JPH1096654A - Air-conditioning line tester - Google Patents

Abstract

PROBLEM TO BE SOLVED: To grasp states of a control panel in a cockpit of an air-conditioning system of an aircraft and an airframe of a controller by setting a computer in which signals of a pressure sensor and a temperature sensor are input and analyzed, etc. SOLUTION: Signals of a pressure sensor 21 and a temperature sensor 25 for detecting a pressure and a temperature of the air flowing in a duct are input and analyzed at a computer 32. A first control part graphically displays states of a control panel in a cockpit, a control device of an airframe controlling an air-conditioning system, and a temperature, a pressure and a flow rate in the duct at the same time in real time through remote control. In order to form a parameter for simulating a fly state high in the sky, a second control part carries out simulations by changing rates of a latitude, the temperature, a speed on the ground, forms a pseudo signal corresponding to the state high in the sky and transmits the signal to a controller 28. A third control part displays operation procedures at a display device and automatically judges whether or not measured items are good.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a test apparatus used for a function test of an air conditioning system (also referred to as an ECS system) of an aircraft and for troubleshooting (finding the cause of a defect).

[0002]

2. Description of the Related Art FIG. 25 shows a conventional technique. In the prior art, (1) when troubleshooting, (a) a temperature sensor value externally attached to the duct of the body, and
The cause of the failure was estimated from the pressure sensor value, (b) the temperature of the air blown out of the cock bit, and the flow rate, and troubleshooting was performed. (2) When performing a functional test, (a) the temperature sensor value and the pressure sensor value externally attached to the duct of the body are displayed independently of each other, and (b) humans make a pass / fail decision. .

[0003]

Problems with the conventional air conditioning system have the following problems. (1) When troubleshooting, the conventional troubleshooting method for the air conditioning system cannot (A) obtain information on the functional components of the airframe or the state of the control panel, etc. (B) Simulating the sky was impossible.

(C) Therefore, theoretical troubleshooting cannot be performed, and much time is required until the cause of the problem is determined. (2) When performing a function test, in the conventional function test method for an air conditioning system, (A) a person makes a determination, which takes time, and furthermore, a determination error may occur. (B) In addition, since the work procedure is performed in accordance with the work procedure manual written on paper, it takes much time, and it takes much time to change the procedure.

[0005]

[Means for Solving the Problems]

(First Means) An air conditioning line tester for an aircraft according to the present invention reads a digital signal from a controller for controlling an air conditioning system of an aircraft from the outside, thereby controlling a control panel in a cockpit of the air conditioning system of the aircraft and controlling the air conditioning system. (A) a controller for controlling an air-conditioning system, (B) a pressure sensor and a temperature sensor for detecting the pressure and temperature of air flowing in a duct, and (C) A) a computer for inputting and analyzing signals of the pressure sensor and the temperature sensor;
(D) A first control unit for remotely and simultaneously graphically displaying the status of the control panel in the cockpit, the status of the control device of the machine controlling the air conditioning system, and the status of the temperature, pressure, and flow rate in the duct in real time. And (E)
In order to create parameters for simulating the flight conditions in the sky conditions (altitude, speed, temperature), on the ground, simulate by changing the altitude, temperature, and speed rates to respond to the sky conditions. Create a pseudo signal,
A second control unit to be transmitted to the controller; and (F) a database unit in which an operator's operation instruction, a test procedure, a measurement item, a pass / fail determination value of the measurement item and parameters are described,
(G) a third control unit for displaying a work procedure on a display device in accordance with the contents described in the database and automatically determining whether or not the value of the measured item is acceptable.

That is, the air-conditioning line tester according to the present invention comprises: (1) at the time of troubleshooting, (a) adjusting the switch position of the control panel in the cockpit, and the air flow rate, which are output as signals from the controller 28 necessary for investigating the cause of the problem The aircraft's information is obtained in an integrated manner from the open / close position of the valve for use, alarm signal, air temperature and flow rate in the duct, and external temperature sensors and pressure sensors. (B) Changes in their status at a location away from the aircraft At the same time, it has a function that can be checked in real time, and (c) also has a function that can simulate the condition of the sky (altitude, speed, temperature) on the ground by changing the rate of change (rate) in response to a problem that occurred in the sky. , (D)
It also has a function to redisplay the results of troubleshooting in the past on the screen.

