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.

Description:
BACKGROUND OF THE INVENTION  
         [0001]    This invention relates generally to electrical control systems, and more specifically to an aircraft electrical control system which disconnects power to a load when a current imbalance is sensed.  
           [0002]    In the electromechanical arts, current imbalances are serious problems that can lead to disastrous results, such as arcing within fuel pumps. Arcing within a fuel pump can lead to a breach of the fuel vessel. In aircraft, such a breach can be catastrophic. Thus, a device or methodology is needed that can suppress this type of arcing, as well as other associated problems. Presently, a common type of current protection device being utilized in aircraft is a thermal circuit breaker. However, arcing typically does not cause thermal circuit breakers to activate. There thus exists a need for an improved ground fault circuit interrupter device, particularly for aircraft. The present invention addresses these and other concerns.  
         SUMMARY OF THE INVENTION  
         [0003]    The present invention is directed towards a ground fault circuit interrupter particularly attractive for use in aircraft for interrupting a circuit having a line side and a load side. The ground fault circuit interrupter can be retrofit to existing aircraft, or can be utilized in newly constructed aircraft and new aircraft designs. The aircraft applicable ground fault circuit interrupter includes a power supply, a circuit to be monitored, a sensor, a logic controller, and a power controller. The power supply is configured to provide power to the sensor and logic controller. A second power supply may optionally be provided to power the power controller. The sensor is configured to sense a current imbalance in the line side of the circuit to be monitored. The logic controller is configured to process input from the sensor. In a presently preferred embodiment, the logic controller compares the sensor signal with a range of sensor signals representing acceptable operation and outputs a signal representing a circuit current imbalance when the sensor signal is outside the acceptable range of signals. The power controller is configured to receive input from the logic controller and remove power to the load side of the circuit when a current imbalance is sensed. In a presently preferred embodiment, the power removal from the load side of the circuit due to a sensed current imbalance is maintained until the power source is cycled.  
           [0004]    The present invention also provides for a method for interrupting an electrical circuit for an electrical load, the electrical circuit having a line side and a load side with a ground fault. Briefly, the method comprises providing a supply of power, continually monitoring the circuit for a current imbalance, sensing a current imbalance in the line side of the circuit, processing input from a power supply and a sensor, receiving input from a logic controller, and interrupting the circuit when a current imbalance is sensed. In one presently preferred aspect, interrupting of the circuit when a current imbalance is sensed is maintained until the power source is cycled. Typically, the load being supplied by the current is a motor. In another preferred aspect, no additional signals, inputs, or sources of power are required. In one presently preferred use of the method, the load side of the circuit is connected to a fuel pump, and arcing is suppressed within the fuel pump.  
           [0005]    Other features and advantages of the present invention will become apparent from the following detailed description taken in conjunction with the accompanying drawings which illustrate, by way of example, the principles of the invention.  
       
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS  
       [0006]    [0006]FIG. 1 illustrates a block diagram of a first embodiment of a control system of the present invention adapted for a Boeing  757  aircraft, for interrupting the circuit when a current imbalance is sensed;  
         [0007]    [0007]FIG. 2 illustrates a detailed view of the power supply portion of the control system shown in FIG. 1;  
         [0008]    [0008]FIG. 3 illustrates a detailed view of the logic controller portion of the control system shown in FIG. 1;  
         [0009]    [0009]FIG. 4 illustrates a detailed view of a sensor for the control system of FIG. 1;  
         [0010]    [0010]FIG. 5 illustrates a block diagram of a second embodiment of a control system of the present invention adapted for a Boeing  747  aircraft, for interrupting the circuit when a current imbalance is sensed;  
         [0011]    [0011]FIG. 6 illustrates a detailed view of the power supply portion of the control system shown in FIG. 5;  
         [0012]    [0012]FIG. 7 illustrates a detailed view of the logic controller portion of the control system shown in FIG. 5;  
         [0013]    [0013]FIG. 8 illustrates a detailed view of a sensor for the control system of FIG. 5;  
         [0014]    [0014]FIG. 9 illustrates a block diagram of an alternate preferred embodiment of a control system of the present invention adapted for providing the speed of a DC relay in an AC application for interrupting the circuit when a current imbalance is sensed;  
         [0015]    [0015]FIG. 10 illustrates a detailed view of a preferred embodiment of one section of the power supply portion of the control system shown in FIG. 9;  
         [0016]    [0016]FIG. 11 illustrates a detailed view of a second section of the power supply portion of the control system shown in FIG. 9;  
         [0017]    [0017]FIG. 12 illustrates a detailed view of the preferred logic controller portion of the control system shown in FIG. 9; and  
         [0018]    [0018]FIG. 13 illustrates a detailed view of a sensor for the control system of FIG. 9. 
