KR20160048529A - Test equipment for electronic engine control unit of aircraft - Google Patents

Abstract

The present invention relates to an apparatus for testing the state of various types of electronic engine control units of an aircraft. The test apparatus for an electronic engine control unit (EECU) of an aircraft, according to the present invention, is connected between a host computer and the EECU through LAN communications and comprises: an interface board, a power source part which supplies power to an input/output part and the EECU, the input/output part, and a LAN communication part. The interface board comprises an interface power supply part, an engine output control part, a simulating part, a voltage level converting part, a voltage-current converting part, and an on/off control part.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to an electronic engine controller

The present invention relates to an aircraft electronic engine controller inspection apparatus, and more particularly to an apparatus for inspecting the state of various types of aircraft electronic engine controllers, including commercial I / O boards and interface boards for level conversion and signal connection,

Full Authority Digital Engine Control (FADEC) is a device that electronically controls an aircraft's jet engine mounted on an aircraft engine. It is used to control air density, throttle lever position, engine temperature, engine pressure, etc. It accepts the current engine condition flight condition as input parameter. These inputs are computed over several dozen times and then derive values for variables such as fuel flow rate, stator position, bleed valve position, etc., and control startup and restart.

FADEC not only provides engine operating efficiency, but also allows engineers to design engine limits and provides engine maintenance reports. Fully automating the operation of the aircraft engine is a serious concern for safety. To solve this problem, FADEC has two or more channels that are the same but completely separated, each channel providing completely independent engine-related functions without any limitations, The engine is controlled using the normal value.

The Electronic Engine Control Unit (ECCU), the centerpiece of FADEC, controls the amount of fuel controlled by the pilot's steering signals and the state of the engine (pressure, temperature, speed, etc.) Periodically ground inspection shall be carried out.

An integrated aircraft control device for comprehensive ground check of aircraft is disclosed in Korean Patent No. 590623. The control panel of the control device includes a front unit including operation units such as various switches and dials for receiving an instruction by the user, a main card for controlling the entire power supply and controlling or inhibiting the start and restart of the aircraft A microprocessor card that performs necessary computation and signal processing, including a voltage regulator and a microprocessor, and an analog card that measures all analog signals and, if necessary, amplifies or controls them, There is a problem that a new design is required.

SUMMARY OF THE INVENTION The present invention has been made to solve the above problems, and it is an object of the present invention to provide a simulation unit, a voltage level conversion unit, and a voltage level conversion unit, using a general commercial device as a communication unit and a commercial input / output unit of an aircraft electronic engine controller (EECU) (EECU) inspection apparatus that minimizes the configuration of an integrated interface board including a power conversion unit, a current conversion unit, and a power supply unit.

An aircraft engine electronic air unit inspection apparatus according to the present invention includes an interface board, an input / output unit, a power supply unit for supplying power to the EECU, an input / output unit, a LAN communication unit and an interface board, ,

The interface board

An interface power unit receiving power from the power unit and supplying power to the EECU;

An engine output control section for transmitting an engine output power signal and converting the voltage level into an analog input section of an input / output section, receiving an engine output signal from an analog output section of the input / output section,

A simulator for receiving and simulating engine output, speed, temperature, pressure and current signals from the analog output;

Compressor output pressure sensor power supply, atmospheric pressure sensor power supply, fuel pressure sensor power supply, oil pressure sensor power supply, ADU power supply, EPU power supply, first spare pressure sensor power supply, second spare pressure sensor power supply, spare RTD power supply, engine output control power supply A voltage level converter for converting the voltage level and inputting the voltage level to the EECU;

Air temperature sensor power supply, fuel temperature sensor power supply, oil temperature sensor power supply, first spare pressure sensor power supply, second spare pressure sensor power supply, spare RTD power supply, engine output control voltage Voltage to be converted into current and input to EECU - A current converter;

And an on / off control unit for processing a signal received from the digital output unit and the digital input unit and inputting the processed signal to the EECU.