(E) Therefore, theoretical and effective troubleshooting can be performed. (2) At the time of the function test, (a) a function for displaying the work procedure on a screen from a database in which the work procedure, measurement items and specified values of the measurement items are described, and automatically measuring and judging the measured values. I have it.

(B) Therefore, a more accurate and quick function test becomes possible. Therefore, it operates as follows. When the operator operates the device and selects the trouble shooting mode or the function test mode, (1) the operation common to both modes (FIGS. 1 to 3), the opening and closing of the cockpit control panel 1 and the control valve of the air conditioning system. The state 2 is displayed graphically, and the presence / absence 3 of the alarm signal is also displayed. Therefore, (a) Even if a sudden trouble occurs in the body, it can be immediately confirmed.

(B) There are two types of duct temperature, one to measure from the temperature board, and the other to receive and measure data from the 1553B board. , And all of the externally mounted temperature sensor and pressure sensor values can be stored. (2) Action only at the time of troubleshooting (FIGS. 1 and 2), (a) Measured values of items to be monitored (for example, 8 items) are displayed in real time on a numerical and graphic basis, in a time-based manner. Is done.

(B) Then, when the pilot changes the temperature set value or the like of the control panel 1 in the cockpit, the volume and switches of the control panel on the screen are displayed as if they were in the cockpit.

(C) When the operator inputs a simulation signal of altitude, temperature and speed values to the controller 6, changes in the control valve, temperature, pressure, flow rate and the like according to the flight state can be confirmed.

(D) The simulation signal includes a start value, an end value,
The rate of change (rate) can be set. (3) Function only at the time of functional test (FIG. 3) (a) Test procedure 7 is displayed on the screen.

(B) The pass / fail judgment at this time is automatically performed by 8. (C) The result is stored on the hard disk of the computer. (D) Further, the description content of the database can be easily rewritten only with knowledge of the data format (FIG. 9). (E) Therefore, it is possible to easily change, add, or delete the test procedure.

[0014]

BEST MODE FOR CARRYING OUT THE INVENTION

(First Embodiment) FIG. 1 shows a first embodiment of the present invention.
24 to FIG. FIG. 1 is a screen display diagram (1) of a control device in a remote display, a simulation signal setting, and a function test according to the first embodiment of the present invention.

FIG. 2 is a screen display diagram (2) of a control device in remote display, simulation signal setting, and function test according to the first embodiment of the present invention. FIG. 3 is a screen display diagram (3) of the control device in remote display, simulation signal setting, and function test according to the first embodiment of the present invention.

FIG. 4 is a conceptual diagram of the connection between the airframe and the function test apparatus according to the first embodiment of the present invention. FIG. 5 is an external view of a cable and a sensor of the device according to the first embodiment of the present invention. FIG. 6 is a connection block diagram of the airframe and the function test device according to the first embodiment of the present invention.

FIG. 7 shows a signal according to the first embodiment of the present invention.
Electrical wiring diagram. FIG. 8 is a view showing an operation procedure (PAD) according to the first embodiment of the present invention. FIG. 9 is a diagram showing a test procedure database according to the first embodiment of the present invention.

FIG. 10 is an explanatory view (1) of a display screen according to the first embodiment of the present invention. FIG. 11 is an explanatory view (2) of a display screen according to the first embodiment of the present invention. FIG. 12 is an explanatory view (3) of a display screen according to the first embodiment of the present invention.

FIG. 13 is an explanatory view (4) of a display screen according to the first embodiment of the present invention. FIG. 14 is an explanatory view (5) of a display screen according to the first embodiment of the present invention. FIG. 15 is an explanatory view (6) of a display screen according to the first embodiment of the present invention.

