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8 条记录 (耗时 0.015 秒)

    Piston Type Aircraft Engine
    1.
    发明申请
    Piston Type Aircraft Engine 审中-公开
    活塞式飞机发动机

    公开(公告)号：US20080027620A1

    公开(公告)日：2008-01-31

    申请号：US11679130

    申请日：2007-02-26

    申请人： Josef Feuerlinger ,  Heinz Lippitsch ,  Johann Bayerl

    发明人： Josef Feuerlinger ,  Heinz Lippitsch ,  Johann Bayerl

    IPC分类号： B64D27/00

    CPC分类号： F02B75/22 ,  B64D27/04 ,  F02B37/00 ,  F02B61/04 ,  F02B2075/027 ,  F02M63/0295 ,  F16F15/173 ,  Y02T10/144 ,  Y02T50/44 ,  Y10T74/2184

    摘要： 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.

    摘要翻译： 公开了一种用于推进飞行器的推进组件。 组件包括四冲程内燃机，可操作地连接到发动机的螺旋桨轴和连接到发动机并被配置为监测和控制发动机的至少一个操作参数的电子控制单元。 发动机包括总共位移小于19.6升的两至十二个气缸，以及可操作地连接到气缸的曲轴。 当发动机在正常条件下运行时，曲轴以至少3,000rpm的速度旋转。 发动机还包括闭环液体冷却系统和燃料喷射系统。 发动机的总功率输出为140至600马力，总湿重小于1.1 kg / hp。 发动机符合当前的RTCA DO-160d，RTCA DO-178b和美国FAA FAR33指南。

    Piston type aircraft engine
    2.
    发明申请
    Piston type aircraft engine 审中-公开
    活塞式飞机发动机

    公开(公告)号：US20050132984A1

    公开(公告)日：2005-06-23

    申请号：US10845585

    申请日：2004-05-14

    申请人： Josef Fuerlinger ,  Heinz Lippitsch ,  Johann Bayerl

    发明人： Josef Fuerlinger ,  Heinz Lippitsch ,  Johann Bayerl

    IPC分类号： B64D27/04 ,  F16F15/173 ,  F02B75/22

    CPC分类号： F02B75/22 ,  B64D27/04 ,  F02B37/00 ,  F02B61/04 ,  F02B2075/027 ,  F02M63/0295 ,  F16F15/173 ,  Y02T10/144 ,  Y02T50/44 ,  Y10T74/2184

    摘要： 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.

    摘要翻译： 公开了一种用于推进飞行器的推进组件。 组件包括四冲程内燃机，可操作地连接到发动机的螺旋桨轴和连接到发动机并被配置为监测和控制发动机的至少一个操作参数的电子控制单元。 发动机包括总共位移小于19.6升的两至十二个气缸，以及可操作地连接到气缸的曲轴。 当发动机在正常条件下运行时，曲轴以至少3,000rpm的速度旋转。 发动机还包括闭环液体冷却系统和燃料喷射系统。 发动机的总功率输出为140至600马力，总湿重小于1.1 kg / hp。 发动机符合当前的RTCA DO-160d，RTCA DO-178b和美国FAA FAR33指南。

    Piston type aircraft engine
    3.
    发明申请
    Piston type aircraft engine 审中-公开
    活塞式飞机发动机

    公开(公告)号：US20060214054A1

    公开(公告)日：2006-09-28

    申请号：US11339847

    申请日：2006-01-26

    申请人： Josef Fuerlinger ,  Heinz Lippitsch ,  Johann Bayerl

    发明人： Josef Fuerlinger ,  Heinz Lippitsch ,  Johann Bayerl

    IPC分类号： B64D33/00 ,  B64D33/10

    CPC分类号： F02B75/22 ,  B64D27/04 ,  F02B37/00 ,  F02B61/04 ,  F02B2075/027 ,  F02M63/0295 ,  F16F15/173 ,  Y02T10/144 ,  Y02T50/44 ,  Y10T74/2184

    摘要： 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.

