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1. 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。

2. 发明申请

US20060219424A1 Harness outlet structure of engine 有权
标题翻译：发动机线束结构
公开(公告)号：US20060219424A1
公开(公告)日：2006-10-05
申请号：US11394282
申请日：2006-03-31
申请人： Akira Hamazu , Mamoru Mikame , Daisuke Hayashi , Kiyoaki Yokoyama , Hiroshi Uruno
发明人： Akira Hamazu , Mamoru Mikame , Daisuke Hayashi , Kiyoaki Yokoyama , Hiroshi Uruno
IPC分类号： H02G3/04
CPC分类号： H02G3/0666 , H02G3/22
摘要： A harness outlet structure of an engine permitting a reliable shield at a harness outlet of the engine. The structure includes a wiring harness is clamped by a shield cover and an engine main body via a grommet bracket. The grommet bracket includes a groove having a width equivalent to the thickness of the shield cover disposed circumferentially between two flange portions of the grommet bracket. A harness overall for shielding the wiring harness is mounted externally on a proximal end of the grommet bracket. The harness overall is a shield outer jacket body formed from braided metal fibers. The harness overall is inserted over an outside of the proximal end of the grommet bracket until one end of the harness overall contacts the flange portion. The harness overall is then joined by a coupling ring.
摘要翻译：发动机的线束出口结构允许在发动机的线束出口处具有可靠的屏蔽。该结构包括线束，其由屏蔽罩和发动机主体通过索环支架夹紧。索环支架包括一个槽，该槽的宽度等于在环形支架的两个凸缘部分周向设置的屏蔽盖的厚度。整体用于屏蔽线束的线束外部安装在索环支架的近端。整体线束是由编织金属纤维形成的护罩外护套。整个线束被插入到索环支架的近端的外侧，直到线束的一端与凸缘部分接触。然后，整个线束通过联接环连接。

3. 发明授权

US07339119B2 Harness outlet structure of engine 有权
标题翻译：发动机线束结构
公开(公告)号：US07339119B2
公开(公告)日：2008-03-04
申请号：US11394282
申请日：2006-03-31
申请人： Akira Hamazu , Mamoru Mikame , Daisuke Hayashi , Kiyoaki Yokoyama , Hiroshi Uruno
发明人： Akira Hamazu , Mamoru Mikame , Daisuke Hayashi , Kiyoaki Yokoyama , Hiroshi Uruno
IPC分类号： H02G3/00
CPC分类号： H02G3/0666 , H02G3/22
摘要： A harness outlet structure of an engine permitting a reliable shield at a harness outlet of the engine. The structure includes a wiring harness is clamped by a shield cover and an engine main body via a grommet bracket. The grommet bracket includes a groove having a width equivalent to the thickness of the shield cover disposed circumferentially between two flange portions of the grommet bracket. A harness overall for shielding the wiring harness is mounted externally on a proximal end of the grommet bracket. The harness overall is a shield outer jacket body formed from braided metal fibers. The harness overall is inserted over an outside of the proximal end of the grommet bracket until one end of the harness overall contacts the flange portion. The harness overall is then joined by a coupling ring.
摘要翻译：发动机的线束出口结构允许在发动机的线束出口处具有可靠的屏蔽。该结构包括线束，其由屏蔽罩和发动机主体通过索环支架夹紧。索环托架包括一个槽，其宽度等于围绕在索环支架的两个凸缘部分周向设置的屏蔽盖的厚度。整体用于屏蔽线束的线束外部安装在索环支架的近端。整体线束是由编织金属纤维形成的护罩外护套。整个线束插入到索环支架近端的外侧，直到线束的一端与凸缘部分接触。然后，整个线束通过联接环连接。

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。

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