Bell Textron Inc.

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.

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.

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. The first outer frame rail, the second outer frame rail, the first lower inner frame rail, and the second lower inner frame rail are parallel to one another;

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.

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.

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.

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.

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.

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.

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.