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公开(公告)号：US07875989B2
公开(公告)日：2011-01-25
申请号：US11899053
申请日：2007-09-04
CPC分类号： H02J1/10 , H02J9/066 , Y10T307/344
摘要： An aircraft engine power distribution system for an aircraft engine controller, such as a FADEC, is provided where the power source is independent from the conventional airframe power system, without the need for a back-up battery. The aircraft engine power distribution system includes a magnetic generator operated by an aircraft engine. The aircraft engine power distribution system also includes a power distributor that rectifies the generator output and provides the rectified power to the engine controller as its primary source of power. In this configuration, as long as the aircraft engine is able to operate the magnetic generator, the engine controller receives power. Accordingly, the engine controller operates regardless of the operational status of the airframe power system.
摘要翻译： 提供用于飞机发动机控制器（例如FADEC）的飞机发动机配电系统，其中电源独立于常规的机身电力系统，而不需要备用电池。 飞机发动机配电系统包括由飞机发动机操作的磁力发电机。 飞机发动机配电系统还包括一个功率分配器，其对发电机输出进行整流，并将整流后的功率提供给发动机控制器作为其主要电源。 在这种配置中，只要飞机发动机能够操作磁力发电机，发动机控制器就会接收电力。 因此，无论机身电力系统的运行状态如何，发动机控制器都运行。
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公开(公告)号：US20090112440A1
公开(公告)日：2009-04-30
申请号：US11928293
申请日：2007-10-30
IPC分类号： F02D41/00
CPC分类号： F02D41/182 , F02D41/3809 , F02D2200/0402 , F02D2200/0406 , F02D2200/0414 , G01F1/88
摘要： A piston aircraft engine assembly includes a piston aircraft engine, a fuel source, and a control system adapted to deliver fuel from the fuel source to the piston aircraft engine. The control system includes a mass airflow sensing apparatus adapted provide a pressure signal, an electronic engine controller coupled to the mass airflow sensing apparatus, and a set of fuel injectors. The electronic engine controller is adapted to (i) receive the pressure signal from the mass airflow sensing apparatus and (ii) generate a set of fuel injector signals based on the pressure signal received from the mass airflow sensing apparatus. The set of fuel injectors is adapted to meter the fuel in response to the set of fuel injector signals generated by the electronic engine controller.
摘要翻译： 活塞式飞机发动机组件包括活塞飞机发动机，燃料源和适于将燃料从燃料源输送到活塞飞机发动机的控制系统。 控制系统包括适于提供压力信号的质量气流感测装置，耦合到质量气流感测装置的电子发动机控制器和一组燃料喷射器。 电子发动机控制器适于（i）从质量气流感测装置接收压力信号，以及（ii）基于从质量气流感测装置接收的压力信号产生一组燃料喷射器信号。 该组燃料喷射器适于响应于由电子发动机控制器产生的一组燃料喷射器信号来计量燃料。
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3.发明申请公开(公告)号：US20090078027A1
公开(公告)日：2009-03-26
申请号：US11903880
申请日：2007-09-25
IPC分类号： G01L23/22
CPC分类号： F02P5/1522 , F02D35/027 , F02D41/008 , G01L23/225 , Y02T10/46
摘要： An aircraft engine includes a cylinder assembly knock detection and suppression system. The knock detection and control system includes a set of knock detection sensors and an engine controller. Each cylinder assembly of the aircraft engine carries a knock detection sensor and each knock detection sensor is electrically coupled to the engine controller. During operation, each knock detection sensor transmits signals to the engine controller where the signals correspond to detected cylinder assembly vibrations. As the engine controller receives input signals from the sensors, the engine controller filters the input signals to distinguish the input signals as being associated with either knocking or as a non-knock event. In the case where the engine controller detects the occurrence of one or more knock events in a particular cylinder assembly, the engine controller automatically reduces the spark timing for that cylinder assembly and/or increases the volume of fuel delivered to that cylinder assembly.
