Abstract: Flexured sun gears for planetary gear systems. In embodiments, a sun gear includes a spline section configured to couple the sun gear to another component, a gear section configured to mesh with at least one other gear of the planetary gear system, and a flexure section configured to couple the spline section to the gear section. The flexure section of the sun gear may have a flexure wall and a flexure curve, and has a thickness (e.g., in at least a portion of the flexure section) that is smaller than a thickness of the spline section and/or the gear section. The flexure section may enable the gear section to displace or move radially with respect to the spline section in response to a rotational force. For example, the flexure section may not move axially (e.g., may not extend) but may bend and/or rotate in response to the rotational force.

Abstract: A rotor system for an aircraft includes a rotor assembly comprising a plurality of rotor blades connected to a rotor mast, wherein the rotor assembly is tiltable relative to a wing of the aircraft between a first position corresponding to an airplane mode of the aircraft and a second position corresponding to a helicopter mode of the aircraft; and a drive system for providing rotational energy to the rotor assembly via the rotor mast. The drive system includes at least one electric motor for generating rotational energy to a motor shaft; and a gearbox connected to receive rotational energy from the at least one electric motor via the motor shaft and to provide rotational energy to the rotor mast via a rotor shaft, wherein the at least one electric motor is fixed relative to the wing of the aircraft.

Abstract: A compound helicopter includes a fuselage including a fuselage airframe, a translational thrust system coupled to the fuselage airframe and a pylon assembly subject to vibration. The pylon assembly includes a transmission and a rotor system having a main rotor assembly. The compound helicopter also includes a main rotor vibration isolation system including a plurality of augmented liquid inertia vibration eliminator units each having an isolation frequency and each coupled between the fuselage airframe and the pylon assembly to reduce transmission of the pylon assembly vibration to the fuselage airframe at the isolation frequency. Each augmented liquid inertia vibration eliminator unit includes at least one active tuning element movable to tune the isolation frequency thereof.

Abstract: A vehicle comprises a propulsion assembly that includes a rotor system configured to swivel about a pivot axis and a flight control system in communication with the propulsion assembly. In one embodiment, the pivot axis is fixedly oriented at an angle relative to a lateral axis of the vehicle in a plane defined by a longitudinal axis of the vehicle. The flight control system is configured to activate a particular operational mode of the propulsion assembly, in which the rotor system is configured to swivel about the pivot axis to move a rotor axis of the rotor system from a first gimbal angle to a second gimbal angle. In various embodiments, the gimbal angle is configured to change a center of gravity, or direction of thrust vectors, or attitude of the vehicle. The operational mode may comprise a one engine inoperative (OEI) mode in an example embodiment.

Abstract: A landing gear for an aircraft includes a landing strut having proximal and distal ends with the proximal end couplable to the fuselage of the aircraft. The landing strut includes a gas chamber, a liquid chamber, a cylinder and a piston that is movable relative to the cylinder between extended and retracted positions. A wheel is coupled to the distal end of the landing strut. A force sensor is disposed between an extend stop surface of the piston and the chamber. Pressurized gas in the gas chamber biases the piston to the extended position such that the force sensor experiences a preload force. The force sensor is configured to detect a reduction in the preload force during a landing maneuver responsive to contact between the wheel and a landing surface.

Abstract: Techniques are directed to utilizing a liftgate assembly having a platform, a lift subsystem constructed and arranged to selectively raise and lower the platform, and a set of steel beams coupled with the lift subsystem. The set of steel beams is constructed and arranged to hardware mount to a set of aluminum beams of a vehicle. Although the sets of beams are made of different materials, the liftgate assembly and the vehicle body may be securely fastened to each other making the vehicle well suited for a variety of conditions.

Abstract: A system can include a flight controller for an aircraft that includes an electric motor that drives blades with a variable pitch, where the flight controller receives a command to change a flight characteristic of the aircraft and creates a torque command and a revolutions per minute (RPM) command. The system can also include a propulsion assembly, where the propulsion assembly creates a current command based at least in part on the torque command and the RPM command, creates a blade pitch command based at least in part on the torque command and the RPM command, communicates the current command to the electric motor to change a mechanical output of the electric motor, and communicates the blade pitch command to blade actuators to control the pitch of the blades. The current command and the blade pitch command cause the blades of the aircraft to rotate at a predetermined RPM.

Abstract: There is disclosed in one example a flight control computer for a rotary aircraft, including: a first interface to communicatively couple to a flight control input; a second interface to communicatively couple to flight geometry actuators; a data source; a multi-dimensional lookup table including a data structure to correlate flight control inputs to flight geometry actuator outputs according to a third-factor; and circuitry and logic instructions to: receive an input via the first interface; query the data source for the third-factor; query the multi-dimensional lookup table for a control input modifier according to the flight control input and the third-factor; and compute and send via a third interface a flight geometry output according to the control input modifier.

