Vertical take-off and landing aircraft

Abstract

The invention relates to a vertical take-off and landing aircraft with an attitude controller. The aircraft consists of a fuselage (6), two main thrust devices (7) which provide main thrust for the aircraft, and the attitude controller, wherein the attitude controller comprises a power module, attitude adjusting units (2), motors, speed regulator units and a flight control system; the aircraft adopts a double-main-wing structure, wherein the attitude adjusting units are separately connected to the left end of the first main wing (8a), the right end of the first main wing (8a), the left end of the second main wing (8b), and the right end of the second main wing (8b); the attitude adjusting units are ducted fans; the two main thrust devices are separately connected to the left side and the right side of the middle segment of the fuselage in a symmetrical manner, and the ducted fans are adopted; the air outlet of each duct is provided with a control surface; the main thrust device and the attitude adjusting units tilt towards the front of the aircraft; therefore, conventional complex mechanical components can be omitted, and the mechanical structure of the aircraft is simplified; the attitude controller and the main thrust devices are separated, so that the type of an engine adopted by the aircraft, and the types of thrust devices adopted by the aircraft, are not limited.

Description

technical field [0001] The invention relates to an aircraft, in particular to a vertical take-off and landing aircraft with an attitude control device. Background technique [0002] At present, the common vertical take-off and landing aircrafts include helicopters, tilt-rotor aircraft and vertical take-off and landing jet aircrafts. Vertical take-off and landing aircrafts need to rely on the attitude control device to maintain the balance of the aircraft when realizing vertical take-off and landing, and need to rely on the attitude control device to maintain the balance of the aircraft. Realize the control of the flight attitude of the aircraft in level, roll, pitch, and yaw, and realize the vertical take-off and landing, vertical and horizontal flight of the aircraft; the attitude control device refers to the device that controls the flight attitude of the aircraft. [0003] Conventional helicopters are fitted with autotilts, which consist of two main parts: a non-rotating ...

AI Technical Summary

Problems solved by technology

Because the attitude control device used for vertical take-off and landing jet aircraft also uses complex mechanical parts, especially the rotatable nozzle, which not only requires high materials for making, but also is difficult to produce, so the cost of production and maintenance is increased; and This type of attitude control device is only applicable to aircraft that use vectoring nozzles or lift engines or even lift fans connected to engine

Images