Patents by Inventor Claude G. Matalanis
Claude G. Matalanis has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11325695Abstract: A rotor blade of a rotary wing aircraft includes a core defining a trailing edge of the rotor blade and a skin extending from the trailing edge defining an opening including the core. The skin defines an aerodynamic surface of the rotor blade. The rotor blade additionally includes at least one trim tab assembly including a trim portion extending from the core beyond the trailing edge of the rotor blade and an actuation system including at least one actuator disposed within the core. The actuation system is operable to adjust an angle of the trim portion relative to the rotor blade.Type: GrantFiled: April 16, 2020Date of Patent: May 10, 2022Assignee: LOCKHEED MARTIN CORPORATIONInventors: Frank M. Caputo, Timothy James Conti, Claude G. Matalanis
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Patent number: 11174988Abstract: According to one aspect, a lubricant level sensing system for an actuator is provided. The lubricant level sensing system includes a pressure port in an outer housing of the actuator, a pressure sensor, and a pathway from the pressure port to the pressure sensor. The pathway establishes fluid communication between the pressure sensor and a free volume of an internal cavity of the outer housing relative to a lubricant level in the internal cavity such that the pressure sensor detects a pressure of the free volume used to derive the lubricant level.Type: GrantFiled: January 20, 2020Date of Patent: November 16, 2021Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Claude G. Matalanis, Ulf J. Jonsson, John D. Cannata, Brian E. Wake
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Publication number: 20210323660Abstract: A rotor blade of a rotary wing aircraft includes a core defining a trailing edge of the rotor blade and a skin extending from the trailing edge defining an opening including the core. The skin defines an aerodynamic surface of the rotor blade. The rotor blade additionally includes at least one trim tab assembly including a trim portion extending from the core beyond the trailing edge of the rotor blade and an actuation system including at least one actuator disposed within the core. The actuation system is operable to adjust an angle of the trim portion relative to the rotor blade.Type: ApplicationFiled: April 16, 2020Publication date: October 21, 2021Inventors: Frank M. Caputo, Timothy James Conti, Claude G. Matalanis
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Publication number: 20200278082Abstract: According to one aspect, a lubricant level sensing system for an actuator is provided. The lubricant level sensing system includes a pressure port in an outer housing of the actuator, a pressure sensor, and a pathway from the pressure port to the pressure sensor. The pathway establishes fluid communication between the pressure sensor and a free volume of an internal cavity of the outer housing relative to a lubricant level in the internal cavity such that the pressure sensor detects a pressure of the free volume used to derive the lubricant level.Type: ApplicationFiled: January 20, 2020Publication date: September 3, 2020Inventors: Claude G. Matalanis, Ulf J. Jonsson, John D. Cannata, Brian E. Wake
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Patent number: 10571074Abstract: According to one aspect, a lubricant level sensing system for an actuator is provided. The lubricant level sensing system includes a pressure port in an outer housing of the actuator, a pressure sensor, and a pathway from the pressure port to the pressure sensor. The pathway establishes fluid communication between the pressure sensor and a free volume of an internal cavity of the outer housing relative to a lubricant level in the internal cavity such that the pressure sensor detects a pressure of the free volume used to derive the lubricant level.Type: GrantFiled: August 27, 2015Date of Patent: February 25, 2020Assignee: SIKORSKY ARICRAFT CORPORATIONInventors: Claude G. Matalanis, Ulf J. Jonsson, John D. Cannata, Brian E. Wake
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Patent number: 10538313Abstract: An aircraft is provided and includes a fuselage including a top and a tail, a main rotor apparatus disposed at the top of the fuselage, which rotates one or more rotors to generate lift, and an active flow control (AFC) system. The AFC system includes plasma actuators configured to generate plasma at a location adjacent to the main rotor apparatus and/or at the tail of the fuselage.Type: GrantFiled: November 19, 2015Date of Patent: January 21, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Brian E. Wake, Claude G. Matalanis, Patrick Bowles
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Publication number: 20190241258Abstract: A rotor blade deflection sensing system including a rotor blade having a first surface, a second surface, a third surface and a fourth surface. At least two fiber optic sensor arrays are mounted to the rotor blade. At least one of the at least two fiber optic sensor arrays is mounted to one of the first surface, the second surface, the third surface and the fourth surface and another of the at least two fiber optic sensor arrays being mounted to another of the first surface, a second surface, a third surface and a fourth surface. A controller is operatively connected to the at least two fiber optic sensor arrays. The controller determines one or more of a flapwise and an edgewise displacement based on inputs from the at least two fiber optic sensor arrays.Type: ApplicationFiled: May 12, 2017Publication date: August 8, 2019Inventors: Derek Geiger, Seung Bum Kim, Claude G. Matalanis, Brian E. Wake, Patrick Bowles
