CN209911466U

CN209911466U - Comprehensive test box for testing electrical circuit of aircraft accessory

Info

Publication number: CN209911466U
Application number: CN201920103577.3U
Authority: CN
Inventors: 樊旭阳
Original assignee: Beijing Fengrong Aviation Technology Co Ltd
Current assignee: Beijing Fengrong Aviation Technology Co Ltd
Priority date: 2019-01-22
Filing date: 2019-01-22
Publication date: 2020-01-07
Anticipated expiration: 2029-01-22

Abstract

The utility model discloses a comprehensive test box that is used for electrical return circuit of airborne vehicle annex to test. The test box consists of a power supply, a Hall sensor test loop, a torque motor control loop, an on/off and mode selection solenoid valve loop, a pressure differential sensor voltage monitoring loop and a control panel; firstly, mounting tested aircraft accessories on a test bed, connecting a pressure pipeline to the tested aircraft accessories, and then connecting electric sockets C1, C2 and C3 of a comprehensive test box with corresponding electric plugs of the tested aircraft accessories according to requirements; switching on U1 and U2 power supplies, fixing switches and button positions according to a control panel, and testing an electrical circuit of the aircraft accessory; the utility model has the advantages of simple control panel, convenient operation, high adjusting precision, easy adjustment and monitoring and high working efficiency; the testing requirement of the electrical loop of the flow control valve can be met, and the application range is wide.

Description

Comprehensive test box for testing electrical circuit of aircraft accessory

Technical Field

The utility model belongs to the technical field of the detection of aircraft part, in particular to a comprehensive test box that is used for test of aircraft annex electrical circuit.

Background

With the increasing progress of technology, the control of the aircraft system is gradually changed from the previous mechanical control to the telex control, and many aircraft accessories use torque motors, electromagnetic valves, sensors, position indicators, etc. to control the aircraft accessories, and monitor the adjustment action and the position. Aircraft accessories have become increasingly complex in circuitry and require more specialized and advanced equipment for functional testing.

Disclosure of Invention

The utility model aims at providing a comprehensive test box for testing an electrical loop of an aircraft accessory against the defects of the prior art, which is characterized in that the comprehensive test box is used for testing a flow control valve in an aircraft bleed air system; the test box comprises (1) a torque motor power supply U2 and a control loop; (2) a control circuit of the solenoid valve; (3) the Hall sensor test loop is used for monitoring the position of the valve; (4) a monitoring loop of pressure and differential pressure sensor voltage and (5) an external power supply U1; (6) a control panel of the integrated test box; wherein, the external power supply U1 is respectively connected with a Hall sensor test circuit, a torque motor power supply U2, a control circuit and a pressure and differential pressure sensor voltage monitoring circuit through a k1 switch; the torque motor power supply U2 and the control circuit are connected with the J port of the C1 socket through an ammeter and connected with the torque motor, and the torque motor is grounded through a port H of the C1 socket; meanwhile, a protection circuit and an N port of the C1 socket are designed in the comprehensive test box and grounded, so that the damage to circuit accessories on the valve caused by unstable voltage and current in an accident situation is prevented.

The structural layout of the control panel of the comprehensive test box is as follows: (1) the left side of the upper part is provided with an external power supply button switch and a K1 switch, wherein the external power supply button switch and the K1 switch comprise buttons of 28V, 15V, 4.5V and 5V; the middle part is a K5 switch of a Hall sensor, which comprises three buttons of 4.5V output, closing and not closing; the sensor monitoring test K6 switch is arranged on the right, and comprises a 15V button, a digital voltmeter V1 of an inlet pressure sensor and a digital voltmeter V2 of a differential pressure sensor; (2) the left side of the lower part is provided with a torque motor power button, a control loop K2 switch and a 0-200mA digital display ammeter A; the solenoid valve control circuit on the right comprises a solenoid valve K4 switch and a mode selection K3 switch, and is provided with an on/off button and a mode button.

The control loop of the torque motor power supply U2 is powered by an XL5135A-5 power supply with adjustable current, and the adjustable range of the current is 0-200 mA.

