fitting, and a rack operably coupled between the fuselage gear and the door gear.

Abstract: A manufacturing system includes a stator base, a plurality of movers, one or more end effectors, and a controller. The stator base has a planar stator surface covering an array of electrical coils configured to generate an electromagnetic field. The movers each contain multiple permanent magnets configured to cause the movers to levitate and move relative to the stator surface in response to the electromagnetic field. The end effectors are coupled to the movers, and each end effector perform one or more functions in relation to a material sheet. The controller activates the electrical coils in a manner causing independent, coordinated movement of the movers over the stator surface, and causing the end effectors to engage with and operate on the material sheet.

Abstract: Flaperon actuation systems for aircraft are disclosed herein. An example aircraft includes a wing including, a fixed wing portion, a flaperon, and an actuation system. The actuation system includes a first actuator coupled to the fixed wing portion. The first actuator is operable to move the flaperon along a first degree of freedom between a stowed position in which the flaperon is aligned with the fixed wing portion and a deployed position in which the flaperon is moved downward relative to the fixed wing portion. The actuation system also includes a linkage assembly coupled between the fixed wing portion and the flaperon. The linkage assembly includes a second actuator operable to move the flaperon along a second degree of freedom to pitch the flaperon between an upward position and a downward position.

Abstract: Convertible monuments for aircraft cabins that house at least one lavatory can comprise moveable wall sections that can be reversibly deployed from a stowed configuration to a deployed configuration to form a temporary convertible monument having a monument footprint that overlaps at least a portion of an aircraft interior egress pathway during flight, and efficiently uses previously unused aircraft interior space during aircraft flight.

Abstract: A lift system for an aircraft includes a first galley cart, a second galley cart, a floor deck, and a frame. The frame defines a first storage zone, a second storage zone, and a third storage zone that are stacked. A bottom end of the first storage zone is aligned with the floor deck, a top end of the second storage zone is aligned with the floor deck, and a bottom end of the third storage zone is aligned with a top end of the first storage zone. The lift system also includes a first lift configured to move the first galley cart from the first storage zone to the second storage zone and a second lift configured to move the second galley cart from the first storage zone to the third storage zone.

Abstract: A thermal protection system is provided for a vehicle moving with velocity through a free stream of air. The system comprises a substrate layer having coolant feed holes through which coolant can pass, and an insulation layer bonded to the substrate layer and covering the coolant feed holes of the substrate layer. The system also comprises a honeycomb layer including (i) a first major surface bonded to the insulation layer, (ii) a second major surface opposite the first major surface and exposed to the free stream of air, and (iii) a cell structure that shifts a thermal boundary interface from between the insulation layer and the first major surface of the honeycomb layer to the second major surface of the honeycomb layer. Surface cooling of the insulation layer and the substrate layer is provided by coolant passing through the coolant feed holes of the substrate layer into the insulation layer as the vehicle moves with velocity through the free stream of air.

Abstract: A tiltrotor includes a plurality of blades that are circumferentially offset from one another. The tiltrotor also includes a pitch mechanism configured to cause the blades to pitch from a first blade pitch to a second blade pitch. The pitch mechanism includes a pitch actuator configured to move from a first pitch actuator position to a second pitch actuator position. The pitch mechanism also includes a link coupled to the pitch actuator. The link is configured to transfer movement from the pitch actuator to the blades to thereby cause the blades to actuate from the first blade pitch to the second blade pitch in response to the pitch actuator moving from the first pitch actuator position to the second pitch actuator position. The link includes a first link portion, a second link portion, and a joint therebetween.

Abstract: A friction stir welding (FSW) tool includes a pin configured to extend through a joint line between edges of two work pieces and to rotate to perform a FSW process that welds the two work pieces together at the joint line. A housing is coupled to a distal end of the pin to enable rotation of the pin relative to the housing. The housing includes a main body having one or more cooling channels having one or more arcuate segments. One or more sliders are coupled to the main body of the housing.

Abstract: A system and a method include one or more sensors configured to detect one or more forces in relation to one or more components within an internal cabin of a vehicle. An imaging device is configured to acquire one or more images of the internal cabin of the vehicle. A control unit is in communication with the one or more sensors and the imaging device. The control unit is configured to determine one or more incidents within the internal cabin based on the one or more forces detected by the one or more sensors, and the one or more images acquired by the imaging device. The system and the method can also provide recommendations regarding actions to take in response determining incident(s).

Abstract: An aircraft comprising a weapons pod including an enclosure mounted to an outer mold line of the aircraft, and at least one missile rail launcher mounted entirely within and fixed to the enclosure.