Structure arrangement method of well-shaped reaction torque rudder

Abstract

The invention belongs to the field of aircraft structure design, and in particular relates to a structural layout method of an anti-torque rudder. The invention provides a layout method of an anti-torque rudder, which can be applied to small ducted unmanned aerial vehicles; it is based on a well-shaped anti-torque rudder, by determining the airfoil of the anti-torque rudder and simulating the aerodynamic layout of the anti-torque rudder , the design of the distance between anti-torque rudder and propeller disk, the design of the combination mode of combined rudder and the structural design of anti-torque rudder, the structural layout method of the well-shaped anti-torque rudder is obtained; through theoretical and experimental demonstration, this method can be used to design more conveniently The anti-torque rudder with reasonable structure and practical application is produced.

Description

technical field [0001] The invention belongs to the field of aircraft structure design, and in particular relates to a structural layout method of an anti-torque rudder. Background technique [0002] The thrust provided by the engine of the small single-blade ducted UAV realizes flight actions such as vertical take-off and hovering. At the same time, the rotation of the rotor also generates a torque around the central axis of the vertical aircraft, which will seriously affect the stability of the UAV. and reliability. [0003] Single-propeller fixed-wing aircraft overcome the influence of propeller spin by shifting the center of gravity or adjusting the thrust line of the engine, and single-rotor helicopters use the tail rotor to balance the torque generated by the main propeller. Due to its own structural characteristics, small single-blade ducted UAVs usually use a set of anti-torque rudders to achieve torque balance. Deflection in the same direction, under the action of...

AI Technical Summary

Problems solved by technology

[0004] At present, the layout of small ducted UAV anti-torque rudders has not yet formed a unified scheme and overall design ideas. Most of the research teams at home and abroad have not conducted detailed analysis and demonstration on the uniform distribution of anti-torque rudders. The influence of parameters such as the number of parallel rudder blades, the staggered angle of rudder blades, and the distance between parallel rudder blades on its overall aerodynamic characteristics has not yet been clearly analyzed.

As a result, most of the current layouts of ducted UAV anti-torque rudders cannot make full use of their aerodynamic characteristics, and cannot fully improve the overall aerodynamic characteristics and stability of UAVs.

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