Abstract: A method of arbitrating communications between unmanned aerial system (UAS) devices includes: receiving, at a first communication component of a first UAS device, information for transmission to a destination associated with a second UAS device; inserting, by a first arbiter executing on the first communication component, a message sequence indication into a payload of a data packet that contains the information; transmitting, by the first arbiter, a respective copy of the data packet over each of a plurality of communication links established between the first and second UAS devices; receiving, at a second communication component of the second UAS device, one or more copies of the data packet; and determining in accordance with the message sequence indication, by a second arbiter executing on the second communication component, for each received copy of the data packet, whether to deliver the information to the destination.

Abstract: A rotor-blade weight-carrier system includes a weight carrier positioned within a rotor blade and a plurality of weights positioned within the weight carrier.

Abstract: A rotorcraft propulsion system includes a mast coupled to a rotor assembly, a gear coupled to the mast, the gear during use producing an axial reaction force, a flexure shaft extending from the gear, where the flexure shaft does not rotate with the gear and the flexure shaft flexes in response to radial loads from the gear, and a load cell on the flexure shaft to measure the axial reaction force.

Abstract: An aircraft-transport skid system includes a first outer frame rail, a second outer frame rail, a first lower inner frame rail, a second lower inner frame rail, and a plurality of lateral support rails connecting the first outer frame rail, the second outer frame rail, the first lower inner frame rail, and the second lower inner frame rail.

Abstract: An aircraft landing gear shimmy damping device for aircraft landing gear with castering may include a centering cam engaged in a curvic slot in an internal diameter of an aircraft landing gear wheel spindle when the landing gear wheel is aligned with forward ground travel of the aircraft, engaging a landing gear wheel shimmy dampener. The centering cam may be pushed out of the curvic slot when the aircraft begins to turn, disengaging the landing gear wheel shimmy dampener, and may slide back into the curvic slot and (re)engage the shimmy dampener, when the landing gear wheel is realigned with forward ground travel of the aircraft.

Abstract: A hybrid power system for a vertical takeoff and landing (“VTOL”) aircraft including a first power source operable to provide a power output for at least a forward flight mode; and a second power source configured to provide a high specific power output for an altitude adjustment flight mode, the second power source including an auxiliary gas generator coupled to a turbine and a drive system. In other aspects, there is provided a VTOL aircraft and methods for providing power to a VTOL aircraft.

Abstract: In accordance with one embodiment of the present disclosure, a method for manufacturing a honeycomb core sandwich panel includes placing a thermoset facesheet in contact with a thermoplastic honeycomb core without using a separate adhesive and attaching the thermoset facesheet to the thermoplastic honeycomb core by using a curing profile comprising a temperature that is lower than a gel point temperature of the thermoset facesheet and higher than a softening point temperature of the thermoplastic honeycomb core.

Abstract: A fuel tank includes an outer wall and a compliant layer disposed within a space at least partially defined by the outer wall. An aircraft includes a fuel cell and a fuel tank having an outer wall and a compliant layer disposed within a space at least partially defined by the outer wall. A method of operating a fuel tank includes providing an external wall and disposing a compliant layer of material within a space of the fuel tank that is at least partially defined by the external wall.

Abstract: A method of producing an article of manufacture includes printing a break-wire conductive-material pattern via an additive-manufacturing process and applying the break-wire conductive-material pattern to a surface of a component. A shape of the break-wire conductive-material pattern fits the surface of the component.

Abstract: A bearing raceway for a shaft includes a tubular sleeve comprising a raceway section and a clamp section, the raceway section having a hardened outer surface and a first, axially linear, inner surface, and the clamp section having first threads and a second, axially non-linear, inner surface, where the first threads are configured to mate with second threads on a nut to clamp the tubular sleeve to the shaft.

Abstract: An apparatus for introducing a test load to a rotor blade test specimen for fatigue testing includes a body extending along a longitudinal axis in a first direction from a first end to a second end, and the body having an internal cavity with an opening at the second end configured to dispose a tip portion of the rotor blade test specimen.

Abstract: A system includes a chip detector that includes a magnet, the chip detector operable to collect a plurality of chips in a lubricant flow. The system also includes a radiation sensor associated with the magnet and operable to detect radiation emitted by at least some of the plurality of chips collected by the magnet.

Abstract: A vehicle includes a first rotor system having a rotor blade having an axis of rotation, a rotatable inboard drive component, and a rotatable outboard drive component. The first rotor system further includes a flexible closed loop component associated with each of the inboard drive component and the outboard drive component. Movement of the closed loop component can selectively cause at least one of rotation of the rotor blade about the axis of rotation and movement of the axis of rotation.

Abstract: A battery system is described with methods and systems for thermally isolating a battery module experiencing thermal runaway. In one embodiment, a thermal actuator can cut a busbar coupling neighboring battery modules together, thereby preventing or slowing the spread of thermal runaway. In other embodiments, a fusible material can joint portions of a busbar. High temperatures can cause the fusible material to melt off of the busbar portions and thereby break the thermal or electrical conductivity between busbar portions and neighboring modules.

Abstract: A laminated elastomeric journal bearing has an outer sleeve having an inner surface, at least a portion of each end of the inner surface being a concave surface of revolution, and an inner sleeve having an outer surface, at least a portion of each end of the outer surface being a convex surface of revolution. Alternating layers of elastomer and metal are located between the sleeves, with adjacent surfaces of the layers and the sleeves being adhered to each other.

Abstract: A folding step system includes a housing forming an interior space and a step comprising a step surface. The step is movable between a stowed configuration in which substantially all of the step surface is disposed within the interior space and a deployed configuration in which at least a portion of the step surface is disposed outside of the interior space and at least a portion of the step surface is disposed within the interior space.

Abstract: An aircraft includes a fuselage having a former therein and a work platform system. The work platform system includes a platform that is moveable between a stowed configuration and a deployed configuration. The work platform system also has a hinge pin received by the platform. A platform stop is carried by the former and configured to inhibit rotation of the platform about the hinge pin when the platform is in the deployed configuration. The hinge pin is carried by the former.

Abstract: Systems and methods are described for applying a self-heating structural adhesive to components of aircraft or other structures. A conductive scrim can be placed in between layers of adhesive for use in joining two components together. Leads can be provided to apply an electrical current to the scrim, which can raise the temperature of the system and cure the adhesives, creating a strong bond with a conductive layer there between.

Abstract: A rotor-hub-flap anisotropic-sensor system includes a rotor hub, a plurality of anisotropic-sensor arrangements interoperably coupled to the rotor hub and operable to measure flapping of the rotor hub, a plurality of rotor blades connected to the rotor hub, and at least one flight control computer interoperably coupled to the plurality of anisotropic-sensor arrangements.

Abstract: A system includes a driver monitor system configured to receive information about driver operation, a relationship table comprising information about an expected relationship between driver operation and a preload force, and a driver controller configured to control a driver in response to the information about driver operation and according to the relationship table. A method of managing a preload force includes providing a first component, providing a second component for compression against the first component, operating a driver to move the first component into contact with the second component, monitoring an operation of the driver, and determining an expected preload force in response to the operation of the driver.