Flight control method of deformable unmanned aerial vehicle

Abstract

The invention provides a flight control method of a deformable unmanned aerial vehicle. The deformable unmanned aerial vehicle has a canard type telescopic forward-swept wing and single vertical fin aerodynamic arrangement; according to the adjustment and analysis of a root-locus method, a high-low speed deformable unmanned aerial vehicle can perform the adjustment on parameters of a controller through a design method of a low-speed controller, and therefore the design requirement on the controllers under two flight speeds can be met. Matching the deformation time and the control time of an engine is part of a control strategy of the deformable unmanned aerial vehicle; and as shown in the analysis of the flight mechanics design, the thrust of the engine is changed prior to implementing the process and the strategy under the deformation time.

Description

Technical field [0001] The invention provides a flight control method of a deformable unmanned aerial vehicle, which belongs to the field of controller design and control strategy in a flight control system, and is mainly applied to the deformation control of a deformable unmanned aerial vehicle. Background technique [0002] Transformable drones are the direction of development of a new generation of drones. Traditional aircraft adopt methods of changing the shape of the wing, such as changing the sweep angle and changing the camber of the airfoil, to adapt to different flight states such as take-off and landing, cruising and high-speed flight, and strive to obtain more ideal performance. However, this approach has complex mechanisms, limited functions, and low efficiency, and it is difficult to adapt to the requirements of a wider range of flight environment changes (such as speed, climate, altitude, etc.), resulting in limited application of traditional UAVs. The deforma...

AI Technical Summary

Problems solved by technology

[0003] In the prior art, the parameters of the deformed UAV are generally set according to the controller tuning method of the commonly used fixed-wing aircraft, which has certain limitations, because the dynamic characteristics of the aircraft itself have undergone a large change in the deformed state, and it is necessary to A more comprehensive investigation of the changes in various flight conditions faced by the controller can design a robust controller

At present, there is no control method for the UAV to continue to fly stably after the wings of the deformable UAV are stretched and deformed.

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