A vertical take-off and landing fixed-wing aircraft that

Abstract

The invention discloses a vertical take-off and landing fixed wing aircraft which comprises a body, a left wing and a right wing arranged on the body, wherein a rotary shaft is integrally mounted on the left wing and the right wing, the rotary shaft runs through the whole body transversely, a ring gear is fixedly mounted on the outer surface of the rotary shaft located at the body part, and the gear is controlled to rotate by a pneumatic rotating device; a tilting mechanism is arranged at the joint of the left wing and the right wing of the machine and the body; a plurality of propeller powerdevices are respectively symmetrically arranged at the rear ends of the left wing and the right wing of the aircraft; a plurality of aerodynamic devices are symmetrically arranged on the front and rear sides of the upper surfaces of the left wing and the right wing of the aircraft. At that same time, the aircraft has the advantage of simple structure, good maintainability and low cost, and has very broad application prospects. The invention can not only take off and land vertically and hover at a fixed point like a helicopter, but also has the high-speed cruising capability of a jet fixed-wingaircraft.

Description

technical field [0001] The invention relates to the technical field of aircraft, and more specifically relates to a fixed-wing aircraft capable of vertical lift. Background technique [0002] Since fixed-wing aircraft need a certain time and distance to take off and land, there are certain requirements for the takeoff and landing site. However, building landing sites is expensive, time-consuming, and easily destroyed during wartime. Therefore, people hope to have a kind of aviation vehicle that can take off and land in narrow space always for a long time. The birth of the helicopter satisfies this need of people. The rotor of a helicopter is both a lifting surface and a control surface, which enables the helicopter to take off and land vertically and hover at a fixed point. But just as the structural form of the fixed-wing aircraft determines its shortcomings in take-off and landing, the structural form of the helicopter also determines its shortcomings in some aspects, s...

AI Technical Summary

Problems solved by technology

But just as the structural form of the fixed-wing aircraft determines its shortcomings in take-off and landing, the structural form of the helicopter also determines its shortcomings in some aspects, such as: large empty weight coefficient, small load coefficient, and large cruising power-to-weight ratio , the aerodynamic efficiency is low, so the economy is poor; the structure is complex and fragile but expensive; the vibration is large and the stability is not good; due to the airflow asymmetry of the rotor in the forward flight working environment, the maximum forward flight speed of the helicopter is affected by the compressibility of the forward blades And the limitation of the airflow separation of the backward blades, the maximum cruising speed of conventional helicopters is usually around 300 km / h

Images