     
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS  
       [0019]    [0019]FIG. 1 illustrates a preferred embodiment of a control system  10 , adapted for a Boeing 757 aircraft, and FIG. 5 illustrates a preferred embodiment of a control system  10 , adapted for a Boeing 747 aircraft, each being constructed in accordance with the present invention for disconnecting power to a load when a current imbalance is sensed. Referring to FIGS. 1 and 5, the aircraft applicable ground fault circuit interrupter  10  of the invention interrupts a circuit  20  having a line side  24  and a load side  26  with a ground fault. The load may be a motor, or any electrical device drawing a load, where protection of equipment or personnel is desired. The ground fault circuit interrupter of the invention includes a power supply  30 , a sensor  40 , a logic controller  50 , and a power controller  60 . The power supply is configured to provide power to the logic controller, and the sensor is configured to sense a current imbalance in the line side  24  of the circuit  20 , and to output a sensor signal to the logic controller. The logic controller is configured to receive and process the sensor signal input from the sensor, and the power controller is configured to receive input from the logic controller and remove power to the load side of the circuit when a current imbalance is sensed.  
         [0020]    [0020]FIGS. 2 and 6 illustrate a detailed view of a preferred embodiment of the power supply, and FIGS. 3 and 7 illustrate a detailed view of a preferred embodiment of the logic controller. Referring to FIGS. 4 and 8, showing a sensor for use in the control system of the invention, in a preferred embodiment of the present invention, the sensor preferably includes the IC U7, which is an Amploc Pro 5 Hall effect linear sensor with an output of 233 mV/A when operated at 10V. All three pump power-phase wires pass through the sensor core. Kirchhcoff&#39;s current law states that the net current in a node is 0. Considering the wye connection point of the pump winding and looking back to the inputs of the phase windings, the net current in the phase windings, when algebraically summed, is 0. If a ground fault exists, that is where the current is supplied through the sensor but does not return through the sensor, the algebraic sum of the currents in the phase wires would be equal to the ground fault current. For example, a fourth wire could be added to the wye connection point, and returned to the power source, but not pass through the sensor. The net current in all four wires would still be 0, but the imbalance current that passed through the sensor, by way of the three phase wires, would be equal to the current in the fourth wire.  
         [0021]    In a preferred embodiment, the output of the sensor is approximately one-half of the supply voltage, for no measured imbalance. Amplifier U 3 A amplifies the signal by a factor of 10. The gain is set by the ratio of resistors R 5  and R 3 . The 3 db point is where the reactance of capacitor C 4  is equal to the resistance of R 5 . This occurs at 3386 Hz. Resistors R 1 , R 2 , and R 4  bias the amplifier and have been selected so that a maximum value of 1 meg, for resistor R 4 , is required to adjust the amplifier output to mid supply with the sensor at its specified worse case high output. Calibration for the worse case low output of the sensor is easily achieved.  
         [0022]    Amplifiers U 3 B and U 3 C, and resistors R 6 , R 7 , and R 8  are set to detect a current imbalance greater than about 1.5A. A high output from amplifier U 3 B or U 3 C indicates an imbalance is present in excess of the 1.5A threshold. IC U 4 A “OR&#39;s” the outputs from amplifiers U 3 B and U 3 C. A logic 0 at its output indicates one or the other failure condition is present. Simultaneous imbalance inputs can be handled but are physically not possible since a positive imbalance cannot exist at the same time as a negative imbalance.  
