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A flight test method capable of measuring the stability margin of a multi-input multi-output flight control system

A technology of flight control system and system stability, applied in the direction of control/adjustment system, aircraft control, non-electric variable control, etc., to achieve obvious military effects

Inactive Publication Date: 2011-06-22
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Abstract
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  • Application Information

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Problems solved by technology

The purpose of the present invention is only suitable for SISO flight control system for existing classical stability margin flight test method, may

Method used

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  • A flight test method capable of measuring the stability margin of a multi-input multi-output flight control system
  • A flight test method capable of measuring the stability margin of a multi-input multi-output flight control system
  • A flight test method capable of measuring the stability margin of a multi-input multi-output flight control system

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Embodiment Construction

In order to improve the classical stability margin flight test method, expand the scope of application of the stability margin concept, at first need to define

MIMO system stability margin. For this purpose, consider the general unit feedback system shown in Fig. 4. In order to use the robustness criterion, the Fig.

4 is transformed into the general analysis block diagram of system robustness shown in Fig. 5. where P is the input hysteresis matrix, which is defined as the identity matrix and

The sum of the open-loop transfer matrices of the input loop, that is, P=I+G. Secondly, measure the roll axis and yaw axis input signals xR, xY, vice

Wing and rudder excitation signal uR, uY; get roll axis and yaw axis output yR, yY from yR=xR-uR, yY=xY-uY; calculate

4 transfer function components:

[0052]

Wherein XR, YR, XY, YY are respectively xR, yR, xY, the Fourier transform of yY. Combining the 4 transfer function components into

The minimum singular value σ(P) and the m...

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Abstract

The invention provides a flight test method for measuring the stability margin of a multi-input multi-output flight control system. The steps include: (1) inputting a frequency sweep excitation signal to the flight control system to be tested; (2) obtaining the open-loop transfer function of the flight control system Matrix (3) Calculate the minimum singular value σ(P) and the minimum eigenvalue λ(P) of the system hysteresis matrix P=I+G; (4) Calculate the guaranteed amplitude margin and guaranteed phase according to the MIMO system stability margin formula Margin; (5) In order to reduce conservatism, replace σ(P) with λ(P) and substitute it into the calculation formula of MIMO system stability margin to obtain amplitude margin and phase margin. The invention proposes a new index for evaluating the MIMO system stability margin, a new index for evaluating the MIMO system, and proposes a set of flight test methods for obtaining the MIMO system stability margin, including test principles, test actions and flight test data processing procedures. Also proposed two conservative methods to reduce the stability margin of the MIMO system, improved the stability margin test flight technology of the single-input single-output (SISO) flight control system, and provided a basis for the flight test research of the multiple-input multiple-output (MIMO) flight control system and the new generation of fighters. The development provided technical support.

Description

The flight test method capable of measuring the stability margin of the multi-input multi-output flight control system Technical field [0001] The present invention relates to a flight test method of a multi-input multi-output flight control system stability margin. Background technique [0002] Stability margin is an important indicator of the control system. In the national military standard, the stability margin of the flight control system is clearly defined It is a necessary flight test project for modern new aircraft. However, the classical stability margin is for a single-input single-output (SISO) system, it cannot reflect the impact of various uncertainties on the multiple-input multiple-output system (MIMO). In order to pursue better maneuverability, modern fighters generally adopt the MIMO flight control system cross-linked in the horizontal direction. with With the in-depth research on MIMO systems and the emergence of robust control theory, it is found tha...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/00B64C19/00G06F7/00
Inventor 瞿福存
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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