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Determination method of digital controller control parameters of cabin pressure control system

A cockpit pressure control and digital controller technology, applied in the direction of electrical digital data processing, instruments, special data processing applications, etc., can solve the problem of not being retrieved, and achieve the effect of eliminating bulging and improving comfort

Active Publication Date: 2016-08-24
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

Its disadvantage is: when the plane takes off, the cabin pressure will follow the climb of the plane for a period of time, and the phenomenon of "bulge" will appear. After the pressure reaches a certain value, the cabin pressure of the aircraft increases to the original equilibrium state
Public literature on determining the control parameters of the digital controller of the integrated digital cockpit pressure control system has not been retrieved

Method used

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  • Determination method of digital controller control parameters of cabin pressure control system
  • Determination method of digital controller control parameters of cabin pressure control system
  • Determination method of digital controller control parameters of cabin pressure control system

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Experimental program
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Embodiment

[0045] see figure 1 , to determine the control parameters of the digital controller of a certain type of aircraft cabin pressure control system, the steps to determine the control parameters of the digital controller are as follows:

[0046] 1. Connection test device: the test device includes an air tank 4 for simulating the atmospheric environment of aircraft flight, an air tank 5 for simulating the aircraft cockpit environment, an air source 6 and a simulated atmospheric pressure sensor 7, the air inlet of the air tank 5 is connected to the A gas source 6 with a flow regulating function is connected, the gas outlet of the gas tank 5 is connected with the gas tank 4 through the electric exhaust valve 3, and the simulated atmospheric pressure sensor 7 is installed in the inner cavity of the gas tank 4, and the simulation of the simulated atmospheric pressure sensor 7 The atmospheric pressure signal output end is connected with the simulated atmospheric pressure signal input en...

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Abstract

The invention belongs to the technology of plane environment control, and relates to the improvement of a method for determining a control parameter of a digital controller of a cabin pressure control system. The method for determining the control parameter of the digital controller of the cabin pressure control system is characterized by including the following steps that a testing device is connected, a quick change area of an exhaust valve under a typical airport environment is determined, the minimum value in the H1 and H2 is selected, and the parameter and the parameter action range of the digital controller are determined. By means of the method for determining the control parameter of the digital controller of the cabin pressure control system, the phenomenon of 'swelling' in the rapid climbing process of a plane is removed, and the comfort of flight personnel and passengers is improved.

Description

technical field [0001] The invention belongs to aircraft environment control technology, and relates to an improvement on a method for determining control parameters of a digital controller of a cockpit pressure control system. Background technique [0002] At present, the cockpit pressure regulation system mainly adopts the pneumatic pressure regulation system, see "Aircraft Cockpit Air Parameter Control", Wang Jun, Xu Yanghe, National Defense Industry Press, 1980.12. . Its disadvantage is: when the plane takes off, the cabin pressure will follow the climb of the plane for a period of time, and the phenomenon of "bulge" will appear. After the pressure reaches a certain value, the cabin pressure of the aircraft increases to the original equilibrium state. When the aircraft climbs rapidly, the "bulge" will cause large pressure fluctuations in the cockpit, which will affect the eardrums of the personnel and cause discomfort to the flight personnel and passengers. New aircra...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F19/00B64D13/04
Inventor 何成军
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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