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Airplane full static pressure test system based on adaptive PID method and method

A test system, full static pressure technology, applied in the direction of measuring the rate of increase and deceleration of the fluid, using liquid/vacuum degree for liquid tightness measurement, etc., can solve the difficult to meet the test requirements of the full static pressure system, full static pressure test equipment Inconvenient use and maintenance

Active Publication Date: 2016-09-28
CIVIL AVIATION UNIV OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the existing technical problems, aiming at the inconvenience in the use and maintenance of the full static pressure test equipment of airlines, and to solve the current situation that the test requirements of the full static pressure system are difficult to meet, and to provide a low cost, simple structure, An aircraft full static pressure test system and method based on an adaptive PID method capable of rapid testing, convenient calibration and maintenance, convenient access to aircraft systems, and meeting the test requirements of airline maintenance manuals

Method used

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  • Airplane full static pressure test system based on adaptive PID method and method
  • Airplane full static pressure test system based on adaptive PID method and method
  • Airplane full static pressure test system based on adaptive PID method and method

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Embodiment Construction

[0105] In order to illustrate the present invention more clearly, the implementation manners of the present invention will be described in detail below with reference to the accompanying drawings.

[0106] Such as Figure 1 to Figure 12 Shown, a kind of aircraft full static pressure test system based on adaptive PID method, comprises control core module, power supply module, isolated power supply module, optocoupler isolator, 485 bus module, relay module, signal transmitter 1, signal transformer Transmitter II, proportional valve module I, proportional valve module II, man-machine interface module, sensor I, sensor II, sensor III, sensor IV, solenoid valve I, solenoid valve II, solenoid valve III, solenoid valve IV, solenoid valve Ⅴ. Vacuum pump and compressor.

[0107] One of the power modules is connected to the control core module and the human-computer interface module through the isolated power module, the other is connected to the vacuum pump and the compressor, and the...

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Abstract

The invention relates to an airplane full static pressure test system based on an adaptive PID method and a method. According to the method, a power source starts power supply, self check is carried out; if correct, an analysis step of an instruction is carried out; if not correct, re-input of the instruction is carried out; a core module is controlled for converting and analyzing the instruction; the instruction is actuated; whether an emergency stop instruction is emitted is determined; if yes, the program is ended; if not, acquisition of pressure values of a sensor II and a sensor IV starts; values of the sensor II and the sensor IV are continuously acquired; the core module is controlled for checking whether a target value is reached; if yes, the progress is over; if not, the instruction is re-actuated. Through the method, a precise and reliable pressure source can be provided by the system for an airplane according to setting of an operator, real-time response can be carried out according to different demands of a test process, the airplane can be protected under emergent situations such as shedding of a pressure connector, and test tasks prescribed in an airplane manual can be accomplished according to demands of the airplane manual.

Description

technical field [0001] The invention belongs to the field of automatic testing, in particular to an aircraft full static pressure testing system and method based on an adaptive PID method. Background technique [0002] The full static pressure test system is used in the infield maintenance and outfield maintenance where the full static pressure test of the aircraft is required. The system provides corresponding air pressure sources for the aircraft full static pressure system according to the operating instructions of the tester. At present, the aircraft full static pressure test system has high purchase cost, high maintenance cost, and long maintenance cycle, which brings inconvenience to the normal operation of the airline company, and even brings certain risks to flight safety due to the change of accuracy and air tightness caused by long-distance transportation. influences. In addition, the existing tester mainly relies on the ball valve for pressure change operation, w...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M3/26
CPCG01M3/26
Inventor 段照斌张鹏杜海龙栗中华李静昭钮伟龙杜航航刘意刘博
Owner CIVIL AVIATION UNIV OF CHINA
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