Abstract: A controller area network (CAN) distribution system for an aircraft includes flight control computers (FCCS) for operation of the aircraft; a first bus bundle is in communication with the FCCs, and directs communication from the FCCs to a left front rotor assembly and a right rear rotor assembly; a second bus bundle in communication with the FCCs, the second bus bundle directs communication from the FCCs to a right front rotor assembly and a left rear rotor assembly; and a third bus bundle in communication with the FCCs, the third bus bundle directs communication from the FCCs to a left wing tip rotor assembly and a right wing tip rotor assembly; the first bus bundle, the second bus bundle, and the third bus bundle are to balance bandwidth, optimize total bus length and width, and provide adequate control after a failure of any two busses.

Abstract: A flight control system for a tiltrotor aircraft includes a plurality of propulsion systems each independently tiltable between a vertical position and a horizontal position by aircraft effectors. A flight control computer controls the tiltrotor aircraft effectors in response to inputs from inceptors. The flight control computer comprises one or more processors and a memory storing instructions for controlling aircraft effectors. The instructions cause the flight control computer to receive inputs from a first inceptor and a second inceptor, and apply flight control laws to map the inputs to command longitudinal and vertical movement of the tiltrotor aircraft. The first inceptor inputs command longitudinal speed and acceleration in both hover and cruise flight modes, while the second inceptor inputs command climb and descent rates in both hover and cruise flight modes.

Abstract: A power distribution system includes a first battery and first power distribution unit providing power to a first rotor assembly and a fourth rotor assembly, the first and fourth rotor assemblies are outer front rotor assemblies; a second battery and second power distribution unit providing power to a second rotor assembly, the second rotor assembly is an inboard front rotor assembly; a third battery and third power distribution unit providing power to a third rotor assembly, the third rotor assembly is another inboard front rotor assembly; and a fourth battery and fourth power distribution unit providing power to the first rotor assembly and the fourth rotor assembly; the first, second, third, and fourth power distribution units are implemented with consideration of possible failure modes of one or more of the first, second, third, and fourth batteries.

Abstract: A system including a headset including a left ear assembly, a right ear assembly, a headband connecting the left ear assembly and the right ear assembly, and a switch configured to toggle the headset between a first mode for receiving radio frequency (RF) broadcast signals and a second mode for receiving Bluetooth signals. Other embodiments are described.

Abstract: A controller area network (CAN) distribution system for an aircraft includes flight control computers (FCCS) for operation of the aircraft; a first bus bundle is in communication with the FCCs, and directs communication from the FCCs to a left front rotor assembly and a right rear rotor assembly; a second bus bundle in communication with the FCCs, the second bus bundle directs communication from the FCCs to a right front rotor assembly and a left rear rotor assembly; and a third bus bundle in communication with the FCCs, the third bus bundle directs communication from the FCCs to a left wing tip rotor assembly and a right wing tip rotor assembly; the first bus bundle, the second bus bundle, and the third bus bundle are to balance bandwidth, optimize total bus length and width, and provide adequate control after a failure of any two busses.

Abstract: A method for making an alloy of aluminum and silicon with rare earth metals and metals of Groups 4b, 5b and 6b of the Periodic Table in which the flux system CaF.sub.2 -CaO-Al.sub.2 O.sub.3 is used as a solvent to provide a reactive medium for the reactions through which alloys are formed, the method comprising reducing the oxides of the alloying metals with aluminum in the presence of silicon in the flux maintained liquid at a temperature between about 1250.degree. C - 1600.degree. C while maintaining the flux basic to suppress the activity of Al.sub.2 O.sub.3 and forming the alloys in the flux from the reduced metals.