摘要翻译： 飞机发动机包括气缸组件爆震检测和抑制系统。 爆震检测和控制系统包括一组爆震检测传感器和发动机控制器。 飞机发动机的每个气缸组件携带爆震检测传感器，并且每个爆震检测传感器电耦合到发动机控制器。 在操作期间，每个爆震检测传感器将信号发送到发动机控制器，其中信号对应于检测到的气缸组件振动。 当发动机控制器从传感器接收输入信号时，发动机控制器对输入信号进行滤波，以将输入信号与敲击或非敲击事件相关联。 在发动机控制器检测到特定气缸组件中发生一个或多个撞击事件的情况下，发动机控制器自动地减小该气缸组件的火花正时和/或增加输送到该汽缸组件的燃料的体积。
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公开(公告)号：US20090058183A1
公开(公告)日：2009-03-05
申请号：US11899053
申请日：2007-09-04
IPC分类号： H02J3/38
CPC分类号： H02J1/10 , H02J9/066 , Y10T307/344
摘要： An aircraft engine power distribution system for an aircraft engine controller, such as a FADEC, is provided where the power source is independent from the conventional airframe power system, without the need for a back-up battery. The aircraft engine power distribution system includes a magnetic generator operated by an aircraft engine. The aircraft engine power distribution system also includes a power distributor that rectifies the generator output and provides the rectified power to the engine controller as its primary source of power. In this configuration, as long as the aircraft engine is able to operate the magnetic generator, the engine controller receives power. Accordingly, the engine controller operates regardless of the operational status of the airframe power system.
摘要翻译： 提供用于飞机发动机控制器（例如FADEC）的飞机发动机配电系统，其中电源独立于常规的机身电力系统，而不需要备用电池。 飞机发动机配电系统包括由飞机发动机操作的磁力发电机。 飞机发动机配电系统还包括一个功率分配器，其对发电机输出进行整流，并将整流后的功率提供给发动机控制器作为其主要电源。 在这种配置中，只要飞机发动机能够操作磁力发电机，发动机控制器就会接收电力。 因此，无论机身电力系统的运行状态如何，发动机控制器都运行。
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公开(公告)号：US08131406B2
公开(公告)日：2012-03-06
申请号：US12100244
申请日：2008-04-09
IPC分类号： G01C23/00
CPC分类号： F02C9/00 , B64F5/60 , F05D2260/80 , F05D2270/708
摘要： One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.
摘要翻译： 一个实施例涉及在飞行之前测试飞行器的方法。 该方法包括从飞行前测试输入源接收用户信号，该用户信号指示飞行器的飞行员指示发动机控制电路，该引擎控制电路被布置成在飞行期间以电子方式控制飞行器的一组活塞发动机的操作 ，以自动方式开始测试飞机。 该方法包括响应于用户信号，从发动机控制电路进行飞机的飞行前试验。 该方法包括在完成飞行前测试之后，从发动机控制电路输出飞行前测试的结果。
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公开(公告)号：US07828509B2
公开(公告)日：2010-11-09
申请号：US11708414
申请日：2007-02-20
IPC分类号： F04D29/10
CPC分类号： F04C15/0038 , F02M37/045 , F04C14/26
摘要： A fuel pump includes a bearing element disposed in proximity to an impeller. The bearing element is configured to form a fuel seal with the impeller and to drain fuel leaked from the pump chamber back into the pump chamber. The bearing element minimizes leakage of fuel from the pump chamber into an engine coupled to the impeller. The fuel pump also includes redundant lip seals configured to provide redundant sealing relative to a shaft of the impeller within the fuel pump in order to minimize engine oil from entering the pump chamber and to minimize fuel from entering the engine. Integration of both the bearing element and the redundant lip seals as part of the fuel pump results in the fuel pump having a relatively compact size.
