Low-speed wind channel virtual flying test aircraft model designing method

Abstract

The invention relates to a low-speed wind channel virtual flying test aircraft model designing method and belongs to the field of wind channel virtual flying test model designing. By the method, a control plane driving mode is optimized, and a model operation plane can be changed a control plane automatically to realize a model pneumatic / movement / control coupling function. Weight and inertial load of a model are reduced, balancing of center of mass of the model is realized in the aspect of structural design, and aircraft model reference center, model actual center of mass and virtual flying supporting mechanism rotating center are ensured to be coincident at the same time. The method meets requirements of processing techniques and test equipment, processing accuracy of the model meets requirements on virtual flying wind channel test data measuring accuracy, and the model is stable in running when being applied in virtual flying wind channel tests and convenient to mount and demount.

Description

technical field [0001] The invention relates to a design method of a low-speed wind tunnel virtual flight test aircraft model. Background technique [0002] Wind tunnel tests usually provide aerodynamic parameters for aircraft design and control system design. However, with the continuous improvement of the maneuvering characteristics of the aircraft, higher requirements are put forward for the performance of the aircraft. At present, there is no good description and prediction of the overload, stability and control force required for the maneuvering of the aircraft at high angles of attack. ground test method. For this problem, an advanced wind tunnel dynamic test technology, that is, wind tunnel virtual flight test technology, has been developed in recent years. This technology makes it possible to realize the flight dynamics characteristics of the aircraft, the flight control system, and the comprehensive verification of the navigation system in the wind tunnel by simul...

AI Technical Summary

Problems solved by technology

The wind tunnel virtual flight test also requires the use of a scaled model, especially for airplanes, whose geometric scale is relatively small. In addition to the unsteady aerodynamic force during the test, in order to achieve the attitude control of the model, it is also necessary to consider the The control computer, attitude measurement system, steering gear control system, etc. are installed in appropriate positions inside the scaled model. The design process of the test model is very complicated, and after the model is scaled down, the overall structure must meet the requirements of light weight and high strength.

At this time, the use of metal materials can no longer meet the requirements.

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