Measurement method for high-aspect-ratio wing control surface inside hinge moment

Abstract

The invention provides a measurement method for the high-aspect-ratio wing control surface inside hinge moment. The measurement method comprises the steps of obtaining first pressure factor distribution in the direction along the course on the outermost side of a control surface on the inner side of a wing which is not cut off; obtaining second pressure factor distribution in the direction along the course on the outermost side of a control surface of a wing which is cut off by a preset length; according to the first pressure factor distribution and the second pressure factor distribution, determining the length of the wing; carrying out a wind tunnel experiment on the wing with the determined length, and measuring the wing control surface inside hinge moment.

Description

technical field [0001] This application relates to the field of aviation aerodynamic layout, and specifically provides a method for measuring the inner hinge moment of a wing rudder surface with a super large aspect ratio. Background technique [0002] As individuals and society continue to increase the flight time and range of aircraft, in order to achieve higher aerodynamic efficiency, the aspect ratio of aircraft will also increase. Therefore, aircraft with super large aspect ratio is one of the important directions of current development. At present, there are two ways to obtain hinge torque, one is special wind tunnel test, and the other is CFD simulation calculation. However, in the high-speed wind tunnel test, a wing with a super-large aspect ratio will cause a larger bending moment than the general small-to-medium aspect ratio aircraft due to its too long span length, resulting in a large elastic deformation. The current hinge moment measurement balance In other wor...

AI Technical Summary

Problems solved by technology

However, in the high-speed wind tunnel test, a wing with a super-large aspect ratio will cause a larger bending moment than the general small-to-medium aspect ratio aircraft due to its too long span length, resulting in a large elastic deformation. The current hinge moment measurement balance In other words, the excessive deformation of the wing will have a greater impact on the accuracy of its measurement and even affect the normal use of the balance, making it difficult to obtain accurate test data or even to carry out normal tests

In CFD calculation, because the rudder surface is usually at the trailing edge, the flow near the rudder surface is very complicated, especially after the rudder surface is deflected, it is easy to generate a detachment vortex, and there is serious airflow separation, so it is difficult to carry out accurate simulation and obtain an accurate hinge in CFD calculation. Moment value

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