Rear single-ducted fan type composite wing manned aircraft with non-thrust composite auxiliary wings

Abstract

The invention discloses a composite lift aircraft with an extended platform. The composite lift aircraft is composed of a rear single-ducted fan type composite wing aircraft body, non-thrust self-energy-supply composite auxiliary wings assembled on the two sides of the rear single-ducted fan type composite wing aircraft body, and a manned bin. The rear single-ducted fan type composite wing aircraft body comprises a fuselage, composite lift wings fixedly mounted on the two sides of the fuselage, and a propeller thruster. The fuselage is arranged as a deck platform; the composite lift wings areinternally provided with self-closed ducted fans, and wing hinges are designed on the outer sides of the composite lift wings; and self-closed ducted fans are arranged inside the non-thrust self-energy-supply composite auxiliary wings, and one sides or the two sides of the non-thrust self-energy-supply composite auxiliary wings are provided with electro-hydraulic gas connectors and wing hinges, and movably connected with the composite lift wings through the wing hinges. The manned bin is mounted on the lower portion of the fuselage. The composite lift aircraft has the characteristics that thetakeoff and landing distance is short, the flight speed is high, the wings are high in structural strength and can store energy, flight energy consumption is low, and the hang time is long; and the large-area composite lift wings can achieve the effect of a glider under the emergency situation, the safety of the aircraft is greatly improved, and the safety of personnel and materials is guaranteed.

Description

technical field [0001] The invention relates to an aircraft, in particular to a rear single-duct fan-type composite wing manned aircraft with a non-push composite auxiliary wing, which 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 the disadvant...

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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