Space stability analysis method of aircraft control system

An analysis method and control system technology, applied in electrical testing/monitoring, etc., can solve problems such as difficult to meet system performance requirements

Active Publication Date: 2019-11-15
GUILIN UNIV OF AEROSPACE TECH
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Problems solved by technology

Based on the above reasons, it is difficult to design an aircraft control system or pilot with a single linear controller to meet the performance requirements of the system. Therefore, when designing an aircraft control system or an autopilot, a comprehensive consideration and analysis of the three-channel performance of the aircraft is required.

Method used

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  • Space stability analysis method of aircraft control system
  • Space stability analysis method of aircraft control system
  • Space stability analysis method of aircraft control system

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Embodiment

[0081] refer to figure 2 , image 3 , a method for analyzing space stability of an aircraft control system, comprising the steps of:

[0082] 1) Obtain aerodynamic data: use the wind tunnel test or aerodynamic calculation of the aircraft to obtain the aerodynamic data of the aircraft, and use the aerodynamic data to analyze various characteristics of the aircraft. The various characteristics of the aircraft are the maximum available overload, the rate of turn , balance angle of attack, because the aerodynamic data of the aircraft can reflect various characteristics of the aircraft, so the spatial stability analysis of the aircraft needs to analyze the characteristics of the aerodynamic moment, aerodynamic force and engine thrust parameters of the aircraft, and analyze the characteristics of the aircraft in each The performance under these conditions is used to judge whether the results of the space stability analysis of the aircraft control system are reasonable and reliable...

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Abstract

The invention discloses a space stability analysis method of an aircraft control system. The method comprises the following steps: 1), acquiring aerodynamic data; 2), solving aerodynamic derivatives on the basis of the aerodynamic data, and establishing a coupled aircraft motion equation between channels; 3),performing linearization analysis; 4),testing linearization analysis performance and improving results. Overall assessment and comprehensive design of aircraft flight tests can be achieved with the method, cause analysis and design improvement direction are provided for various instabilities of the aircraft under specific conditions, algorithm design work can also be promoted, various coupling flight states can be taken into account more comprehensively, and the method has obvious significance for accelerating the development progress of aircrafts.

Description

technical field [0001] The invention relates to the stability technology of an aircraft control system, in particular to a space stability analysis method of an aircraft control system. Background technique [0002] The flight control system of modern high-performance aircraft requires fast dynamic response, small overshoot, and strong interference suppression ability. During the flight phase of the aircraft at a high angle of attack, the inclined channel of the aircraft is affected by a strong induced roll disturbance moment. The conventionally designed linear control method may not be able to suppress the influence of the disturbance torque in time, resulting in an excessively large and fast response to the tilt angle rate. When the rolling angular rate exceeds a certain limit, the inertial device of the aircraft itself will fail; in addition, the drastic changes in the rolling angle and rolling angular rate will cause strong coupling between channels, and in severe cases...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B23/02
CPCG05B23/02
Inventor 王建琦汪冬梅
Owner GUILIN UNIV OF AEROSPACE TECH
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