         [0023]    If a fault condition exists, it passes through IC U 5 A presenting a logic 1 to the latch comprised of ICs U 4 B and U 4 C. A logic 1, at pin  5 , forces the output pin  4  low, turning transistor Q 1  off, which removes the drive signal to the power control stage. Pin  9 , the other input to the latch, is normally at logic 0. This will cause pin  10  to go high, setting the latch by presenting a logic  1  to pin  6 .  
         [0024]    In a preferred embodiment, the powerup sequence initializes the power control section to the non-operate mode. This is accomplished by presenting a logic 0 to pin  2  of IC USA to mimic a current imbalance condition.  
         [0025]    The powerup reset pulse created by IC U 5 B, resistor R 13 , capacitor C 5  and diode CR 8  is typically 7 msec. The reset is determined by the time it takes to charge capacitor C 5  through resistor R 13  to the threshold set by IC U 5 B. Diode CR 8  provides a quick reset.  
         [0026]    Diodes CR 1 , CR 2 , CR 3 , CR 4 , CR 5 , and CR 6  form a full-wave three-phase bridge. Capacitor C 1  acts as the storage device for the 281V peak voltage produced by the bridge. The regulator is a preferably buck-type configuration with the abnormal architecture of having the inductor in the lower side. This is acceptable because the circuit does not have to be referenced to earth ground. In fact, the on-board electrical ground is approximately 270 V above earth ground.  
         [0027]    Preferably, the switcher operates in an non-conventional mode. If it senses that output voltage is low, it turns on and remains on until the current through inductor L 1  reaches a pre-determined amount. Otherwise, the cycle is skipped. Energy is stored in inductor L 1  and transferred to output capacitor C 3  through diode CR 7 . Proper regulation is determined by Zener VR1 and optocoupler U 2 . Capacitor C 2  serves to store a small amount of energy that the regulator uses to operate its internal circuitry.  
         [0028]    Referring to FIGS.  9 - 13 , illustrating an alternate preferred embodiment of a control system of the present invention adapted for an AC-DC application, to interrupt the circuit when a current imbalance is sensed. As is shown in FIG. 9, the aircraft applicable ground fault circuit interrupter  10  of the invention interrupts a circuit  20  having a line side  24  and a load side  26  with a ground fault. The load may be a motor, or any electrical device drawing a load, where protection of equipment or personnel is desired. The ground fault circuit interrupter of the invention includes a power supply  30 , a sensor  40 , a logic controller  50 , and a power controller  60 . The power supply is configured to provide power to the logic controller, and the sensor is configured to sense a current imbalance in the line side  24  of the circuit  20 , and to output a sensor signal to the logic controller. The logic controller is configured to receive and process the sensor signal input from the sensor, and the power controller is configured to receive input from the logic controller and remove power to the load side of the circuit when a current imbalance is sensed.  
         [0029]    [0029]FIGS. 10 and 11 illustrate a detailed view of a preferred embodiment of the power supply. FIG. 12 illustrates a detailed view of a preferred embodiment of the logic controller. Referring to FIG. 13, showing a sensor for use in the control system of the invention, in a preferred embodiment of the present invention, the sensor preferably includes the IC U7, which is an Amploc Pro 5 Hall effect linear sensor with an output of 233 mV/A when operated at 10V. All three pump power-phase wires pass through the sensor core. Kirchhcoff&#39;s current law states that the net current in a node is 0. Considering the wye connection point of the pump winding and looking back to the inputs of the phase windings, the net current in the phase windings, when algebraically summed, is 0. If a ground fault exists, that is where the current is supplied through the sensor but does not return through the sensor, the algebraic sum of the currents in the phase wires would be equal to the ground fault current. For example, a fourth wire could be added to the wye connection point, and returned to the power source, but not pass through the sensor. The net current in all four wires would still be 0, but the imbalance current that passed through the sensor, by way of the three phase wires, would be equal to the current in the fourth wire.  