The pressure and differential pressure sensor voltage monitoring loop is characterized in that an external power supply U1 is connected with the input of a 7815 three-terminal voltage stabilizer through a diode, the output of the 7815 three-terminal voltage stabilizer is connected with an A port of a C2 socket through a K6, and the A port of the C2 socket is connected with an A port of a C3 socket; the port B of the C2 socket is connected with a digital voltmeter V1 of the inlet pressure sensor, and the port B of the C3 socket is connected with a digital voltmeter V2 of the differential pressure sensor; the voltage monitoring range is 0-20 VDC.

The Hall sensor test loop is a monitoring loop for the position of the valve; the test loop is characterized in that an external power supply U1 is connected with a 6V voltage stabilizer of a Hall sensor test loop through a diode and then is connected to a port B of a C1 socket through a K5 switch, and the positive end and the negative end of an input end of an internal power supply of a tested Hall sensor are respectively connected with the port B and the port A of the C1 socket; the output end of the Hall sensor is connected with a transposition switch, the transposition switch of the tested Hall sensor is provided with closed and non-closed gears, and the non-closed gear is connected with the +6V end of an amplifier of the Hall sensor test loop through a port C of a socket C1; the closing gear is connected with the-6V end of the other amplifier of the Hall sensor test circuit through the D port of the C1 socket; the ground end of the Hall sensor to be tested is grounded through a P port of the C1 socket.

The control circuit of the electromagnetic valve comprises an on/off electromagnetic valve and mode selection, one path of the control circuit of the electromagnetic valve is connected with an electromagnetic valve switch module of the Hall sensor to be tested through a K4 switch and a T port of a C1 socket, and is grounded through a G port of a C1 socket; the electromagnetic valve switch module is grounded through an S port of a C1 socket; the other mode K3 switch of the electromagnetic valve control loop and the L port of the C1 socket are connected with the mode selection module of the tested Hall sensor and are grounded through the K port of the C1 socket; the solenoid valve switch module is grounded through the port M of the C1 socket.

The mode of the electromagnetic valve control circuit is selected into an electric control mode and a pneumatic mode.

The beneficial effects of the utility model are that utilize the comprehensive test box to test the annex electric circuit of aircraft, realize the electric loop control and the control to flow control valve annex in the aircraft bleed system through circuit design. The power supply part has high regulation precision, can realize the continuous control of the torque motor, and can realize the monitoring of the pressure and the pressure difference inside the valve by monitoring the pressure and the voltage of the pressure difference sensor. The realization is rapid and the operation is simple; the utility model discloses can satisfy this type flow control valve electric loop test requirement, application scope is wider.

Drawings

FIG. 1 is a schematic diagram of an integrated test cassette circuit;

FIG. 2 is a control panel diagram of the integrated test cassette.

Detailed Description

The utility model relates to a comprehensive test box that is used for electrical return circuit of airborne vehicle annex to test. The following description is made with reference to the accompanying drawings.

Fig. 1 shows a schematic circuit diagram of an integrated test cassette for testing flow control valves in a bleed air system of an aircraft; the test box comprises (1) a torque motor power supply U2 and a control loop; (2) a control circuit of the solenoid valve; (3) the Hall sensor test loop is used for monitoring the position of the valve; (4) a monitoring loop of pressure and differential pressure sensor voltage and (5) an external power supply U1; (6) a control panel of the integrated test box; wherein, the external power supply U1 is respectively connected with a Hall sensor test circuit, a torque motor power supply U2, a control circuit and a pressure and differential pressure sensor voltage monitoring circuit through a k1 switch; the torque motor power supply U2 and the control circuit are connected with the J port of the C1 socket through an ammeter and connected with the torque motor, and the torque motor is grounded through a port H of the C1 socket; meanwhile, a protection circuit and an N port of the C1 socket are designed in the comprehensive test box and grounded, so that the damage to circuit accessories on the valve caused by unstable voltage and current in an accident situation is prevented.

