KR100840613B1 - Aircraft Automatic Rudder Trim Control System Test Device - Google Patents

Abstract

The present invention relates to a test apparatus for an automatic aircraft rudder trim control device, and more particularly, to an aircraft connecting terminal connected to an aircraft, an automatic rudder trim control device connecting terminal and an aircraft connecting terminal connected to an automatic rudder trim control, and an automatic A plurality of connection lines for connecting the rudder trim control device connection terminals are provided for each signal, so that the signal output from the aircraft is transmitted to the automatic rudder trim control device and the signal output from the automatic rudder trim control device is transmitted to the aircraft. A connecting portion to perform; A measuring unit for measuring a transmission signal between the aircraft and the automatic rudder trim control device, having a plurality of drawing lines for drawing signals from each connection line, and a plurality of measuring terminals respectively formed at ends of the drawing lines. Wow; Aircraft auto rudder consisting of a switch unit installed at each take-out line and provided with a plurality of selection switches to turn on / off signal transmission to a corresponding measurement terminal and select a measurement terminal at the time of measurement. A test apparatus for a trim control device.

According to the present invention, by easily measuring signals exchanged between the aircraft and the automatic rudder trim control device through a multimeter, the automatic rudder trim control device can be easily bench-tested. In addition, there is an advantage that can solve the problem of consumption of test time, inefficiency caused by re-installation during maintenance, and improvement of reliability.

Automatic rudder trim control device, aircraft, test device

Description

Aircraft Automatic Rudder Trim Control System Test Device             

1 is a perspective view showing the shape of a conventional automatic rudder trim control device.

Figure 2 is a perspective view showing the shape and application state of the aircraft automatic rudder trim control device test apparatus according to a preferred embodiment of the present invention.

FIG. 3 is a conceptual diagram schematically illustrating a configuration and circuit connection of an apparatus for testing aircraft automatic rudder trim control shown in FIG. 2.

4 is a flowchart illustrating a flow of a process of measuring a rudder trim tap position signal during a test using the test apparatus of the aircraft automatic rudder trim control device illustrated in FIGS. 2 and 3.

<Description of the symbols for the main parts of the drawings>

10: automatic rudder trim control device

11: I / O terminal of automatic rudder trim control device

20: connecting cable

30: Automatic rudder trim control connection terminal of aircraft

1000: Test device for aircraft automatic rudder trim control device                 

100: connection

110: aircraft connection terminal

120: automatic rudder trim control device connection terminal

131 ~ 141: connecting line

200: measuring unit

210 ~ 220: Drawout line

240 ~ 250: Measurement terminal

300: switch unit

310 ~ 320: Selection switch

The present invention is connected to the aircraft and the automatic rudder trim control device to easily measure signals exchanged with each other through a multimeter, so that the bench test of the automatic rudder trim control device can be easily performed. The present invention relates to a test apparatus for an aircraft automatic rudder trim control device.

In general, an aircraft equipped with a propeller is equipped with an automatic rudder trim control device for performing the attitude correction of the aircraft by preventing the aircraft from being leaned to one side during flight.                         

1 is a perspective view showing the shape of a conventional automatic rudder trim control device, as shown, the automatic rudder trim control device 10 is formed in a box shape, the interlocking terminal inside the aircraft through the input and output terminal 11 30 is connected to the connection cable 20, from the equipment of the attitude detection and trim control system in the aircraft, that is, attitude attitude reference device (AHRS: Attitude Heading Reference System (AHRS), flap micro switch, control surface trim control panel, etc. It receives the information and outputs the rudder trim control signal of the aircraft.

However, when the automatic rudder trim control device 10 is abnormal, it is difficult to properly control the flight balance of the aircraft, and thus the probability of serious flight accident increases, so the automatic rudder trim control device 10 should always check its correct operation. do.

Therefore, in the related art, the automatic rudder trim control device 10 is mounted on an aircraft, and then the operation test of the automatic rudder trim control device 10 is carried out at the ground test of the aircraft to the automatic rudder trim control device 10. Check if there is any problem.

By the way, when checking the conventional automatic rudder trim control device 10, it is not possible to directly determine whether or not the abnormality of each signal exchanged between the aircraft and the automatic rudder trim control device 10 mounted on the aircraft, when the failure is found There is a problem that takes a long time to find the cause.

Because, in order to measure the exchange signal between the aircraft and the automatic rudder trim control device 10, tearing off the connection cable 20 connecting the aircraft and the automatic rudder trim control device 10 to find the signal line and then the signal Because it has to be measured.