According to the present invention, a general-purpose commercial device is used for a communication unit and an input / output unit including an analog digital converter (ADC), a digital analog converter (DAC), a digital input output (DIO) and an analog input output Thereby minimizing the configuration of the integrated interface board including the simulation unit, the voltage level conversion unit, the current conversion unit, and the power supply unit, thereby facilitating the production of an electronic engine controller (ECCU) inspection apparatus for an aircraft.

The present invention facilitates the development of an electronic engine controller (EECU) inspection apparatus for a variety of aircraft having different signal levels by minimizing the configuration of the integrated interface board.

1 is a block diagram showing a configuration of an aircraft electronic engine controller (EECU) inspection apparatus according to the present invention.
2 is a diagram showing an input / output configuration of an interface board of an aircraft electronic engine controller (EECU) inspection apparatus.
3 is a diagram showing an external configuration of an aircraft electronic engine controller (EECU) inspection apparatus according to the present invention.
4 is a circuit diagram of an interface board power supply unit according to the present invention.
5 is a circuit diagram constituting an engine output control simulation unit according to the present invention.
6 is a circuit diagram constituting a velocity sensor, a temperature sensor, a pressure sensor, and a current simulator according to the present invention.
7 is a circuit diagram constituting a voltage level converting section according to the present invention.

Hereinafter, an aircraft electronic engine controller (ECCU) inspection apparatus according to the present invention will be described with reference to the drawings.

1, an EECU testing apparatus according to the present invention includes a power supply unit 100, an input / output unit 200, a LAN communication unit 300, and an interface board 400, and is connected to a host computer and an EECU do.

The power supply unit 100 includes a first power supply unit for supplying DC 24 V power to the interface board 400 and the input and output unit 200 respectively and a second power supply unit for supplying DC 28 V power to the EECU.

The input and output unit 200 includes an input and output power unit 210, an input and output control unit 220, a communication unit 230, an analog output unit 240, an analog input unit 250, a digital output unit 260, and a digital input unit 270 do.

Table 1 is a table showing the configuration and functions of the input / output unit 200.

Components function Power supply Power supply for all input and output The control unit Main controller of input / output part (RT-OS equipped) SBC-TM1 Control unit and host PC connection terminal I / O Pack


The communication unit (M706) ARINC, SERIAL, CAN communication Analog output (IP231-16) 16 channels Analog input (IP330A) 32 channels Digital input / output (IP408) 32 channels CB1 Connect I / O pack M706 to I / O sub bus CB2 Connect two I / O packs IP231-16 to I / O bus CB3 One I / O pack IP231-16 and IP330A connected to I / O sub bus CB4 Connect two I / O packs IP408 to I / O bus TM1 Connect CB1's I / O to interface board TM2 Connect CB2's I / O to interface board TM3 Connect CB3's I / O to interface board TM4 Connect CB4's I / O to interface board

The input / output power supply unit 210 receives power of DC 24V from the power supply unit 100 and supplies power to the entire input / output unit. The input / output control unit 220 is a single board controller (SBC) equipped with an RT-OS (Real Time Operating System) as a main controller connected to the host PC to control the operation of the entire input / output unit 200 . The communication unit 230 is connected to the interface board through the terminal TM1 for ARINC 429, CAN (Controller Area Network), and serial communication with the interface board 400. The analog output unit 240 is composed of three 16-channel packs and is connected to the interface board 400 via the terminals TM2 and TM3. Two 16-channel packs are connected through the terminal TM2, Are connected via the terminal TM3. The analog input unit 250 is composed of one 32-channel pack and is connected to the interface board 400 through the terminal TM3. Digital Output Unit 260 The SLC digital input unit 270 is composed of two 32-channel packs and is connected to the interface board 400 via the terminal TM4. The communication unit 230, the analog output unit 240, the analog input unit 250, the digital output unit 260, and the digital input unit 270 are each mounted on a carrier board and connected to the input / output sub-bus.

The LAN communication unit 300 makes data transmission between the input / output unit 300 and the interface board 400 of the EECU testing apparatus and the host PC and the EECU through ARINC 429, CAN (Controller Area Network), or serial method, 8 ports, but is not limited thereto.

