A low-speed wind tunnel virtual flight experiment support device and its application method

Abstract

The present invention discloses a low-speed wind tunnel virtual flying experimental support device which comprises a base, an airfoil support seat, a pre-bent support rod and a three-degree-of-freedom joint. The base is fixedly installed at the center position of a wind tunnel test section basic platform. The bottom end of the airfoil support seat is vertical and is fixedly installed on the base. The cross section of the airfoil support seat is parallel to a wind tunnel flow coming direction. One end of the pre-bent support rod is connected to the top end of the airfoil support seat, the other end of the pre-bent support rod is connected to the three-degree-of-freedom joint, and the cross section of the pre-bent support rod is parallel to the wind tunnel flow coming direction. The rotation center of the three-degree-of-freedom joint is in an axis in a wind tunnel and is hinged to an aircraft model. The hinged position is provided with a fine burning device which allows the mass center of the aircraft model coincides with the rotation center of the three-degree-of-freedom joint. According to the invention, the large range three-axis attitude free support of the aircraft model in a virtual flying experiment can be realized, the structure is simple, the interference is small, the accuracy is high, and the installation and adjustment methods are simple.

Description

technical field [0001] The invention belongs to the technical field of wind tunnel experiment devices, and in particular relates to a low-speed wind tunnel virtual flight experiment support device and a use method thereof. Background technique [0002] In the low-speed wind tunnel virtual flight experiment, the support device is used to support the aircraft model, constrain the degree of freedom of three-axis displacement motion, and provide the degree of freedom of three-axis attitude motion. Require. [0003] The existing support devices for virtual flight experiments can be divided into two types based on the design principle: tensioning type and kinematic joint series superposition type. [0004] The tension-type support device uses 8 tension lines to fix a collar on the wind tunnel test section, and the collar is connected to the aircraft model through a two-degree-of-freedom motion ring. Although the support of the tensioned support device has less interference with ...

AI Technical Summary

Problems solved by technology

Although the support of the tensioned support device has less interference with the flight experiment, it still has the following disadvantages: one is that the degree of freedom of the yaw angle cannot be realized; the other is that the achievable pitch and roll degrees of freedom are not large; It is a complex structure, difficult to install and debug

Although this kind of supporting device has a simple structure, it has the following disadvantages: First, there is an error in the orthogonal alignment between the joint rotating shafts, and the alignment error between the center of mass of the aircraft model and the intersection of the rotating shaft is relatively large, which causes the dynamics of the aircraft model to be affected by the supporting device. Second, some mechanisms in this kind of supporting device will move together with the aircraft model, causing the supporting device to interfere with the flight test. Big

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