KR100462939B1 - System for controlling an aircraft refuele r - Google Patents

Abstract

The present invention relates to a control system for an aircraft refueling vehicle that can electronically control the operation of the braking device and the oil supply device.

The control system of an aircraft refueling vehicle according to the present invention includes an interlock brake operation valve 11 for operating a brake device upon receiving a signal from the first to fifth interlock brake switches 1, 3, 5, 7 and 9, and brake operation indication. A brake interlock control unit 20 for controlling the operation of the lamp 13; The signal is input from the water detector 31, the air pressure switch 33, and the spare 35 to the water detector display 41, the air pressure display 43, and the spare display 45 of the system monitor 97. A monitoring control unit 50 for transmitting; A thermal relief controller (60) for receiving a signal from the first signal output unit (23) of the brake interlock controller (20) to control the operation of the thermal relief valve (65); A deadman control unit 70 for receiving a signal from the deadman switches 81 and 82 to control operations of the deadman valve 83, the deadman operation display lamp 84, and the alarm device 85; It is characterized in that it consists of a recovery tank amplifying control unit 90 for controlling the operation of the recovery pump 96 by receiving a signal from the water level sensor 95 for detecting the full water of the recovery tank.

Description

System for controlling an aircraft refuele r}

The present invention relates to a control system for an aircraft refueling vehicle, and more particularly, to a control system for an aircraft refueling vehicle that can electronically control operations of a braking device and a refueling device.

Applicant's patent 314423 (registered October 30, 2001) introduces a "multiple control system for aircraft refueling vehicles."

However, since the multiple control system of the aircraft refueling vehicle controls the operation of the aero braking system and the refueling system, frequent air leakage occurs in the pneumatic circuit, and mechanical failure is caused by a high frequency of failure of the pneumatic valve. Moisture condensation occurs in the condensate water, the condensate is frozen, the operation of the oil supply and braking device is an error occurs because there is a problem that the operation of the aircraft due to refueling the aircraft within a given time.

Accordingly, an object of the present invention relates to a control system of an aircraft refueling vehicle capable of refueling an aircraft within a given time without being affected by the seasons and the external environment while electronically controlling the operation of the braking device and the oil supply device.

1 is a block diagram illustrating a control system of an aircraft refueling vehicle according to the present invention.

2 is a logic circuit of a control system for an aircraft refueling vehicle according to the present invention.

* Description of Signs of Main Parts of Drawings *

20: brake interlock control unit 50: monitoring control unit

60: thermal relief controller 70: deadman control unit

90: recovery tank embossing control unit

The control system of the aircraft refueling vehicle according to the present invention for achieving the above object is provided in the first interlock switch, the deck holder (mount deck) mounted on the lift (lift) when you want to refuel the aircraft 2nd interlock brake switch mounted, 3rd interlock brake switch mounted on fit coupler, 4th interlock brake switch mounted on reel-nozzle holder, 5th interlock brake switch mounted on PTO An interlock brake operation valve for operating the brake device upon receiving a signal from the brake, and a brake interlock control unit for controlling the operation of the brake operation indicator lamp;

A water detector that checks the full water of the water sump tank, which stores the contaminated water separated from the fuel by a filter separator, and detects the proper air supply pressure of the compressor. Air pressure switch, a flow detector to detect the malfunction of the flow meter (spare) to receive a signal from the water detector display, air pressure display, spare display of the system monitor A monitoring controller for transmitting a signal;

Thermal relief valve for receiving a signal from the first signal output unit of the brake interlock control unit and the second signal output unit of the monitoring control unit to prevent the pressure rise due to the expansion of the internal temperature of the piping parts and lines when the equipment is stored A thermal relief controller to control operation;

A deadman controller which receives a signal from a deadman switch and controls an operation of a deadman valve, a deadman operation indicator lamp, and an alarm device;

The recovery tank emptying controller, which is installed in the recovery tank, receives a signal from the water level sensor that detects the fullness of the recovery tank, controls the operation of the recovery pump, and sends a signal to the recovery pump display of the system monitor. It is characterized in that the configuration.

The first to fifth interlock brake switches may be proximity sensor switches or micro limit switches, and may detect an on / off signal using a micro safety current.