FIG. 16 is an explanatory view (7) of a display screen according to the first embodiment of the present invention. FIG. 17 is an explanatory view (8) of a display screen according to the first embodiment of the present invention. FIG. 18 is an explanatory view (9) of a display screen according to the first embodiment of the present invention.

FIG. 19 is an explanatory view (10) of a display screen according to the first embodiment of the present invention. FIG. 20 is an explanatory view (11) of a display screen according to the first embodiment of the present invention. FIG. 21 shows the first embodiment of the present invention.
Display screen explanatory drawing (12) which concerns on an Example.

FIG. 22 is an explanatory view (13) of a display screen according to the first embodiment of the present invention. FIG. 23 is an explanatory view (14) of a display screen according to the first embodiment of the present invention. FIG. 24 shows the first embodiment of the present invention.
It is a display screen explanatory view (15) which concerns on an Example. (1) Description of Apparatus FIGS. 1 to 3 show screen displays of the control apparatus in remote display, simulation signal setting, and function test according to the first embodiment of the present invention.

FIG. 4 shows an external view of the connection between the aircraft and the device. As shown in FIG. 4, a function test device 200 is connected to a fuselage 100 of an aircraft. FIG. 5 shows an external view of the function test apparatus. As shown in FIG. 5, the function test device includes a bus cable 11 connecting the fuselage controller and the function test test device, a temperature sensor 12 connecting to the fuselage side duct,
The cable 13 has a hose and a tube 17 for connecting the body side duct to the pressure sensor 16, a cable 15 for connecting the pressure sensor 16 to the function test device 18, and an extension cable 14 for the pressure sensor.

FIG. 6 is a block diagram showing the cables and the locations where the sensors are attached to the body. FIG. 7 shows a signal flow. The pressure and temperature of the air flowing in the duct are detected by sensors (21, 25), and the current value from the pressure sensor 21 is converted to a voltage by a voltage conversion resistor 23 through a pressure sensor J1 receptacle 22, and the control device 37 A /
The voltage value is input to a D (analog / digital) board 24.

The voltage value from the temperature sensor 25 is input to the temperature board 27 of the control device 37 through the temperature sensor panel jack 26. At this time, the voltage value corresponding to the pressure value and the temperature value changes in proportion to the pressure and temperature values.

The bus signal from the air-conditioning controller 28 is received by the 1553B bus coupler 29, amplified, and input to the I / F board 30 of the control unit 37 of the 1553B. Here, the “1553B I / F board 30”
An interface board for exchanging signals with the machine-side controller 28.

The signals received by each board of the I / O expansion unit 31 of the control device 37 are processed by the computer 32 on the data of the control device 37 and their values and information are displayed on a screen.

A hard disk is built in the main body of the computer 32 of the control device 37 in order to store each data and the result of the pass / fail judgment in the function test. First control unit 10
The first, second control unit 102, third control unit 103, and database unit 104 serve as data input / output by a board in the I / O expansion unit 31 of the control device 37 and a program in a personal computer. 1 The control unit 101 controls A /
The D board, the temperature board, the 1553B I / F board and the program, and the second control unit 102
The F board and the program, the third control unit 103 is a program, and the database unit 104 is a database file called from the program.

The programs and database files are stored in the hard disk of the computer 32 of the control device 37. As an input device of the control device 37 to the computer (personal computer) 32, a ten keyboard 33 is used.
And mouse 3 for manually selecting monitor items
4 are provided.

A printer 35 is provided for outputting a pass / fail judgment result in the function test mode, a screen in the troubleshooting mode, and a hard copy. The uninterruptible power supply 36 is provided so that the computer (personal computer) and the extension unit can function normally even at the time of a power interruption or power failure. (2) Test Flow Next, a test flow will be described in detail with reference to FIGS. (2.1) Setup (preparation to start) Check that all cables, temperature sensors, and pressure sensors are attached and that power is supplied.

