Low-speed wind tunnel horizontal free flight model attitude measurement method

Abstract

The invention is applicable to the technical field of wind tunnel tests, and provides a low-speed wind tunnel horizontal free flight model attitude measurement method. The method comprises the following steps: S10, placing an aircraft model in a wind tunnel test section, and arranging a plurality of cameras at the tops of two sides of the aircraft model and outside the wind tunnel test section; S20, calibrating the plurality of cameras at the same time; S30, establishing a world coordinate system and a body axis coordinate system; S40, setting a plurality of mark points on the aircraft model, and obtaining position information of the plurality of mark points in the world coordinate system; and S50, calculating an attitude angle and an airflow angle of the aircraft model according to the position information of the plurality of mark points in the body axis coordinate system. The attitude measurement method provided by the invention can be suitable for research of horizontal free flight of different models of aircrafts in the wind tunnel, has good versatility, is simple to use and operate, can be popularized to other low-speed wind tunnels, and has good engineering application prospects.

Description

technical field [0001] The invention relates to the field of wind tunnel tests, in particular to a method for measuring the attitude of a low-speed wind tunnel horizontal free-flying model. Background technique [0002] When performing horizontal free flight tests in low-speed wind tunnels, it is usually necessary to obtain the attitude angle of the aircraft model in real time ( Ψ , θ , φ ), airflow angle ( α , β ) and other relevant information, which are used for the feedback of the flight control system or the recording of flight history parameters. [0003] In the prior art, the low-speed wind tunnel model free flight test generally obtains three attitude angles ( Ψ , θ , φ ), through the wind vane sensor installed on the head of the aircraft to achieve the angle of attack α , sideslip angle β Isogas flow angle measurement. Among them, the disadvantages of using the attitude reference system are mainly as follows: placing it inside the aircraft increases th...

AI Technical Summary

Problems solved by technology

Among them, the disadvantages of using the attitude reference system are mainly as follows: placing it inside the aircraft increases the difficulty of model design and inertia trimming; when the aircraft moves violently, the output of the attitude reference system will jump

The use of wind vane sensors has the following disadvantages: it cannot be used below a certain wind speed or the measurement error is too large; the wind vane measurement results are obviously affected by wind speed, aircraft angle of attack and sideslip angle, and the installation position of the wind vane, resulting in the need for a large number of calibrations before use. Work; the measurement range is limited and cannot be used for high angle of attack flight; the large volume will destroy the surface flow field of the aircraft model, increasing the difficulty of system identification and modeling

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