摘要翻译： 燃料泵包括设置在叶轮附近的轴承元件。 轴承元件构造成与叶轮形成燃料密封，并将从泵室泄漏的燃料排放回泵室。 轴承元件使燃料从泵室泄漏到与叶轮连接的发动机中最小化。 燃料泵还包括冗余唇形密封件，其配置成相对于燃料泵内的叶轮的轴提供冗余的密封，以便最小化发动机油进入泵室并使燃料进入发动机最小化。 作为燃料泵的一部分，轴承元件和冗余唇形密封件的集成导致燃料泵具有相对紧凑的尺寸。
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公开(公告)号：US07827965B2
公开(公告)日：2010-11-09
申请号：US11928293
申请日：2007-10-30
CPC分类号： F02D41/182 , F02D41/3809 , F02D2200/0402 , F02D2200/0406 , F02D2200/0414 , G01F1/88
摘要： A piston aircraft engine assembly includes a piston aircraft engine, a fuel source, and a control system adapted to deliver fuel from the fuel source to the piston aircraft engine. The control system includes a mass airflow sensing apparatus adapted provide a pressure signal, an electronic engine controller coupled to the mass airflow sensing apparatus, and a set of fuel injectors. The electronic engine controller is adapted to (i) receive the pressure signal from the mass airflow sensing apparatus and (ii) generate a set of fuel injector signals based on the pressure signal received from the mass airflow sensing apparatus. The set of fuel injectors is adapted to meter the fuel in response to the set of fuel injector signals generated by the electronic engine controller.
摘要翻译： 活塞式飞机发动机组件包括活塞飞机发动机，燃料源和适于将燃料从燃料源输送到活塞飞机发动机的控制系统。 控制系统包括适于提供压力信号的质量气流感测装置，耦合到质量气流感测装置的电子发动机控制器和一组燃料喷射器。 电子发动机控制器适于（i）从质量气流感测装置接收压力信号，以及（ii）基于从质量气流感测装置接收的压力信号产生一组燃料喷射器信号。 该组燃料喷射器适于响应于由电子发动机控制器产生的一组燃料喷射器信号来计量燃料。
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公开(公告)号：US20080199302A1
公开(公告)日：2008-08-21
申请号：US11708414
申请日：2007-02-20
IPC分类号： F04D1/04
CPC分类号： F04C15/0038 , F02M37/045 , F04C14/26
摘要： A fuel pump includes a bearing element disposed in proximity to an impeller. The bearing element is configured to form a fuel seal with the impeller and to drain fuel leaked from the pump chamber back into the pump chamber. The bearing element minimizes leakage of fuel from the pump chamber into an engine coupled to the impeller. The fuel pump also includes redundant lip seals configured to provide redundant sealing relative to a shaft of the impeller within the fuel pump in order to minimize engine oil from entering the pump chamber and to minimize fuel from entering the engine. Integration of both the bearing element and the redundant lip seals as part of the fuel pump results in the fuel pump having a relatively compact size.
摘要翻译： 燃料泵包括设置在叶轮附近的轴承元件。 轴承元件构造成与叶轮形成燃料密封，并将从泵室泄漏的燃料排放回泵室。 轴承元件使燃料从泵室泄漏到与叶轮连接的发动机中最小化。 燃料泵还包括冗余唇形密封件，其配置成相对于燃料泵内的叶轮的轴提供冗余的密封，以便最小化发动机油进入泵室并使燃料进入发动机最小化。 作为燃料泵的一部分，轴承元件和冗余唇形密封件的集成导致燃料泵具有相对紧凑的尺寸。
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公开(公告)号：US20090259350A1
公开(公告)日：2009-10-15
申请号：US12100244
申请日：2008-04-09
IPC分类号： B64D31/00
CPC分类号： F02C9/00 , B64F5/60 , F05D2260/80 , F05D2270/708
摘要： One embodiment is directed to a method for testing an aircraft prior to flight. The method includes receiving a user signal from a pre-flight test input source, the user signal indicating that a pilot of the aircraft has directed engine control circuitry, which is arranged to electronically control operation of a set of piston engines of the aircraft during flight, to begin testing the aircraft in an automated manner. The method includes, in response to the user signal, conducting a pre-flight test of the aircraft from the engine control circuitry. The method includes, upon completion of the pre-flight test, outputting a result of the pre-flight test from the engine control circuitry.
摘要翻译： 一个实施例涉及在飞行之前测试飞行器的方法。 该方法包括从飞行前测试输入源接收用户信号，该用户信号指示飞行器的飞行员指示发动机控制电路，该引擎控制电路被布置成在飞行期间以电子方式控制飞行器的一组活塞发动机的操作 ，以自动方式开始测试飞机。 该方法包括响应于用户信号，从发动机控制电路进行飞机的飞行前试验。 该方法包括在完成飞行前测试之后，从发动机控制电路输出飞行前测试的结果。
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