Inspection tester for airplane power supply system

Abstract

An airplane power supply system inspection tester comprises a case, a panel is arranged on the case, an interface is arranged on the panel and connected with an airplane power supply system inspection interface, direct-current voltages output by an airplane power supply system are electrically connected with a direct-current voltage sensor, and alternating-current voltages output by the airplane power supply system are electrically connected with an alternating-current voltage sensor and a frequency sensor. The AC voltage sensor, the DC voltage sensor and the frequency sensor are connected with an acquisition port of the Modbus-TCP data acquisition module. A plurality of direct-current voltage sensors, alternating-current voltage sensors, frequency sensors and optical coupling modules are used for collecting direct-current voltage, alternating-current voltage, frequency and switching value parameters of a power supply system, collected data are transmitted to a Modbus-TCP collection module, and after being processed, the collected data are transmitted to a touch integrated industrial personal computer. And an operator can observe the fine change of each parameter of the power supply system in the whole time period, so that the use effect of the equipment is greatly improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft maintenance assistance, and particularly relates to an aircraft power supply system checker. Background Art

[0002] For the existing inspection of aircraft power supply systems, a checker is connected to the inspection interface of the aircraft power supply system through a connection cable. The on-off signals are displayed through indicator lights. A multi-position wave switch 1 is used to switch and connect a DC voltmeter to measure and display the DC voltage. A multi-position wave switch 2 is used to switch and connect an AC voltmeter and a frequency meter to measure and display the AC voltage and its frequency.

[0003] Since only one DC voltmeter, one AC voltmeter and one frequency meter are used, and a wave switch is used to switch and display the data of multiple channels, it is impossible to simultaneously display the test data of all channels. Moreover, the ordinary electrical parameter measuring instruments used do not have the function of storing and reviewing data. During the use process, it is very likely that the operator will miss the changes of important data, thus causing the equipment to lose the function of monitoring the power supply system. Summary of the Invention

[0004] The technical problem to be solved by the utility model is to provide an aircraft power supply system checker to solve the defects of the above-mentioned aircraft power supply system checker.

[0005] To solve the above technical problem, the technical solution adopted by the utility model is as follows:

[0006] The aircraft power supply system checker includes a chassis. A panel is provided on the chassis. An interface is provided on the panel to connect with the inspection interface of the aircraft power supply system, and each DC voltage output by the aircraft power supply system is electrically connected to a DC voltage sensor. Each AC voltage output by the aircraft power supply system is electrically connected to an AC voltage sensor and a frequency sensor. The AC voltage sensor, the DC voltage sensor and the frequency sensor are connected to the acquisition ports of a Modbus-TCP data acquisition module.

[0007] The above-mentioned panel is provided with a human-machine interface screen HMI, and the human-machine interface screen HMI is communicatively connected to the Modbus-TCP data acquisition module.

[0008] The above-mentioned human-machine interface screen HMI is connected to the Modbus-TCP data acquisition module through a communication bus.

[0009] The interface on the above-mentioned panel connected to the inspection interface of the aircraft power supply system is an aviation socket.

[0010] The above-mentioned human-machine interface screen HMI is a touch screen.

[0011] An aircraft power system checker provided by the utility model uses multiple DC voltage sensors, AC voltage sensors, frequency sensors and optocoupler modules to collect the DC voltage, AC voltage, frequency and digital input / output parameters of the power system. The collected data is transmitted to the Modbus-TCP acquisition module, processed and then transmitted to the touch integrated industrial computer. The real-time display, storage and data curve playback of test data are realized through Labview software. It enables operators to observe the subtle changes of each parameter of the power system in the entire time period, greatly improving the use effect of the equipment. Brief Description of the Drawings

[0012] The present invention will be further described below in conjunction with the drawings and embodiments:

[0013] Figure 1 is the three-dimensional structure diagram of the aircraft power system checker of the utility model;

[0014] Figure 2 is the working principle diagram of the utility model;

[0015] Figure 3 is the wiring schematic diagram of the data acquisition module Figure 1 ;

[0016] Figure 4 is the wiring schematic diagram of the data acquisition module Figure 2 ;

[0017] Figure 5 is the schematic diagram of the DC voltage acquisition board;

[0018] Figure 6 is the wiring diagram of the frequency sensor.

