The Boeing Company

Thomas A Zientek

Geoffrey P McKnight

Chia-Ming Chang

Douglas Reinhard Ludin

Joshua M Montgomery

Tiffany A Stewart

Janet M Hogan

Richard Bussom

Michael A McVeigh

Robert P Narducci

Terrence S Birchette

Friedrich K Straub

Daniel M Podgurski

Evhen M Mychalowycz

A method and apparatus for moving a blade of a rotorcraft. The method comprises operating the rotorcraft and applying a torque to an elongate member connected to a tip portion of the blade during operation of the rotorcraft using a tip actuation mechanism that is external to the blade and associated with the elongate member such that the tip portion of the blade rotates about an axis through the blade.

Apparatus, system, and method for pitching and twisting a blade of a rotorcraft

An acoustic barrier structure can include a support structure that defines a plurality of cells, a weight attached to the support structure, and at least one resonant membrane covering one of the plurality of cells. The at least one resonant membrane can comprise at least one weight. The at least one resonant membrane can have an anti-resonant frequency and the support structure with the weight can provide wide frequency band gaps between odd resonance modes while suppressing structure-membrane coupled modes to enable the anti-resonance of the at least one resonant membrane.

Acoustic barrier support structure

A stiff in-plane gimbaled rotor head for a rotorcraft, such as a helicopter, includes a vertically extending rotor shaft, a center hub disposed on the rotor shaft for conjoint rotation therewith, and an outer hub surrounding the center hub and coupled thereto through a spherical gimbal bearing for conjoint rotation therewith, and such that the outer hub is also capable of an angular range of gimbaling movement relative to the center hub. A plurality of rotor blades, which may include three or more blades, is coupled to the rotor shaft through the inner and outer hubs by a constant velocity joint that enables the blades to be rotated in a common plane about the axis of the rotor shaft while controlling the respective pitches of the blades and such that any other relative in-plane and out-of-plane movements of the blades during rotation is prevented.

Low maintenance stiff in plane gimbaled rotor head

Embodiments of systems and methods for enhancing the performance of rotary wing aircraft through reduced torque, noise and vibration are disclosed. In one embodiment, a method includes configuring the rotorcraft in a selected flight condition, communicating input signals to a control system operable to position sails coupled to tips of blades of a rotor assembly, processing the input signals according to a constraint condition to generate sail positional information, and transferring the sail positional information to the sail. Alternately, input signals may be communicated to a control system operable to position a plurality of sails, each sail having an aerodynamic shape and positioned proximate to a tip portion of the rotor blade. The input signals may be configured to rotate each sail about a longitudinal axis into a corresponding pitch angle independently of the other sails.

System and method for improved rotor tip performance

Low-noise airfoils and methods of reducing noise. One embodiment provides an aerodynamic member that includes two body portions coupled to each other. The second body portion includes a plurality of airfoil members in a fixed relationship with each other. Optionally, the airfoil members may define an open end of the second body portion. In the alternative, the member can include a third body portion that has an airfoil shape and that is coupled to the second body portion opposite the first body portion. Preferably, the first portion, the airfoil members, and third portion are 12%, 8%, and 2% thickness/chord airfoils respectively. Further, the aerodynamic member may be a rotor blade on a tandem helicopter. Another embodiment provides a cambered airfoil with two coupled body portions one of which has air foil members. One of the body portions includes a slot there through with airfoil members on opposite sides of the slot.

Cascade rotor blade for low noise

The present invention discloses systems and methods for the performance enhancement of rotary wing aircraft through reduced torque, noise and vibration. In one embodiment, a system includes a sail having an aerodynamic shape positioned proximate to a tip of the rotor blade. An actuator may be configured to rotate the sail relative to the blade tip. a A control system receives information from a rotorcraft system and commands the actuator to rotate the sail to a predetermined favorable rotor blade operating condition. In another embodiment, a method includes configuring the rotorcraft in a selected flight condition, communicating input signals to a control system operable to position sails coupled to tips of blades of a rotor assembly, processing the input signals according to a constraint condition to generate sail positional information, and transferring the sail positional information to the sail.

A rotor system () for a helicopter () includes a rotating shaft (). A gimbaled hub assembly () is coupled to the rotating shaft (). Rotating blades () and non-rotating blades () are coupled to the gimbaled hub assembly (). The non-rotating blades () provide lift for the helicopter () in forward flight unloading the rotating blades. The rotating and non-rotating blades () provide equal and opposite rolling moments for lift offset operation.

Growing community of inventors

Drexel Hill, PA, United States of America

Thomas A Zientek