Airplane hydraulic test distributed test system and method thereof

Abstract

The invention discloses an airplane hydraulic test distributed test system and a method thereof, belonging to the technical field of measurement and control. The test system comprises a data acquisition instrument module (1), a test controller (2), a signal conditioner (3), a network switch (4), an LXI instrument control data bus (5), a field data module (6), an interface conversion module (7), a field data bus (8), a series communication data bus (9) and test software and is characterized in that a plurality of data buses are simultaneously used, and various data acquisition modules are adopted in the test system to finish the data acquisition in the measurement of various signals and the long-line transmission of the measured signals. The system of the invention has compact and simple structure, small space size, reliable operation, high test accuracy and favorable expansibility and tailorability.

Description

technical field [0001] The invention belongs to the technical field of measurement and control, and relates to a distributed test system for aircraft hydraulic tests, in particular to a distributed test system and a test method for measuring various physical quantities such as pressure, flow, and temperature of an aircraft hydraulic system. Background technique [0002] In the test of aircraft hydraulic system, it is required to complete the measurement of hydraulic fluid characteristic parameters: pressure, flow, temperature, and stress / strain and other signals, and the mechanical motion parameters of hydraulic control system and actuation system: linear displacement, angular displacement, force, torque , speed and other signals, as well as the measurement of voltage, current and other signals in the logic control of the system. In actual tests, the measurement of rapidly changing signals such as pressure pulsation, instantaneous peak pressure, and stress / strain requires hi...

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Problems solved by technology

[0003] In the above-mentioned test measurement, because the measurement parameters need to be derived from the hydraulic system components and accessories distributed in different positions of the aircraft, the traditional measurement is developed based on GPIB (General Purpose Interface Bus), VXI (VME eXtensions for Instrumentation) or PXI (PCIeXtensions For Instrumentation) instrument control bus test system, the measurement signals scattered in different positions are introduced into the test system, a large number of test cables and long-term transmission often need to spend a lot of energy and time to solve signal transmission and test interference, noise, etc. Problem; secondly, the test system based on GPIB, or VXI or PXI instrument control bus can only use one sampling rate for data acquisition operation for all test signals, and it is difficult to take into account the simultaneous high-speed data acquisition and slow data acquisition. operation; third, in the face of multiple signal measurements in the test, it is necessary to develop or configure test recording instruments for different signal measurements, such as for the measurement of stress / strain signals, a special stress / strain measurement system is required, and for pressure, In the measurement of signals such as displacement, conventional data acquisition systems can be used

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