Tailstock type vertical take-off and landing unmanned aerial vehicle

Abstract

The invention discloses a tailstock type vertical take-off and landing unmanned aerial vehicle which comprises a vehicle body and wing assemblies. The wing assembly comprises three rotors, two of the rotors are symmetrically arranged at the tail part of the fuselage, and the third rotor is arranged at the tail part of the fuselage and is located at the position of the symmetry plane of the other two rotors; one end of each rotor is connected with the fuselage, a motor cabin is arranged at the other end of each rotor, a motor is arranged in each motor cabin, and propellers in transmission connection with the motors are arranged on the motor cabins; an air sliding flow rudder is arranged at the bottom of the end, close to the motor cabin, of each rotor wing, each air sliding flow rudder has a rotating stroke in the thickness direction of the rotor wing, and a steering engine in transmission connection with the air sliding flow rudder is arranged in each rotor wing. A complex blade pitch changing device and an automatic inclinator are omitted, an air sliding flow rudder is designed, the stability of the posture of an aircraft body is controlled through propeller sliding flow, the complexity of an aircraft control system is reduced, the cost is reduced, meanwhile, in the vertical take-off and landing state, lift losses generated by wings to propeller airflow are reduced, and the power output efficiency is improved.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a tail-sitting vertical take-off and landing unmanned aerial vehicle. Background technique [0002] The precise definition of a vertical take-off and landing vehicle (VTOL) is: it can take off / land at zero speed, has the ability to hover, and can fly horizontally in the way of a fixed-wing aircraft. [0003] In the aviation field in the 21st century, when fixed-wing aircraft have vertical take-off and landing capabilities, it will bring great benefits to applications in various industries. This type of fixed-wing aircraft is different from traditional taxi take-off and landing or catapult take-off aircraft. It does not require special airports and runways, nor does it need complicated ejection devices. It only needs a small flat ground to take off and land, so this This type of aircraft has very low requirements on the takeoff and landing environment, and can ta...

AI Technical Summary

Problems solved by technology

However, the V-22 Osprey uses two helicopter rotors. In the vertical take-off and landing mode, the rotors need an automatic tilter to control the stability of the attitude of the aircraft, which increases the difficulty of control, and the blades use a periodic pitch change device, which makes the mechanism extremely complicated. , which also increases the cost; and when the V-22 Osprey is in the vertical take-off and landing mode, the rotor slipstream blows on the wing surface, causing a large loss of lift, and forcing the wing to increase the structural strength, which in turn leads to the structural weight of the aircraft. increase, decrease aircraft performance

[0008] In recent years, there have also been some studies on vertical take-off and landing aircraft, but basically they all have relatively obvious problems, such as a tailless layout single person disclosed in patent CN103287576A Tail-sitting vertical take-off and landing aircraft, the control stability of the two-rotor + elevon is not high, and the positive ambient wind speed is too high to exceed the control limit of the UAV, increasing the risk of crashing in the vertical take-off and landing state. At the same time, its When the flying wing layout is in level flight, the elevons must control the roll motion and the pitch motion at the same time. Coupled together, it is easy to exceed the stroke of the actuator, which limits the maneuverability of the UAV.

Another example is the tilting vertical take-off and landing aircraft disclosed in patent CN108482668A, which has too many tilting mechanisms, which increases the risk of the system and reduces reliability. Needs so much power, becomes redundant weight

Images