Vertical takeoff and landing unmanned aerial vehicle with foldable fixed wings based on dual-duct fan power system

Abstract

The invention discloses a vertical takeoff and landing unmanned aerial vehicle with foldable fixed wings based on a dual-duct fan power system. A dual-duct fan power system which is horizontally arranged at the tail of the body of the unmanned aerial vehicle in a tail-driving arrangement is adopted, so that lifting force for vertical takeoff and landing and thrust for horizontal flying are provided for an aircraft; a control surface which is arranged at the exit of each duct in a deflected manner is used for providing vector thrust, so that quick attitude change is realized; wings adopt a folding wing configuration, when the aircraft vertically takes off and lands / flies at a low speed, the wings are folded to decrease the frontal area of cross wind, and when the aircraft flies horizontally, the wings are unfolded to obtain large lifting force; and combined optimization of ducts and the wings is adopted, the wings are arranged in a specific duct air flow region, the duct suction generates a Coanda effect at a wing edge, so that the properties of the wings are improved. Multi-mold flight tasks such as vertical takeoff and landing, high-speed cruise, and the like of the aircraft are realized; the vertical takeoff and landing aircraft is high in aerodynamic efficiency during hanging in the air / flying at a low speed; and the vertical takeoff and landing unmanned aerial vehicle is high in anti-disturbance capacity during takeoff and landing / hanging in the air. The vertical takeoff and landing unmanned aerial vehicle is low in energy consumption, small in noise and high in safe reliability.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a foldable fixed-wing vertical take-off and landing unmanned aerial vehicle based on a dual-duct fan power system. Background technique [0002] Vertical take-off and landing aircraft has always been a hot spot in aeronautical engineering research. In recent years, due to the progress of materials, energy, power and control technology, many advanced schemes have been applied to vertical take-off and landing aircraft. At present, the main configuration designs of several types of carrier-based vertical take-off and landing aircraft mainly include: tilting power mechanism (including tilting wings, etc.), auxiliary vertical lift and tailstock structure. [0003] (1) Tilting rotor is currently the most typical vertical take-off and landing scheme. By rotating the rotor shaft, it can function as both a helicopter rotor and a fixed-wing propeller. The most typical aircraft is the Amer...

AI Technical Summary

Problems solved by technology

Its disadvantage is that it is difficult to control the flight state transition process, and it is greatly disturbed by wind

In addition, its power system needs to achieve a thrust-to-weight ratio of at least 1 or more, the radius of the propeller disc is large, the speed is high, and the aerodynamic resistance is large in level flight, so it is difficult to achieve a high cruising speed.

At the same time, the flying wing structure has a large windward area during the vertical take-off and landing and transition process, and is greatly disturbed by gusts.

[0006] Most of the existing vertical take-off and landing aircraft configurations are faced with the small aerodynamic effect of the operating wing surface during take-off and landing, so they are easily affected by unstable airflow, and the exposed large-size rotors will also be affected by gusts of wind (while the nose is installed It often affects the communication and sensing equipment of the electronic cabin); the tilting power mechanism is complex and vulnerable, the control stability is poor, and the auxiliary redundant power is low in efficiency, which is not suitable for the design of large load and long range

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