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。

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。