Patents by Inventor Jean-Philippe Pineau
Jean-Philippe Pineau 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: 10724915Abstract: A static pressure measurement probe system comprises: a base to be fixed onto the cockpit of an aircraft; at least one local pressure tapping formed through the base and coupled to a pressure measurement sensor; for each local pressure tapping, at least two assemblies each comprising an optical window that is transparent to a laser radiation and a laser anemometry probe configured to take anemometry measurements in an imaginary cylinder centred on the local pressure tapping and of a diameter less than 3 cm and of a height less than 4 cm counted from the outer end of the local pressure tapping, so that the measurements are within the airflow limit layer.Type: GrantFiled: May 25, 2018Date of Patent: July 28, 2020Assignee: THALESInventors: Jean-Pierre Schlotterbeck, Jean-Philippe Pineau
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Patent number: 10472074Abstract: The invention relates to an aircraft provided with at least one piece of aeronautic equipment fastened to the outside skin of the aircraft and a heater for heating the piece of aeronautic equipment. The heater is in the form of a thermodynamic closed circuit loop circulating heat-transfer fluid and including an evaporator and a heat source located inside the aircraft and a condenser located in the piece of aeronautic equipment or an appendage thereto. Fasteners in the form of tubular tabs include tubular channels for circulating the heat-transfer fluid.Type: GrantFiled: July 27, 2016Date of Patent: November 12, 2019Assignee: THALESInventors: Adrien Desjardins, Frederic Martin, Claude Sarno, Romain Hodot, Jean-Philippe Pineau
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Patent number: 10329024Abstract: A heater of a piece of aeronautic equipment is intended to be arranged at the skin of an aircraft. The equipment includes a part intended to be arranged at the skin of the aircraft and elements for heating the part. The heating element include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section. At least part of the equipment is made from a material with a low heat conductivity.Type: GrantFiled: July 27, 2016Date of Patent: June 25, 2019Assignee: THALESInventors: Romain Hodot, Claude Sarno, Frederic Martin, Jean-Philippe Pineau
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Patent number: 10183753Abstract: A piece of aeronautic equipment intended to equip an aircraft, the equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (25a) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.Type: GrantFiled: July 27, 2016Date of Patent: January 22, 2019Assignee: THALESInventors: Jean-Philippe Pineau, Claude Sarno, Romain Hodot, Frederic Martin
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Publication number: 20180356309Abstract: A static pressure measurement probe system comprises: a base to be fixed onto the cockpit of an aircraft; at least one local pressure tapping formed through the base and coupled to a pressure measurement sensor; for each local pressure tapping, at least two assemblies each comprising an optical window that is transparent to a laser radiation and a laser anemometry probe configured to take anemometry measurements in an imaginary cylinder centred on the local pressure tapping and of a diameter less than 3 cm and of a height less than 4 cm counted from the outer end of the local pressure tapping, so that the measurements are within the airflow limit layer.Type: ApplicationFiled: May 25, 2018Publication date: December 13, 2018Inventors: Jean-Pierre SCHLOTTEBECK, Jean-Philippe PINEAU
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Patent number: 9975639Abstract: A piece of aeronautic equipment intended to equip an aircraft, the equipment piece (25) including at least one part intended to be arranged at a skin (27) outside of the aircraft and heating elements for that part, which include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which condensation of the heat transfer fluid can occur in the appendage to heat it, outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section, at least the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base (120) for fastening on the skin of the aircraft from which support elements (130) for a Pitot tube (140) provided with lateral static pressure taps (150) extend.Type: GrantFiled: July 27, 2016Date of Patent: May 22, 2018Assignee: THALESInventors: Romain Hodot, Claude Sarno, Frederic Martin, Adrien Desjardins, Jean-Philippe Pineau
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Publication number: 20170029123Abstract: The invention relates to an aircraft provided with at least one piece of aeronautic equipment (100), the equipment comprising at least one part intended to be arranged at a skin (27) of the aircraft, and means for fastening on said skin outside the aircraft and means for heating the part, characterized in that the fastening means comprise means in the form of tubular tabs (101, 102), in that the heating means comprise a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates, the closed circuit comprising an evaporator associated with means forming a heat source arranged inside the aircraft and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section, at least partially formed in the tubular tabs (101, 102) of the fastening means.Type: ApplicationFiled: July 27, 2016Publication date: February 2, 2017Inventors: Adrien DESJARDINS, Frederic MARTIN, Claude SARNO, Romain HODOT, Jean-Philippe PINEAU
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Publication number: 20170029124Abstract: A piece of aeronautic equipment intended to equip an aircraft, the equipment piece (25) including at least one part intended to be arranged at a skin (27) outside of the aircraft and heating elements for that part, which include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which condensation of the heat transfer fluid can occur in the appendage to heat it, outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section, at least the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base (120) for fastening on the skin of the aircraft from which support elements (130) for a Pitot tube (140) provided with lateral static pressure taps (150) extend.Type: ApplicationFiled: July 27, 2016Publication date: February 2, 2017Inventors: Romain HODOT, Claude SARNO, Frederic MARTIN, Adrien DESJARDINS, Jean-Philippe PINEAU
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Publication number: 20170029120Abstract: A heating of a piece of aeronautic equipment intended to be arranged at the skin of the aircraft. The equipment (25) includes a part (30, 31) intended to be arranged at the skin (27) of the aircraft and elements for heating the part. The heating element include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel with an empty section. At least part of the equipment is made from a material with a low heat conductivity.Type: ApplicationFiled: July 27, 2016Publication date: February 2, 2017Inventors: Romain HODOT, Claude SARNO, Frederic MARTIN, Jean-Philippe PINEAU
