A test device for an aircraft engine parameter acquisition display

Abstract

The application discloses a kind of aircraft engine parameter acquisition display front tester, including cabinet and the direct current voltage module, alternating voltage module, main hydraulic pressure module, auxiliary hydraulic pressure source module, oil pressure source module, exhaust temperature source module, test adaptation and control unit, system power supply unit, bus analysis unit, industrial computer and display installed in cabinet, the direct current voltage module, alternating voltage module, main hydraulic pressure module, auxiliary hydraulic pressure source module, oil pressure source module and exhaust temperature source module constitute excitation signal simulation unit, the test adaptation and control unit are used to control the working state of the composition excitation signal simulation unit, and analog signal is transmitted to industrial computer by bus analysis unit, and the state information of excitation signal simulation unit is displayed by display. The front tester of the application is simple in overall structure, convenient operation and use, and has good economic and social benefits.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine technology, and more specifically to a pre-installation test device for an aircraft engine parameter acquisition display. Background Technology

[0002] The engine parameter acquisition and display system is a comprehensive display system for the main operating parameters of important systems such as the aircraft's AC / DC power supply system, hydraulic system, and engine system. It is primarily used to measure critical operating parameters such as DC voltage, AC voltage, main hydraulic pressure, auxiliary hydraulic pressure, lubricating oil pressure, and engine exhaust temperature. In aircraft research and production, this type of measurement and display system has always been a key focus for users in product quality control. Currently, there is a lack of testing equipment for this type of display system. For aircraft manufacturers, it is essential to possess such a pre-installation testing system to meet the needs of research and production, serving as a testing and assurance capability for analyzing and determining whether there are any problems with this type of display system during use. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to address the problems existing in the background art by providing a tester that can test engine parameter acquisition displays. This tester can meet the testing requirements of aircraft engine parameter acquisition displays before installation. Specifically, it is a pre-installation tester for aircraft engine parameter acquisition displays.

[0004] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is as follows: a pre-installation test device for an aircraft engine parameter acquisition display, comprising a cabinet, the interior of which is divided into four cavities, from top to bottom: a first cavity, a second cavity, a third cavity, and a fourth cavity. It also includes a DC voltage module, an AC voltage module, a main hydraulic pressure module, an auxiliary hydraulic pressure source module, a lubricating oil pressure source module, an exhaust temperature source module, a test adapter and control unit, a system power supply unit, a bus parsing unit, an industrial computer, and a display. The display is installed in the first cavity inside the cabinet, the industrial computer is installed in the second cavity inside the cabinet, the bus parsing unit is installed inside the industrial computer, and the bus parsing unit is used to receive and parse test parameters. The test adapter and control unit is installed in the third cavity inside the cabinet. The DC voltage module, AC voltage module, main hydraulic pressure module, auxiliary hydraulic pressure source module, lubricating oil pressure source module, and exhaust temperature source module constitute an excitation signal simulation unit. This excitation signal simulation unit is installed inside the test adapter and control unit. The test adapter and control unit controls the operating status of the excitation signal simulation unit and transmits the analog signal to the industrial computer via the bus parsing unit. The status information of the excitation signal simulation unit is displayed on a monitor. The system power supply unit is installed in the fourth cavity inside the cabinet and provides power to the excitation signal simulation unit, test adapter and control unit, bus parsing unit, industrial computer, and monitor. The monitor is electrically connected to the industrial computer via a cable.

[0005] Furthermore, in the pre-installation test apparatus for an aircraft engine parameter acquisition display described in this invention, the test adapter and control unit includes a control switch, a socket, a plug, and a control panel. A DC voltage module, an AC voltage module, a main hydraulic pressure module, an auxiliary hydraulic pressure source module, a lubricating oil pressure source module, and an exhaust temperature source module installed inside the test adapter and control unit are connected to the corresponding control switch, socket, and plug via cables to form an excitation signal simulation unit. The control panel also includes control knobs and displays corresponding to the DC voltage module, AC voltage module, main hydraulic pressure module, auxiliary hydraulic pressure source module, lubricating oil pressure source module, and exhaust temperature source module. The test adapter and control unit controls the operating status of the DC voltage module, AC voltage module, main hydraulic pressure module, auxiliary hydraulic pressure source module, lubricating oil pressure source module, and exhaust temperature source module respectively through the control knobs on the control panel, and displays their status parameter values ​​on the displays.

