Bell Helicopter Textron Inc.

Textron Innovations Inc.

Brendan P Lanigan

Christopher Edward Foskey

Albert Gerard Brand

Jimmy Charles Narramore

James H Harse

Joshua Robert O'Neil

Helmuth Peter Koelzer

Michael Kenneth Farrell

Albert G Brand

Jimmy Narramore

Joshua R O'NEIL

Joshua R 0'Neil

Leading edge fairing

Rotor blade

In one embodiment, a vertical stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a vertical orientation. The airfoil structure comprises a leading edge and a trailing edge, wherein the trailing edge is configured to form a blunt shaped edge. The airfoil structure further comprises a root end and a tip end, wherein the airfoil structure is tapered from the root end to the tip end. The airfoil structure is also cambered. Finally, the airfoil structure is further configured to be mounted with a rotor, and is also further configured to house one or more internal components associated with the aircraft.

Aircraft vertical stabilizer design

In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade, including providing a blade member having a leading edge and a trailing edge; providing a leading edge extension member; and coupling the leading edge extension member to a portion of the leading edge of the blade member to form the rotor blade. In a second aspect, there is a rotor blade including a blade member having a leading edge, and a trailing edge; and a leading edge extension member disposed on the leading edge of the blade member, wherein the leading edge extension member is configured to extend the chord length of at least a portion of the rotor blade. In a third aspect, there is a leading edge extension member for a rotor blade including a convex exterior surface configured to extend at least a portion of the chord length of the rotor blade.

Method and apparatus to improve lift to drag ratio of a rotor blade

A proprotor assembly for a tiltrotor aircraft having a forward flight mode. The proprotor assembly includes a spinner subjected to freestream airflow during forward flight. The spinner is elongated to form a tapered leading portion and a substantially cylindrical aft portion. The spinner forms a plurality of rotor blade cutouts exposing an inner chamber. The proprotor assembly includes a plurality of proprotor blade assemblies protruding radially from the spinner through the rotor blade cutouts. The rotor blade cutouts are formed at the substantially cylindrical aft portion of the spinner to reduce the freestream airflow into the inner chamber via the rotor blade cutouts during forward flight, thereby reducing drag experienced by the tiltrotor aircraft.

Spinners for use on tiltrotor aircraft

In one embodiment, a horizontal stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a horizontal orientation. The airfoil structure comprises a leading edge, a trailing edge, a top surface, and a bottom surface. Moreover, the airfoil structure is cambered, wherein a camber of the airfoil structure forms a concave slope on the top surface and a convex slope on the bottom surface.

Aircraft horizontal stabilizer design

A system and method to control fuselage torque of an aircraft. The system includes a tail boom having a first surface that creates a high-pressure region in a downward rotorwash and a second surface that creates a low-pressure region in the downward rotorwash. The difference in pressure regions creates a lateral force that opposes the fuselage torque.

Airfoil shaped tail boom

A tail boom adapted for counteracting a fuselage torque created by an engine carried by a fuselage of a rotary aircraft. The tail boom is positioned within the rotorwash from the rotary and includes a first side surface contoured to create a low-pressure region of an airfoil and a second opposing side surface contoured to create a high-pressure region of an airfoil. The pressure difference between the high-pressure region and the low-pressure region causes the tail boom to move towards the low-pressure region, resulting in a lateral force opposing the torque on the fuselage.

Growing community of inventors

Grapevine, TX, United States of America

Brendan P Lanigan