1, the interface board 400 includes an interface power unit 410, an engine output control unit 420, a speed sensor simulation unit 430, a temperature sensor simulation unit 440, a pressure sensor simulation unit 450, A current simulation unit 460, a voltage level converter 470, a voltage-current converter 480, an on / off controller 490, and connection terminals for connection to the input / output unit and the EECU.

2 is a diagram showing the input / output configuration of the interface board, and Table 2 is a table showing the configuration and function of the connection terminals of the interface board.

Configuration function IFJ1 Connected with TM1 in I / O IFJ2 Connection with TM2 of I / O IFJ3 Connection with TM3 of I / O IFJ4 Connection with TM4 of I / O IFJ5 POWER SUPPLY connection IFJ6 Connecting the ammeter to indicate the current consumed by the EECU IFJ7 Interface board power and EECU power input IFJ8 It is connected with the connection connectors J1 and J3 of the EECU inspection device and communicates with EECU and digital signal input / output IFJ9 EECU Connected with the connection connectors J1, J3 of the test equipment, EECU power supply and analog signal input / output IFJ11 EECU is connected to the connection connectors J2 and J4 of the test equipment and communicates with EECU and digital signal input / output IFJ12 EECU is connected to the connection connectors J2, J4 of the test equipment, and the EECU power supply and analog signal input / output

2, the connection terminal IFJ1 of the interface board is connected to the input / output unit communication unit M706 via the TM1 of the input / output unit 200, and the TM2 of the input / output unit 200 is connected to the connection terminal IFJ2. Output port 200 via the TM3 of the input / output section 200 to one analog output pack IP231-16 and one analog input pack IP330A via the connection terminal IFJ3, And the connection terminal IFJ4 is connected to the two digital input / output packs IP408 via TM4 of the input / output unit 200. [ A power supply (POWER SUPPLY) is connected to the connection terminal IFJ5 and an ammeter of EECU channels A and B is connected to the connection terminal IFJ6. And is mounted on the front side of the EECU inspection apparatus as shown in FIG. EECU's channel A communication, digital I / O, power and analog I / O signals are connected to the connection terminal (J1 J3), and channel B communication, digital signal input / output, power supply, and analog input / output signals of the EECU are transmitted / received to / from the EECU through the connection connectors J2 and J4 to the connection terminals IFJ10 and IFJ11. , J2, J3, J4) are connected to the rear side of the EECU inspection apparatus.

3, the EECU inspection apparatus according to the present invention has a main power source voltmeter and ammeter of AC 22V, channel A and B ammeter of EECU, a LAN connector, an input / output power switch, a main power switch, and an EECU power supply And four EECU connector insertion portions, a main power connector insertion portion, and a fan are mounted on the rear portion thereof.

Table 3 is a table showing the description of the input / output signals converted by the interface board and the signal specifications.

[Table 3]

1 and 4, the interface power supply unit 410 supplies the power (+28 V_EECU-A) of DC 28V received from the second power supply unit 210 via the terminal IFJ7 to the connector J1) to the EECU, and the power supplied to the EECU is preferably DC28V +/- 0.5V.

As shown in FIGS. 1 and 5, the engine output control unit 420 receives the engine output power signal PLA-A_EX of 3 to 7.5 V from the EECU and level-converts the engine output power signal PLA-A_EX to 12 to 30 V, And receives an engine output signal PLA-AP of 0.8 to 4.0 V from the analog output unit 240 of the input / output unit 200 and converts the voltage-current (VI) of 4 to 20 mA into an EECU .

As shown in FIGS. 1 and 6, the speed sensor simulator 430 transfers the high-pressure shaft speed and the fan speed to the EECU. That is, the high-pressure shaft speed signal NH-A_P of +10 to -10 V (corresponding to 0 to 2000 Hz) is received and simulated from the analog output section 240 of the input / output section 200 and input to the EECU, (Corresponding to 0 to 2000 Hz) of the fan speed signal NF-A_P from the analog output unit 240 of the EEPROM 200 to the EECU.