In addition, if a failure is found in the automatic rudder trim control device 10, the inefficiency of detaching the already mounted automatic rudder trim control device 10 from the aircraft for the failure repair and mounting on the aircraft again after repairing the failure There are also problems that exist.

The present invention was devised to solve these problems, and is connected to the aircraft and the automatic rudder trim control device so that signals exchanged with each other can be easily measured through a multimeter, thereby simply bench testing the automatic rudder trim control device. An object of the present invention is to provide an aircraft automatic rudder trim control device testing device.

In order to achieve the above object, the present invention, in the device for testing the normal operation of the automatic rudder trim control device of the aircraft, the aircraft connection terminal connected to the aircraft, automatic rudder trim control device connected to the automatic rudder trim control A plurality of connection lines for connecting the connecting terminal and the aircraft connecting terminal and the automatic rudder trim control device connecting terminal are provided for each signal, and the signal output from the aircraft is transmitted to the automatic rudder trim control device and output from the automatic rudder trim control device. A connection unit for transmitting a signal to the aircraft; A measuring unit for measuring a transmission signal between the aircraft and the automatic rudder trim control device, having a plurality of drawing lines for drawing signals from each connection line and a plurality of measuring terminals respectively formed at ends of the drawing lines. Wow; It is provided with a switch unit which is provided in each lead-out line and provided with a plurality of selection switches to turn on / off signal transmission to a corresponding measurement terminal, so that the measurement terminal can be selected at the time of measurement.

Hereinafter, preferred embodiments of the present invention will be described with reference to the accompanying drawings so that those skilled in the art can easily implement the present invention in detail.

First, in adding reference numerals to components of each drawing, the same components are described so as to have the same reference numerals as much as possible even if displayed on different drawings.

Figure 2 is a perspective view showing the shape and application state of the aircraft automatic rudder trim control device test apparatus according to a preferred embodiment of the present invention, Figure 3 is a configuration and circuit of the aircraft automatic rudder trim control device test apparatus shown in FIG. A conceptual diagram schematically showing the connection.

As shown in Figure 2, the test apparatus 1000 of the aircraft automatic rudder trim control device according to a preferred embodiment of the present invention is connected to the aircraft and the automatic rudder trim control device 10, respectively, the aircraft and the automatic rudder trim control device (10) performs a function to measure the signal exchanged between.

For the sake of understanding, first, the signals exchanged between the aircraft and the automatic rudder trim control device 10 will be described.

1. Engine torque signal (TQ: Torque): The engine torque signal is an analog signal and is input to the automatic rudder trim control device 10 from an engine torque sensor inside the aircraft. This signal ranges from 0 to 80mV.

2. Arlink 429 (ARINC429) signal: When the input data is ARINC429 serial data, this signal is a signal input from the attitude orientation reference apparatus to the automatic rudder trim control device 10. The form of this signal is ARINC429 bus data, the signal range is -4 to + 4 g, the Octal Label is 332, and the transmission rate is 100 KHz (if High Speed).

The ARINC429 serial data signal is also a serial data bus signal using the same connector / pin and wire harness as the aircraft's speed signal and the aircraft's transverse acceleration signal on the system.

3. Flap position signal: The flap position signal is used to distinguish the flight shape according to the flap position, that is, the cruise shape, the landing shape, and the takeoff shape. This signal is an automatic rudder trim control device from the flap micro switch. 28Vdc discrete signal input to (10).

4. Rudder trim tap position signal (TAP POS): Rudder trim tap position signal is a rudder trim to accurately control the rudder trim motor of the aircraft according to the rudder trim command calculated by the automatic rudder trim control device 10. This signal indicates the current trim tap position from the motor. This signal is an analog signal so that the trim tap position of -5 to +20 degrees corresponds to an electrical signal of 0 to 18 Vdc, but there is actually some error range. Therefore, this signal should be able to be scaled to match the signal of the actual trim motor.

5. Engage signal: Engage signal is a signal for operating the auto rudder trim control device 10 in auto rudder trim mode and is input from the trim control panel of the control surface, which is one of the components of the auto rudder trim control system. Signal. This signal is generated by the pilot turning on / off the cage switch of the trim control panel.

6. Engage Hold Signal: This signal is connected to the trim control panel's in-gauge switch. When this switch is + 28Vdc, the trim control panel's in-cage switch can be kept on. Will be. Therefore, when the error occurs in the automatic rudder trim control device 10, the signal is opened to automatically turn off the engagement gauge to operate in the manual rudder trim mode. It becomes possible.