The brake interlock control unit receives a signal from five interlock brake switches in the first input signal controller, calculates and outputs the signal to the first signal output unit, and the brake override switch is electrically connected directly to the first signal output unit. The first signal output unit may transmit signals to the interlock brake operation valve and the interlock brake display of the system monitor, the brake operation display lamp, the brake release display lamp, and the thermal relief controller.

The brake interlock controller may be configured to input signals of the first to fifth interlock brake switches to the first input signal controller through an inverter.

The monitoring controller outputs a signal to the second signal output unit when a signal is input from the water detector, the air pressure switch, or the spare to the second input signal controller, and the water detector display of the system monitor and the air pressure display are output from the second signal output unit. In this case, each piece of information is displayed on each display by transmitting a signal to the spare display.

The monitoring control unit calculates a signal input to the second input signal controller and if there is no error, the second signal output unit sends a signal to the third signal input controller of the deadman control unit and the fourth signal input controller of the recovery tank lifting control unit. It characterized in that for transmitting.

When the deadman control unit receives signals from the first and second deadman switches and the second signal output unit of the monitoring control unit to the third input signal controller, the deadman controller calculates a signal received from the third input signal controller to operate the first timer. By transmitting a signal to the third signal output unit through, the signal is transmitted to the deadman control display of the system monitor, characterized in that the deadman valve is opened to refuel the aircraft.

When the trigger signal is input to the first timer from the third input signal controller, the deadman control unit counts the first timer for a predetermined time, and the deadman valve is opened to supply oil while the first timer counts. When the counting of the first timer ends, a reset signal is input to the third input signal controller, and when a trigger signal is input to the first timer, a signal is simultaneously input to a second timer so that the second timer Counting for a predetermined time, the deadman operation display lamp is turned on through the lamp signal output unit during the count time of the second timer.

When the count time of the second timer expires, the third timer counts for a predetermined time, and at this time, the alarm device issues an alarm sound during the count time of the third timer through the alarm signal output unit.

The first and second deadman switches may detect an on / off signal using a microsafety current.

The recovery tank lifting control unit transmits a signal from the fourth input signal controller to the recovery tank lifting controller when a signal is input from the second signal output unit of the level sensor and the monitoring control unit. Receiving a signal from the third signal output unit in conjunction with the deadman operation is characterized in that for transmitting the signal to the recovery pump display of the system monitor through the fourth signal output unit and operates the recovery pump.

In addition, when a signal is input from the second signal output unit of the water level sensor and the monitoring controller to the fourth input signal controller, the recovery tank lifting control unit transmits a signal from the fourth input signal controller to the recovery tank amplifier controller, It receives a power signal and transmits a signal to the recovery pump display of the system monitor separately from the deadman operation and operates the recovery pump.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

1A and 1B, FIGS. 1A and 1B are separate views of a control system of an aircraft refueling vehicle according to the present invention, which may not be illustrated in one view.

The control system of an aircraft refueling vehicle according to the present invention includes a first interlock brake switch (1) mounted on a lift, a second interlock brake switch (3) mounted on a deck holder, and a first coupler mounted on a pit coupler. 3 Interlock brake operation valve 11 for operating the brake device upon receiving a signal from the interlock brake switch 5, the fourth interlock brake switch 7 mounted on the reel nozzle holder, and the fifth interlock brake switch 9 mounted on the PTO. A brake interlock controller 20 for controlling the operation of the brake operation indicator lamp 13; A water detector 31 for checking the full water capacity of the water storage tank storing water separated from the fuel by the filter separator, an air pressure switch 33 for detecting the supply air pressure of the compressor, a power, a brake interlock, Deadman control, which receives a signal from the spare 35 for detecting an abnormality of the flow meter and transmits a signal to the water detector display 41, air pressure display 43, spare display 45 of the system monitor 97 A monitoring controller 50; Thermal to control the operation of the thermal relief valve 65 to prevent the pressure rise by the internal temperature expansion of the piping parts and lines when receiving the signal from the first signal output unit 23 of the brake interlock control unit 20 Relief controller 60; A deadman control unit 70 for receiving a signal from the deadman switches 81 and 82 to control operations of the deadman valve 83, the deadman operation display lamp 84, and the alarm device 85; A recovery tank lifting control unit 90 mounted on the recovery tank to control the operation of the recovery pump 96 by receiving a signal from the water level sensor 95 that detects the fullness of the recovery tank, and to transmit a signal to the system monitor 97. It is composed of

