Textron Innovations Inc.

Bell Helicopter Textron Inc.

University of Notre Dame Du Lac

Tommie Lynn Wood

Shyhpyng Jack Shue

Alan Carl Ewing

John James Corrigan

Eric Thomas Bird

Thomas C Corke

Frank B Stamps

Richard Erler Rauber

Albert Gerard Brand

Patrick R Tisdale

David Popelka

James M McCollough

William L McKeown

Flint O Thomas

David A Popelka

David Shatzman

Duane L Hicks

Martiqua Post

Julian L Jenkins

Flint Thomas

Thomas Corke

A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. An exemplary aircraft for using the method and apparatus of a reconfigurable flight control system is a quad tilt rotor. The quad tilt rotor provides a variety of redundant and back-actuators, as such, having a robust and highly qualified reconfigurable flight control system is very desirable.

Method and apparatus for aircraft sensor and actuator failure protection using reconfigurable flight control laws

The present application includes a main rotor assembly for an aircraft. The rotor assembly has a main rotor mast configured for rotation about a mast axis and two yokes pivotally connected to the mast for rotation therewith about the mast axis. Each yoke is independently pivotable relative to the mast about at least one flap axis that is generally perpendicular to the mast axis. In at least one embodiment, a torque splitter connects the yokes and allows for limited rotation of the yokes relative to each other about the mast axis. Each yoke is configured for the attachment of rotor blades extending generally radially relative to the mast axis.

Multiple-yoke main rotor assembly

According to one embodiment, a rotorcraft includes a main rotor system, an anti-torque rotor system, an anti-torque rotor enhancement system, and an anti-torque rudder system. The anti-torque rotor enhancement system includes an aerodynamic structure having an opening therethrough and a support structure coupling the aerodynamic structure to the body of the rotorcraft such that the opening is positioned proximate to a rotation path of the at least one anti-torque rotor blade. The anti-torque rudder system includes at least one rudder surface operable to provide a second force on the body in the direction of rotation of the at least one main rotor blade.

Rotorcraft anti-torque rotor and rudder system

A vortex generator system comprises one or more plasma streamwise vortex generators (PSVGs) or plasma wedge vortex generators (PWVGs). The PSVGs and PWVGs each comprises a first electrode and a second electrode separated by a dielectric layer. The first electrode extends in a longitudinal direction. The PSVGs and PWVGs can be installed on a surface arranged to receive airflow in a certain flow direction. The PSVGs have a rectangular first electrode is exposed and extends at least somewhat parallel to the expected flow direction, whereas the first electrode of the PWVGs is more triangular in shape. When an AC voltage is applied to the first and second electrodes, a plasma forms along edges of the first electrode. The plasma imposes a body force in a cross-flow direction, which induces a cross-flow velocity that, in combination with the mean flow, produces streamwise-oriented counter-rotating vortices.

System and method for aerodynamic flow control

A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix and a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. A sensor management tool is provided for input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.

An aircraft includes a surface over which an airflow passes. A plasma actuator is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.

Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft

An apparatus for interconnection in a helicopter tail rotor control linkage for changing the pitch of the tail rotor blades in response to predetermined inputs is provided. The apparatus comprises a linkage member having a variable geometry, an actuator, and a control unit. In a preferred embodiment, the control unit utilizes a microcontroller to monitor inputs corresponding to ambient air condition and automatically vary the maximum tail rotor pitch so as to provide maximum tail rotor authority over a range of altitudes.

Tail rotor authority control for a helicopter

Nozzles for discharging high velocity air are positioned on either side of an aircraft engine exhaust duct exit. High velocity air is discharged tangential to an outer surface of each nozzle and follows the contour thereof. The nozzles are positioned so that when the high velocity air separates from the outer surface of the respective nozzles, it flows outwardly relative to the aircraft's fuselage structure. The high velocity air from the nozzle closest to the aircraft's fuselage structure impinges on the exhaust gas stream, deflecting the stream away from the fuselage. The high velocity air from the nozzle furthest from the fuselage creates a low pressure area which deflects the exhaust gas stream away from the fuselage. In combination, the two nozzles deflect the exhaust gas stream away from the fuselage to a significant degree.

Growing community of inventors

Arlington, TX, United States of America

Tommie Lynn Wood