Rear single-propeller type composite wing aircraft with twin-duct composite ailerons and additional wings

Abstract

The invention discloses a rear single-propeller type composite wing aircraft with twin-duct composite ailerons and additional wings. The rear single-propeller type composite wing aircraft comprises anaircraft body, composite lifting ailerons which are fixed on two sides of the aircraft body as well as duct fan propellers, wherein self-closed duct fans are arranged in the composite lifting ailerons; aileron hinges are designed on the outer sides of the composite lifting ailerons; the duct fan propeller is arranged at the front end of each propeller thrust self-energy supplied composite aileron; self-closed duct fans are arranged inside the propeller thrust self-energy supplied composite ailerons; an electro-hydraulic and pneumatic interface and an aileron hinge are arranged on two sides ofeach propeller thrust self-energy supplied composite aileron; each propeller thrust self-energy supplied composite aileron is movably connected with the corresponding composite lifting aileron by theaileron hinge on one side; a cargo warehouse is arranged at the bottom of the aircraft body. The rear single-propeller type composite wing aircraft disclosed by the invention has the characteristicsof short take-off and landing distance, high flight speed, high structural strength of the ailerons, capability of storing energy by the ailerons, low flight energy consumption, long hang time, high safety and the like; the additional wing adopts composite lifting, so as to ensure application range of power.

Description

technical field [0001] The invention relates to an aircraft, in particular to a rear single-blade compound-wing cargo aircraft with a double-duct compound auxiliary wing and an additional wing, and belongs to the technical field of aircraft equipment. Background technique [0002] Existing aircraft are mainly divided into two categories: fixed-wing and vertical take-off and landing aircraft (such as helicopters and multi-rotors). Of course, there is also a vertical take-off and landing fixed-wing product. The traditional fixed wing has the advantages of fast flight speed, low energy consumption, etc., but it has the disadvantages that the main wing and the horizontal tail are not connected front and rear, the wing structure is not strong, easy to be damaged, the take-off and landing requirements are high, and the take-off and landing distance is long; the traditional vertical The take-off and landing aircraft has the advantages of convenient take-off and landing, but has th...

AI Technical Summary

Problems solved by technology

The traditional fixed wing has the advantages of fast flight speed, low energy consumption, etc., but it has the disadvantages that the main wing and the horizontal tail are not connected front and rear, the wing structure is not strong, easy to be damaged, the take-off and landing requirements are high, and the take-off and landing distance is long; the traditional vertical The take-off and landing aircraft has the advantages of convenient take-off and landing, but has the disadvantages of high energy consumption, low safety factor, poor load capacity, slow horizontal flight speed, and easy crash; although the current vertical take-off and landing fixed wing has the characteristics of convenient take-off and landing , but the controllability is not ideal when flying horizontally, and there are disadvantages such as large flight resistance, high energy consumption, and low safety factor.

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