JPH07108997A - Aircraft automatic test equipment - Google Patents

Abstract

(57) [Summary] [Objective] To provide a device for automatically performing functional tests of eight systems (aileron, stabilizer, rudder; legs, steering, brakes, drag chute; throttle) of an aircraft having electric signal control. [Structure] A simulated signal generator that incorporates a simulated signal generation board to supply a simulated signal to the aircraft side, a plurality of exterior sensors such as tilt angle sensors and potentiometers that measure the control surface angle, and an alarm circuit that the aircraft itself has. An operation signal capturing device composed of a plurality of internal sensors using signals,
A measurement value display device that incorporates a digital multimeter controlled by a microcomputer and can display and print out measurement values, and a microcomputer that incorporates the above-mentioned simulated signal generation device, above-mentioned operation signal acquisition device, above-mentioned measurement value display device And an operation control device for controlling.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an automatic test apparatus for performing a functional test of an aircraft having electric signal control.

[0002]

2. Description of the Related Art FIG. 5 is a diagram showing an example of a conventional function test method for an aircraft having electric signal control. Conventionally, operation control equipment (01) is manufactured for each test system (control system, landing system, power system), and an operator (02) operates the operation control equipment (01) to input a simulated signal to the aircraft. , 8 systems of aircraft (aileron, stabilizer, ladder;
I was doing functional tests on the legs, steering, brakes, drag chute, and throttle). On the other hand, measurer (03)
Measures the amount of operation (angle, length, time, etc.) of the aircraft operating part using a goniometer, scale, clock, etc.
It was confirmed whether or not the operation amount of the aircraft operation part with respect to the operation simulation signal of 2) satisfies the specified required value. As mentioned above, there were multiple target systems, and it was necessary to attach and detach the operation control equipment each time, and work efficiency was poor.

[0003]

The conventional aircraft function tests have the following problems to be solved. An operator and a measurer are required for each operation control / measurement point, and a plurality of workers are required. Since humans intervene in operation control and measurement, the reliability of measured values is low due to human error. It is necessary to manufacture test equipment for each system to be tested and to manage and store multiple test equipment.

[0004]

SUMMARY OF THE INVENTION In order to solve the above-mentioned conventional problems, the present invention is based on a simulation signal generator which incorporates a simulation signal generation substrate and generates a simulation signal, and which is attached to an aircraft based on the simulation signal. A measurement value display device that incorporates an operation signal acquisition device having a plurality of sensors for measuring predetermined physical quantities and a digital multimeter controlled by a microcomputer, and displays and prints out the measurement values measured by the operation signal acquisition device. And an operation control device for controlling the simulated signal generator, the actuating signal take-in device, and the measurement value display device with a microcomputer incorporated therein.

[0005]

In the present invention, based on the simulated signal generated by the simulated signal generating device, the plurality of sensors of the operation signal capturing device attached to the aircraft respectively measure predetermined physical quantities, and the measured values are measured values. Since a series of operations of displaying and printing out on the display device is controlled by the operation control device, it is possible to automate the operation of the operation control unit, the measurement of the operation amount, the quality judgment of the measured value, and the recording.
As a result, labor saving, shortening of test time, and improvement of reliability of measured values are achieved. Further, it is possible to integrate a plurality of test equipments for each system to be tested into one equipment, which facilitates the handling and storage of the equipments.

[0006]

DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 is an overall schematic view showing an embodiment of the present invention,
2 is a system block diagram of the equipment main body in FIG. 1, FIG.
Is a diagram illustrating the exterior sensor of this embodiment, and FIG. 4 is a program flow chart of this embodiment.

First, as shown in FIG. 1, the test apparatus of the present embodiment comprises an equipment main body (21) in which an operation control device, a simulated signal generating device and a measured value display device are integrated, and an operating part of an aircraft. An operation signal capturing device (22) composed of a plurality of sensors for measuring the amount of installation operation and a cable (23) connecting the operation signal capturing device (22) and the aircraft equipment to the equipment body are roughly distinguished.