    摘要翻译： 公开了一种用于推进飞行器的推进组件。 组件包括四冲程内燃机，可操作地连接到发动机的螺旋桨轴和连接到发动机并被配置为监测和控制发动机的至少一个操作参数的电子控制单元。 发动机包括总共位移小于19.6升的两至十二个气缸，以及可操作地连接到气缸的曲轴。 当发动机在正常条件下运行时，曲轴以至少3,000rpm的速度旋转。 发动机还包括闭环液体冷却系统和燃料喷射系统。 发动机的总功率输出为140至600马力，总湿重小于1.1 kg / hp。 发动机符合当前的RTCA DO-160d，RTCA DO-178b和美国FAA FAR33指南。

    Pop-off valve for an aircraft engine having a turbocharger control system and propeller control system by stepper motor
    7.
    发明授权
    Pop-off valve for an aircraft engine having a turbocharger control system and propeller control system by stepper motor 失效
    具有涡轮增压器控制系统和通过步进电机的螺旋桨控制系统的飞机发动机的弹出阀

    公开(公告)号：US07086230B2

    公开(公告)日：2006-08-08

    申请号：US10787247

    申请日：2004-02-27

    申请人： Johann Bayerl

    发明人： Johann Bayerl

    IPC分类号： F02B33/44 ,  F02B37/00 ,  F02B37/10 ,  F02B77/00 ,  F02B37/16 ,  F02D23/00 ,  F02D23/02 ,  F16K17/04 ,  F03D1/00

    CPC分类号： B64C11/303 ,  F02B37/183 ,  F02B37/186

    摘要： A pop-off valve that, in one embodiment, provides overboost protection for an aircraft engine, is described. The pop-off valve includes a housing adapted for connection to a portion of a drive device containing a pressure medium. It also includes a pressure body movably disposed in the housing such that, in operation, a first side of the pressure body is exposed to the pressure medium while a second side is exposed to a reference force. In addition, the pop-off valve incorporates a control device adapted to receive at least one signal concerning at least one operating parameter of the drive device and, in response to the operating parameter signal, to control the reference force. As a result of movement of the pressure body within the housing, at least one first opening in the housing is exposed, permitting venting of the pressure medium.

    摘要翻译： 描述了在一个实施例中为飞机发动机提供过载保护的弹出阀。 弹出阀包括适于连接到包含压力介质的驱动装置的一部分的壳体。 它还包括可移动地设置在壳体中的压力体，使得在操作中，压力体的第一侧暴露于压力介质，而第二侧暴露于参考力。 此外，弹出阀包括适于接收关于驱动装置的至少一个操作参数的至少一个信号并且响应于操作参数信号来控制参考力的控制装置。 由于压力体在壳体内移动，壳体中的至少一个第一开口被暴露，允许压力介质的排放。

    Vibration damper for aircraft engine
    8.
    发明授权
    Vibration damper for aircraft engine 失效
    飞机发动机减振器

    公开(公告)号：US06883752B2

    公开(公告)日：2005-04-26

    申请号：US10071233

    申请日：2002-02-11

    申请人： Thomas Koch ,  Johann Bayerl

    发明人： Thomas Koch ,  Johann Bayerl

    IPC分类号： B64D27/04 ,  F16F15/173 ,  B64D35/00

    CPC分类号： F02B75/22 ,  B64D27/04 ,  F02B37/00 ,  F02B61/04 ,  F02B2075/027 ,  F02M63/0295 ,  F16F15/173 ,  Y02T10/144 ,  Y02T50/44 ,  Y10T74/2184

    摘要： An internal combustion engine for an aircraft is described. The internal combustion engine includes a crankshaft defining first and second ends, a propeller, and a transmission disposed between the first end of the crankshaft and the propeller, operatively connecting the propeller to the crankshaft. A torsion bar is disposed between the first end of the crankshaft and the transmission, operatively connecting the crankshaft to the transmission. A torsional vibration damper is operatively connected at one of the first and the second ends of the crankshaft.

    摘要翻译： 描述了一种用于飞行器的内燃机。 内燃机包括限定第一和第二端的曲轴，螺旋桨和布置在曲轴的第一端和螺旋桨之间的变速器，其将螺旋桨可操作地连接到曲轴。 扭杆设置在曲轴的第一端和变速器之间，可操作地将曲轴连接到变速器。 扭转振动阻尼器可操作地连接在曲轴的第一端和第二端中的一端。