Wind tunnel test unmanned aerial vehicle attack angle automatic adjusting system
An automatic adjustment and wind tunnel test technology, which is used in motor vehicles, aerodynamic tests, unmanned aerial vehicles, etc., can solve problems such as large errors and low efficiency, achieve simple structure, simplify test procedures, and improve measurement accuracy and efficiency effects
Pending Publication Date: 2021-02-12
南京禾谱航空科技有限公司
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Problems solved by technology
[0004] The invention aims to solve the problems of large errors and low efficiency in the measurement of the angle of attack of the existing wind tunnel test, and proposes an automatic adjustment system for the angle of attack of the drone
Method used
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Embodiment Construction
[0011] The base 13 is welded by triangle iron, which improves the strength of the base and the stability of the system. The lead screw 3 and the base 13 are fixed together by bolts, and form a triangular layout with the base 13, which enhances the pitching stability of the lead screw 3 . The stepping motor 1 is installed on the top of the leading screw, and is connected with the leading screw 3 through the motor controller 2 .
[0012] The angle regulator 8 is fixed on the lead screw slider 14 by bolts, and the height is adjusted as the lead screw slider 14 moves up and down, and the height is fixed by the positioning bracket 4 . A section of the positioning bracket 4 is bolted to the chute 10, the chute 10 is on both sides of the lead screw 3, and the other end is hinged on the aircraft strut 6 through a pin, the positioning bracket 4, the aircraft strut 6 and the lead screw 3 form a triangle The stable structure achieves the purpose of fixed height and stable angle. One en...
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The invention discloses a wind tunnel test unmanned aerial vehicle attack angle automatic adjusting system. The automatic adjusting system comprises a stepping motor, a motor controller, a lead screw,a positioning support, an aircraft supporting rod, an angle adjusting sliding block, an angle adjuster, a sliding groove, a control box, a lead screw sliding block and a base. The lead screw slidingblock is installed on the lead screw, and the lead screw is installed on the motor controller and connected with the stepping motor. The unmanned aerial vehicle is fixed to the aircraft supporting rod, the aircraft supporting rod is installed on the angle adjusting sliding block, the angle adjusting sliding block is hinged to the angle adjuster, and the angle adjuster is fixed to the lead screw sliding block. The front end of the positioning support is hinged to the aircraft supporting rod, and the rear end of the positioning support is connected with the sliding groove; the base is fixed to the lower end of the sliding rail; and the control box is fixed to the back of the sliding rail and internally provided with a power source, a single-chip microcomputer and a touchpad. The attack angleis adjusted under the action of the airplane supporting rod, the angle adjusting sliding block and the angle adjuster; the movement distance of the lead screw sliding block is calculated through thesingle-chip microcomputer, and the stepping motor is controlled to make the gravity center of the unmanned aerial vehicle located in the wind field middle section.
Description
technical field [0001] The invention relates to the technical field of wind tunnel test measurement, in particular to an automatic adjustment system for the angle of attack of an unmanned aerial vehicle. Background technique [0002] Aerodynamics is currently one of the most active and promising disciplines in the world of science, and wind tunnel testing is the most effective measure in the field of aerodynamics research. In the process of developing various aircraft, missiles and other aircraft, the wind tunnel is an indispensable experimental facility. In the wind tunnel, the airflow required for the experiment can be artificially generated and controlled, and the airflow state around the aircraft during flight can be simulated, and the effect of the airflow on the aircraft can also be quantitatively observed. By observing the physical phenomena in the wind tunnel, the aerodynamic characteristics of the aircraft can be studied accordingly. Therefore, the wind tunnel test...
Claims
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Patent Timeline
Login to View More IPC IPC(8): G01M9/02G01M9/04B64F5/60
CPCG01M9/02G01M9/04B64F5/60B64U10/00
Inventor 刘文帅姚小敏韩文霆
Owner 南京禾谱航空科技有限公司