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Patent number: 10232929Abstract: A rotary wing aircraft includes a fuselage having a plurality of surfaces, at least one engine mounted in the fuselage, and a rotor assembly including a rotor shaft and plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. A rotor shaft fairing extends between the fuselage and the rotor assembly and about at least a portion of the rotor shaft. The rotor shaft fairing includes an outer surface. A plate member is mounted to and projects proudly of the at least a portion of the rotor shaft fairing. The plate member is configured and disposed to increase an aspect ratio of and reduce induced drag on the rotor shaft fairing as well as reduce rotor hub wake size.Type: GrantFiled: September 15, 2016Date of Patent: March 19, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Patrick Bowles, ByungYoung Min, Barbara Brenda Botros, Brian E. Wake, Claude G. Matalanis
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Patent number: 10220939Abstract: A rotary wing aircraft includes a fuselage having a plurality of surfaces. At least one engine is mounted in the fuselage. A rotor assembly includes a rotor shaft a plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. An active air discharge opening extends through one of the plurality of surfaces of the fuselage and one of the plurality of surface portions of the rotor assembly, and an active air generation system is mounted in the fuselage. The active air generation system is configured and disposed to generate and direct a flow of air through the active air discharge opening to disrupt an airstream flowing over the one of the plurality of surfaces of the fuselage and the one of the plurality of surface portions of the rotor assembly.Type: GrantFiled: September 12, 2016Date of Patent: March 5, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: ByungYoung Min, Barbara Brenda Botros, Razvan Virgil Florea, Patrick Bowles, Claude G. Matalanis, Brian E. Wake
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Publication number: 20180281932Abstract: An aircraft is provided and includes a fuselage including a top and a tail, a main rotor apparatus disposed at the top of the fuselage, which rotates one or more rotors to generate lift, and an active flow control (AFC) system. The AFC system includes plasma actuators configured to generate plasma at a location adjacent to the main rotor apparatus and/or at the tail of the fuselage.Type: ApplicationFiled: November 19, 2015Publication date: October 4, 2018Inventors: Brian E. WAKE, Claude G. MATALANIS, Patrick BOWLES
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Publication number: 20170336024Abstract: According to one aspect, a lubricant level sensing system for an actuator is provided. The lubricant level sensing system includes a pressure port in an outer housing of the actuator, a pressure sensor, and a pathway from the pressure port to the pressure sensor. The pathway establishes fluid communication between the pressure sensor and a free volume of an internal cavity of the outer housing relative to a lubricant level in the internal cavity such that the pressure sensor detects a pressure of the free volume used to derive the lubricant level.Type: ApplicationFiled: August 27, 2015Publication date: November 23, 2017Inventors: Claude G. Matalanis, Ulf J. Jonsson, John D. Cannata, Brian E. Wake
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Publication number: 20170225772Abstract: A rotary wing aircraft includes a fuselage having a plurality of surfaces. At least one engine is mounted in the fuselage. A rotor assembly includes a rotor shaft a plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. An active air discharge opening extends through one of the plurality of surfaces of the fuselage and one of the plurality of surface portions of the rotor assembly, and an active air generation system is mounted in the fuselage. The active air generation system is configured and disposed to generate and direct a flow of air through the active air discharge opening to disrupt an airstream flowing over the one of the plurality of surfaces of the fuselage and the one of the plurality of surface portions of the rotor assembly.Type: ApplicationFiled: September 12, 2016Publication date: August 10, 2017Inventors: ByungYoung Min, Barbara Brenda Botros, Razvan Virgil Florea, Patrick Bowles, Claude G. Matalanis, Brian E. Wake
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Publication number: 20170225771Abstract: A rotary wing aircraft includes a fuselage having a plurality of surfaces, at least one engine mounted in the fuselage, and a rotor assembly including a rotor shaft and plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. A rotor shaft fairing extends between the fuselage and the rotor assembly and about at least a portion of the rotor shaft. The rotor shaft fairing includes an outer surface. A plate member is mounted to and projects proudly of the at least a portion of the rotor shaft fairing. The plate member is configured and disposed to increase an aspect ratio of and reduce induced drag on the rotor shaft fairing as well as reduce rotor hub wake size.Type: ApplicationFiled: September 15, 2016Publication date: August 10, 2017Inventors: Patrick Bowles, ByungYoung Min, Barbara Brenda Botros, Brian E. Wake, Claude G. Matalanis
