A vertical take-off and landing tilt-rotor fixed-wing aircraft

Abstract

The invention relates to a tilt-rotor fixed wing aircraft with a vertical take-off and landing function. The tilt-rotor fixed wing aircraft comprises an aircraft body, wings and a tail, wherein the wings and the tail are mounted on the aircraft body. Pitching and tilting power devices are arranged on the left side and the right side of the aircraft body. A front landing gear and a main landing gear are arranged at the bottom of the aircraft body. An equipment hatch is arranged on the upper portion of the aircraft body, and an aviation telemetering camera is arranged in an equipment cabin. A control cabin hatch is arranged on the upper portion of the aircraft body, and a control device is arranged in a control cabin. A reverse-torsional balance power device is arranged on the rear portion of the aircraft body. The wings are mounted on the two sides of the aircraft body and provided with wing control planes. The tail is connected with the aircraft body through tail supporting rods and comprises a horizontal tail, a pitching control plane, a vertical tail and a yaw control plane. The tilt-rotor fixed wing aircraft has the advantages that the vertical take-off and landing, tilting and level flight of the aircraft can be achieved through one power system, take-off and landing of an unmanned aerial vehicle are not limited by fields, the structural weight can be better reduced, the aircraft can fly more stably, the flying time is longer, operation is simpler, and the flying process is more intelligent.

Description

Technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a vertical take-off and landing tilt-rotor fixed-wing aircraft. Background technique [0002] Among the fixed-wing UAVs in the prior art, generally only the functions of taxi take-off, catapult take-off, and hybrid vertical take-off and landing are available. The take-off and landing of the aircraft will be affected by the environment and the environment, resulting in a reduction in the strength and life of the aircraft. Too much is too complicated, the weight of the aircraft structure is too much, and the cruise radius of the aircraft will be shortened. Summary of the invention [0003] The purpose of the present invention is to provide a vertical take-off and landing tilt-rotor fixed-wing aircraft in view of the deficiencies in the prior art, so that the aircraft can achieve vertical take-off and landing functions. [0004] In order to achieve the above objectives, th...

AI Technical Summary

Problems solved by technology

[0002] In the fixed-wing unmanned aerial vehicles in the prior art, generally only taxi takeoff, catapult takeoff, and hybrid vertical takeoff and landing functions can be used, which will cause the takeoff and landing of the aircraft to be affected by the environment, resulting in a reduction in the strength and life of the aircraft. Too many are too complicated, the aircraft structure wastes too much weight, and the cruising radius of the aircraft will be shortened accordingly

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