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    Piston type aircraft engine
    4.
    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
    5.
    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。

    Piston Type Aircraft Engine
    6.
    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。

    Crankcase for a combustion engine
    7.
    发明授权
    Crankcase for a combustion engine 有权
    用于内燃机的曲轴箱

    公开(公告)号：US06253726B1

    公开(公告)日：2001-07-03

    申请号：US09566946

    申请日：2000-05-08

    申请人： Heinz Lippitsch ,  Thomas Koch ,  Karl Glinsner

    发明人： Heinz Lippitsch ,  Thomas Koch ,  Karl Glinsner

    IPC分类号： F02F700

    CPC分类号： F16C9/02 ,  F02B75/22 ,  F02F7/0053

    摘要： 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).

    摘要翻译： 描述了一种用于内燃机的曲轴箱（1），其具有沿V形成的气缸，其沿着经过曲轴（6）的轴线的分离平面（4）分成两部分（2,3），这样的一半连接 彼此通过与曲轴轴承（7）的任一侧上的分离平面（4）成直角的轴承螺钉（9）和通过圆柱形适配器（12）彼此连接，所述适配器锁定到装配的钻孔中 13）设置在两个半壳体（2,3）之间。 为了实现有利的施工条件，提出平行于曲轴（6）的轴线延伸的适配器（12）位于分离平面（4）中，并且均由一个轴承螺钉（9）穿透。 在第二实施例中，适配器（12）位于曲轴轴承（7）的每一侧的两个轴承螺钉（9）之间。