The switch of the uninterruptible power supply and the switch of the personal computer are turned on, and an initial input screen is displayed. (2.2) Initial input (Fig. 8) Enter the date, date, minute, measurer, inspector, temperature and humidity, air pressure, and machine number.

Here, the date, month, day, hour and minute are displayed by default by the internal calendar and timer of the personal computer (6).
2). The names of the measurer and the examiner are read from a file stored in the hard disk as text and displayed (61).

This registered name can be easily changed. When this screen is completed, a file for saving data is automatically created on the hard disk. (2.3) Test item selection screen, test preparation equipment and pre-test item procedure window (FIG. 8) Select a functional test (air source cart or engine run) or trouble shooting (42, 43).

Regardless of which is selected, the test preparation equipment window and the pre-test item procedure window 64 are displayed, and the operation is performed according to the contents. When it becomes more than one page in the window, it scrolls by one page.

Since these equipments and procedure contents are read and displayed as texts stored in the hard disk, they can be easily changed. (2.4) Function test start screen (when function test is selected) (Fig. 8) The bus signal from the aircraft is read and displayed on the control panel, the opening and closing of each valve, the alarm (bit), etc. (4)
3) Check if the operation is normal.

Since the shapes and display positions of the symbols displayed on the screen are stored as text files on the hard disk, they can be easily changed. (2.5) Functional test execution (Figs. 8 to 24) When the functional test is started, the database stored in the hard disk is read, and the test execution contents are displayed at the bottom of the screen for three steps, and the result screen is displayed. The required values (maximum value, minimum value) of the measurement item are displayed (65).

The measurement is automatically performed (66). When the measurement is completed, the actually measured value is displayed on the screen, and a pass / fail judgment is made. This scrolls one line each time one line is executed.

The execution may be performed automatically such as determination of a measurement item, or performed manually by a switch operation. If there is a pass / fail decision, it is saved on the hard disk regardless of the result.

FIG. 9 shows a database sample, and the details of each item of the database are shown below. In addition,
Symbols such as (1) and (2) in the following description of FIG. 9 correspond to symbols such as in FIG.

In FIG. 9, (1) indicates a step NO. (2): No / Yes 0: The step is invalid, 1: The step is valid (3): Comment display color 15 (white); Message or operator operation 2 (green); Operator confirms Or judgment 3 (Wed); Automatic measurement & judgment 4 (Red); Recorded by the worker 5 (Purple); Transmit altitude or temperature or speed parameter to the air conditioning (ECS) controller (4) Comment 50 characters maximum (Cannot be blank) (5) Manual / automatic 0 (man); Manual 1 (rcv); Reception 2 (snd); Transmission (6) Average number 1 to (Number) (7) Wait time 0 (8): Item No. 0 to 51 for received data 100 to 109 for transmitted data (9): Manual / automatic reception and transmission of minimum value or transmission value 5 (10) Is valid only for the maximum value received data (2.6 ) Troubleshooting item selection screen (Fig. 8)
(Fig. 18) (If trouble shooting is selected) Since the troubles expected in advance are registered, if there is a corresponding trouble in the trouble shooting sample window, select a sample therefrom, and monitor item, altitude, temperature Then, the speed is confirmed and registered collectively (67).

If the trouble does not apply to this,
Select Manual in the troubleshooting sample window and select the monitor item with the mouse (6
8). Next, in order to input a simulation signal to the controller, a start value, an end value, and a rate value of altitude, temperature, and speed are input (69).

Since the sample items are stored as files on the hard disk, they can be easily registered, deleted, and changed. (2.7) Troubleshooting start screen (Fig. 8-
(Fig. 19) The bus signal from the aircraft is read and the control panel
Opening / closing of each valve, alarm (bit), etc. are displayed on the screen, so whether they are normal or not, and 8 items selected on the troubleshooting selection screen displayed on the screen and altitude, temperature, speed start, end, Check if the rate value is correct (70).