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Publication number: 20170029122Abstract: A piece of aeronautic equipment intended to equip an aircraft, the equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (25a) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.Type: ApplicationFiled: July 27, 2016Publication date: February 2, 2017Inventors: Jean-Philippe PINEAU, Claude SARNO, Romain HODOT, Frederic MARTIN
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Patent number: 9116162Abstract: A probe for measuring the total pressure of a flow and a method for implementing the probe is provided. The probe is intended to be fitted in an aircraft. The probe comprises a Pitot tube and means for reheating the probe assembly. The probe also comprises means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow independently of the means for determining the average temperature of the probe. If the temperature delivered by the means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow is less than the first reference temperature, then an additional reheating of regions of the Pitot tube likely to accumulate particles conveyed by the flow is triggered.Type: GrantFiled: December 8, 2012Date of Patent: August 25, 2015Assignee: THALESInventors: Henri Leblond, Yves Jaulain, Jean-Philippe Pineau
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Patent number: 9021856Abstract: A device is provided for checking a flow pressure measurement probe as well as a probe comprising the device. The probe includes an internal volume and at least one orifice for communication with the outside of the volume. The device includes: an acoustic transmitter and an acoustic receiver that are intended to be connected to the internal volume so that the transmitter transmits an acoustic signal that propagates in the internal volume and so that the receiver picks up an observed acoustic signal; and, means for comparing the observed signal with a reference signal. The device may be a stand-alone device or may be integrated into the probe.Type: GrantFiled: May 9, 2011Date of Patent: May 5, 2015Assignee: ThalesInventors: Henri Leblond, Philippe Guichard, Jean-Philippe Pineau
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Patent number: 8397563Abstract: The invention relates to an aeronautical probe designed to be mounted on the skin of an aircraft and comprising a probe body protruding from the skin of the aircraft and a heater for de-icing an external surface of the probe body. According to the invention, the heater comprises two self-supporting electrodes and heating resistive elements. Each electrode is formed of an electrically insulating substrate and of an electrically active portion forming one face of the electrode in question. Each resistive element is in contact with the faces of the electrodes. The notable advantages of the invention are that it makes it possible to reduce the operating temperature of the resistive elements and the phenomena of fatigue in the mechanical link between the electrodes and the resistive elements due to different expansion coefficients.Type: GrantFiled: November 28, 2008Date of Patent: March 19, 2013Assignee: ThalesInventors: Jean-Philippe Pineau, Bernard Ledain
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Publication number: 20120118037Abstract: A device is provided for checking a flow pressure measurement probe as well as a probe comprising the device. The probe includes an internal volume and at least one orifice for communication with the outside of the volume. The device includes: an acoustic transmitter and an acoustic receiver that are intended to be connected to the internal volume so that the transmitter transmits an acoustic signal that propagates in the internal volume and so that the receiver picks up an observed acoustic signal; and, means for comparing the observed signal with a reference signal. The device may be a stand-alone device or may be integrated into the probe.Type: ApplicationFiled: May 9, 2011Publication date: May 17, 2012Applicant: THALESInventors: Henri LEBLOND, Philippe GUICHARD, Jean-Philippe PINEAU
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Publication number: 20110036160Abstract: The invention relates to an aeronautical probe designed to be mounted on the skin of an aircraft and comprising a probe body protruding from the skin of the aircraft and a heater for de-icing an external surface of the probe body. According to the invention, the heater comprises two self-supporting electrodes and heating resistive elements. Each electrode is formed of an electrically insulating substrate and of an electrically active portion forming one face of the electrode in question. Each resistive element is in contact with the faces of the electrodes. The notable advantages of the invention are that it makes it possible to reduce the operating temperature of the resistive elements and the phenomena of fatigue in the mechanical link between the electrodes and the resistive elements due to different expansion coefficients.Type: ApplicationFiled: November 28, 2008Publication date: February 17, 2011Applicant: THALESInventors: Jean-Philippe Pineau, Bernard Ledain
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Patent number: 7726993Abstract: The invention relates to a device for connecting an item of equipment and two cables, one of which carries electrical data and the other of which carries pneumatic data. The device comprises an electrical socket and a pneumatic socket, both mounted on an item of equipment, an electrical plug secured to a cable, the electrical plug being intended to be connected to the electrical socket, and a pneumatic plug secured to a cable, the pneumatic plug being intended to be connected to the pneumatic socket. According to the invention, when the pneumatic plug is in a connected but unlocked position, the electrical plug cannot be plugged in.Type: GrantFiled: November 30, 2005Date of Patent: June 1, 2010Assignee: ThalesInventors: Marc Simeon, Jean-Philippe Pineau, Jean-Claude Brizion
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Publication number: 20100015830Abstract: The invention relates to a device for connecting an item of equipment and two cables, one of which carries electrical data and the other of which carries pneumatic data. The device comprises an electrical socket and a pneumatic socket, both mounted on an item of equipment, an electrical plug secured to a cable, the electrical plug being intended to be connected to the electrical socket, and a pneumatic plug secured to a cable, the pneumatic plug being intended to be connected to the pneumatic socket. According to the invention, when the pneumatic plug is in a connected but unlocked position, the electrical plug cannot be plugged in.Type: ApplicationFiled: November 30, 2005Publication date: January 21, 2010Applicant: THALESInventors: Marc Simeon, Jean-Philippe Pineau, Jean-Claude Brizion