Abstract: A rotor assembly including a fixed fairing including an interface portion and a hub fairing including a depression. The depression is configured to receive at least a portion of the interface portion. The hub fairing is rotatable relative to the fixed fairing.

Abstract: A rotary wing aircraft and a rotor assembly of a rotary wind aircraft is disclosed. The rotary wing aircraft includes at least one engine, and the rotor assembly is coupled to the at least one engine. The rotor assembly includes a first rotor hub, a second rotor hub, and a shaft fairing between the first rotor hub to the second rotor hub, the shaft fairing defined by a chord that varies between the first rotor hub and the second rotor hub.

Abstract: A rotor assembly includes a first rotor hub and a second rotor hub. The second rotor hub is coupled to the first rotor hub via a shaft fairing. The first rotor hub has a flat first surface coupled to the shaft fairing and a curved second surface opposite the flat first surface. The second rotor hub has a flat first surface on the lower side and a curved second surface opposite the flat first surface.

Abstract: A rotorcraft is provided and includes a fuselage. The fuselage includes drag generating portions, a main rotor assembly and an auxiliary propulsor having an expected propulsion efficiency. The auxiliary propulsor is disposed to ingest boundary layer flows and in wake regions associated with the drag generating portions and is provided with a corresponding increase in the expected propulsion efficiency thereof.

Abstract: A rotary wing aircraft and a rotor assembly of a rotary wind aircraft is disclosed. The rotary wing aircraft includes at least one engine, and the rotor assembly is coupled to the at least one engine. The rotor assembly includes a first rotor hub, a second rotor hub, and a shaft fairing between the first rotor hub to the second rotor hub, the shaft fairing defined by a chord that varies between the first rotor hub and the second rotor hub.

Abstract: A main rotor blade assembly for a rotary wing aircraft is provided including a main rotor blade root region, a main rotor blade inboard region arranged outboard of said main rotor blade root region, a main rotor blade main region arranged outboard of said main rotor blade inboard region, and a main rotor blade tip region arranged outboard of said main rotor blade main region. At least one of chord, twist, sweep, airfoil shape, and thickness/chord of the main rotor blade assembly has been optimized to achieve balanced high speed forward flight and hover relative to both efficiency and high thrust capability.

Abstract: A rotor assembly includes a first rotor hub and a second rotor hub. The second rotor hub is coupled to the first rotor hub via a shaft fairing. The first rotor hub has a flat first surface coupled to the shaft fairing and a curved second surface opposite the flat first surface. The second rotor hub has a flat first surface on the lower side and a curved second surface opposite the flat first surface.

Abstract: A propulsor system for a rotary winged aircraft includes a propeller including having a propeller hub rotatable about a propeller axis and a plurality of propeller blades secured to and extending radially outwardly from the propeller hub. The propeller is oriented on the rotary winged aircraft to provide forward thrust for the rotary winged aircraft when the propeller is rotated about the propeller hub. A plurality of guide vanes non rotatable about the propeller axis are positioned upstream of the plurality of propeller blades. The plurality of guide vanes are positioned to turn an airflow flowing into the plurality or propeller blades, thereby reducing an angle of attack of the plurality of propeller blades relative to the airflow.

Abstract: A rotorcraft is provided and includes a fuselage. The fuselage includes drag generating portions, a main rotor assembly and an auxiliary propulsor having an expected propulsion efficiency. The auxiliary propulsor is disposed to ingest boundary layer flows and in wake regions associated with the drag generating portions and is provided with a corresponding increase in the expected propulsion efficiency thereof.

Abstract: A main rotor blade assembly for a rotary wing aircraft is provided including a main rotor blade root region, a main rotor blade inboard region arranged outboard of said main rotor blade root region, a main rotor blade main region arranged outboard of said main rotor blade inboard region, and a main rotor blade tip region arranged outboard of said main rotor blade main region. At least one of chord, twist, sweep, airfoil shape, and thickness/chord of the main rotor blade assembly has been optimized to achieve balanced high speed forward flight and hover relative to both efficiency and high thrust capability.

Abstract: A propulsor system for a rotary winged aircraft includes a propeller including having a propeller hub rotatable about a propeller axis and a plurality of propeller blades secured to and extending radially outwardly from the propeller hub. The propeller is oriented on the rotary winged aircraft to provide forward thrust for the rotary winged aircraft when the propeller is rotated about the propeller hub. A plurality of guide vanes non rotatable about the propeller axis are positioned upstream of the plurality of propeller blades. The plurality of guide vanes are positioned to turn an airflow flowing into the plurality or propeller blades, thereby reducing an angle of attack of the plurality of propeller blades relative to the airflow.

