Patents by Inventor Bernard Gemmati

Bernard Gemmati 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).

  • Patent number: 10196130
    Abstract: An adjustable and rotary rudder bar for a rotary wing aircraft. The rudder bar comprises a pedal bar, a main body, two pedals connected to the pedal bar on either side of the main body, a slider device enabling the pedal bar to slide relative to the main body, a structure fastened to a floor of the aircraft, and a shaft having a first axis (A1). The shaft is secured to the main body, and the main body is movable in turning relative to the structure about the first axis (A1) thus causing the main body, the pedal bar, and the pedals to turn simultaneously.
    Type: Grant
    Filed: July 26, 2016
    Date of Patent: February 5, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventors: Bernard Gemmati, Florian Feugas, Christophe Pujol
  • Publication number: 20170029092
    Abstract: An adjustable and rotary rudder bar for a rotary wing aircraft. The rudder bar comprises a pedal bar, a main body, two pedals connected to the pedal bar on either side of the main body, a slider device enabling the pedal bar to slide relative to the main body, a structure fastened to a floor of the aircraft, and a shaft having a first axis (A1). The shaft is secured to the main body, and the main body is movable in turning relative to the structure about the first axis (A1) thus causing the main body, the pedal bar, and the pedals to turn simultaneously.
    Type: Application
    Filed: July 26, 2016
    Publication date: February 2, 2017
    Inventors: Bernard GEMMATI, Florian FEUGAS, Christophe PUJOL
  • Patent number: 8967524
    Abstract: A hydraulic control valve (10) provided with at least one body (11) having a jacket (12) with a feed orifice (13). The hydraulic control valve (10) has a transfer rod (15) provided with at least one fluid transfer duct (16), at least one orifice (17) present inside the jacket (12), and a second orifice (18) arranged outside the jacket (12). The jacket (12) has a feed chamber (25) connected to said feed orifice (13) and a main fluid-return chamber (30) connected to discharge means (50) for discharging the fluid, control means (20) being secured to the jacket (12) in order to move the jacket (12) in translation relative to said transfer rod (15) so as to control the flow of fluid within said transfer rod (15).
    Type: Grant
    Filed: June 6, 2013
    Date of Patent: March 3, 2015
    Assignee: Airbus Helicopters
    Inventors: Maxime Leclercq, Bernard Gemmati, Philippe Veron, Francois Malburet
  • Publication number: 20140353433
    Abstract: A fly-by-wire control mechanism for a rotorcraft, the mechanism comprising a stick (1) hinged to tilt in multiple directions on a support (2), detector means (6) for detecting the tilting position of the stick (1) and generating electrical signals (7), and force feedback means providing the pilot with a sensation of forces (12) opposing tilting of the stick (1). The stick (1) includes a rod (13) having its distal end held in fixed manner in the support (2), while providing a movable mount for the stick (1) on the support (2). Causing the stick (1) to tilt leads to flexing of the rod (13) from its anchor zone (16) in the support (2), with the resistance of the rod (13) to flexing deformation serving to develop the opposing forces (12) and also being measured in order to generate the electrical signals (7).
    Type: Application
    Filed: May 28, 2014
    Publication date: December 4, 2014
    Applicant: AIRBUS HELICOPTERS
    Inventors: Bernard GEMMATI, Brice LEBERNICHEUX, Jean-Evrard BRUNEL
  • Patent number: 8684314
    Abstract: For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a centering rod (22) to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant (25) forms a bearing point for the series actuator (21), so that an emergency control actuate a airfoil surface (11).
    Type: Grant
    Filed: March 12, 2012
    Date of Patent: April 1, 2014
    Assignees: Airbus Helicopters, Airbus Helicopter Deutschland GmbH
    Inventors: Bruno Chaduc, Patrick Hellio, Bernard Gemmati, Karsten Krok
  • Publication number: 20140003941
    Abstract: A hydraulic control valve (10) provided with at least one body (11) having a jacket (12) with a feed orifice (13). The hydraulic control valve (10) has a transfer rod (15) provided with at least one fluid transfer duct (16), at least one orifice (17) present inside the jacket (12), and a second orifice (18) arranged outside the jacket (12). The jacket (12) has a feed chamber (25) connected to said feed orifice (13) and a main fluid-return chamber (30) connected to discharge means (50) for discharging the fluid, control means (20) being secured to the jacket (12) in order to move the jacket (12) in translation relative to said transfer rod (15) so as to control the flow of fluid within said transfer rod (15).
    Type: Application
    Filed: June 6, 2013
    Publication date: January 2, 2014
    Inventors: Maxime Leclercq, Bernard Gemmati, Philippe Veron, Francois Malburet
  • Patent number: 8540184
    Abstract: The present invention relates to an aircraft (1) comprising an airframe (2) provided with a fuselage (10) and fixed wings (20), a rotary wing (30), at least two propellers (41, 42), and a power plant suitable for driving said rotary wing (30) and said propellers (41, 42) into rotation.