Here, "8 items selected on the trouble shooting selection screen" means that when trouble shooting is performed,
Eight monitors can be made at the same time, but if a certain trouble is selected, eight monitor places are automatically selected according to the trouble. (2.8) Troubleshooting execution screen (Figs. 8 to 22) When troubleshooting starts, the following items are executed simultaneously. (A) The data value of the monitor item is displayed in real time as a numerical value and a graphic. (B) The altitude, temperature, and speed values are numerically displayed (71). (C) The state of switches and variable knobs on the control panel in the cockpit is displayed, and the position can be visually grasped (71). (D) The open / close status of the valve is displayed in color (71). (E) If a trouble occurs during troubleshooting and a warning signal is generated, the contents of the warning and the total number of warnings are displayed in the bit monitor window (71).

Since the contents of the alarm are stored as a text file on the hard disk, they can be easily changed. (F) Total time from start of measurement is displayed (7
1). (G) Altitude, temperature, and speed parameters can be changed during measurement (72). (H) When data is saved, all input signals from the machine are recorded on the hard disk regardless of the monitor items. (2.9) Result display screen (FIGS. 8 to 24) Select a data file to be redisplayed in the data file window (73). (A) As display items, monitor items, pressure & temperature, and variable data selected in troubleshooting can be graphically displayed in bit data units (74). (B) Also, they can be displayed simultaneously (75). (C) This applies to all data in the hard disk.

[0045]

As described above, the present invention has the following advantages. (1) In troubleshooting and function tests during engine operation, equipment is brought into an isolated room. Even in the inevitable state, the status of the control panel in the cockpit is displayed, so that the pilot operation can be visually confirmed. (2) The open / close state of the air conditioning control valve of the machine can be visually confirmed. (3) When an alarm occurs, the name of the alarm is displayed on the screen, so that it is possible to immediately confirm what kind of trouble has occurred in the aircraft. (4) By simulating by changing the altitude, temperature, and speed rates, theoretical troubleshooting can be performed and the time required for troubleshooting can be reduced.

[Brief description of the drawings]

FIG. 1 is a screen display diagram (1) of a control device in a remote display, a simulation signal setting, and a function test according to a first embodiment of the present invention.

FIG. 2 is a screen display diagram (2) of the control device in the remote display, the simulation signal setting, and the function test according to the first embodiment of the present invention.

FIG. 3 is a screen display diagram (3) of the control device in the remote display, the simulation signal setting, and the function test according to the first embodiment of the present invention.

FIG. 4 is a conceptual diagram of a connection between an airframe and a function test apparatus according to the first embodiment of the present invention.

FIG. 5 is an external view of a cable and a sensor of the device according to the first embodiment of the present invention.

FIG. 6 is a connection block diagram of the airframe and the function test device according to the first embodiment of the present invention.

FIG. 7 is a signal and electric wiring diagram according to the first embodiment of the present invention.

FIG. 8 is a view showing an operation procedure according to the first embodiment of the present invention.

FIG. 9 is a diagram showing a database of a test procedure according to the first embodiment of the present invention.

FIG. 10 is an explanatory view (1) of a display screen according to the first embodiment of the present invention.

FIG. 11 is an explanatory view (2) of a display screen according to the first embodiment of the present invention.

FIG. 12 is an explanatory view (3) of a display screen according to the first embodiment of the present invention.

FIG. 13 is an explanatory view (4) of a display screen according to the first embodiment of the present invention.

FIG. 14 is an explanatory view (5) of a display screen according to the first embodiment of the present invention.

FIG. 15 is an explanatory view (6) of a display screen according to the first embodiment of the present invention.

FIG. 16 is an explanatory view (7) of a display screen according to the first embodiment of the present invention.

FIG. 17 is an explanatory view (8) of a display screen according to the first embodiment of the present invention.

FIG. 18 is an explanatory view (9) of a display screen according to the first embodiment of the present invention.

FIG. 19 is an explanatory view (10) of a display screen according to the first embodiment of the present invention.

FIG. 20 is an explanatory view (11) of a display screen according to the first embodiment of the present invention.

FIG. 21 is an explanatory view (12) of a display screen according to the first embodiment of the present invention.