As shown in FIGS. 1 and 6, the temperature sensor simulator 440 is configured to simulate the ambient temperature, the fuel temperature, the oil temperature, the starter / generator temperature, the first spare thermocouple temperature, the second spare thermocouple temperature, To the EECU. That is, an exhaust gas temperature signal (T6-A_P) of -2 to +42 mV (corresponding to -53 to +1019 ℃) is received from the analog output section 240 of the input / output section 200 and is input to the EECU, A -P from the analog output section 240 of the input / output section 200 to +8 to +14 mV (corresponding to -51 to + 104 ° C), inputs the analogized temperature signal TAMB-A_P to the EECU, A_P) of +9 to +14 mV (corresponding to -25 to +104 캜) from the analog output section 240 of the input / output section 200, and inputs the fuel temperature signal TFuel- Receives an oil temperature signal (TOil-A_P) of +9 to +16 mV (corresponding to -25 to + 157 ° C) from the analog output unit 250 and inputs the oil temperature signal to the EECU. The starter / generator temperature signal (TSG-A_P) of +42 to + 190 mV (corresponding to -21 to +221 캜) is received from the analog output section 240 and is sampled and input to the EECU. Also, the first spare thermocouple temperature signal (TC_SP_1-A_P) of -2 to +42 mV (corresponding to -53 to +1019 캜) is received from the analog output section 240 and is sampled and input to the EECU, +8 to +14 mV (corresponding to -51 to + 104 ° C), receives and simulates a second spare thermocouple temperature signal (TC_SP_2-A_P) of + 42mV (corresponding to -53 to +1019 ° C) (RTD_SP_1-A_P) of the spare RTD temperature signal (RTD_SP_1-A_P) and inputs it to the EECU.

As shown in FIGS. 1 and 6, the pressure sensor simulator 450 simulates the atmospheric pressure, the fuel pressure, the oil pressure, the compressor discharge pressure, the first spare pressure, and the second spare pressure and delivers them to the EECU. That is, the air pressure signal PAMB-A_P of 0 to +10 V (corresponding to 0.8 to 1.2 Bar) is received and simulated from the analog output unit 240 of the input / output unit 200 and input to the EECU, (Corresponding to 0 to 10 Bar) from the analog output unit 240 and receives the fuel pressure signal PFuel-A_P of 0 to +10 V (corresponding to 0 to 25 Bar) And receives the compressor output pressure signal PS3-A_P of 0 to + 10V (corresponding to 0 to 10 Bar) from the analog output section 240 And inputs them to the EECU. Also, the first spare pressure signal PS1_SP_1-A_P of 0 to + 10V is received from the analog output unit 240, and the first spare pressure signal PS1_SP_1-A_P is input from the analog output unit 240 to the EECU. Receives and simulates the signals (PS1_SP_2-A_P) and inputs them to the EECU.

1 and 6, the current simulating unit 460 receives and simulates a signal GPcur-A of 0 to + 10V from the analog output unit 240 and inputs it to the EECU.

1 and 7, the voltage level converter 470 includes a compressor output pressure sensor power supply, an atmospheric pressure sensor power supply, a fuel pressure sensor power supply, an oil pressure sensor power supply, an ADU (Antenna Distribution Unit) Emergency Power Unit) power, the first spare pressure sensor power supply, the second spare pressure sensor power supply, the spare RTD power supply, and the engine output control power supply, and inputs them to the EECU.