    Type: Grant
    Filed: November 16, 2010
    Date of Patent: September 24, 2013
    Assignee: Eurocopter
    Inventor: Bernard Gemmati
  • Patent number: 8393569
    Abstract: A breakable coupling device for coupling together first and second main transmission shafts stationary in translation along a longitudinal axis of rotation of the device comprises a blocking device having a discontinuous first housing and a continuous second housing forming a closed loop; a compression device; at least one drive device connecting the blocking device and the compression device together in rotation about the longitudinal axis below a predetermined torque, wherein the discontinuous first housing is configured to receive the at least one drive device below the predetermined torque; and a shifting device configured to shift the at least one drive device non-reversibly from the discontinuous first housing towards the continuous second housing when the torque exerted on the at least one drive device is greater than the predetermined torque.
    Type: Grant
    Filed: May 19, 2009
    Date of Patent: March 12, 2013
    Assignee: Eurocopter
    Inventors: Bernard Gemmati, Philippe Vincent, Romuald Biest
  • Patent number: 8376266
    Abstract: A method of controlling the yaw attitude of a hybrid helicopter including a fuselage and an additional lift surface provided with first and second half-wings extending from either side of the fuselage, each half-wing being provided with a respective first or second propeller. The hybrid helicopter has a thrust control suitable for modifying the first pitch of the first blades of the first propeller and the second pitch of the second blades of the second propeller by the same amount. The hybrid helicopter includes yaw control elements for generating an original order for modifying the yaw attitude of the hybrid helicopter by increasing the pitch of the blades of one propeller and decreasing the pitch of the blades of the other propeller, the original order is optimized as a function of the position of the thrust control to obtain an optimized yaw control order that is applied to the first and second blades.
    Type: Grant
    Filed: May 5, 2010
    Date of Patent: February 19, 2013
    Assignee: Eurocopter
    Inventors: Bernard Gemmati, Nicolas Queiras, Paul Eglin
  • Patent number: 8282035
    Abstract: The present invention relates to a mechanical device (1) suitable for combining first and second pitch control orders for controlling the blade pitch of at least one rotary assembly, the device comprising a carrier structure (10) suitable for being fastened to a support (5) by at least one main fastener pin (13) about which said carrier structure (10) is capable of performing a pivoting movement. In addition, the device includes at least one connection lever (20, 30) per rotary assembly, and at least one secondary fastener pin (25, 35) per connection lever (20, 30), said secondary fastener pin (25, 35) being secured firstly to said carrier structure (10) and being fastened secondly by rotary means (26, 36) to the connection lever (20, 30).
    Type: Grant
    Filed: June 2, 2010
    Date of Patent: October 9, 2012
    Assignee: Eurocopter
    Inventors: Bernard Gemmati, Romuald Biest, Guillaume Franchini
  • Publication number: 20120241563
    Abstract: For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a centering rod (22) to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant (25) forms a bearing point for the series actuator (21), so that an emergency control actuate a airfoil surface (11).
    Type: Application
    Filed: March 12, 2012
    Publication date: September 27, 2012
    Applicants: EUROCOPTER DEUTSCHLAND GMBH, EUROCOPTER
    Inventors: Bruno Chaduc, Patrick Hellio, Bernard Gemmati, Karsten Krok
  • Patent number: 8240617
    Abstract: The present invention relates to haptic feedback for operating at least one manual flight control device (21) for controlling the cyclic pitch of the blades (5) of a rotary wing (4) of a hybrid helicopter (1) via power assistance (27). Said operations of said control device (21) are defined according to a predetermined damping force relationship (A) that is a function of an instantaneous load factor of the hybrid helicopter (1) in such a manner that the instantaneous load factor is maintained between its minimum and maximum limit values in proportion to a position of a thrust control member (20) between its minimum and maximum thrust values (23, 22).
    Type: Grant
    Filed: July 15, 2010
    Date of Patent: August 14, 2012
    Assignee: Eurocopter
    Inventors: Romuald Biest, Bernard Gemmati, Julien Pruss
  • Patent number: 8196857
    Abstract: The present invention relates to a bellcrank (40) for a flight-attitude-changing linkage (27, 25A, 28A) of the variable gain type. The linkage (27, 25A, 28A) connects a manual flight control device of a rotary wing aircraft (1), e.g. a hybrid helicopter, to at least one airfoil of said aircraft (1) suitable for causing a change in flight attitude. Said bellcrank (40) includes first and second sliders (50, 52). Said first slider (50) is connected to a movable portion (57, 61) of a setpoint flight-attitude-changing linkage (24) that delivers a setpoint, with movements of said linkage causing the gain of said variable-gain linkage (27, 25A, 28A) to be adjusted, which gain is proportional to the position of said movable portion (57, 61).
