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 allowing for the connection of boom-mounted stabilizers on an inverted V-tail aircraft where hinge connections are provided between the bottom of each stabilizer and each boom, and an additional hinge connection is provided at the tops of each of the stabilizers at the apex where the two are connected. The movability of the stabilizers together to be joined at the apex avoids costs in engineering and manufacture.

Abstract: A wing conversion system is configured to rotate an engine of a vertical takeoff and landing aircraft relative to a wing section between flight modes. The wing conversion system includes a spindle, a conversion actuator, a drive ring, and a holding element. The spindle is rotatably supported for rotation with the engine and relative to the wing section about a spindle axis. The drive ring is drivingly engaged between the spindle and the output shaft, with the output shaft and spindle being rotatable with each other about the spindle axis. The holding element engages the drive ring and urges the drive ring into engagement with the output shaft and spindle.

Abstract: A landing gear system for an aerial device includes a mounting structure and a main landing gear. The mounting structure is configured to be attached relative to a fuselage of the aerial device. The main landing gear includes a pair of aft swept struts and wheels mounted on each of the aft swept struts. The pair of aft swept struts is attached relative to the mounting structure and extends downwardly and rearwardly relative thereto.

Abstract: An electromechanical blade pitch control system includes a propeller hub, a blade having an adjustable pitch angle, and a blade bearing hub operably coupled to the blade. The system includes a linear actuator operably coupled to the blade bearing hub and a rotary actuator operably coupled to the linear actuator via a planetary gear system. The system is configured such that the blade bearing hub, linear actuator, and rotary actuator are housed within the propeller hub, and further configured such that actuation of the linear actuator results in a change in a pitch angle of the blade.

Abstract: An electromechanical pitch control system for modifying a collective blade pitch of a multi-blade propeller includes a pitch control rod mechanically coupled via a distal end to a plurality of blades of a propeller, a bearing assembly operatively connected to a proximal end of the pitch control rod, and an electric actuator operatively connected to the bearing assembly. The bearing assembly allows the electric actuator to remain stationary while the pitch control rod rotates with the propeller. The electric actuator is configured to translate the pitch control rod in a longitudinal direction for adjusting an incidence angle of the blades.

Abstract: Embodiments are directed to systems and methods for controlling a tiltrotor aircraft using a flight control system. A flight control computer is configured to control aircraft effectors in response to inputs from inceptors. The flight control computer stores instructions for controlling aircraft effectors. The instructions cause the flight control computer to perform the steps of converting a signal representing longitudinal motion of a first inceptor into a fore-and-aft translational rate command for the tiltrotor aircraft; converting a signal representing lateral motion of the first inceptor into a side-to-side translational rate command for the tiltrotor aircraft; converting a signal representing longitudinal motion of a second inceptor into a height rate command for the tiltrotor aircraft; and converting a signal representing lateral motion of the second inceptor to a yaw rate command for the tiltrotor aircraft.