| 摘要 |
An electrical power shutdown system for an aircraft includes a battery (B), a battery relay (BR), a plurality of aircraft status sensor switches (SSW), an electrical bus (EB) leading to the power utilization system, a main battery switch (BSW), and a control unit (CS). When the status sensor switches indicate shutdown of the aircraft, the control unit activates a timer (TMR) that controls disconnect elements (Q1, IR) to cause deenergization of the battery relay after a time interval if the pilot forgets to open the main battery switch. The control unit (CS) prevents resetting (closing of the battery relay) on momentary interruption of the positive battery power under shutdown conditions but allows such resetting on momentary interruption of such positive power under normal operative conditions and prevents such resetting regardless of the status if the main battery switch is open. Also, the control unit (CS) limits current flow to virtually zero in the "off" state and allows only minimal current flow in the timed-out state of the timer. Moreover, the control unit allows battery connection not only under normal operative conditions but also for a time interval under shutdown conditions.
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