Foldable type combined wing freight aircraft with double-propeller-thrust combined auxiliary wings

Abstract

The invention relates to a foldable type combined wing freight aircraft with double-propeller-thrust combined auxiliary wings. A rear-thrust-free type combined wing aircraft of the foldable type combined wing freight aircraft comprises a machine body and combined lift force wings which are arranged on the two sides of the machine body in a foldable mode, wherein the machine body is set as a deck platform, self-sealed ducted fans are arranged in the combined lift force wings, and wing hinges are designed on the outer sides of the combined lift force wings. Propeller thrusters are arranged at the front ends of propeller-thrust self-power combined auxiliary wings, self-sealed ducted fans are arranged in the propeller-thrust self-power combined auxiliary wings, an electricity, liquid and gas connector and a wing hinge are arranged on one side or two sides of each propeller-thrust self-power combined auxiliary wing, the propeller-thrust self-power combined auxiliary wings are movably connected with the combined lift force wings through the wing hinges, and a freight cabin is arranged under the machine body. The foldable type combined wing freight aircraft disclosed by the invention hasthe characteristics of short rising and landing distance, quick flying speed, high wing structure strength, low flying energy consumption, long hang time, high safety and the like; the wings can be used for storing energy; the auxiliary wings utilize combined lift force, so that a power adaption range is ensured.

Description

technical field [0001] The invention relates to an aircraft, in particular to a foldable compound-wing cargo aircraft with double-propeller thrust and compound auxiliary wings, 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 disadvantages...

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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