Ducted aircraft control structure and control method thereof

Abstract

The invention discloses a ducted aircraft control structure. The ducted aircraft control structure comprises propellers, reverse twisting blades and control surfaces which are arranged in a duct from top to bottom; the engine drives the propeller to provide main lift force, the rotating shaft of the propeller is an airframe Z axis, and the main lift force direction coincides with the airframe Z axis all the time; the reverse twisting blades are fixed to the duct, cannot rotate and are mainly used for balancing pneumatic torque which is generated by the blades in the rotating process and are opposite to the rotating direction; the control surfaces comprise four groups of pneumatic control surfaces, namely a first control surface, a second control surface, a third control surface and a fourth control surface; and the four groups of pneumatic control surfaces are uniformly distributed in the horizontal plane, each group of pneumatic control surfaces is independently controlled by one motor, and each group of pneumatic control surfaces can independently control the attitude, so that various torques required by the aircraft are provided. According to a ducted aircraft control method, the aircraft is controlled in the form of reverse twisting blades and four groups of pneumatic control surfaces, and the control flexibility of the aircraft is remarkably improved.

Description

technical field [0001] The invention relates to the field of ducted aircraft, in particular to a ducted aircraft control structure and a control method thereof. Background technique [0002] Ducted aircraft are widely used in aircraft power systems because of their high safety and the fact that ducts can ensure that the propellers in the ducts provide thrust at relatively high speeds. Compared with the traditional ducted UAV, the single ducted aircraft has higher control flexibility while reducing the radial space of the aircraft. [0003] The flight control system is the key function bearing system of the aircraft, and its reliability is directly related to the flight reliability and safety reliability of the aircraft. At present, there are serious problems in the safe use of civilian UAVs, low-level duplication of core systems such as flight control, and narrow application fields of conventional multi-rotor configurations. Therefore, how to provide a ducted aircraft cont...

AI Technical Summary

Problems solved by technology

At present, there are problems such as prominent problems in the safe use of civilian UAVs, low-level duplication of core systems such as flight control, and narrow application fields of conventional multi-rotor configurations.

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