FIG. 22 is an explanatory view (13) of a display screen according to the first embodiment of the present invention.

FIG. 23 is an explanatory view (14) of a display screen according to the first embodiment of the present invention.

FIG. 24 is an explanatory view (15) of a display screen according to the first embodiment of the present invention.

FIG. 25 is a conceptual diagram showing a conventional troubleshooting.

[Explanation of symbols]

1 Trouble shooting screen (control panel status display window in cockpit) 2 Trouble shooting screen (open / close valve change window) 3 Trouble shooting screen (alarm monitor window) 4 Trouble shooting screen (saved message) 5 Trouble shooting screen ( Monitor item graphic display) 6 Troubleshooting execution screen (Altitude, temperature, speed parameter change) 7 Functional test execution screen (Test procedure display window) 8 Functional test execution screen (Automatic data judgment window) 11 Bus cable between air conditioning controller test equipment 12 Temperature sensor 13 Cable between temperature sensor test devices 14 Pressure sensor extension cable 15 Cable between pressure sensor test devices 16 Pressure sensor 17 Pressure sensor 17 Body hose, tube 18 Main body of pressure test device 21 Pressure sensor 22 Pressure sensor J1 receptacle 23 Current-> Voltage conversion resistor 24 A / D board 25 Temperature sensor 26 Temperature sensor panel jack 27 Temperature board 28 Air-conditioning controller 29 1553B bus coupler 30 1553BI / F board 31I / 0 expansion unit 32 computer 33 numeric keyboard 34 mouse 35 printer 36 uninterruptible power supply 37 controller 41 initial input 42 test item selection 43 ftp (functional test procedure) (functi)
on test procedure) 44 ftp execution 45 Troubleshoot sample selection 46 Monitor item selection confirmation 47 Altitude, temperature, speed, parameter setting 48 Troubleshooting (manual) start 49 Troubleshooting (sample) start 50 Troubleshooting execution 51 Result display data data File selection 52 Result display 61 Inspector selection screen of initial input screen 62 Initial input screen 63 Test item selection screen 64 Test preparation equipment screen and test item procedure screen 65 Function test execution screen (maximum value, minimum value display) 66 Function test execution Screen (during automatic execution) 67 Monitor item selection confirmation screen 68 Monitor item manual selection screen 69 Monitor item (manual) altitude, temperature and speed setting screen 70 Troubleshooting start screen 71 Troubleshooting actual Screen 72 Troubleshooting execution screen (altitude, temperature, speed change) 73 Result display data file selection screen 74 Result display item list screen 75 Result display screen (graphic display) 100 Aircraft 101 First control unit 102 Second control unit 103 No. 3 control unit 104 database unit 200 function test device

Claims (1)

[Claims] A function having a system capable of grasping a control panel in a cockpit of an air conditioning system of an aircraft and a body state of a control device by reading a digital signal from a controller for controlling an air conditioning system of the aircraft from outside. (A) a controller (28) for controlling an air conditioning system, (B) a pressure sensor (21) and a temperature sensor (25) for detecting the pressure and temperature of air flowing through a duct, and (C) the pressure. A computer (32) for inputting and analyzing signals from the sensor (21) and the temperature sensor (25); (D) a state of a control panel in a cockpit, a state of a control device of a body for controlling an air conditioning system, and a duct. Temperature, pressure, and flow conditions within the
A first control unit (101) for simultaneously real-time graphic display remotely and (E) sky conditions (altitude, speed,
In order to create parameters for simulating the flight condition at (temperature), on the ground, by simulating changing altitude, temperature, and speed rates, a pseudo signal corresponding to the sky condition was created, and the controller (F) a second control unit (102) to transmit; (F) a database unit (104) in which operator's operation instructions, test procedures, measurement items, pass / fail determination values and parameters of the measurement items are described, and (G)
An air conditioning system for an aircraft, comprising: a third control unit (103) for displaying a work procedure on a display device in accordance with the contents described in the database (104) and automatically determining whether or not the value of the measured item is acceptable. Line tester.