Canard flying wing aerodynamic layout unmanned aerial vehicle

Abstract

The invention discloses a canard flying wing aerodynamic layout unmanned aerial vehicle, and the unmanned aerial vehicle comprises main wings, full-motion canard wings, a full-motion vertical tail wing and a vehicle body, and the flying performance of a fixed wing aircraft is well improved by fusing flying wing aerodynamic layout and canard aerodynamic layout. The main wings adopt flying wing structures, so that the structural mass can be reduced, the effective lift area is increased, and the immersion area is reduced. The full-motion canard is added in front of the main wing, so that the pitching control range of the unmanned aerial vehicle is widened, and meanwhile, the maximum lift coefficient of the flying wing is increased. Compared with the performances of a conventional aerodynamiclayout fixed-wing unmanned aerial vehicle, the lifting force is improved by about 13.3%, the effective load is improved by about 8.6%, the unmanned aerial vehicle has outstanding performance in the aspect of low speed, the minimum flight speed can be reduced to 6 m / s, and the flight speed is reduced by about 37% compared with a single-flying-wing type aerodynamic layout unmanned aerial vehicle. Compared with a single-flying-wing type aerodynamic layout unmanned aerial vehicle, a pair of canard wings is additionally arranged on the structure, so that the lift-drag ratio of the unmanned aerial vehicle is reduced by about 5.25%.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a canard flying wing aerodynamic layout unmanned aerial vehicle. Background technique [0002] At present, fixed-wing aircraft has a conventional layout, a tailless layout, and a three-wing layout, etc., which mainly generate relative motion between the aircraft and the air, and use the air pressure difference between the upper and lower surfaces of the wings to generate lift to enable the aircraft to fly. Conventional layout aircraft has higher stability, higher controllability, and more convenient maintenance, but it has problems such as large resistance and heavy structural quality; flying wing layout has many advantages in terms of structural quality and flight performance, but Pitch control is its fatal pain point; although the canard layout has a larger pitch operation range, a larger stall controllable range, smaller trim resistance, and greater lift when ...

AI Technical Summary

Problems solved by technology

Conventional layout aircraft has higher stability, higher controllability, and more convenient maintenance, but it has problems such as large resistance and heavy structural quality; flying wing layout has many advantages in terms of structural quality and flight performance, but Pitch control is its fatal pain point; although the canard layout has a larger pitch operation range, a larger stall controllable range, smaller trim resistance, and greater lift when flying at high angles of attack and level flight, but At the same time, there are also shortcomings such as complex structure and high flight speed.

[0003] In short, there are still deficiencies in structural quality, controllable range, and task load in the existing fixed-wing UAV-related technologies that need to be resolved urgently

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