    Type: Grant
    Filed: June 1, 2010
    Date of Patent: June 12, 2012
    Assignee: Eurocopter
    Inventors: Bernard Gemmati, Romuald Biest, Carine Mirman
  • Patent number: 8181550
    Abstract: A rotary actuator incorporating a force relationship includes a twistably-deformable structure having a first and a second end plate and a helical spring with a first and a second terminal end secured on the first and the second end plate, respectively, and wherein the first and the second end plate have a first and a second notch, respectively, and wherein the first and the second notch have a first and a second contact zone, respectively. The rotary actuator further includes an outlet shaft and a motor assembly having an outlet gear configured to drive the twistably-deformable structure so as to drive the outlet shaft in rotation, wherein the motor assembly, the twistably-deformable structure and the outlet shaft are disposed in succession. The rotary actuator has a first finger constrained to rotate with the outlet gear and a second finger constrained to rotate with the outlet shaft.
    Type: Grant
    Filed: November 20, 2009
    Date of Patent: May 22, 2012
    Assignee: Eurocopter
    Inventors: Bernard Gemmati, Romuald Biest
  • Patent number: 7969110
    Abstract: The invention relates to an actuator having an (auto)synchronous rotary electric motor and a reversible speed-reducing gearbox coupled to the motor to be driven in rotation thereby An outlet shaft is coupled to the speed-reducing gearbox to be driven in rotation thereby A first angular position sensor and a control circuit are connected to the motor. The circuit delivers a motor power supply signal that varies as a function of a position setpoint signal applied to the control circuit and as a function of signals delivered by the angular position sensor. The gearbox has a plurality of speed-reducing each having a pair of gears mounted to rotate about two parallel axes of rotation.
    Type: Grant
    Filed: September 8, 2008
    Date of Patent: June 28, 2011
    Assignee: Eurocopter
    Inventors: Philippe Vincent, S├ębastien Pellegrino, Bernard Gemmati
  • Patent number: 7946536
    Abstract: The present invention relates to a device for interconnecting first and second control sticks (1, 2) for controlling an aircraft in roll and in pitch, the device comprising a pitch interlinking shaft (20) and roll interlinking means (10) respectively for interlinking the first and second control sticks (1, 2) during pitch movements and/or during roll movements. The device is remarkable in that the roll interlinking means (10) are arranged inside the pitch interlinking shaft (20).
    Type: Grant
    Filed: July 18, 2007
    Date of Patent: May 24, 2011
    Assignee: Eurocopter
    Inventor: Bernard Gemmati
  • Publication number: 20110114798
    Abstract: The present invention relates to an aircraft (1) comprising an airframe (2) provided with a fuselage (10) and fixed wings (20), a rotary wing (30), at least two propellers (41, 42), and a power plant suitable for driving said rotary wing (30) and said propellers (41, 42) into rotation.
    Type: Application
    Filed: November 16, 2010
    Publication date: May 19, 2011
    Applicant: EUROCOPTER
    Inventor: Bernard Gemmati
  • Publication number: 20110024551
    Abstract: The present invention relates to haptic feedback for operating at least one manual flight control device (21) for controlling the cyclic pitch of the blades (5) of a rotary wing (4) of a hybrid helicopter (1) via power assistance (27). Said operations of said control device (21) are defined according to a predetermined damping force relationship (A) that is a function of an instantaneous load factor of the hybrid helicopter (1) in such a manner that the instantaneous load factor is maintained between its minimum and maximum limit values in proportion to a position of a thrust control member (20) between its minimum and maximum thrust values (23, 22).
    Type: Application
    Filed: July 15, 2010
    Publication date: February 3, 2011
    Applicant: EUROCOPTER
    Inventors: Romuald Biest, Bernard Gemmati, Julien Pruss
  • Publication number: 20100308178
    Abstract: The present invention relates to a bellcrank (40) for a flight-attitude-changing linkage (27, 25A, 28A) of the variable gain type. The linkage (27, 25A, 28A) connects a manual flight control device of a rotary wing aircraft (1), e.g. a hybrid helicopter, to at least one airfoil of said aircraft (1) suitable for causing a change in flight attitude. Said bellcrank (40) includes first and second sliders (50, 52). Said first slider (50) is connected to a movable portion (57, 61) of a setpoint flight-attitude-changing linkage (24) that delivers a setpoint, with movements of said linkage causing the gain of said variable-gain linkage (27, 25A, 28A) to be adjusted, which gain is proportional to the position of said movable portion (57, 61).
    Type: Application
    Filed: June 1, 2010
    Publication date: December 9, 2010
    Applicant: EUROCOPTER
    Inventors: Bernard Gemmati, Romuald Biest, Carine Mirman
  • Publication number: 20100308157
    Abstract: The present invention relates to a mechanical device (1) suitable for combining first and second pitch control orders for controlling the blade pitch of at least one rotary assembly, the device comprising a carrier structure (10) suitable for being fastened to a support (5) by at least one main fastener pin (13) about which said carrier structure (10) is capable of performing a pivoting movement. In addition, the device includes at least one connection lever (20, 30) per rotary assembly, and at least one secondary fastener pin (25, 35) per connection lever (20, 30), said secondary fastener pin (25, 35) being secured firstly to said carrier structure (10) and being fastened secondly by rotary means (26, 36) to the connection lever (20, 30).
    Type: Application
    Filed: June 2, 2010
    Publication date: December 9, 2010
    Applicant: EUROCOPTER
    Inventors: Bernard Gemmati, Romuald Biest, Guillaume Franchini