[0006] Furthermore, in the pre-installation tester for an aircraft engine parameter acquisition display described in this invention, the lubricating oil pressure source module includes a potentiometer. The potentiometer is composed of a resistance network of 10 precision potentiometers of model 3296. The corresponding range is selected by a band switch to meet the pressure simulation input of the lubricating oil pressure source module.

[0007] Furthermore, in the pre-installation tester for an aircraft engine parameter acquisition display described in this invention, the main hydraulic pressure module and the auxiliary hydraulic pressure source module are configured to meet the pressure input requirements of the main hydraulic pressure module and the auxiliary hydraulic pressure source module by applying a 10V DC reference voltage to both ends of a precision potentiometer and adjusting the precision potentiometer.

[0008] Furthermore, in the pre-installation test apparatus for aircraft engine parameter acquisition display described in this invention, the bus parsing unit includes an ARNIC-429 data bus. The bus parsing unit uses the C++ programming language to receive and parse test parameters from the ARNIC-429 bus data. The bus parsing unit transmits the received and parsed test parameters to an industrial control computer and displays the test status information of the test excitation source composed of a DC voltage module, an AC voltage module, a main hydraulic pressure module, an auxiliary hydraulic pressure source module, a lubricating oil pressure source module, and an exhaust temperature source module on the display.

[0009] Compared with existing technologies, the pre-installation tester for aircraft engine parameter acquisition displays described in this invention has the following advantages: Through a configured cabinet, DC voltage modules, AC voltage modules, main hydraulic pressure modules, auxiliary hydraulic pressure source modules, lubricating oil pressure source modules, exhaust temperature source modules, test adapter and control units, system power supply units, bus parsing unit blocks, industrial control computers, and displays are centrally located in different cavities within the cabinet in a layered manner. By testing different parameters before installation, it can not only meet the testing and assurance requirements for the main functions and performance indicators of parameter acquisition display systems for various types of aircraft engines, but also meet the needs of flexible development of aviation testing technology. Its overall structure is simple, convenient to operate and use, and has good economic and social benefits. Attached Figure Description

[0010] The present invention will now be described in further detail with reference to the accompanying drawings.

[0011] Figure 1 This is a schematic diagram of the structure of the present invention;

[0012] Figure 2 This is a schematic diagram of the panel structure of the test adapter and control unit described in this invention;

[0013] Figure 3 This is a schematic diagram of the ARNIC-429 data bus test interface structure in the bus parsing unit described in this invention;

[0014] Figure 4 This is the electrical schematic diagram of the present invention;

[0015] Figure 5 This is a block diagram of the internal circuit principle of the test adapter and control unit described in this invention.

[0016] The attached diagram shows: 1-DC voltage module, 2-AC voltage module, 3-main hydraulic pressure module, 4-auxiliary hydraulic pressure source module, 5-lubricating oil pressure source module, 6-exhaust temperature source module, 7-test adapter and control unit, 8-system power supply unit, 9-bus parsing unit, 10-industrial computer, 11-display. Implementation

[0017] To further illustrate the concept of the present invention, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings:

[0018] like Figures 1 to 5 As shown, the pre-installation test apparatus for an aircraft engine parameter acquisition display according to the present invention includes a cabinet, the interior of which is divided into four cavities, from top to bottom: a first cavity, a second cavity, a third cavity, and a fourth cavity. It also includes a DC voltage module 1, an AC voltage module 2, a main hydraulic pressure module 3, an auxiliary hydraulic pressure source module 4, a lubricating oil pressure source module 5, an exhaust temperature source module 6, a test adapter and control unit 7, a system power supply unit 8, a bus parsing unit 9, an industrial computer 10, and a display 11. The display 11 is installed in the first cavity inside the cabinet, the industrial computer 10 is installed in the second cavity inside the cabinet, the bus parsing unit 9 is installed inside the industrial computer 10, and the bus parsing unit 9 is used to receive and parse test parameters. The test adapter and control unit 7 is installed in the third cavity inside the cabinet. The DC voltage module 1, AC voltage module 2, main hydraulic pressure module 3, auxiliary hydraulic pressure source module 4, lubricating oil pressure source module 5, and exhaust temperature source module 6 constitute an excitation signal simulation unit. The excitation signal simulation unit is installed inside the test adapter and control unit 7. The test adapter and control unit 7 is used to control the working status of the excitation signal simulation unit and transmit the analog signal to the industrial computer 10 through the bus parsing unit 9. The status information of the excitation signal simulation unit is displayed on the display 11. The system power supply unit 8 is installed in the fourth cavity inside the cabinet 12 and is used to provide power to the excitation signal simulation unit, the test adapter and control unit 7, the bus parsing unit 9, the industrial computer 10, and the display 11. The display 11 is electrically connected to the industrial computer 10 through a cable.

