METHOD FOR MONITORING AN ENGINE STARTING SYSTEM AND ENGINE INCLUDING STARTING SYSTEM MONITOR
    2.
    发明申请
    METHOD FOR MONITORING AN ENGINE STARTING SYSTEM AND ENGINE INCLUDING STARTING SYSTEM MONITOR 有权
    用于监测发动机起动系统和发动机的方法,包括起动系统监视器

    公开(公告)号:US20100175656A1

    公开(公告)日:2010-07-15

    申请号:US12602983

    申请日:2007-06-18

    申请人: John Elvin Doub

    发明人: John Elvin Doub

    IPC分类号: F02N11/08 H02J7/04

    摘要: In a method of monitoring an engine starting system in an engine, the engine starting system includes a charging system, a battery, a starter, a flywheel, and a controller. The controller and monitors can monitor components and systems associated with starting of an engine, such as engine or cranking speed, power cylinder unit compression, injection timing, and proper fuel delivery to predict and/or diagnose problems. For example, a charging system voltage is monitored and the charging system voltage is compared with predetermined charging system voltage values. Voltage of the battery is monitored and battery voltage is compared with predetermined battery voltage values. A signal to an operator is provided if one or more of the charging system voltage and the battery voltage are outside of predetermined ranges for the one or more of the charging system voltage and the battery voltage.

    摘要翻译: 在监视发动机起动系统的方法中,发动机启动系统包括充电系统,电池,起动器,飞轮和控制器。 控制器和监视器可以监测与起动发动机相关联的组件和系统,例如发动机或起动速度,动力缸单元压缩,喷射正时和适当的燃料输送以预测和/或诊断问题。 例如,监视充电系统电压,并将充电系统电压与预定的充电系统电压值进行比较。 监视电池的电压,并将电池电压与预定的电池电压值进行比较。 如果一个或多个充电系统电压和电池电压在充电系统电压和电池电压中的一个或多个的预定范围之外,则向操作者提供信号。

    Integrated inward turning inlets and nozzles for hypersonic air vehicles
    7.
    发明申请
    Integrated inward turning inlets and nozzles for hypersonic air vehicles 有权
    集成向内转向入口和喷嘴用于超音速飞行器

    公开(公告)号:US20070187550A1

    公开(公告)日:2007-08-16

    申请号:US11354358

    申请日:2006-02-14

    申请人: John Elvin

    发明人: John Elvin

    IPC分类号: B64C1/00

    摘要: A hypersonic waverider aircraft is disclosed that includes a first engine and an inlet including a throat. The inlet is configured to generate three-dimensional flow compression during hypersonic flight with a weak shock wave that begins at the leading edge surfaces of the inlet and coalesces ahead of the throat, and a weak shock wave that begins at the point of coalescence of the weak shock wave and extends to the throat. The inlet includes a v-shaped lip open to freestream airflow in one side of the inlet.

    摘要翻译: 公开了一种超音速摇摆飞机,其包括第一发动机和包括喉部的入口。 入口配置为在超音速飞行期间产生三维流动压缩,其中弱冲击波从入口的前缘表面开始并在喉部之前聚结,并且在聚结点处开始的弱冲击波 弱冲击波延伸到喉咙。 入口包括一个v形嘴,可以在入口一侧的自由流气流中开口。