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Aircraft aerodynamic identification correction method and medium

An aircraft and aerodynamic technology, which is applied in the field of aircraft aerodynamic identification and correction, can solve problems such as the difficulty of nonlinear mathematical models, and achieve the effect of improving accuracy

Active Publication Date: 2020-02-21
SHANGHAI INST OF ELECTROMECHANICAL ENG
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  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

The general linear model directly applies the aerodynamic and static derivatives obtained by identification, while the nonlinear mathematical model describing complex aerodynamic characteristics is difficult to directly apply

Method used

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  • Aircraft aerodynamic identification correction method and medium
  • Aircraft aerodynamic identification correction method and medium

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0027] An aircraft aerodynamic identification correction method, such as figure 1 shown, including the following steps:

[0028] S1. Use the wind tunnel to obtain the aerodynamic coefficient and aerodynamic moment coefficient of the aircraft under predetermined roll angle, Mach number, attack angle, and rudder deflection angle; establish a non-linear aerodynamic mathematical model of the aircraft.

[0029] The nonlinear aerodynamic mathematical model of the aircraft is:

[0030] C 6×1 =A 6×n x n×1

[0031] In the formula, C 6×1 is the aerodynamic coefficient or aerodynamic moment coefficient, A 6×n is the coefficient matrix, X n×1 is a set of bases that are linearly independent, n is X n×1 rank.

[0032] S2. Based on the flight test data of the aircraft, use but not limited to dynamic equations or kinematic equations to obtain flight aerodynamic coefficients and flight aerodynamic moment coefficients under different working conditions. Flight test test data include a...

Embodiment 2

[0042] A computer-readable storage medium, on which a computer program is stored. When the program is executed by a processor, the steps of the aircraft aerodynamic identification and correction method described in Embodiment 1 are realized.

Embodiment 3

[0044] A method for aerodynamic identification and correction of an aircraft, comprising the following steps:

[0045] (1) From the speed, altitude, acceleration, angular velocity, rudder deviation and other signals measured in the flight test, the flight aerodynamic coefficient and flight aerodynamic moment coefficient of the corresponding working conditions are obtained;

[0046] (2) Take the flight aerodynamic coefficient and flight aerodynamic moment coefficient of the flight state as the data samples of the nonlinear aerodynamic mathematical model of the aircraft, and establish a set of overdetermined equations together with the original wind tunnel test data sample points;

[0047] (3) Solve the overdetermined equations, obtain the corrected aerodynamic coefficient and the corrected aerodynamic moment coefficient, and establish the corrected nonlinear aerodynamic mathematical model of the aircraft.

[0048] specific:

[0049] (1) From the speed, altitude, acceleration, ...

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Abstract

The invention discloses an aircraft aerodynamic identification correction method and a medium, and belongs to the technical field of aerodynamic design. The method aims at a nonlinear aerodynamic mathematical model of an aircraft with complex aerodynamic characteristics. Based on the fact of flight test state diversity, flight test data and wind tunnel test data are jointly used as modeling samplepoints, a corrected aerodynamic mathematical model is established by solving an overdetermined equation set, identification can be carried out along with the development stage, the flight test samplepoints are continuously increased, and the precision of the aerodynamic mathematical model is improved.

Description

technical field [0001] The invention relates to an aircraft aerodynamic identification and correction method and a medium, belonging to the technical field of aerodynamic design. Background technique [0002] Usually, after the shape of the aircraft is basically determined, the aerodynamic mathematical model formula is given according to the shape of the aircraft and certain mathematical ideas, and then the wind tunnel test project is formulated, and the input of the aerodynamic mathematical model is obtained through the wind tunnel test (that is, as a sample point for modeling) , so as to determine the three-dimensional aerodynamic mathematical model of the aircraft used in the flight test. After the flight test, the aerodynamic coefficient should be identified according to the flight test situation, and the mathematical model should be corrected. The general linear model directly applies the aerodynamic and static derivatives obtained by identification, but it is difficul...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F30/17
Inventor 傅建明唐海敏王波兰李欣益廖欣李克勇肖志斌张学斌
Owner SHANGHAI INST OF ELECTROMECHANICAL ENG
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