7. ARTS Fail Signal: This signal is transmitted to the alarm device when an error occurs in the automatic rudder trim control device 10 or when the power is not supplied to the automatic rudder trim control device 10. This signal is output + 28Vdc when the system is in normal operation, and is open or ground when the system fails or power is not supplied.

8. Operation mode signal: The operation mode signal is a signal used to determine the operation mode of the automatic rudder trim control device 10.

9. Bit switch signal: The bit switch signal self-diagnoses the automatic rudder trim control device 10 or stores the operation related data of the automatic rudder trim control device 10 in a non-volatile memory (NVM) during flight. It is a switch signal used to.

10. Bit ramp signal: The bit ramp signal is transmitted from the automatic rudder trim control device 10 to the trim control panel. When the bit store switch signal is input to the automatic rudder trim control device 10 at a speed of 70 Kts or less, the automatic rudder trim control device 10 turns on the bit lamp for five seconds during the bit period. In addition, if no error is found in the device during the bit period, this bit lamp turns off immediately, and if the device finds an error during the bit period, the bit lamp blinks for about 10 seconds and then turns off.

11. RS422 signal: The RS422 signal is used when downloading a program to the automatic rudder trim control device 10 or checking the automatic rudder trim control device 10. Communication with the automatic rudder trim control device 10 by the RS422 serial communication method.

As above.

Meanwhile, referring to FIG. 3, the test apparatus 1000 of the automatic aircraft rudder trim control device includes a connection part 100, a switch part 300, and a measurement part 200.

The connection unit 100 is connected to the aircraft rudder trim control connection terminal 30 of the aircraft and the rudder rudder control device connectable to the input and output terminal 11 of the rudder rudder trim control device 10. By connecting the terminal 120 and the aircraft connecting terminal 110 and the automatic rudder trim control device connecting terminal 120 to each other, the signal output from the aircraft is transmitted to the automatic rudder trim control device 10 and the automatic rudder trim control device The signal output from 10 includes a plurality of connection lines 130 to 140 which are transmitted to the aircraft, and performs a function of interworking the aircraft and the automatic rudder trim control device 10.

At this time, the aircraft rudder trim control connection terminal 30 and the aircraft rudder terminal 110 of the automatic rudder trim control device test apparatus 1000 and the input / output terminal 11 of the rudder trim control device 10 and the automatic rudder trim The auto rudder trim control device connection terminals 120 of the control device test device 1000 are connected to each other via a connection cable 20.

The measurement unit 200 includes a plurality of lead lines 210 to 220 for drawing signals from the respective connection lines 130 to 140 of the connection unit 300 and the ends of the lead lines 210 to 220. Equipped with a measuring terminal (240 ~ 250) of the, to perform the function to measure the output signal of the aircraft or automatic rudder trim control device 10 input through the connection unit 100 using the multimeter (40) do.

In this case, the configuration of the measurement terminals 240 to 250 includes an engine torque signal measurement terminal 240 so as to measure an engine torque signal, an aerck 429 measurement terminal 241 capable of measuring an aerck 429 signal, and a flap. Flap position signal measuring terminal 242 capable of measuring position signals, rudder trim tap position signal measuring terminal 243 capable of measuring rudder trim tap position signals, and engagement gauge capable of measuring engagement signals The measurement terminal 244, the gauge hold signal measurement terminal 245 capable of measuring the signal measurement signal, the artefact measurement terminal 246 capable of measuring the artefact signal, and the operation mode signal. Operation mode signal measurement terminal 247 which can measure, the bit switch signal measurement terminal 248 which can measure a bit switch signal, the bit ramp signal measurement terminal 249 which can measure a bit ramp signal, and an egg. S422 signal side It is composed of Al-S 422 measuring terminal 250 that can be preferred.

The switch unit 300 is provided in each of the lead-out line (210 ~ 220) of the above-described connection unit a plurality of select switches 310 to turn on (on) / off (Off) the signal transmission to the corresponding measurement terminals (240 ~ 250) And 320 to perform a function of selecting a desired measurement terminal 240 to 250 during measurement.

In this case, the configuration of the detailed selection switches 310 to 320 of the switch unit 300 corresponds to each of the measurement terminals 240 to 250, so that the engine torque signal measurement selection switch 310 and the alink 429 signal measurement selection switch 311 ), Flap position signal measurement selection switch 312, rudder trim tap position signal measurement selection switch 313, Engage signal measurement selection switch 314, Engage hold signal measurement selection switch 315, Arts Fail signal measurement selection The switch 316, the operation mode signal measurement selection switch 317, the bit switch signal measurement selection switch 318, the bit ramp signal measurement selection switch 319, and the RS422 signal measurement switch 320.