[0019] In the figure: chassis 1, panel 2, aviation socket 3, human-machine interaction screen HMI 4, Modbus-TCP data acquisition module 5, AC voltage sensor 6, DC voltage sensor 7, frequency sensor 8. Specific Embodiments

[0020] The technical solution of the present utility model will be described in detail below in conjunction with the drawings and embodiments.

[0021] The aircraft power system checker includes a chassis 1. A panel 2 is provided on the chassis 1. The panel 2 is provided with interfaces connected to the inspection interfaces of the aircraft power system, and each DC voltage output by the aircraft power system is electrically connected to the DC voltage sensor 7. Each AC voltage output by the aircraft power system is electrically connected to the AC voltage sensor 6 and the frequency sensor 8. The AC voltage sensor 6, the DC voltage sensor 7 and the frequency sensor 8 are connected to the acquisition ports of the Modbus-TCP data acquisition module 5.

[0022] The above-mentioned panel 2 is provided with a human-machine interaction screen HMI4, and the human-machine interaction screen HMI4 is communicatively connected to the Modbus-TCP data acquisition module 5.

[0023] The above-mentioned human-machine interaction screen HMI4 and the Modbus-TCP data acquisition module 5 are connected through a communication bus.

[0024] The interface on the above-mentioned panel 2 connected to the aircraft power system inspection interface is the aviation socket 3.

[0025] The above-mentioned human-machine interaction screen HMI4 is a touch screen.

[0026] Embodiment:

[0027] The aircraft power system inspection instrument includes 8 parts: a chassis, a panel, an aviation socket, an all-in-one touch computer, a Modbus-TCP data acquisition module, an AC voltage sensor, a DC voltage sensor, and a frequency sensor. The three-dimensional structure diagram is as Figure 1 shown.

[0028] The present invention connects the aviation socket to the interface of the receiving machine through a cable, and respectively collects the DC voltage, AC voltage, and frequency signals of the aircraft through the AC voltage sensor, DC voltage sensor, and frequency sensor, and outputs a 0-5V standard voltage signal to the Modbus-TCP data acquisition module for centralized collection. The collected data is transmitted to the all-in-one touch computer for processing through Ethernet using the Modbus-TCP protocol. The all-in-one touch computer realizes the real-time display, storage, and data curve playback of the DC voltage, AC voltage, and frequency signals through the Labview software. The working principle block diagram is as follows Figure 3 shown.

[0029] It should be noted that the solution of the above technical problems requires programming and uses software parts. However, the software is only a part of the technical solution of the present utility model, and its means are all prior arts. The key to solving the technical problems of the present utility model is the new technology of the shape, structure, and their combination. Therefore, it shall not be determined that the content of this application does not belong to the protection object of the utility model on the grounds that software or programs need to be used.

Claims

1. Aircraft power system tester, characterized in that: The invention comprises a chassis (1), wherein a panel (2) is provided on the chassis (1), wherein an interface is provided on the panel (2) and is connected to an inspection interface of an aircraft power system, and each DC voltage output by the aircraft power system is electrically connected to a DC voltage sensor (7), and each AC voltage output by the aircraft power system is electrically connected to an AC voltage sensor (6) and a frequency sensor (8), and the AC voltage sensor (6), the DC voltage sensor (7) and the frequency sensor (8) are connected to a collection port of a Modbus-TCP data collection module (5).

2. The aircraft power system inspection instrument according to claim 1, characterized in that: The panel (2) is provided with a human-machine interaction screen HMI (4), and the human-machine interaction screen HMI (4) is communicatively connected to a Modbus-TCP data acquisition module (5).

3. The aircraft power system inspection instrument according to claim 2, characterized in that: The human-machine interaction screen HMI (4) is connected to the Modbus-TCP data acquisition module (5) via a communication bus.

4. The aircraft power system inspection instrument according to claim 3, characterized in that: The interface on the panel (2) that is connected to the aircraft power system inspection interface is an aviation socket (3).

5. The aircraft power system inspection instrument according to claim 4, characterized in that: The human-machine interaction screen HMI (4) is a touch screen.

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