FIG. 2 is a diagram of a control panel of the integrated test cassette. The structure layout is as follows: (1) the left side of the upper part is provided with an external power supply button switch and a K1 switch, wherein the external power supply button switch and the K1 switch comprise buttons of 28V, 15V, 4.5V and 5V; the middle part is a K5 switch of a Hall sensor, which comprises three buttons of 4.5V output, closing and not closing; the sensor monitoring test K6 switch is arranged on the right, and comprises a 15V button, a digital voltmeter V1 of an inlet pressure sensor and a digital voltmeter V2 of a differential pressure sensor; (2) the left side of the lower part is provided with a torque motor power button, a control loop K2 switch and a 0-200mA digital display ammeter A; the solenoid valve control circuit on the right comprises a solenoid valve K4 switch and a mode selection K3 switch, and is provided with an on/off button and a mode button. The following is a detailed description of each part of the composition:

The Hall sensor test loop is a monitoring loop for the position of the valve; the test loop is a 6V voltage stabilizer of which an external power supply U1 is connected with a Hall sensor test loop through a diode, and the voltage is regulated to 4.5VDC through twice voltage regulation for supplying power to the Hall sensor. Then the power supply is connected to the port B of the C1 socket through a K5 switch, and the positive end and the negative end of the input end of the internal power supply of the Hall sensor to be detected are respectively connected with the port B and the port A of the C1 socket; the output end of the Hall sensor is connected with a transposition switch, the transposition switch of the tested Hall sensor is provided with closed and non-closed gears, and the non-closed gear is connected with the +6V end of an amplifier of the Hall sensor test loop through a port C of a socket C1; the closing gear is connected with the-6V end of the other amplifier of the Hall sensor test circuit through the D port of the C1 socket; the ground end of the Hall sensor to be tested is grounded through a P port of the C1 socket.

The control circuit of the electromagnetic valve comprises an on/off electromagnetic valve and mode selection, one path of the control circuit of the electromagnetic valve is connected with an electromagnetic valve switch module of the Hall sensor to be tested through a K4 switch and a T port of a C1 socket, and is grounded through a G port of a C1 socket; the electromagnetic valve switch module is grounded through an S port of a C1 socket; the other mode K3 switch of the electromagnetic valve control loop and the L port of the C1 socket are connected with the mode selection module of the tested Hall sensor and are grounded through the K port of the C1 socket; the solenoid valve switch module is grounded through the port M of the C1 socket. Wherein the mode selection is an electric control mode and a pneumatic mode.

The working principle of the comprehensive test box for testing the electrical circuit of the aircraft accessory is as follows: firstly, according to the circuit connection shown in the figure 1, the tested aircraft accessory is installed on a test bench, a pressure pipeline is connected to the tested aircraft accessory, and then the electric sockets C1, C2 and C3 of the comprehensive test box are connected with the corresponding electric plugs of the tested aircraft accessory according to the requirements; the external power supply U1 and the torque motor power supply U2 are switched on; entering a test program, wherein the specific test steps are as follows: operating according to the control panel of figure 2,

1) the digital display type ammeter A displays that the current of the torque motor is adjusted within the range of 0-200mA, controls the torque motor on the valve and further controls the valve air release amount so as to realize the control of the angle position of the valve;

2) the electromagnetic valve is opened or closed through K3 and K4 switches, and modes of the electromagnetic valve and the electromagnetic valve are selected and switched in an electric control/pneumatic mode, so that the opening/closing of the valve and the switching of the electric control/pneumatic mode are realized;

3) connect hall sensor test circuit respectively through the k1 switch, realize monitoring the demonstration to the hall sensor break-make nature of installation on the valve through hall sensor control circuit, install the pilot lamp of two control hall sensor breakdowns on the comprehensive test box display panel for show break-make. The non-closed gear is connected with the +6V end of an amplifier of the Hall sensor test circuit through a port C of the socket C1; the closing gear is connected with the-6V end of the other amplifier of the Hall sensor test circuit through the D port of the C1 socket; the two amplifiers are used for monitoring the on-off of the Hall sensor and indicating the on-off performance through the two indicating lamps.

4)7815 output DC15V of three terminal voltage stabilizer is connected with pressure and pressure difference sensor voltage monitoring loop through K6, mode selection of electromagnetic valve in step 2) is electric control mode, through adjusting current of adjustable current power XL5135A-5, to control actuating angle of torque motor, test function of accessory under electric control working condition, monitor Hall sensor position indication and pressure/pressure difference value (displayed by digital display voltmeter V1, V2). After the test is finished, a mode selection button of the electromagnetic valve is switched to a pneumatic mode, the measuring accessory functions in the pneumatic mode, the Hall sensor position indication and the pressure/pressure difference value are monitored, and the voltage monitoring range is 0-20 VDC.