[0019] To ensure more precise control signals and a more user-friendly human-machine interface, and for ease of operation and use, the test adapter and control unit 7 includes a control switch, socket, plug, and control panel. The DC voltage module 1, AC voltage module 2, main hydraulic pressure module 3, auxiliary hydraulic pressure source module 4, lubricating oil pressure source module 5, and exhaust temperature source module 6, installed inside the test adapter and control unit 7, are connected to the corresponding control switch, socket, and plug via cables, forming an excitation signal simulation unit. The control panel also includes control knobs and displays corresponding to the DC voltage module 1, AC voltage module 2, main hydraulic pressure module 3, auxiliary hydraulic pressure source module 4, lubricating oil pressure source module 5, and exhaust temperature source module 6. The test adapter and control unit 7 controls the operating status of the DC voltage module 1, AC voltage module 2, main hydraulic pressure module 3, auxiliary hydraulic pressure source module 4, lubricating oil pressure source module 5, and exhaust temperature source module 6 via the control knobs on the control panel, and displays their status parameter values ​​on the displays. The display panel related to DC voltage module 1 includes a DC voltage display frame and control knobs; the display panel related to AC voltage module 2 includes three-phase A-phase, B-phase, and C-phase AC voltage display frames and corresponding control knobs; the display panels related to main hydraulic pressure module 3 and auxiliary hydraulic pressure source module 4 respectively include pressure and voltage displays for groups A and B, and corresponding control knobs; the display panel related to lubricating oil pressure source module 5 includes control buttons for adjusting lubricating oil pressure, lubricating oil sensors, lubricating oil simulators, and lubricating oil metering; the display panel related to exhaust temperature source module 6 includes exhaust temperature simulation signal input and control buttons for different gears (GR23Ⅰ and GR23Ⅱ). Additionally, it includes wiring terminals and related control knobs for product power supply and lighting power supply. See details below. Figure 2 As shown.

[0020] To make the simulated lubricating oil pressure input more accurate and the operation more convenient, the main hydraulic pressure module 3 and the auxiliary hydraulic pressure source module 4 adjust the precision potentiometer by applying a 10V DC reference voltage to both ends of the precision potentiometer to meet the pressure input of the main hydraulic pressure module 3 and the auxiliary hydraulic pressure source module 4; while the lubricating oil pressure source module 5 includes a potentiometer, which is composed of 10 3296 model precision potentiometers forming a resistance network, and the corresponding range is selected by a band switch to meet the pressure simulation input of the lubricating oil pressure source module 5.

[0021] To make the test data display more intuitive, the bus parsing unit 9 includes an ARNIC-429 data bus. The bus parsing unit 9 uses C++ programming language to receive and parse the ARNIC-429 bus data and test parameters. The bus parsing unit 9 transmits the received and parsed test parameters to the industrial control computer 10, and displays the test status information of the test excitation source consisting of the DC voltage module 1, AC voltage module 2, main hydraulic pressure module 3, auxiliary hydraulic pressure source module 4, lubricating oil pressure source module 5, and exhaust temperature source module 6 on the display 11. The EICAS-ARNIC429 bus data, abbreviated as ARNIC-429 data bus, includes the following test parameters: AC 115V / A phase, AC 115V / B phase, AC 115V / C phase, DC bus voltage, A group main hydraulic pressure, B group main hydraulic pressure, A group auxiliary hydraulic pressure, B group auxiliary hydraulic pressure, lubricating oil pressure, A group exhaust temperature, and B group exhaust temperature. It also displays the corresponding test parameter labels and quantities. The specific test interface structure is as follows: Figure 3 As shown.

[0022] The electrical principle of the pre-installation test device for aircraft engine parameter acquisition display described in this invention is as follows: Figure 4 As shown, the internal circuit principle of the test adapter and control unit is as follows: Figure 5 As shown, the specific working principle is as follows: The engine parameter acquisition and display system is mainly used to monitor the AC and DC power supply voltage of the aircraft. Simultaneously, through main and auxiliary hydraulic sensors, lubricating oil pressure sensors, and thermocouples, it is used to acquire and display the main operating performance parameters of the engine. Therefore, its detection system mainly realizes the power supply control of the test system and finished product, providing test excitation sources such as DC voltage, AC voltage, main hydraulic pressure, auxiliary hydraulic pressure, lubricating oil pressure, and exhaust temperature to simulate the operation of the aircraft system. It completes the parsing and display of ARNIC429 bus data sent by the engine parameter acquisition and display system, and finally meets the measurement requirements of the engine parameter acquisition and display system's functions and performance accuracy through the test adapter and control unit. Since the DC voltage module, AC voltage module, main hydraulic pressure module, auxiliary hydraulic pressure source module, lubricating oil pressure source module, exhaust temperature source module, test adapter and control unit, system power supply unit, bus parsing unit, industrial computer, and display involved in this invention are all commonly used modules in aircraft engine parameter acquisition, their specific structures and connections are not described in detail. Their application in the pre-installation tester described in this invention aims to test whether the main functions and performance indicators meet the test assurance requirements.