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Patent number: 9688395Abstract: A boundary layer ingesting (BLI) blade having a span is provided and includes a root section connectable to a hub, a tip section disposable at a distance from the hub and having a pitch and a body extending in a spanwise dimension from the root section to the tip section. The root section has a local pitch from the root section to about a 70% span location, which is less than the pitch at the tip section, to thereby reduce local angles of attack in a boundary layer region defined in and around the root section.Type: GrantFiled: December 4, 2013Date of Patent: June 27, 2017Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Blake Almy Moffitt, Thomas G. Tillman, Brian E. Wake, Byung-Young Min, Claude G. Matalanis
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Publication number: 20170174326Abstract: A rotary wing aircraft includes a fuselage having a plurality of surfaces, at least one engine mounted in the fuselage, and a rotor assembly including a rotor shaft, and plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. A plurality of vortex generators is mounted relative to at least one of the plurality of surfaces of the fuselage and the plurality of surface portions of the rotor assembly. The plurality of vortex generators operate to disrupt a boundary layer of air flowing over the one of the plurality of surfaces and the plurality of surface portions to reduce drag on the one of the fuselage and the rotor assembly.Type: ApplicationFiled: September 14, 2016Publication date: June 22, 2017Inventors: Patrick Bowles, Barbara Brenda Botros, ByungYoung Min, Claude G. Matalanis, Brian E. Wake
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Publication number: 20170096212Abstract: A rotor hub fairing system for use in a counter-rotating, coaxial rotor system is provided including an upper hub fairing defined about an axis and a lower hub fairing defined about the axis. A shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The geometry of the shaft fairing is configured to encourage a wake adjacent the upper hub fairing to form collectively with a wake adjacent the lower hub fairing.Type: ApplicationFiled: July 11, 2016Publication date: April 6, 2017Inventors: Razvan Virgil Florea, Patrick Bowles, Barbara Brenda Botros, ByungYoung Min, Claude G. Matalanis, Brian E. Wake
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Patent number: 9407121Abstract: An electromechanical rotary actuator including a housing including first end that extends to a second end through an intermediate portion that defines a longitudinal axis, and an internal cavity. An electric motor is arranged within the internal cavity. The electric motor includes a shaft having first shaft end and a second shaft end. A drive member is arranged within the housing along the longitudinal axis. The drive member includes an input shaft operatively coupled to the first shaft end and an output shaft. An output shaft member is coupled to the output shaft of the drive member. At least one bearing assembly supports one of the output shaft member and the first shaft end, and a preload member is arranged within the housing and configured to apply a compressive axial force to the at least one bearing, the drive member and the electric motor.Type: GrantFiled: May 31, 2012Date of Patent: August 2, 2016Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: Claude G. Matalanis, Andrzej Ernest Kuczek, Ulf J. Jonsson, Brian E. Wake, Zaffir A. Chaudhry, Paul Brewer
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Patent number: 9291101Abstract: A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse. The inlet duct has a surface defining the second ellipse which curves away from the first ellipse, such that the second ellipse is larger at an intermediate location. The second ellipse is even larger at a downstream end of the inlet duct leading into a fan.Type: GrantFiled: February 20, 2014Date of Patent: March 22, 2016Assignee: United Technologies CorporationInventors: Razvan Virgil Florea, Claude G. Matalanis, Mark B. Stucky
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Patent number: 9278755Abstract: A rotor blade assembly includes a rotor blade including one or more pockets and a housing located on the rotor blade within one or more pockets. The housing is secured to the rotor blade via one or more dovetail joints. A drive mechanism for a control surface of a rotor blade includes an actuator and a rocker operably connected to the actuator. At least one hinge rod is operably connected to the rocker and operably connected to a control surface at a control surface pivot. The drive mechanism translates substantially linear motion of the actuator into rotational motion of the control surface about the control surface pivot.Type: GrantFiled: February 11, 2011Date of Patent: March 8, 2016Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Claude G. Matalanis, Andrzej Ernest Kuczek, Zaffir A. Chaudhry, Brian E. Wake, Vijaya Ramaraju Lakamraju, Alan Matthew Finn, Fanping Sun, Ulf J. Jonsson
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Patent number: 9203459Abstract: A rotary wing aircraft includes a rotor assembly includes a rotor sensor generating a rotor sensor time domain signal; a rotor transform module converting the rotor sensor time domain signal to a rotor sensor frequency domain signal; and a rotor transceiver for transmitting the rotor sensor frequency domain signal over a transfer medium; an airframe assembly including: an airframe transceiver receiving the rotor sensor frequency domain signal; and an airframe transform module converting the rotor sensor frequency domain signal to the rotor sensor time domain signal. Signals from the airframe assembly may also be converted to the frequency domain prior to transfer over the transfer medium to the rotor assembly.Type: GrantFiled: April 18, 2013Date of Patent: December 1, 2015Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Harshad S. Sane, Claude G. Matalanis, Derek Geiger, Donald W. Fowler