Method for correcting unmanned aerial vehicle control matrix based on wind tunnel test data and CFD calculation

Abstract

Provided is a method for correcting an unmanned aerial vehicle control matrix based on wind tunnel test data and CFD calculation. Due to the fact that flight control needs pneumatic control, the reliable control matrix is provided. The wind tunnel test data of a planar model with an unconventional pneumatic layout is extracted, the dynamic derivative of a design point is subjected to local correction, and the influence of the unconventional layout on a traditional layout empirical formula is effectively eliminated. Compared with an existing control matrix providing method, an original method refers to ab control matrix research researched through a traditional unmanned aerial vehicle engineering design method, is obtained mainly based on experience summarized through many years of conventional appearance pneumatic layout design, has limitation to the unconventional layout and is disconnected from a wind tunnel test link. The conventional force measurement data of a wind tunnel test of the planar model is utilized creatively, the control matrix is corrected, and a more precise control matrix is provided for PID parameter control.

Description

technical field [0001] The present invention relates to a correction method of UAV control matrix based on wind tunnel test data and CFD calculation. At the same time, taking into account the wind tunnel test data and CFD calculation results for reference, it can quickly realize conventional layout and unconventional layout flight control in engineering The calculation of the matrix is ​​mainly used in the process of aircraft aerodynamic design, and belongs to the technical field of aeronautical aircraft aerodynamic design. Background technique [0002] In the process of aircraft design, the design of the control rate usually needs to be provided by the aerodynamic cooperation department. Once the flight control matrix provides a large error, it will lead to the extension of the design cycle and the decrease of the design accuracy. The flight control matrix is ​​mainly provided by the aerodynamic department. The use of traditional empirical formulas is limited to the convent...

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Problems solved by technology

[0002] In the process of aircraft design, the design of the control rate usually needs to be provided by the aerodynamic coordination department. Once the flight control matrix provides a large error, it will lead to an extension of the design cycle and a decrease in the design accuracy

The flight control matrix is ​​mainly provided by the aerodynamic department. The use of traditional empirical formulas is limited to the conventional aerodynamic layout. There are certain errors in the calculation of the shape of the unconventional layout and the approximate conventional layout. With the future aerodynamic layout ( Based on the shape obtained by aerodynamic design optimization), the development error will become larger and larger

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