[0023] Other aspects of this invention that are not detailed herein are all conventional techniques known to those skilled in the art.

[0024] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention can have various modifications and variations. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A pre-installation test fixture for an aircraft engine parameter acquisition display, comprising a cabinet, the interior of which is divided into four cavities, from top to bottom being a first cavity, a second cavity, a third cavity, and a fourth cavity, characterized in that: It also includes a DC voltage module (1), an AC voltage module (2), a main hydraulic pressure module (3), an auxiliary hydraulic pressure source module (4), a lubricating oil pressure source module (5), an exhaust temperature source module (6), a test adapter and control unit (7), a system power supply unit (8), a bus parsing unit (9), an industrial computer (10), and a display (11). The display (11) is installed in the first cavity inside the cabinet, the industrial computer (10) is installed in the second cavity inside the cabinet, the bus parsing unit (9) is installed inside the industrial computer (10), and the bus parsing unit (9) is used to receive and parse test parameters. The test adapter and control unit (7) is installed in the third cavity inside the cabinet. The DC voltage module (1), AC voltage module (2), main hydraulic pressure module (3), auxiliary hydraulic pressure source module (4), lubricating oil pressure source module (5), and exhaust temperature source module (6) form an excitation signal simulation unit. The excitation signal simulation unit is installed inside the test adapter and control unit (7). The test adapter and control unit (7) is used to control the working state of the excitation signal simulation unit and transmit the simulation signal to the industrial computer (10) through the bus parsing unit (9). The status information of the excitation signal simulation unit is displayed on the display (11). The system power supply unit (8) is installed in the fourth cavity inside the cabinet (12) and is used to provide power to the excitation signal simulation unit, the test adapter and control unit (7), the bus parsing unit (9), the industrial computer (10), and the display (11). The display (11) is electrically connected to the industrial computer (10) through a cable. The test adapter and control unit (7) includes a control switch, socket, plug and control panel. The DC voltage module (1), AC voltage module (2), main hydraulic pressure module (3), auxiliary hydraulic pressure source module (4), lubricating oil pressure source module (5) and exhaust temperature source module (6) installed inside the test adapter and control unit (7) are connected to the corresponding control switch, socket and plug through cables to form an excitation signal simulation unit. The control panel is also provided with control knobs and displays corresponding to the DC voltage module (1), AC voltage module (2), main hydraulic pressure module (3), auxiliary hydraulic pressure source module (4), lubricating oil pressure source module (5) and exhaust temperature source module (6). The test adapter and control unit (7) controls the working status of the DC voltage module (1), AC voltage module (2), main hydraulic pressure module (3), auxiliary hydraulic pressure source module (4), lubricating oil pressure source module (5) and exhaust temperature source module (6) respectively through the control knobs in the control panel, and displays their status parameter values ​​respectively through the display. The bus parsing unit (9) includes an ARNIC-429 data bus. The bus parsing unit (9) uses the C++ programming language to receive and parse the ARNIC429 bus data and test parameters. The bus parsing unit (9) transmits the received and parsed test parameters to the industrial control computer (10) and displays the test status information of the test excitation source composed of the DC voltage module (1), AC voltage module (2), main hydraulic pressure module (3), auxiliary hydraulic pressure source module (4), lubricating oil pressure source module (5) and exhaust temperature source module (6) through the display (11). The lubricating oil pressure source module (5) includes a potentiometer. The potentiometer is composed of 10 precision potentiometers of model 3296 forming a resistance network. The corresponding range is selected by a band switch to meet the pressure simulation input of the lubricating oil pressure source module (5). The main hydraulic pressure module (3) and the auxiliary hydraulic pressure source module (4) are configured to meet the pressure input requirements of the main hydraulic pressure module (3) and the auxiliary hydraulic pressure source module (4) by applying a 10V DC reference voltage to both ends of the precision potentiometer and adjusting the precision potentiometer.

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