The first to fifth interlock brake switches 1, 3, 5, 7, and 9 may be proximity sensor switches or micro limit switches, and short may be generated by sensing an on / off signal using a micro safety current. No spark occurs, and no malfunction occurs even when exposed to moisture. The microsafety current is, for example, 0.7 V when the switch is turned on and a low voltage of 0 V flows when the switch is turned off. The power consumption is also less than 0.01 A, and the power consumption is 7 mV.

The brake interlock control unit 20 receives signals from five interlock brake switches 1, 3, 5, 7 and 9 in the first input signal controller 21, calculates the signals, and outputs the signals to the first signal output unit 23. The brake override override switch 15 is electrically connected directly to the first signal output unit 23, and the first signal output unit 23 is an interlock brake operation valve 11 and a brake operation indicator lamp 13. ), A signal may be transmitted to the brake release display lamp 17 and the thermal relief controller 60.

In addition, the brake interlock control unit may input signals of the first to fifth interlock brake switches 1, 3, 5, 7 and 9 to the first input signal controller 21 through the inverter 10.

Reference numeral 25 is a fuse and the main power input from the fuse box is a signal is transmitted to the main power display of the system monitor.

The brake interlock control unit configured as described above operates as follows.

When a signal is input to the input signal controller 21 from any one of the first to fifth interlock brake switches 1, 3, 5, 7, 9, the signal output unit 23 is input from the input signal controller 21. By transmitting a signal, the signal output unit 23 transmits a signal to the interlock brake actuating valve 11 to open the interlock brake actuating valve 11, and thus the aircraft refueling vehicle is automatically braked and the brake actuation indication is displayed. The lamp 13 lights up. In addition, when the brake signal is input to the signal output unit 23 from the brake-override switching switch 15 while the signal is input from the input signal controller 21 to the signal output unit 23, the interlock brake is activated. The valve 11 continues to open and the signal output section 23 at the brake-override switching switch 15 is independent of the signal input of the first to fifth interlock brake switches 1, 3, 5, 7 and 9. When the low override signal is input, the interlock brake operation valve 11 is closed to release the brake of the vehicle, the brake operation indication lamp 13 is turned off, and the brake release indication lamp 17 is turned on for a predetermined time.

The monitoring controller 50 outputs a signal to the second signal output unit 53 when a signal is input from the water detector 31, the air pressure switch 33, and the spare 35 to the second input signal controller 51. The second signal output unit 53 transmits a signal to the water detector display 41, the air pressure display 43, and the spare display 45 of the system monitor 97 so that each information is transmitted to each display. Is displayed. In addition, the monitoring control unit 50 calculates a signal input to the second input signal controller 51 and if there is no abnormality, the third signal input controller of the deadman control unit 70 in the second signal output unit 53 ( 71) and a signal to the fourth signal input controller 83 of the recovery tank lifting control unit 80.

The water detector 31, the air pressure switch 33, and the spare 35 may detect an on / off signal using a micro safety current.

The thermal relief controller 60 receives a brake locking signal from the first signal output unit 23 of the brake interlock controller 20, thereby preventing the pressure in the oil supply pipe line from being lowered for refueling the aircraft.