AC is externally applied to the equipment body (21).
115V, 400Hz and AC100V, 60Hz and DC
28V is supplied and used as a power source. This AC
As shown in FIG. 2, the power supply (1) for the microcomputer Z80, the simulated signal power supply (2), and the relay board power supply (3) are converted from 100 V, 60 Hz using a DC converter. Of these, the simulated signal power source (2) is distributed to various voltages of -15 VDC to +15 VDC by the simulated signal distributor (4), and via the relay board (5) controlled by the microcomputer Z80,
It is supplied to the aircraft side drive equipment as a simulated signal (6),
This activates the operating part of the aircraft.

On the other hand, the position signal of the aircraft-side operating portion is the internal sensor signal (7) of the function of the aircraft equipment itself,
Exterior sensor signal newly manufactured as an accessory (8)
It is divided into. These position signals are taken into the digital multimeter (9) controlled by the microcomputer Z80, and displayed and printed out. A prescribed value of the position signal on the aircraft side with respect to the simulated signal input value is programmed in the equipment body (1), and a quality judgment is also performed at the time of printing out.

In the automatic function test mode, decimal 2
By operating the digit digital switch (10), an arbitrary test item can be selected according to the flow set on the program. In addition, which test item is currently being performed is displayed on the display (11) as a two-digit number indicating a process. On the other hand, it is also possible to manually control one operation / one operation using a toggle switch.

An example of the exterior sensor is shown in FIG. First, FIG. 3A shows the measurement of the steering angle of the aileron (roll control) at the wing tip. In this case, the tilt angle sensor (31) is utilized, the one-touch clamp (32) is used to fix the sensor signal almost at the center of the aileron control surface, and the sensor signal is transferred via the adapter cable (33) to the digital multimeter (reference numeral 9 in FIG. 2). )).

Next, FIG. 3B shows the measurement of the steering angle of the horizontal stabilizer (pitch control) at the upper end of the tail. Also in this case, the inclination angle sensor (34) is used as in the aileron, and the left cover mounting screw is used for mounting.

FIG. 3 (c) shows the rudder angle measurement of the rudder (yaw control) at the tail end of the tail. In this case, the potentiometer (35) is used to mount the sensor assembly using the access cover mounting screw hole of the aircraft.

[0014]

According to the present invention, the following effects can be obtained. 1) The operation, measurement, and pass / fail judgment of the functional test of the aircraft are automated, and the conventional two-person work can be performed by one person. 2) Human error due to human intervention is reduced and the reliability of measured values is improved. 3) By integrating the equipment, it is possible to perform a functional test with a single equipment, which facilitates test preparation work and equipment management.

[Brief description of drawings]

FIG. 1 is an overall schematic diagram showing an embodiment of the present invention.

FIG. 2 is an overall block diagram of the above embodiment.

FIG. 3 is a diagram illustrating an exterior sensor of the operation signal capturing device according to the above embodiment.

FIG. 4 is a program flow chart of the above embodiment.

FIG. 5 is a diagram showing an example of a conventional aircraft test method.

[Explanation of symbols]

 (01) Operation control equipment (02) Operator (03) Measurer (1), (2), (3) Power supply (4) Simulated signal distributor (5) Relay board (6) Simulated signal (7) Interior sensor Signal (8) Exterior sensor signal (9) Digital multimeter (10) Digital switch (11) Display (21) Instrument body (22) Actuator signal capture device (23) Cable (31) Tilt angle sensor (32) One-touch clamp ( 33) Adapter cable (34) Tilt sensor (35) Potentiometer

Front Page Continuation (72) Inventor Akio Mori 10 Oemachi, Minato-ku, Nagoya City Mitsubishi Heavy Industries Ltd. Nagoya Aerospace Systems Works

Claims (1)

[Claims] 1. A simulation signal generator that incorporates a simulation signal generation substrate to generate a simulation signal, and an operation signal capture device that is attached to an aircraft and that has a plurality of sensors that measure predetermined physical quantities based on the simulation signal. A measurement value display device that incorporates a digital multimeter controlled by a microcomputer to display and print out the measurement values measured by the operation signal acquisition device, and a simulation signal generation device that incorporates the microcomputer and the operation signal acquisition device And an operation control device for controlling the measurement value display device, which is an automatic test device for an aircraft.