Abstract: A bearing restraint, for use on a rotorcraft with a rotor mast and bearing assembly. The bearing restraint interfacing with a mast groove along the rotor mast to longitudinally restrain the bearing assembly. The bearing restraint includes a pilot ring, groove collar, and retaining ring.

Abstract: One embodiment is a navigation system for an aircraft including a positioning system to generate information related to a position of the aircraft, a group of cameras mounted to a body of the aircraft, each camera of the group of cameras to simultaneously capture images of a portion of an environment that surrounds the aircraft, and a processing component coupled to the positioning system and the group of cameras, the processing component to determine a current position of the aircraft based on the information related to the position of the aircraft and the images.

Abstract: Various implementations directed to managing access for a manufacturing system are provided. In one implementation, a method may include receiving access management request data at an automated provisioning system of an entity. The method may also include determining ready task data based on the received access management request data. The method may further include transmitting provisioning request data based on the determined ready task data. The method may additionally include transmitting status request data after a predetermined amount of time. The method may also include receiving the external status data. The method may further include determining generic status data based on the received external status data. The method may additionally include performing access management operations based on the determined generic status data. The method may also include manufacturing physical components using the manufacturing system based on the access management operations.

Abstract: An aircraft is described with both VTOL (vertical takeoff and landing) capabilities and convention airplane capabilities. A preferred embodiment comprises a fuselage and fixed wing, with one boom on either side of the fuselage. Each boom comprises a tilt rotor on a fore end and a fixed rotor on the aft end. Both rotors can be directed vertically for VTOL capability. During cruise the tilt rotors can be directed forward for thrust and the fixed rotors can be stopped and directed along the boom axis, minimizing drag. The described embodiments have advantages in weight savings and maneuverability compared to other VTOL aircraft.

Abstract: A drive system for a rotorcraft includes first and second gearbox assemblies and a lubrication assembly. The lubrication assembly includes first and second lubrication systems and a valve connected between the first and second lubrication systems such that when the valve is in a first position, a test mode of operation of the lubrication assembly is enabled and when the valve is in a second position, a normal mode of operation of the lubrication assembly is enabled. The lubrication assembly also includes a valve control unit operable to instruct the valve to selectively move between the first position and the second position.

Abstract: Systems, methods and non-transitory computer readable storage media for airspace management within an airspace region at a node of a peer to peer network having a plurality of nodes and maintaining a blockchain containing a current deconflicted flight schedule for the airspace region. One method includes receiving requests for airspace reservations, each including flight plan data, from other nodes over the peer to peer network, compiling the flight plan data to identify conflicts between the requests and the current deconflicted flight schedule, validating the flight plan data of the requests that do not conflict with the current deconflicted flight schedule to generate validated airspace reservations, creating a block containing the validated airspace reservations and interlinking the block with the blockchain such that the blockchain contains a new deconflicted flight schedule for the airspace region for broadcast to the other nodes over the peer to peer network.

Abstract: A magnetorheological damper, wherein the damper comprises a housing that is at least partially filed with a magnetorheological fluid, and a magnetorheological valve disposed within the housing. The valve includes a magnetically permeable core having at least one coil reservoir formed therein, and at least one conductor coil, wherein each conductor coil is disposed around a portion of the core within a respective one of the coil reservoir(s). The valve additionally includes a fluid flow path adjacent the conductor coil(s). The fluid flow path is structured and operable to allow the magnetorheological fluid to flow adjacent the conductor coil(s). The valve further includes at least one coil cover, wherein each coil cover is disposed over a respective one of the coil(s) such that the respective coil is protected from exposure to magnetorheological fluid flowing through the fluid flow path.

Abstract: A spinner is described that can provide aerodynamic advantages for vertical takeoff and landing (VTOL) aircraft. The spinner can be shaped with multiple faces divided by chines. The chines can run down the edge of the spinner to fairings that can cover rotor blades and/or couplings between rotor blades and the rotor hubs of the aircraft. During forward flight the rotor blades can be folded down into recesses on the spinner. The spinner and fairings can provide aerodynamic advantages in addition to protection for sensitive components within the rotor and blades apparatus. This improves efficiency and allows the aircraft to fly faster.

Abstract: A golf car canopy extension panel that is connectable to a canopy main panel, wherein the extension panel comprises a first extension longitudinal water channel that is fluidly connectable to a first main longitudinal water channel main panel, and a second extension longitudinal water channel that is fluidly connectable to a second main longitudinal water channel of the main panel, wherein the first and second extension longitudinal water channels each comprise a termination end structured and operable to direct water to exit the respective extension longitudinal water channel at an end of a sidewall of the respective extension longitudinal water channel.