Abstract: A power controller is positioned within a current path between the line side and the load side of an electrical circuit. The power controller closes the current path in the presence of a control supply and opens the current path in the absence of the control supply. A power supply electrically connected to the current path provides the control supply. A sensor system receives power from the power supply, monitors the current in the current path and outputs a sensor signal indicative of a current condition within the current path. A logic controller also receives power from the power supply, receives the sensor signal and removes the control supply from the power controller when the sensor signal does not satisfy an established criteria. The sensor system may include one or both of an imbalance sensor for monitoring the current balance among two or more electrical lines and over-current sensors for monitoring current in individual lines.

Abstract: The aircraft applicable current imbalance detection and circuit interrupter interrupts an electrical circuit when a current imbalance is sensed. The current imbalance detection and circuit interrupter includes a housing, power supplies, a sensor for sensing a current imbalance at the line side of the electrical circuit, a logic controller and a power controller. In a preferred embodiment, the invention can also include a fault indicator, a press to test switch and a reset switch. The power supplies provide power to the sensor, logic controller, and the power controller. The logic controller receives input from the sensor and the relay control signal, and the power controller receives input from the logic controller, and interrupts power to the load side of the electrical circuit when the sensor senses a current imbalance. Power interruption due to a sensed current imbalance is maintained until the line side power source is cycled.

Abstract: The aircraft applicable current imbalance detection and circuit interrupter interrupts an electrical circuit when a current imbalance is sensed. The current imbalance detection and circuit interrupter includes a housing, power supplies, a sensor system for sensing a current imbalance at the line side of the electrical circuit, a logic controller and a power controller including a power relay having contacts capable of surviving carry-break and make-carry-break types of ground fault conditions at anticipated current levels. At power up, the device performs a test to confirm that none of the relay contacts have failed in a closed position, and to check whether a switching FET which controls the relay coil has shorted.

Abstract: The aircraft applicable current imbalance detection and circuit interrupter interrupts an electrical circuit when a current imbalance is sensed. The current imbalance detection and circuit interrupter includes a housing, power supplies, a sensor for sensing a current imbalance at the line side of the electrical circuit, a logic controller and a power controller. In a preferred embodiment, the invention can also include a fault indicator, a press to test switch and a reset switch. The power supplies provide power to the sensor, logic controller, and the power controller. The logic controller receives input from the sensor and the relay control signal, and the power controller receives input from the logic controller, and interrupts power to the load side of the electrical circuit when the sensor senses a current imbalance. Power interruption due to a sensed current imbalance is maintained until the line side power source is cycled.

Abstract: The aircraft applicable current imbalance detection and circuit interrupter interrupts an electrical circuit when a current imbalance is sensed. The current imbalance detection and circuit interrupter includes a housing, power supplies, a sensor for sensing a current imbalance at the line side of the electrical circuit, a logic controller and a power controller. In a preferred embodiment, the invention can also include a fault indicator, a press to test switch and a reset switch. The power supplies provide power to the sensor, logic controller, and the power controller. The logic controller receives input from the sensor and the relay control signal, and the power controller receives input from the logic controller, and interrupts power to the load side of the electrical circuit when the sensor senses a current imbalance. Power interruption due to a sensed current imbalance is maintained until the line side power source is cycled.

Abstract: The aircraft applicable current imbalance detection and circuit interrupter interrupts an electrical circuit when a current imbalance is sensed. The current imbalance detection and circuit interrupter includes a housing, power supplies, a sensor for sensing a current imbalance at the line side of the electrical circuit, a logic controller and a power controller. In a preferred embodiment, the invention can also include a fault indicator, a press to test switch and a reset switch. The power supplies provide power to the sensor, logic controller, and the power controller. The logic controller receives input from the sensor and the relay control signal, and the power controller receives input from the logic controller, and interrupts power to the load side of the electrical circuit when the sensor senses a current imbalance. Power interruption due to a sensed current imbalance is maintained until the line side power source is cycled.

Abstract: The aircraft applicable ground fault circuit interrupter interrupts a circuit when a current imbalance is sensed. The circuit interrupter includes a power supply, a sensor for sensing a current imbalance at the line side of the circuit, a logic controller, and a power controller. The power supply provides power to the sensor, logic controller, and the power controller. The logic controller receives input from the sensor, and the power controller receives input from the logic controller, and interrupts power to the load side of the circuit when the sensor senses a current imbalance. Power interruption due to a sensed current imbalance is maintained until the power source is cycled. The circuit interrupter is preferably autonomous, requiring no additional signals, inputs, or sources of power.

Abstract: A power controller is positioned within a current path between the line side and the load side of an electrical circuit. The power controller closes the current path in the presence of a control supply and opens the current path in the absence of the control supply. A power supply electrically connected to the current path provides the control supply. A sensor system receives power from the power supply, monitors the current in the current path and outputs a sensor signal indicative of a current condition within the current path. A logic controller also receives power from the power supply, receives the sensor signal and removes the control supply from the power controller when the sensor signal does not satisfy an established criteria. The sensor system may include one or both of an imbalance sensor for monitoring the current balance among two or more electrical lines and over-current sensors for monitoring current in individual lines.

Abstract: The aircraft applicable current imbalance detection and circuit interrupter interrupts an electrical circuit when a current imbalance is sensed. The current imbalance detection and circuit interrupter includes a housing, power supplies, a sensor for sensing a current imbalance at the line side of the electrical circuit, a logic controller and a power controller. In a preferred embodiment, the invention can also include a fault indicator, a press to test switch and a reset switch. The power supplies provide power to the sensor, logic controller, and the power controller. The logic controller receives input from the sensor and the relay control signal, and the power controller receives input from the logic controller, and interrupts power to the load side of the electrical circuit when the sensor senses a current imbalance. Power interruption due to a sensed current imbalance is maintained until the line side power source is cycled.

Abstract: The aircraft applicable ground fault circuit interrupter interrupts a circuit when a current imbalance is sensed. The circuit interrupter includes a power supply, a sensor for sensing a current imbalance at the line side of the circuit, a logic controller, and a power controller. The power supply provides power to the sensor, logic controller, and the power controller. The logic controller receives input from the sensor, and the power controller receives input from the logic controller, and interrupts power to the load side of the circuit when the sensor senses a current imbalance. Power interruption due to a sensed current imbalance is maintained until the power source is cycled. The circuit interrupter is preferably autonomous, requiring no additional signals, inputs, or sources of power.