Patents by Inventor Heinz Lippitsch
Heinz Lippitsch 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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Publication number: 20080027620Abstract: A propulsion assembly for propelling an aircraft is disclosed. The assembly includes a four stroke internal combustion engine, a propeller shaft that is operatively connected to the engine, and an electronic control unit that is connected to the engine and is configured to monitor and control at least one operating parameter of the engine. The engine includes two to twelve cylinders having a total displacement of less than 19.6 liters, and a crankshaft that is operatively connected to the cylinders. The crankshaft rotates at a speed of at least 3,000 rpm when the engine is operating under normal conditions. The engine also includes a closed loop liquid cooling system and a fuel injection system. The engine has a total power output of 140 to 600 hp, and a total wet installed weight of less than 1.1 kg/hp. The engine meets current RTCA DO-160d, RTCA DO-178b, and US FAA FAR33 guidelines.Type: ApplicationFiled: February 26, 2007Publication date: January 31, 2008Applicant: BRP-ROTAX GMBH & CO. KGInventors: Josef Feuerlinger, Heinz Lippitsch, Johann Bayerl
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Publication number: 20060214054Abstract: A propulsion assembly for propelling an aircraft is disclosed. The assembly includes a four stroke internal combustion engine, a propeller shaft that is operatively connected to the engine, and an electronic control unit that is connected to the engine and is configured to monitor and control at least one operating parameter of the engine. The engine includes two to twelve cylinders having a total displacement of less than 19.6 liters, and a crankshaft that is operatively connected to the cylinders. The crankshaft rotates at a speed of at least 3,000 rpm when the engine is operating under normal conditions. The engine also includes a closed loop liquid cooling system and a fuel injection system. The engine has a total power output of 140 to 600 hp, and a total wet installed weight of less than 1.1 kg/hp. The engine meets current RTCA DO-160d, RTCA DO-178b, and US FAA FAR33 guidelines.Type: ApplicationFiled: January 26, 2006Publication date: September 28, 2006Applicant: BRP-Rotax GmbH & Co. KGInventors: Josef Fuerlinger, Heinz Lippitsch, Johann Bayerl
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Publication number: 20050254948Abstract: An aircraft control system includes a propeller governor in which a motor is used to apply a compression force on a speeder spring, and a turbocharger in which a motor is used to actuate a needle valve associated with a diaphragm cell. An electronic control unit may be used to control the motor in the propeller governor and the motor in the turbocharger. The integration of the propeller governor and the turbocharger into a single control system decreases the number of individual adjustments that must be performed manually by the pilot.Type: ApplicationFiled: June 29, 2005Publication date: November 17, 2005Applicant: Bombardier-Rotax GmbH & Co. KGInventors: Thomas Koch, Heinz Lippitsch, Johann Bayerl, Manfred Moseneder, Gerald Mayr
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Patent number: 6938418Abstract: An aircraft control system includes a propeller governor in which a stepper motor is used to apply a compression force on a speeder spring, and a turbocharger in which a stepper motor is used to actuate a needle valve associated with a diaphragm cell. An electronic control unit may be used to control the stepper motor in the propeller governor and the stepper motor in the turbocharger. The integration of the propeller governor and the turbocharger into a single control system decreases the number of individual adjustments that must be performed manually by the pilot.Type: GrantFiled: August 8, 2003Date of Patent: September 6, 2005Assignee: BRP-Rotax GmbH & Co. KGInventors: Thomas Koch, Heinz Lippitsch, Johann Bayerl, Manfred Moseneder, Gerald Mayr
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Publication number: 20050132984Abstract: A propulsion assembly for propelling an aircraft is disclosed. The assembly includes a four stroke internal combustion engine, a propeller shaft that is operatively connected to the engine, and an electronic control unit that is connected to the engine and is configured to monitor and control at least one operating parameter of the engine. The engine includes two to twelve cylinders having a total displacement of less than 19.6 liters, and a crankshaft that is operatively connected to the cylinders. The crankshaft rotates at a speed of at least 3,000 rpm when the engine is operating under normal conditions. The engine also includes a closed loop liquid cooling system and a fuel injection system. The engine has a total power output of 140 to 600 hp, and a total wet installed weight of less than 1.1 kg/hp. The engine meets current RTCA DO-160d, RTCA DO-178b, and US FAA FAR33 guidelines.Type: ApplicationFiled: May 14, 2004Publication date: June 23, 2005Inventors: Josef Fuerlinger, Heinz Lippitsch, Johann Bayerl
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Publication number: 20040025505Abstract: An aircraft control system includes a propeller governor in which a stepper motor is used to apply a compression force on a speeder spring, and a turbocharger in which a stepper motor is used to actuate a needle valve associated with a diaphragm cell. An electronic control unit may be used to control the stepper motor in the propeller governor and the stepper motor in the turbocharger. The integration of the propeller governor and the turbocharger into a single control system decreases the number of individual adjustments that must be performed manually by the pilot.Type: ApplicationFiled: August 8, 2003Publication date: February 12, 2004Applicant: Bombardier-Rotax GmbH & Co. KGInventors: Thomas Koch, Heinz Lippitsch, Johann Bayerl, Manfred Moseneder, Gerald Mayr
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Patent number: 6637202Abstract: An aircraft control system includes a propeller governor in which a stepper motor is used to apply a compression force on a speeder spring, and a turbocharger in which a stepper motor is used to actuate a needle valve associated with a diaphragm cell. An electronic control unit may be used to control the stepper motor in the propeller governor and the stepper motor in the turbocharger. The integration of the propeller governor and the turbocharger into a single control system decreases the number of individual adjustments that must be performed manually by the pilot.Type: GrantFiled: March 16, 2002Date of Patent: October 28, 2003Assignee: Bombardier-Rotax GmbH & Co. KGInventors: Thomas Koch, Heinz Lippitsch, Johann Bayerl, Manfred Moseneder, Gerald Mayr
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Publication number: 20020088225Abstract: An aircraft control system includes a propeller governor in which a stepper motor is used to apply a compression force on a speeder spring, and a turbocharger in which a stepper motor is used to actuate a needle valve associated with a diaphragm cell. An electronic control unit may be used to control the stepper motor in the propeller governor and the stepper motor in the turbocharger. The integration of the propeller governor and the turbocharger into a single control system decreases the number of individual adjustments that must be performed manually by the pilot.Type: ApplicationFiled: March 16, 2002Publication date: July 11, 2002Inventors: Thomas Koch, Heinz Lippitsch, Johann Bayerl, Manfred Moseneder, Gerald Mayr
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Patent number: 6253726Abstract: A crankcase (1) is described for a combustion engine with cylinders arranged in V formation that is divided into two parts (2, 3) along a plane of separation (4) going through the axis of the crankshaft (6), such halves connected with each other by means of bearing screws (9) at right angles to the plane of separation (4) on either side of the crankshaft bearing (7), and by means of cylindrical adapters (12), which lock into fitting drill holes (13) provided between the two case halves (2, 3). In order to achieve beneficial construction conditions, it is proposed that the adapters (12) running parallel to the axis of the crankshaft (6) lie in the plane of separation (4) and are each penetrated by one bearing screw (9). In a second embodiment, the adapters (12) are positioned between two of the bearing screws (9) on each side of the crankshaft bearing (7).Type: GrantFiled: May 8, 2000Date of Patent: July 3, 2001Assignee: Bombardier-Rotax GmbHInventors: Heinz Lippitsch, Thomas Koch, Karl Glinsner