Abstract: A leading edge slat for multi-element rotor blade applications which provide multiple benefits and provide design direction which has heretofore been unexplored.

Abstract: A multi-element rotor blade includes a main element and an active slat movable relative to the main element. The slat rotates and translates relative to the main element from a base position. The base position provides a compromise between minimum coefficient of drag CD and maximum coefficient of lift CLmax. In the advancing blade, since the airspeed thereof is significantly greater than the retreating blade, the slat is positively rotated from the base position to minimizes drag at low angles of attack. In the retreating blade, since the airspeed thereof is significantly lower than the advancing blade, the slat is negatively rotated and translated to maximize the coefficient of lift CLmax.

Abstract: Two neural networks are used to control adaptively a vibration and noise-producing plant. The first neural network, the emulator, models the complex, nonlinear output of the plant with respect to certain controls and stimuli applied to the plant. The second neural network, the controller, calculates a control signal which affects the vibration and noise producing characteristics of the plant. By using the emulator model to calculate the nonlinear plant gradient, the controller matrix coefficients can be adapted by backpropagation of the plant gradient to produce a control signal which results in the minimum vibration and noise possible, given the current operating characteristics of the plant.

Abstract: Two neural networks are used to control adaptively a vibration and noise-producing plant. The first neural network, the emulator, models the complex, nonlinear output of the plant with respect to certain controls and stimuli applied to the plant. The second neural network, the controller, calculates a control signal which affects the vibration and noise producing characteristics of the plant. By using the emulator model to calculate the nonlinear plant gradient, the controller matrix coefficients can be adapted by backpropagation of the plant gradient to produce a control signal which results in the minimum vibration and noise possible, given the current operating characteristics of the plant.

Abstract: An elastomeric coupler assembly having a helical elastomeric bearing movably supports an active slat relative to a main element. An inner elastomeric coupler assembly and an outer elastomeric coupler assembly support the slat therebetween. Centrifugal force operates to drive the slat to a first position and an actuator rod operates in tension to pull upon the inner elastomeric coupler assembly to drive the slat in opposition to the centrifugal force to a second position. The helical elastomeric bearing is layered such that it defines a section of a circular helix. The circular helix provides a coupling, which converts a linear input parallel to a virtual hinge axis into a rotary output to pitch the slat. In operation, centrifugal force operates to slide the slat outboard toward the blade tip such that the attached slat moves elastomerically along the helical arc of the helical elastomeric bearing to rotate the slat nose down.

Abstract: An elastomeric coupler assembly having a helical elastomeric bearing movably supports an active slat relative to a main element. An inner elastomeric coupler assembly and an outer elastomeric coupler assembly support the slat therebetween. Centrifugal force operates to drive the slat to a first position and an actuator rod operates in tension to pull upon the inner elastomeric coupler assembly to drive the slat in opposition to the centrifugal force to a second position. The helical elastomeric bearing is layered such that it defines a section of a circular helix. The circular helix provides a coupling, which converts a linear input parallel to a virtual hinge axis into a rotary output to pitch the slat. In operation, centrifugal force operates to slide the slat outboard toward the blade tip such that the attached slat moves elastomerically along the helical arc of the helical elastomeric bearing to rotate the slat nose down.

Abstract: A multi-element rotor blade includes a main element and an active slat movable relative to the main element. The slat rotates and translates relative to the main element from a base position. The base position provides a compromise between minimum coefficient of drag CD and maximum coefficient of lift CLmax. In the advancing blade, since the airspeed thereof is significantly greater than the retreating blade, the slat is positively rotated from the base position to minimizes drag at low angles of attack. In the retreating blade, since the airspeed thereof is significantly lower than the advancing blade, the slat is negatively rotated and translated to maximize the coefficient of lift CLmax.

Abstract: Two neural networks are used to control adaptively a vibration and noise-producing plant. The first neural network, the emulator, models the complex, nonlinear output of the plant with respect to certain controls and stimuli applied to the plant. The second neural network, the controller, calculates a control signal which affects the vibration and noise producing characteristics of the plant. By using the emulator model to calculate the nonlinear plant gradient, the controller matrix coefficients can be adapted by backpropagation of the plant gradient to produce a control signal which results in the minimum vibration and noise possible, given the current operating characteristics of the plant.

Abstract: Two neural networks are used to control adaptively a vibration and noise-producing plant. The first neural network, the emulator, models the complex, nonlinear output of the plant with respect to certain controls and stimuli applied to the plant. The second neural network, the controller, calculates a control signal which affects the vibration and noise producing characteristics of the plant. By using the emulator model to calculate the nonlinear plant gradient, the controller matrix coefficients can be adapted by backpropagation of the plant gradient to produce a control signal which results in the minimum vibration and noise possible, given the current operating characteristics of the plant.