         [0030]    In a preferred embodiment, the output of the sensor is approximately one-half of the supply voltage, for no measured imbalance. Amplifier U 3 A amplifies the signal by a factor of 10. The gain is set by the ratio of resistors R 5  and R 3 . The 3 db point is where the reactance of capacitor C 4  is equal to the resistance of R 5 . This occurs at 3386 Hz. Resistors R 1 , R 2 , and R 4  bias the amplifier and have been selected so that a maximum value of 1 meg, for resistor R 4 , is required to adjust the amplifier output to mid supply with the sensor at its specified worse case high output. Calibration for the worse case low output of the sensor is easily achieved.  
         [0031]    Amplifiers U 3 B and U 3 C, and resistors R 6 , R 7 , and R 8  are set to detect a current imbalance greater than about 1.5A. A high output from amplifier U 3 B or U 3 C indicates an imbalance is present in excess of the 1.5A threshold. IC U 4 A “OR&#39;s” the outputs from amplifiers U 3 B and U 3 C. A logic 0 at its output indicates one or the other failure condition is present. Simultaneous imbalance inputs can be handled but are physically not possible since a positive imbalance cannot exist at the same time as a negative imbalance.  
         [0032]    If a fault condition exists, it passes through IC U 5 A presenting a logic  1  to the latch comprised of ICs U 4 B and U 4 C. A logic 1, at pin  5 , forces the output pin  4  low, turning transistor Q 1  off, which removes the drive signal to the power control stage. Pin  9 , the other input to the latch, is normally at logic 0. This will cause pin  10  to go high, setting the latch by presenting a logic 1 to pin  6 .  
         [0033]    In a preferred embodiment, the powerup sequence initializes the power control section to the non-operate mode. This is accomplished by presenting a logic 0 to pin  2  of IC U 5 A to mimic a current imbalance condition.  
         [0034]    The powerup reset pulse created by IC U 5 B, resistor R 13 , capacitor C 5  and diode CR 8  is typically 7 msec. The reset is determined by the time it takes to charge capacitor C 5  through resistor R 13  to the threshold set by IC U 5 B. Diode CR 8  provides a quick reset.  
         [0035]    Diodes CR 1 , CR 2 , CR 3 , CR 4 , CR 5 , and CR 6  form a full-wave three-phase bridge. Capacitor C 1  acts as the storage device for the 281V peak voltage produced by the bridge. The regulators are a buck-type configuration with the abnormal architecture of having the inductor in the lower side. This is acceptable because the circuit does not have to be referenced to earth ground. In fact, the onboard electrical ground is approximately 270V and 260V above earth ground for the 10 V and 20V supplies respectively.  
         [0036]    Preferably, the switcher operates in an non-conventional mode. If it is sensed that an output voltage is low, the corresponding controller turns on and remains on until the current through inductor L 1  or L 1 A reaches a pre-determined amount. Otherwise, the cycle is skipped. Energy is stored in inductor L 1  or L 1 A and transferred to output capacitor C 3  or C 3 A through diode CR 7  or CR 7 A. Proper regulation is determined by Zener VR1 or VR1A and opto-coupler U 2  or U 2 A. Capacitor C 2  or C 2 A serves to store a small amount of energy that each respective regulator uses to operate its internal circuitry.  
         [0037]    From the above, it may be seen that the present invention provides a method and apparatus for suppressing arcs in electrical equipment in aircraft which may be adapted to a variety of systems and components. As such, it provides more reliable and rapid disconnect of power than previous systems, thus reducing damage from ground faults in the circuits. While a particular form of the invention has been illustrated and described it will also be apparent that various modifications can be made without departing from the spirit and scope of the invention. Accordingly, it is not intended that the invention be limited except as by the appended claims.