Sweepback-variable and short-takeoff and landing fixed-wing aircraft

Abstract

The invention discloses a sweepback-variable and short-takeoff and landing fixed-wing aircraft. The aircraft adopts a double-engine wing layout according to which wing bodies are fused with a small aspect ratio; an engine for driving a corresponding large-diameter propeller is arranged on each of the two sides of the front part of a fuselage, so that most of the surface of the whole aircraft, and control surfaces of vertical tails and elevons on the back side are in the high-speed propeller slipstream, and wings on the two sides can be forwardly and outwardly unfolded or backwardly and inwardly folded synchronously; when the wings are backwardly folded, the wings are completely adhered to the fuselage, the whole aircraft has a cambered streamline aerodynamic outer shape, the lifting area is large, and the flight resistance is reduced; when the wings are opened, the wingspan of the aircraft is greatly increased, so that the cruising economy of the aircraft is greatly improved. Through reasonable matching of the propellers, wing body lifting bodies and variable sweepback wings, the aircraft has short takeoff and landing, high maneuverability and high cruising economy; through optimization on junctions of the wing bodies, the aircraft has relatively small flight resistance when the wing bodies are in unfolded and folded states.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to a variable-sweep short take-off and landing fixed-wing aircraft. Background technique [0002] Fixed-wing aircraft have always been limited by the need for large high-quality take-off and landing sites. In order to reduce the dependence on take-off and landing sites, developed countries in the world have developed various vertical take-off and landing drones. [0003] The twin-engine pancake-shaped aircraft can still maintain a large lift coefficient at a high angle of attack without stalling, so the aircraft can take off at a large angle of attack greater than 20 degrees, thereby shortening the take-off / landing distance. The speed is still stable and controllable above the speed. Even when the thrust-to-weight ratio of the aircraft is greater than 1, the aircraft can take off and land vertically and hover in the air. The distance between the two engines of the twin-engine pancak...

AI Technical Summary

Problems solved by technology

The disadvantage is that the lift-drag ratio of the aircraft is low, the cruising economy is poor, and the flight envelope of the aircraft is narrow.

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