4 is a flowchart illustrating a process of measuring a rudder trim tap position signal during a test using the test apparatus 1000 of the automatic aircraft rudder trim control device illustrated in FIGS. 2 and 3.

First, the operator uses the automatic rudder trim control connection terminal 30 of the aircraft and the input / output terminal 11 of the automatic rudder trim control device to connect the aircraft rudder trim control device 110 and the automatic rudder trim control of the automatic rudder trim control device test apparatus 1000. Connect to the device connection terminal 120 using the connection cable 20, respectively (step: S1).

After connection, when the operator turns on the rudder trim tap position signal measurement selection switch 313 of the switch unit 300 (step: S2), the rudder trim tap position signal measurement selection switch 313 is a rudder trim tap position signal. The lead line 213 connected to the measurement terminal 243 is switched to be connected (step: S3), and the rudder trim tap position signal measurement terminal 243 is applied to the rudder trim tap position signal (step: S4).

Subsequently, the operator uses the red terminal of the multimeter 40 to the positive terminal 243a of the rudder trim tap position signal measuring terminal 243, and the black terminal to the negative terminal 243b of the rudder trim tap position signal measuring terminal 243. To measure the rudder trim tap position signal (step S5), and check whether the rudder trim tap position signal is normal (step S6).

In the same way, by measuring / checking signals exchanged between the aircraft and the automatic rudder trim control device 10 using the multimeter 40, it is possible to know whether the automatic rudder trim control device 10 operates normally. .

As mentioned above, although preferred embodiments of the present invention have been described in detail, those of ordinary skill in the art to which the present invention pertains should realize the present invention without departing from the spirit and scope of the present invention as defined in the appended claims. It will be appreciated that various modifications or changes can be made.

In particular, in the above embodiment, 11 representative signals exchanged between the aircraft and the automatic rudder trim control device 10 have been mentioned, but the other configurations can be applied to the same configuration as the above-described embodiment. Of course it will.

Accordingly, modifications to future embodiments of the present invention will not depart from the technology of the present invention.

As described above, according to the present invention, by easily measuring signals exchanged between the aircraft and the automatic rudder trim control device through a multimeter, the automatic rudder trim control device can be easily bench-tested. There is an advantage in that it can solve the manpower consumption problem, the test time consumption problem, inefficiency caused by the re-installation during maintenance, and the reliability improvement problem.

Claims (2)

In the device for testing the normal operation of the automatic rudder trim control device of the aircraft, The aircraft connection terminal connected to the aircraft, an automatic rudder trim control device connection terminal connected to the automatic rudder trim control, and a plurality of connection lines interconnecting the aircraft connection terminal and the auto rudder trim control device connection terminal for each signal A connection unit configured to transmit a signal output from the aircraft to the auto rudder trim control device and transmit a signal output from the auto rudder trim control device to the aircraft; A plurality of lead-out lines for extracting signals from each of the connection lines and a plurality of measurement terminals respectively formed at the ends of the lead-out lines to measure a transmission signal between the aircraft and the automatic rudder trim control device. Measuring unit; And a switch unit installed at each of the lead-out lines and provided with a plurality of selection switches to turn on / off signal transmission to a corresponding measurement terminal, so that the measurement terminal can be selected at the time of measurement. Test apparatus for aircraft automatic rudder trim control device. 2. The measuring terminal of claim 1, wherein the measuring terminal comprises: an engine torque signal measuring terminal capable of measuring an engine torque signal; an aerck 429 measuring terminal capable of measuring an aerck 429 signal; and a flap capable of measuring a flap position signal. The position signal measurement terminal, the rudder trim tap position signal measurement terminal for measuring the rudder trim tap position signal, the gauge signal measurement terminal for measuring the engagement signal, and the gauge hold signal measurement signal can be measured. Engage hold signal measurement terminal, artsail measurement terminal for measuring the artefact signal, operation mode signal measurement terminal for measuring the operation mode signal, and bit switch signal measurement for the bit switch signal measurement Terminal, a bit ramp signal measurement terminal capable of measuring beat ramp signals, and an RS 422 signal measurement terminal capable of measuring RS422 signals Automatic test equipment of the aircraft rudder trim control device comprising: a.

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