When the deadman controller 70 receives signals from the first and second deadman switches 81 and 82 and the second signal output unit 53 of the monitoring controller 50 to the third input signal controller 71. The deadman valve 83 is opened to the aircraft by transmitting the signal received by the third input signal controller 71 to the third signal output unit 73 through the first timer 72. Refueling takes place. At this time, when a trigger signal is input from the third input signal controller 71 to the first timer 72, the first timer 72 counts for a predetermined time (for example, 180 seconds), and the first timer ( The deadman valve 83 is opened to supply oil while the 72 is counted. When the count of the first timer 72 ends, a signal is inputted to the third input signal controller 71. When a trigger signal is input to the first timer 72, a signal is simultaneously input to the second timer 74 so that the second timer 74 counts for a predetermined time (for example, 180 seconds), and the second timer 74. Deadman's operation display lamp 84 is turned on through the lamp signal output unit 75 during the count time. In addition, when the count time of the second timer 74 ends, the third timer 76 counts for a predetermined time (for example, 30 seconds), and at this time, the alarm device 85 through the alarm signal output unit 77. Beeps for the count time of the third timer 76. Therefore, the operator may re-operate the deadman steering wheel at a predetermined time to refuel the aircraft, and if the operator re-manipulates the deadman steering even while the first timer 72 is counting, the third input signal controller 71 As the trigger signal is input from the first timer 72 to the first timer 72 again, the first timer 72 counts again from the beginning, and lubrication can be continued. In addition, the third input signal controller 71 receives an on signal from the first and second deadman switches 81 or 82 and receives a signal from the second signal output unit 53 of the monitoring controller 50. 1 Sends a trigger signal to timer 72.

The first and second deadman switches 81 and 82 may detect an on / off signal using a micro safety current.

Unexplained reference numeral 79 denotes a fuse.

The recovery tank lifting control unit 90 receives a full water signal of the recovery tank from the level sensor 95 and receives a signal from the second signal output unit 53 of the monitoring control unit 50. The signal is transmitted to the fourth input signal controller 91 to receive the signal, and the recovery pump 96 is operated by transmitting a signal from the recovery tank amplifying controller 92 to the fourth signal output unit 77. Send a signal to (97). As a result, a recovery tank for collecting and storing the aviation oil discharged during visual inspection and sampling of the aviation oil is emptied, and the recovery of the aviation oil is linked with the deadman operation.

In addition, the recovery tank lifting control unit 90 inputs the fourth input when a signal is input from the second signal output unit 53 of the level sensor 95 and the monitoring control unit 50 to the fourth input signal controller 91. The signal is transmitted from the signal controller 91 to the recovery tank amplifying controller 92, and receives the main power signal to recover the recovery pump display of the system monitor 97 through the fourth signal output unit 77 separately from the deadman operation. Signal) and activate the recovery pump.

Power, brake operation indicator (13), brake release indicator (17), water detector display (41), air pressure display (43), spare display (45), deadman operation indicator (84) described above ), The recovery pump display 101, the deadman control display 103, the power display 105, the interlock brake display 107, and the like, lamps indicating the operating state of the aircraft refueling vehicle are collected in one system monitor 97. Can be.

As described above, the control system of the aircraft refueling vehicle according to the present invention can electronically control the operation of the braking system and the refueling system to refuel the aircraft within a given time without being affected by the season and the external environment, the operator continues By monitoring the system, the status and operation of the system can be known.

Claims (12)

