Distributed propelling tail-mounted vertical take-off and landing fixed wing aircraft

Abstract

The invention discloses a distributed propelling tail-mounted vertical take-off and landing fixed wing aircraft which comprises a fuselage, wings, a vertical tail wing, a landing gear, an elevon, a rudder, an internal combustion engine propulsion system, an electric propulsion system, a fuel oil tank, a battery pack and a flight controller. According to needs of cruising power, an internal combustion engine is selected, insufficient thrust and power during vertical take-off and landing are provided by the electric propulsion system, by the propulsion system collocation, the problem of great power differences of vertical take-off and landing and cruising of a vertical take-off and landing aircraft can be solved, and the problem of insufficient control ability of a tail-mounted aircraft in the vertical takeoff and landing process can be solved by distributed propulsion of a plurality of propulsion systems. The distributed propelling tail-mounted vertical take-off and landing fixed wing aircraft has the advantages of high push / heavy ratio, high energy utilization rate and strong control ability and the like.

Description

technical field [0001] The invention belongs to the technical field of aircraft design. Background technique [0002] The propulsion system is a key part of a vertical take-off and landing fixed-wing aircraft. Usually, medium and large vertical take-off and landing fixed-wing aircraft use internal combustion engines such as turboshaft engines as the propulsion system, and small vertical take-off and landing fixed-wing aircraft use motors and batteries as the propulsion system. The number generally does not exceed two. In the vertical take-off and vertical landing stages, the vertical take-off and landing fixed-wing aircraft requires the thrust of the propulsion system to exceed the gravity of the aircraft, so the power demand of the propulsion system is relatively large; Thrust is mainly used to overcome flight resistance. Since fixed-wing aircraft have a large lift-to-drag ratio (usually more than 5), the power required for the propulsion system during cruise flight is sma...

AI Technical Summary

Problems solved by technology

The internal combustion engine has a relatively small power and weight, and high-power internal combustion will bring a weight penalty; the electric propulsion system can run at super-rated power for a short time, and the power and weight are relatively high, but the energy density of the battery is low, and the range of the aircraft using electric propulsion is limited

Images