Textron Innovations Inc.

Bell Textron Inc.

Andrew Thomas Carter

Aaron Alexander Acee

John Richard Mccullough

Sung Kyun Kim

Matthew John Hill

Lynn Francis Eschete

James Everett Kooiman

Andrew Paul Haldeman

Michael Scott Seifert

Michael E Rinehart

Steven Allen Robedeau, Jr

Jason Paul Winter

Derek Ray Eddins

Clegg Benjamin Brian Smith

Steven Ray Ivans

Brent Chadwick Ross

Charles Eric Covington

Jared Mark Paulson

Albert Gerard Brand

Luke Dafydd Gillett

Thomas Dewey Parsons

Glenn Alan Shimek

Mark Loring Isaac

Kent E Donaldson

Bryan Huber

Diana Tinlin

Timothy McClellan Mosig

Shahryar Fotovati

Brian Erik Barnes

Glenn Thornton Lancaster

Craig Lovell

Jeffrey Kirkman

James Rigsby

Madeline Kvaka

A method of designing a rotor blade for a rotary aircraft includes establishing a target thrust-weighted solidity of the rotor blade, calculating a reverse flow circle of the rotor blade at a target forward speed of the rotary aircraft, inboard of the reverse flow circle, decreasing chord of the rotor blade relative to a baseline rotor blade possessing the target thrust-weighted solidity, and outboard of the reverse flow circle, increasing the chord of the rotor blade relative to the baseline rotor blade. The rotor blade possesses the target thrust-weighted solidity of the baseline rotor blade and improved stall margin or speed margin at the target forward speed relative to the baseline rotor blade.

Method and system for inverse-tapered high-speed rotors

In an embodiment, an aircraft includes a drive system, a main engine coupled to the drive system to provide first power, and a supplemental engine coupled to the drive system to provide second power additive to the first power. The aircraft also includes a control system to control the main engine and the supplemental engine to optimize usage of the supplemental engine. The control system is operable to maintain the supplemental engine in a reduced power state at least until a determination is made that supplemental power is needed to satisfy a total power demand of the drive system. The control system is also operable to determine that supplemental power is needed to satisfy the total power demand of the drive system. The control system is further operable to increase a power level of the supplemental engine in response to the determination that supplemental power is needed.

Optimizing usage of supplemental engine power

One embodiment includes a rotary aircraft, including: a main drive rotor; an aircraft body mechanically coupled to the main drive rotor; and first and second flight assist wings passively rotatably coupled to the aircraft body.

Rotatable winglets for a rotary wing aircraft

A rotorcraft has a horizontal stabilizer movable about an axis of rotation and a horizontal stabilizer control system configured to control the horizontal stabilizer to at least one of move the rotorcraft into a minimum drag position, maintain the aircraft in a minimum drag position, efficiently achieve a maneuver, enter efficient autorotation, and maintain efficient autorotation.

Active horizontal stabilizer for high speed rotorcraft

An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. First and second yaw vanes extend aftwardly from the fuselage. A flight control system is configured to direct the thrust vector of the coaxial rotor system and control movements of the yaw vanes. In a VTOL orientation of the aircraft, differential operation of the yaw vanes and/or differential operations of first and second rotor assemblies of the coaxial rotor system provide yaw authority for the aircraft. In a biplane orientation of the aircraft, collective operation of the yaw vanes provides yaw authority for the aircraft.

Yaw control systems for tailsitting biplane aircraft

A rotor system for a rotorcraft includes a rotor hub having a plurality of blade grips coupled thereto. Each blade grip has a rotor blade coupled thereto. A fairing is disposed at least partially around the rotor hub. Each of a plurality of lead-lag dampers is coupled to at least a respective one of the blade grips. Each lead-lag damper has a damper heat exchanger and a fluid pump operably associated therewith. A fairing heat exchanger is in fluid communication with the damper heat exchangers and the fluid pumps. Each lead-lag damper is configured to drive the respective fluid pump responsive to damping operations to pump a cooling fluid from the respective damper heat exchanger to the fairing heat exchanger.

Rotor systems having lead-lag damper cooling

A blade pitch adjustment mechanism includes a pitch cylinder having a first face and pitch slots extending longitudinally from the first face, a blade sleeve having a second face and a blade slot extending longitudinally from the second face, the blade sleeve is configured to be rotationally positioned in the pitch cylinder with the second face located with the first face, wherein the blade slot and the pitch slots are cooperative to form keyway, corresponding to a discrete blade pitch, when the blade slot is aligned with a pitch slot.

Precision blade pitch adjustment

An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. Tail assemblies are coupled to wingtips of the first and second wings each having an elevon that collectively form a distributed array of elevons. A flight control system is configured to direct the thrust vector of the coaxial rotor system and to control movements of the elevons such that the elevons collectively provide pitch authority and differentially provide roll authority for the aircraft in the biplane orientation. In addition, when the flight control system detects an elevon fault, the flight control system is configured to perform corrective action responsive thereto at a distributed elevon level or at a coordinated distributed elevon and propulsion assembly level.

Distributed elevon systems for tailsitting biplane aircraft

An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft has an airframe including first and second wings with a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. A flight control system is configured to direct the thrust vector. In the VTOL orientation, the first wing is forward of the fuselage, the second wing is aft of the fuselage and the coaxial rotor system is configured to provide thrust in line with a yaw axis of the aircraft. In the biplane orientation, the first wing is below the fuselage, the second wing is above the fuselage and the coaxial rotor system is configured to provide thrust in line with a roll axis of the aircraft.

Tailsitting biplane aircraft having a coaxial rotor system

A propulsion assembly for an aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The propulsion assembly includes a housing coupled to the fuselage of the aircraft. A coaxial rotor system includes a first rotor assembly and a second rotor assembly that are rotatable about a common axis of rotation. The first rotor assembly counter-rotates relative to the second rotor assembly. A motor assembly is operably associated with the coaxial rotor system. The motor assembly provides torque and rotational energy to the first rotor assembly and the second rotor assembly. A gimbal assembly couples the coaxial rotor system to the housing such that the coaxial rotor system is tiltable relative to the fuselage to generate a thrust vector.

Thrust vectoring coaxial rotor systems for aircraft

Pair of aircraft wings

Combined aircraft fuselage and empennage

Aircraft

Growing community of inventors

Richland Hills, TX, United States of America

Andrew Thomas Carter