专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US06176080B1 Oxygen concentration sensor abnormality-detecting system for internal combustion engines 有权
标题翻译：内燃机氧浓度传感器异常检测系统
公开(公告)号：US06176080B1
公开(公告)日：2001-01-23
申请号：US09150207
申请日：1998-09-09
申请人： Atsushi Izumiura , Akira Murakami , Hirohisa Kitaura , Seiichi Hosogai , Shigeo Hidai
发明人： Atsushi Izumiura , Akira Murakami , Hirohisa Kitaura , Seiichi Hosogai , Shigeo Hidai
IPC分类号： F01N300
CPC分类号： F02D41/1495 , F02D41/1441 , F02D41/1454
摘要： An oxygen concentration sensor abnormality-detecting system is provided for an internal combustion engine having first and second oxygen concentration sensors arranged in the exhaust system upstream and downstream of a catalytic converter therein. An ECU determines that the first oxygen concentration sensor is functioning abnormally if an output from the first oxygen concentration sensor does not change when an output from the second oxygen concentration sensor changes.
摘要翻译：本发明提供一种用于内燃机的氧浓度传感器异常检测系统，该内燃机具有布置在排气系统中的催化转化器上游和下游的第一和第二氧浓度传感器。如果来自第一氧浓度传感器的输出在来自第二氧浓度传感器的输出变化时，ECU判定第一氧浓度传感器功能异常。

2. 发明授权

US07299121B2 Electronic control device for aviation engine 失效
标题翻译：航空发动机电子控制装置
公开(公告)号：US07299121B2
公开(公告)日：2007-11-20
申请号：US11394094
申请日：2006-03-31
申请人： Hiroshi Uruno , Akira Hamauzu , Kiyoaki Yokoyama , Hirohisa Kitaura
发明人： Hiroshi Uruno , Akira Hamauzu , Kiyoaki Yokoyama , Hirohisa Kitaura
IPC分类号： G06F19/00 , F02P5/00
CPC分类号： F02P15/02 , F02D37/02 , F02D41/266 , F02D2250/12 , F02D2400/08 , F02P5/1518 , F02P15/08 , Y02T10/46
摘要： An electronic control device is provided for an aviation engine. Each cylinder of the engine is equipped with main ignition plugs and back-up ignition plugs. Lane A including a first CPU and lane B including a second CPU are included in an ECU. The ignition control system is multiplexed by the two lanes A, B. The first and second CPU independently calculate ignition timing for each cylinder based on each sensor signal, and then exchange the results of these calculations with each other. At each cylinder, ignition timing is synchronized in such a manner that ignition timing of the main ignition plugs and ignition timing of the back-up ignition plugs match. The electronic control device so configured has a high level of redundancy with a small number of CPU's. Thus, electronic control device can be provided for the aviation engine with few limitations placed in relation to installation location.
摘要翻译：为航空发动机提供电子控制装置。发动机的每个气缸都装有主火花塞和备用火花塞。包括第一CPU的通道A和包括第二CPU的通道B包括在ECU中。点火控制系统由两条通道A，B复用。第一和第二CPU基于每个传感器信号独立计算每个气缸的点火正时，然后将这些计算的结果相互交换。在每个气缸处，点火正时同步，使得主火花塞的点火正时和备用火花塞的点火正时相匹配。如此配置的电子控制装置具有很少的CPU的冗余度。因此，可以为航空发动机提供电子控制装置，相对于安装位置几乎没有限制。

3. 发明授权

US07150255B2 Engine including electrical interference shield 失效
标题翻译：发动机包括电气干扰屏蔽
公开(公告)号：US07150255B2
公开(公告)日：2006-12-19
申请号：US10757025
申请日：2004-01-14
申请人： Hiroshi Uruno , Mamoru Mikame , Hirohisa Kitaura , Akira Hamauzu , Takashi Umemoto , Daisuke Hayashi
发明人： Hiroshi Uruno , Mamoru Mikame , Hirohisa Kitaura , Akira Hamauzu , Takashi Umemoto , Daisuke Hayashi
IPC分类号： F02B75/24 , F02M35/116
CPC分类号： F02M35/10144 , F02B61/04 , F02B67/00 , F02B75/243 , F02M35/10249 , F02M35/1165 , F02M35/16
摘要： A shield cover for an engine is provided to shield electric parts, in an engine wherein an engine body includes a crankcase having a plurality of cylinder bores. An intake chamber common to all of the cylinder bores is spaced away from the crankcase. The shield cover is made in one piece, making it possible to reduce the number of parts and also of the cost, and to achieve a generally compact configuration of the engine. A plurality of electric parts 47L, 47R, 62L, 62R, 64 are disposed around an intake plenum 49, and the plural electric parts 47L, 47R, 62L, 62R, 64 are covered with a shield cover 67 attached to the engine body 12 in such a manner as to cover at least part of the intake plenum 49.
摘要翻译：发动机主体包括具有多个气缸孔的曲轴箱的发动机中，用于发动机的屏蔽罩用于屏蔽电气部件。所有气缸孔共用的进气室与曲轴箱间隔开。屏蔽盖制成一体，使得可以减少部件数量和成本，并且实现发动机的大体紧凑的构造。多个电气部件47L，47R，62L，62R，64设置在进气通风室49周围，多个电气部件47L，47R，62L，62R，64被屏蔽罩以能够覆盖进气室49的至少一部分的方式安装在发动机主体12上。

4. 发明申请

US20060235601A1 Electronic control device for aviation engine 失效
标题翻译：航空发动机电子控制装置
公开(公告)号：US20060235601A1
公开(公告)日：2006-10-19
申请号：US11394094
申请日：2006-03-31
申请人： Hiroshi Uruno , Akira Hamauzu , Kiyoaki Yokoyama , Hirohisa Kitaura
发明人： Hiroshi Uruno , Akira Hamauzu , Kiyoaki Yokoyama , Hirohisa Kitaura
IPC分类号： G06F19/00 , G06G7/70
CPC分类号： F02P15/02 , F02D37/02 , F02D41/266 , F02D2250/12 , F02D2400/08 , F02P5/1518 , F02P15/08 , Y02T10/46
摘要： An electronic control device is provided for an aviation engine. Each cylinder of the engine is equipped with main ignition plugs and back-up ignition plugs. Lane A including a first CPU and lane B including a second CPU are included in an ECU. The ignition control system is multiplexed by the two lanes A, B. The first and second CPU independently calculate ignition timing for each cylinder based on each sensor signal, and then exchange the results of these calculations with each other. At each cylinder, ignition timing is synchronized in such a manner that ignition timing of the main ignition plugs and ignition timing of the back-up ignition plugs match. The electronic control device so configured has a high level of redundancy with a small number of CPU's. Thus, electronic control device can be provided for the aviation engine with few limitations placed in relation to installation location.
摘要翻译：为航空发动机提供电子控制装置。发动机的每个气缸都装有主火花塞和备用火花塞。包括第一CPU的通道A和包括第二CPU的通道B包括在ECU中。点火控制系统由两条通道A，B复用。第一和第二CPU基于每个传感器信号单独计算每个气缸的点火正时，然后将这些计算的结果相互交换。在每个气缸处，点火正时同步，使得主火花塞的点火正时和备用火花塞的点火正时相匹配。如此配置的电子控制装置具有很少的CPU的冗余度。因此，可以为航空发动机提供电子控制装置，相对于安装位置几乎没有限制。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式