That is, when a compressor outlet pressure sensor power supply signal of +2.25 to +2.25 V is input to the analog input unit 250 of the input / output unit 200, the compressor output pressure sensor power supply signal PS3-A_EX of +9 to + And the standby pressure sensor power supply signal (PAMB-A_EX) of +2.25 to +2.25 V is input to the EECU and the standby pressure sensor power supply signal (PAMB-A_EX) of +9 to + And the fuel pressure sensor power supply signal (PFuel-A_EX) of +2.25 to + 8.25 V is input to the EECU and the fuel pressure sensor power supply signal (PFuel-A_EX) of +9 to +33 V is inputted to the analog input unit 250 Level input to the EECU and the oil pressure sensor power supply signal (POil-A_EX) of +9 to + 33V when the oil pressure sensor power supply signal (POil-A_EX) of +2.25 to + 8.25V is input to the analog input unit 250, And inputs them to the EECU. When the first spare pressure sensor power supply signal PS1-SP_1-A_EX of +2.25 to +2.25 V is input to the analog input unit 250, the first spare pressure sensor power supply signal PS1-SP_1- A_EX) and input to the EECU. When the second spare pressure sensor power supply signal (PS1-SP_2-A_EX) of +2.25 to +2.25 V is input to the analog input unit 250, the second spare The level is converted into pressure sensor power supply signal (PS1-SP_2-A_EX) and input to EECU.

The voltage-current converter 480 converts the voltage of the atmospheric temperature sensor power supply, the fuel temperature sensor power supply, the oil temperature sensor power supply, the first spare pressure sensor power supply, the second spare pressure sensor power supply, the spare RTD power supply, And inputs it to the EECU.

That is, when a 1V ambient temperature sensor power supply signal (TAMB-A_EX) is input to the analog input unit 250 of the input / output unit 200, voltage-current conversion is performed with a standby temperature sensor power supply signal TAMB-A_EX of 0.1 mA to the EECU Current input to the analog input unit 250 is input to the EECU when the 1-volt fuel temperature sensor power supply signal TFuel-A_EX is input to the analog input unit 250, and voltage-current converted by the fuel temperature sensor power supply signal TFuel- (TOil-A_EX) is input to the oil temperature sensor 250, the oil-temperature-sensor-power-supply signal TOil-A_EX is input to the EECU. When a spare RTD power supply signal (RTD_SP_1-A_EX) of 1V is input to the analog input unit 250, voltage-to-current conversion is performed with a spare RTD power supply signal (RTD_SP_1-A_EX) of 0.1 mA and input to the EECU.

The on / off control unit 490 processes the 0 or 5V signal received from the digital output unit 250 and the digital input unit 270 and inputs the 0 or 5V signal to the EECU.

An aircraft electronic engine controller (ECCU) inspecting apparatus according to the present invention is connected between a host computer and an EECU so that a host computer can execute simulation commands such as engine output, speed, temperature, pressure, Output unit 200 of the apparatus, the input / output control unit 220 of the input / output unit) transmits the corresponding output to the interface board 400 through the analog output unit 240 of the input / output unit, To the corresponding simulated signal in the simulator and transfers it to the corresponding pin of the EECU.

On the contrary, the values output from the EECU are received by the interface board 400, converted and transmitted to the analog input unit 250 and the input / output control unit 220 of the input / output unit 200, And is output according to a predetermined scale so that the user can see the screen.

As described above, the EECU testing apparatus according to the present invention is a CPIA (Compact Peripheral Component Interconnect) providing a standard I / O module (± 10V AIO, TLL level DIO, etc.) It is possible to improve the reliability of the inspection apparatus and shorten the production period by producing an interface board for converting the output value into the output value.

Also, the EECU inspection apparatus according to the present invention is manufactured in a portable size so that EECU inspection can be performed at any place.

In addition, the EECU testing apparatus according to the present invention can measure and control data at precise timing using the RT-OS, and can control all input / output signals from the host PC and automatically check the EECU.

The foregoing description is merely illustrative of the technical idea of the present invention and various changes and modifications may be made without departing from the essential characteristics of the present invention by those skilled in the art. Therefore, the embodiments disclosed in the present invention are not intended to limit the scope of the present invention but to limit the scope of the present invention. The scope of protection of the present invention should be construed according to the following claims, and all technical ideas within the scope of equivalents thereof should be construed as falling within the scope of the present invention.

