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Flight Test Determination Method for Multi-loop Human-Machine Closed-Loop Characteristics of Statically Unstable Aircraft

A technology of static instability and flight test, applied to instruments, adaptive control, control/regulation systems, etc., can solve problems such as static instability and large modeling errors

Inactive Publication Date: 2013-11-27
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

In order to overcome the large deficiency of existing flight test determination method modeling error, the invention provides a kind of static instability

Method used

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  • Flight Test Determination Method for Multi-loop Human-Machine Closed-Loop Characteristics of Statically Unstable Aircraft

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Embodiment Construction

[0020] With reference to the drawings, the present invention will be described in detail.

[0021] 1. Obtain the closed-loop transfer function frequency characteristics of the statically unstable aircraft multi-loop system through the sweep frequency flight test

Matrix Φ(jω)=G(jω)[I+G(jω)]

-1

.

[0022] In the formula, j is the imaginary symbol, ω represents the frequency, Φ(jω) is the frequency characteristic matrix of the closed-loop transfer function, G(jω)

Is the frequency characteristic matrix of the open-loop transfer function, and I is the identity matrix.

[0023] For ease of description, assume that the statically unstable aircraft 3 inputs and 3 outputs are directly obtained through the frequency sweep flight test.

The frequency characteristic matrix of the closed-loop transfer function of the system is:

[0024]

[0025] 2. The i-th loop corresponds to the man-machine model connected in series to the equivalent open-loop system,

When the system is critically stable, we ...

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Abstract

The invention relates to a method for determining the flight test of the multi-circuit human-machine closed-loop characteristics of a statically unstable aircraft. The method obtains the frequency characteristic matrix of the closed-loop transfer function of the multi-circuit system of the statically unstable aircraft through a frequency-sweeping flight test, and according to the closed-loop transfer function The corresponding relationship between the man-machine model and the aircraft closed-loop system is expressed as an equivalent equation, and according to the critical stability of the system, the formula for determining the man-machine closed-loop characteristics through the frequency characteristic matrix of the closed-loop transfer function is obtained Two calculation formulas, through the multi-parameter analysis method, directly determine the influence of the static gain of the pilot link, the inherent delay characteristics, the lead compensation time constant, and the pilot lag compensation time constant on the system stability margin, so as to determine the man-machine characteristics of the aircraft Whether it can meet the requirements of the national military standard stability margin.

Description

Flight test method for determining multi-loop man-aircraft closed-loop characteristics of statically unstable aircraft law Technical field [0001] The present invention relates to a flight test determination method, in particular to a statically unstable aircraft multi-loop man-machine closed loop Method for determining characteristics of flight test. Background technique [0002] In the development of high-performance aircraft, evaluating the flight quality of an aircraft depends not only on the aircraft itself and The dynamic characteristics of the pilot’s control also depend on the highly consistent coordination between the pilot and the aircraft, and the Into the rationality of function allocation among aircraft flight control systems. Until 1980, the U.S. military standard for evaluating aircraft flight quality There are still serious shortcomings, that is, the driver’s role in the control loop is not considered. Therefore, the evaluation and test There is still a gap i...

Claims

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Application Information

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IPC IPC(8): G05B13/04
Inventor 史忠科
Owner NORTHWESTERN POLYTECHNICAL UNIV
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