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A method for evaluating the control performance of an aircraft cabin pressure control system

A cockpit pressure control and cockpit pressure technology, applied in data processing applications, complex mathematical operations, geometric CAD, etc., can solve problems such as performance index quantification, and achieve the effect of improving control performance

Active Publication Date: 2021-03-26
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] In the past, during the ground test, delivery test, and flight test of the cockpit pressure control system, it was mainly judged whether the control curve of the cockpit pressure met the system design requirements to judge whether the system control was stable, and judged by observing whether the change rate of the cockpit pressure exceeded the range of the system design. Whether the system comfort meets the requirements, and the performance indicators are not quantified

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  • A method for evaluating the control performance of an aircraft cabin pressure control system
  • A method for evaluating the control performance of an aircraft cabin pressure control system
  • A method for evaluating the control performance of an aircraft cabin pressure control system

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Embodiment Construction

[0016] The technical solution will be described in further detail below in conjunction with the accompanying drawings.

[0017] A method for evaluating the control performance of an aircraft cabin pressure control system, the method comprising: under the premise that the control system is stable, the control performance is evaluated by calculating the mean square error value of the cabin pressure and the root mean square value of the cabin pressure change rate, The smaller the mean square error value of the cabin pressure and the root mean square value of the change rate of the cabin pressure, the better the control performance.

[0018] The control performance evaluation method of aircraft cockpit pressure control system is based on the control performance test design of cockpit pressure control system. figure 1 The connection relationship of the control performance test of the cabin pressure control system is given in . The control performance test environment of the cockpi...

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Abstract

The invention belongs to the technical field of aviation simulation, trial flight and test monitoring, and relates to a method for assessing control performance of an aviation cockpit pressure control system. According to the method, the control performance is assessed through calculating a mean square deviation value of cockpit pressure and a root-mean-square value of a cockpit pressure change rate under the premise that the control system carries out control stably; and if the mean square deviation value of the cockpit pressure and the root-mean-square value of the cockpit pressure change rate are smaller, the control performance is better. According to the method, quantitative indexes are provided for control law design and control law parameter optimization in a system development process, so that the control performance of the aviation cockpit pressure control system is furthermore enhanced.

Description

technical field [0001] The invention belongs to the technical field of aviation simulation, flight test and test monitoring, and relates to a control performance evaluation method of an aircraft cockpit pressure control system. Background technique [0002] The aircraft cockpit pressure control system has flight tasks such as normal flight, cargo cabin pressure relief, combat pressure difference, ditching, emergency pressure relief, etc. It is a key system of the environmental control system and is related to the comfort of the passengers and the safety of the aircraft. Therefore, it is particularly important to evaluate the control performance of the cabin pressure control system. Cabin pressure and cabin pressure rate of change are the main performance indicators of the cabin pressure control system. [0003] In the past, during the ground test, delivery test, and flight test of the cockpit pressure control system, it was mainly judged whether the control curve of the coc...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06Q10/06G06F17/18G06F30/15
CPCG06F30/15G06F30/20
Inventor 任明波何成军杨丹
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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