Claims (10)

An aircraft EECU inspection apparatus comprising an interface board, an input / output unit, a power supply unit for supplying power to the EECU, an input / output unit, a LAN communication unit, and an interface board and connected by LAN communication between the host computer and the EECU,
The interface board
An interface power unit receiving power from the power unit and supplying power to the EECU;
An engine output control section for transmitting an engine output power signal and converting the voltage level into an analog input section of an input / output section, receiving an engine output signal from an analog output section of the input / output section,
A simulator for receiving and simulating engine output, speed, temperature, pressure and current signals from the analog output;
Compressor output pressure sensor power supply, atmospheric pressure sensor power supply, fuel pressure sensor power supply, oil pressure sensor power supply, ADU power supply, EPU power supply, first spare pressure sensor power supply, second spare pressure sensor power supply, spare RTD power supply, engine output control power supply A voltage level converter for converting the voltage level and inputting the voltage level to the EECU;
Air temperature sensor power supply, fuel temperature sensor power supply, oil temperature sensor power supply, first spare pressure sensor power supply, second spare pressure sensor power supply, spare RTD power supply, engine output control voltage Voltage to be converted into current and input to EECU - A current converter;
And an on / off control unit for processing signals received from the digital output unit and the digital input unit and inputting the processed signals to the EECU.
The method according to claim 1,
Wherein the communication unit uses ARINC 429, CAN communication, or serial communication method.
The method according to claim 1,
The input /
An input / output power supply unit;
An input / output control unit for controlling input and output of analog and digital data according to a command of the host PC;
A communication unit for connecting the input / output unit and the interface board;
An analog output unit for outputting analog data to the interface board in response to a command from the input / output control unit;
An analog input for receiving analog data from the interface board;
A digital output unit for outputting digital data to the interface board according to a command of the input / output control unit; And
And a digital input unit for receiving digital data from the interface board.
The method according to claim 1,
Wherein the simulator includes a speed sensor simulator, a temperature sensor simulator, and a pressure sensor simulator.
5. The method of claim 4,
Wherein the speed sensor simulator receives and simulates a high-pressure shaft speed signal and a fan speed signal from an analog output unit and transmits the simulated high-speed shaft speed signal and the fan speed signal to the EECU.
6. The method of claim 5,
Wherein the high-pressure shaft speed signal and the fan speed signal are signals of +10 to -10 V corresponding to 0 to 2000 Hz.
5. The method of claim 4,
The temperature sensor simulator receives an atmospheric temperature signal, a fuel temperature signal, an oil temperature signal, a starter / generator temperature signal, a first spare thermocouple temperature signal, a second spare thermocouple temperature signal, and a spare RTD temperature signal from the analog output section And transmits it to the EECU.
8. The method of claim 7,
The ambient temperature is a signal of +8 to +14 mV corresponding to -51 to + 104 ° C,
The fuel temperature is a signal of +9 to +14 mV corresponding to -25 to + 104 ° C,
The oil temperature is a signal of +9 to +16 mV corresponding to -25 to + 157 ° C,
The starter / generator temperature is a signal of +42 to + 190 mV corresponding to -21 to + 221 ° C,
Wherein the first and second spare thermocouple temperatures are -2 to +42 mV signals corresponding to -53 to +1019 ° C,
Wherein the spare RTD temperature is a signal of +8 to +14 mV corresponding to -51 to + 104 ° C.
5. The method of claim 4,
The pressure sensor simulator receives and simulates an atmospheric pressure signal, a fuel pressure signal, an oil pressure signal, a compressor outlet pressure signal, a first spare pressure signal, and a second spare pressure signal from the analog output unit, EECU inspection equipment for aviation.
10. The method of claim 9,
The atmospheric pressure is a signal of 0 to + 10V corresponding to 0.8 to 1.2 Bar,
The fuel pressure is a signal of 0 to + 10V corresponding to 0 to 25 Bar,
The oil pressure is a signal of 0 to + 10V corresponding to 0 to 10 Bar,
The compressor discharge pressure is a signal of 0 to + 10V corresponding to 0 to 10 Bar,
Wherein the first spare pressure signal and the second spare pressure signal are signals of 0 to + 10V.

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