When refueling the aircraft, the first interlock brake switch 1 mounted on the lift, the second interlock brake switch 3 mounted on the deck holder, the third interlock brake switch 5 mounted on the pit coupler, the reel nozzle holder Operation of the interlock brake actuating valve 11 and the brake actuation indication lamp 13 for operating the brake device upon receiving a signal from the fourth interlock brake switch 7 mounted on the brake, the fifth interlock brake switch 9 mounted on the PTO. A brake interlock control unit 20 for controlling the control unit; Water detector 31 for checking the water level of the water storage tank storing the water separated from the fuel by the water separator 31, air pressure switch 33 for detecting the supply air pressure of the compressor, power, brake interlock, dead Receives a signal from the spare 35 for detecting abnormal operation of the man control and flow meter, and transmits the signal to the water detector display 41, the air pressure display 43, and the spare display 45 of the system monitor 97. A monitoring controller 50; The thermal control valve receives the signal from the first signal output unit 23 of the brake interlock control unit 20 to control the operation of the thermal relief valve 65 to prevent the pressure rise due to the temperature expansion of the piping parts and the line inside the equipment storage. Relief controller 60; A deadman control unit 70 for receiving a signal from the deadman switches 81 and 82 to control operations of the deadman valve 83, the deadman operation display lamp 84, and the alarm device 85; Mounted in the recovery tank receives a signal from the water level sensor 95 to detect the full water of the recovery tank to control the operation of the recovery pump 96 and transmits a signal to the recovery pump display 101 of the system monitor 97 The control system of the aircraft refueling vehicle, characterized in that consisting of a recovery tank lifting control unit (90). The method of claim 1, The first to fifth interlock brake switches 1, 3, 5, 7, and 9 may be proximity sensor switches or micro limit switches, and the aircraft may detect an on / off signal using a micro safety current. Refueling control system. The method of claim 1, The brake interlock control unit 20 receives signals from five interlock brake switches 1, 3, 5, 7 and 9 in the first input signal controller 21, calculates the signals, and outputs the signals to the first signal output unit 23. The brake override override switch 15 is electrically connected directly to the first signal output unit 23, and the first signal output unit 23 is an interlock brake operation valve 11 and a brake operation indicator lamp 13. And a brake release indication lamp (17) and a thermal relief controller (60). The method according to claim 1 or 3, The brake interlock control unit 20 may recognize that the signals of the first to fifth interlock brake switches 1, 3, 5, 7 and 9 may be input to the first input signal controller 21 through the inverter 10. A control system for an aircraft refueling vehicle. The method of claim 1, The monitoring controller 50 outputs a signal to the second signal output unit 53 when a signal is input from the water detector 31, the air pressure switch 33, and the spare 35 to the second input signal controller 51. The second signal output unit 53 transmits a signal to the water detector display 41, the air pressure display 43, and the spare display 45 so that respective information is displayed on each display. Control system of aircraft refueling vehicle. The method of claim 5, wherein The monitoring control unit 50 calculates a signal input to the second input signal controller 51, and if there is no abnormality, the second signal output unit 53 controls the thermal relief controller 60 and the deadman control unit 70. 3 The signal input controller (71) and the control system of the aircraft refueling vehicle, characterized in that for transmitting a signal to the fourth signal input controller (83) of the recovery tank lifting control unit (80). The method of claim 1, When the deadman controller 70 receives signals from the first and second deadman switches 81 and 82 and the second signal output unit 53 of the monitoring controller 50 to the third input signal controller 71. Since the third input signal controller 71 calculates the input signal and transmits the signal to the third signal output unit 73 through the first timer 72, the deadman valve 83 is opened to the aircraft. The refueling control system of an aircraft refueling vehicle, characterized in that is made. The method of claim 7, wherein When the trigger signal is input from the third input signal controller 71 to the first timer 72, the deadman controller 70 counts the first timer 72 for a predetermined time, and the first timer ( The deadman valve 83 is opened to supply oil while the 72 is counted, and when the count of the first timer 72 ends, a reset signal is transmitted to the third input signal controller 71. When the trigger signal is input to the first timer 72, the signal is simultaneously input to the second timer 74 so that the second timer 74 counts for a predetermined time, and ramps up during the count time of the second timer 74. Deadman operation display lamp 84 is turned on through the signal output unit 75, the aircraft refueling vehicle control system. The method of claim 8, When the count time of the second timer 74 ends, the third timer 76 counts for a predetermined time, and at this time, the alarm device 85 through the alarm signal output unit 77 causes the third timer 77 to be counted. And a warning sound or a flashing light for a counting time. The method according to claim 1 or 7, The first and second deadman switch (81, 82) is a control system for an aircraft refueling vehicle, it characterized in that it can detect the on / off signal using a fine safety current. The method of claim 1, The recovery tank lifting control unit 90 receives a full water signal of the recovery tank from the level sensor 95 and receives a signal from the second signal output unit 53 of the monitoring control unit 50. The signal is transmitted to the fourth input signal controller 91 to receive the signal, and the recovery pump 96 is operated by transmitting a signal from the recovery tank amplifying controller 92 to the fourth signal output unit 77. A control system for an aircraft refueling vehicle, characterized by transmitting a signal to (97). The method of claim 1, The recovery tank lifting control unit 90 receives the fourth input signal when a signal is input from the second signal output unit 53 of the level sensor 95 and the monitoring control unit 50 to the fourth input signal controller 91. The recovery pump display 101 of the system monitor 97 is transmitted from the controller 91 to the recovery tank amplifying controller 92 and receives the main power signal through the fourth signal output unit 77 separately from the deadman operation. Control signal of the aircraft refueling vehicle.