Sickle wing vertical take-off and landing aircraft

Abstract

The invention provides a sickle wing vertical take-off and landing aircraft which is of an upper single-wing structure. The wing comprises a wing root part and a wing tip part, the front edge of the wing root part is integrally straight, the rear edge of the wing root part is in a convex triangle shape, and the front edge part is provided with a separated tiltable wing surface, a power system anda rotor wing are mounted on the wing surface, the front edge and the rear edge of the wing tip part are both inclined and swept forward integrally relative to the wing root part. The sickle wing vertical take-off and landing aircraft has the advantages of being high in hovering efficiency, good in stability and high in level flight efficiency.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a sickle-wing vertical take-off and landing aircraft. Background technique [0002] In recent years, the requirements for transportation vehicles in terms of environmental protection, low carbon and low noise have become higher and higher, and urban electric vertical take-off and landing aircraft have become more and more popular. In order to cancel the traditional way of pilots flying aircraft and realize the purpose of unmanned flight, many companies and research institutes have made great efforts in their flight control research, mobile phone connection to the Internet, satellite navigation, route planning, capital payment and other aspects have to be developed A set of software systems, but some relatively traditional layouts are still used in the vertical take-off and landing layout and structural optimization design of the aircraft itself, which has not played a positive r...

AI Technical Summary

Problems solved by technology

[0004] Among them, the main feature of the wingtip power tilting layout is that the power system is installed at the wingtips on both sides for tilting and vertical take-off and landing. and turbulence; while the entire wing tilting layout is to tilt the entire wing, this aircraft has high level flight efficiency and hovering efficiency, but the defect is that the huge vertical wing is like a door panel in the hovering state, slightly A little crosswind will affect the attitude of the entire aircraft, which is difficult to control, and the aircraft with this layout needs a lot of tilting propulsion, which is not good for the weight of the whole aircraft; the combined layout of rotor and fixed wing has become more popular in recent years, but It has the defect that there is a lot of waste in the level flight state; the tail seat layout means that the tail is used as the landing gear to support the aircraft. When the aircraft is stopped, the aircraft will always remain upright, like a rocket. The defect of this layout is that it is difficult for the pilot to board and disembark. , and the shutdown state is easily affected by crosswinds; the defect of the rear three-point rotor layout is that the tilt axis is too far away from the aerodynamic pressure (lift) force line. At this time, the center of gravity of the aircraft is close to its aerodynamic center, so another rotor must be installed behind the fuselage. Balance the center of gravity, otherwise the center of gravity in the hovering state is too far away from the tilt axis, which is very dangerous, so a fan must be installed at the tail to balance the pitch, but the extra fan at the tail is a waste mass in level flight; the front and rear multi-point power layout aircraft is in level flight Some or all of the power must be tilted forward. If some of the motors are tilted, the other motors will become wind resistance for level flight. Problems such as too many rotating drive mechanisms will inevitably affect the efficiency of level flight; and the disadvantage of pure rotor layout is that the efficiency of level flight is low

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