Claims

1. A comprehensive test box for testing an electrical circuit of an aircraft accessory is characterized in that the comprehensive test box is used for testing a flow control valve in an aircraft bleed air system; the test box comprises: the device comprises a torque motor power supply U2 and a control loop, a control loop of an electromagnetic valve, a Hall sensor test loop, a monitoring loop for the position of a valve, a monitoring loop for pressure and differential pressure sensor voltage, an external power supply U1 and a comprehensive test box control panel; wherein, the external power supply U1 is respectively connected with a Hall sensor test circuit, a torque motor power supply U2, a control circuit and a pressure and differential pressure sensor voltage monitoring circuit through a k1 switch; the torque motor power supply U2 and the control circuit are connected with the J port of the C1 socket through an ammeter and connected with the torque motor, and the torque motor is grounded through the H port of the C1 socket; meanwhile, a protection circuit and an N port of the C1 socket are designed in the comprehensive test box and grounded, so that the damage to circuit accessories on the valve caused by unstable voltage and current in an accident situation is prevented.

2. The integrated test cassette for aircraft accessory electrical loop testing of claim 1, wherein the structural layout of the integrated test cassette control panel is: the left side of the upper part of the control panel is provided with an external power supply button switch and a K1 switch, wherein the external power supply button switch and the K1 switch comprise 28V, 15V, 4.5V and 5V buttons; the middle part is a K5 switch of a Hall sensor, which comprises three buttons of 4.5V output, closing and not closing; the sensor monitoring test K6 switch is arranged on the right, and comprises a 15V button, a digital voltmeter V1 of an inlet pressure sensor and a digital voltmeter V2 of a differential pressure sensor; the left side of the lower part of the control panel is provided with a torque motor power button, a control loop K2 switch and a 0-200mA digital display ammeter A; the solenoid valve control circuit on the right comprises a solenoid valve K4 switch and a mode selection K3 switch, and is provided with an on/off button and a mode button.

3. The integrated test kit for aircraft accessory electrical loop testing of claim 1, wherein the control loop of the torque motor power supply U2 is powered by an adjustable current XL5135A-5 power supply, the current adjustable range being 0-200 mA.

4. The integrated test kit for aircraft accessory electrical circuit testing of claim 1, wherein the pressure and differential pressure sensor voltage monitoring circuit is an external power source U1 connected to the input of a 7815 three terminal regulator through a diode, the output of the 7815 three terminal regulator being connected to port a of the C2 socket via K6, port a of the C2 socket being connected to port a of the C3 socket; the port B of the C2 socket is connected with a digital voltmeter V1 of the inlet pressure sensor, and the port B of the C3 socket is connected with a digital voltmeter V2 of the differential pressure sensor; the voltage monitoring range is 0-20 VDC.

5. The integrated test cassette for aircraft accessory electrical loop testing of claim 1, wherein the hall sensor test loop is a monitoring loop for valve position; the test loop is characterized in that an external power supply U1 is connected with a 6V voltage stabilizer of a Hall sensor test loop through a diode and then is connected to a port B of a C1 socket through a K5 switch, and the positive end and the negative end of an input end of an internal power supply of a tested Hall sensor are respectively connected with the port B and the port A of the C1 socket; the output end of the Hall sensor is connected with a transposition switch, the transposition switch of the tested Hall sensor is provided with closed and non-closed gears, and the non-closed gear is connected with the +6V end of an amplifier of the Hall sensor test loop through a port C of a socket C1; the closing gear is connected with the-6V end of the other amplifier of the Hall sensor test circuit through the D port of the C1 socket; the ground end of the Hall sensor to be tested is grounded through a P port of the C1 socket.

6. The integrated test cassette for aircraft accessory electrical circuit testing of claim 1, wherein the control loop of the solenoid valve includes an on/off solenoid valve and a mode selection, one path of the solenoid valve control loop is connected to the solenoid valve switch module of the hall sensor under test through the K4 switch and the T port of the C1 socket, and is grounded through the G port of the C1 socket; the electromagnetic valve switch module is grounded through an S port of a C1 socket; the other mode K3 switch of the electromagnetic valve control loop and the L port of the C1 socket are connected with the mode selection module of the tested Hall sensor and are grounded through the K port of the C1 socket; the solenoid valve switch module is grounded through the port M of the C1 socket.

7. The integrated test kit for aircraft accessory electrical circuit testing of claim 6, wherein the mode selection of the solenoid valve control circuit is an electrically controlled mode and a pneumatic mode.