Abstract: One example of a fairing for a rotorcraft includes an outer mold line portion (OML portion) and a bearing portion extending from the OML portion. The OML portion provides at least a portion of an outer mold line of the rotorcraft. Both the OML portion and the bearing portion shield a portion of a structural member. The bearing portion can protect the portion of the structural member from damage resulting from foot traffic associated with accessing an area nearby the structural member.

Abstract: An emergency escape window for a rotorcraft includes a window frame, a window pane set inside the window frame, a plurality of pins connecting the window frame to the fuselage of the rotorcraft, and a release mechanism having at least one actuator connected to a respective pin and constructed to retract the pin from the window frame. The escape window can then be pivoted away and/or completely detached from the fuselage in the event of an emergency to allow occupants to safely exit the rotorcraft. The disclosure also relate to a method of operating an emergency escape window for a rotorcraft and to a rotorcraft having an emergency escape window.

Abstract: An exemplary rotorcraft includes a power train with an engine coupled to a gearbox, a main rotor blade having a mast coupled to the power train, a control input linkage in communication between a pilot input device and the main rotor blade configured to communicate a control input force from the pilot input device to the main rotor blade, and a counterweight system in connection with the control input linkage and the power train to apply a centrifugal force to the control input linkage.

Abstract: An ice-management method for an aircraft includes scavenging torque from a mast of the aircraft with a system that is configured to provide an ice-management capability. The method includes using the scavenged torque to impart a vibratory force to an arm of the system and imparting the vibratory force from the arm to an inner surface of a spinner of the aircraft via a contact of the arm.

Abstract: A method of controlling a tail rotor system of a helicopter includes pivoting a swashplate of the tail rotor system about an axis passing through a diameter of the swashplate. Pivoting the swashplate causes a first linkage of a first pair of linkages coupled between the swashplate and a collective crosshead to move in a first direction and a second linkage of the first pair of linkages coupled between the swashplate and the collective crosshead to move in a second direction that is opposite the first direction. The movement of the first and second linkages causes a plane of rotation of a pair of rotors of the tail rotor system to cant relative to a centerline of a mast of the tail rotor system.

Abstract: A method for generating a simulation model to evaluate a flight control system including determining at least one high level requirement for an aircraft flight system during a non-automated engineering process; generating at least one specification of the high level requirement; generating a model computer-readable program code based on the at least one specification; executing the model computer-readable program code to generate a model code unit; executing the model code unit to generate a procedure document; executing the model code unit to perform a simulation method to generate a bench test computer-readable program code: executing the bench test computer-readable program code on a bench test computing device to generate a simulation output; and comparing the simulation output to the at least one specification of the high level requirement to generate a pass or fail result.

Abstract: A fairing is provided in one example embodiment and may include an apparatus to receive at least one of a foot traffic load and a hand traffic load, wherein the apparatus can include: a step portion that is to receive at least a portion of the foot traffic load; a handhold portion that is to receive at least a portion of the hand traffic load, wherein the handhold portion extends downward from the step portion; and a support structure, wherein the support structure extends downward from of the step portion. The apparatus can include an outer flange attached to the fairing. At least a portion of the step portion the apparatus can be recessed within the fairing at a distance between one inch and three inches from a top surface of the fairing. The handhold portion can include one or more drain holes.

Abstract: A detachable cargo mirror assembly for use on a rotorcraft surface that includes a bracket configured to mount to a surface on the rotorcraft, the bracket comprising a base portion and a retainer portion having a first pair of opposing holes, an elongated arm having two opposing ends, a first end for coupling with the bracket and a second end coupled to a mirror apparatus, the first end having a passage: and a releasable connector configured to engage with the first pair of opposing holes and the passage in the elongated arm when the elongated arm is in a first position to display a desired image on the mirror apparatus. The detachable cargo mirror assembly can be removed or in a stowed position when not in use.

Abstract: A rotor system for an aircraft including a driving member; an externally driven rim configured to be rotated by the driving member; a hub having a hub axis, the hub including a rotatable housing and a non-rotatable housing; a plurality of rotor blade assemblies rotatably coupled to the rotatable housing of the hub and the externally driven rim such that rotation of the externally driven rim rotates the plurality of rotor blade assemblies about the hub axis, each rotor blade assembly having a rotor blade rotatable about a respective pitch change axis; and a pitch control mechanism operably associated with the hub and the plurality of rotor blade assemblies, wherein, actuation of the pitch control mechanism rotates each rotor blade assembly about the respective pitch change axis to collectively control the pitch of the rotor blade, thereby generating a variable thrust output. Also, a method of operating the rotor system.

Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, an adapter ring, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the swashplate and the adapter ring, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the swashplate and the adapter ring, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

Abstract: An example of a hub for a tail rotor includes a body configured to couple to a mast of a rotor system, a trunnion disposed within the body, first and second shafts disposed on opposite sides of the trunnion, first and second end plates secured to the body, and first and second end bearings, the first end bearing disposed between the first shaft and the first end plate and the second end bearing disposed between the second shaft and the second end plate.

Abstract: An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A plurality of hydraulic or electric motors are disposed within or attached to the closed wing, fuselage or spokes in a distributed configuration. A propeller is proximate to a leading edge of the closed wing or spokes and operably connected to each hydraulic or electric motor. A source of hydraulic or electric power is disposed within or attached to the closed wing, fuselage or spokes and coupled to each hydraulic or electric motor disposed within or attached to the closed wing, fuselage or spokes. A controller is coupled to each hydraulic or electric motor, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

Abstract: Systems and methods include providing an aircraft with a ducted rotor assembly. The ducted rotor assembly includes a housing having a duct, a rotor drive mechanism coupled to a rotor system, and a plurality of stators that both structurally support the rotor drive mechanism within the duct of the housing and carry a fluid through internal fluid passages in the plurality of stators to provide cooling to the rotor drive mechanism. Some of the stators carry fluid to the rotor drive mechanism, where the fluid absorbs heat from the rotor drive mechanism, and some of the stators carry fluid away from the rotor drive mechanism. The rotor system generates an airflow over the stators carrying fluid away from the rotor drive mechanism to effect transfer between the fluid and the airflow.

Abstract: In a first aspect, there is a personal air vehicle including a body having a forward portion, a central portion and an aft portion; a first ducted fan supported by the forward portion of the body; a second ducted fan supported by the aft portion of the body; and third and fourth ducted fans supported by the left and right sides of the body and pivotable relative to the body. An aspect provides a method of flying the personal air vehicle.

Abstract: The present invention achieves technical advantages as an engine compartment drainage system that allows fluid on an engine deck to exit an engine compartment, while shielding fluid from airflow. A fluid drainage apparatus utilizes a funnel member to direct fluid to an external drain line. A drain shield circumscribes the top end of the funnel member and upwardly extending therefrom and directs airflow away from the funnel member. A plurality of deck holes are disposed in the drain shield, such that fluid on the deck can enter the funnel member and exit the engine compartment. A fluid drainage system, disposes the fluid drainage apparatus in an engine deck to allow fluid on the deck to enter a funnel member of the apparatus and direct it toward the external drain line.

Abstract: A notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer; isolating the notch; and selectively etching the notch to provide an etched surface of the notch; wherein at least a portion of the re-melt material layer has been removed from the notch. In one aspect, there is provided a notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer, the specimen includes steel or an alloy thereof; isolating the notch; and selectively etching the notch with a first etching solution and a second etching solution to provide an etched surface on the notch; wherein at least a portion of the re-melt material layer has been removed from the notch.

Abstract: An aircraft capable of vertical takeoff and landing and stationary flight includes a distributed airframe coupled to a modular fuselage. The modular fuselage has a longitudinal axis substantially parallel to a rotational axis of three or more propellers. The modular fuselage includes a rear module substantially disposed within a perimeter of the distributed airframe, a front module removably connected to the rear module and substantially aligned with the longitudinal axis. One or more engines or motors are disposed within or attached to the distributed airframe or fuselage. The three or more propellers are proximate to a leading edge of the distributed airframe, distributed along the distributed airframe, and operably connected to the one or more engines or motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight.

Abstract: A fuel-cell system at 540 VDC for powering an electrical load of a rotorcraft with a first fuel cell and a second fuel cell. Each fuel cell is configured identically and features a positive electrical node and a negative electrical node. Each fuel cell is configured to provide one half of the electrical load of the rotorcraft and one half of the voltage of the electrical load.

Abstract: A stack fuel cell array featuring paired fuel-cell systems combined to generate 540 VDC for a rotorcraft. Power from the hydrogen-based fuel cells is provided to the rotorcraft. A rated electrical load of the rotorcraft helps determine how many paired fuel-cell systems are needed during any fuel-cell systems failures. Each of the paired fuel-cell systems is coupled to an electrical load of the rotorcraft. The system detects any fuel cell failures and removes other working fuel cells as needed to balance the electrical system.

Abstract: A rotorcraft featuring a fuselage, a forward fuselage ducted fan located in the fuselage, and an aft fuselage ducted fan located in the fuselage. The rotorcraft is directly powered by electricity and can be supplemented with additional powers sources. Two sets of pivoting ducted fans provide additional lift and thrust as needed to control the rotorcraft.