Load reducing and high lift device applied to unmanned aerial vehicle

Abstract

The invention relates to a load reducing and high lift device applied to an unmanned aerial vehicle. The device includes: an electric ducted fan, an electronic speed controller and a power supply unit, wherein the electric ducted fan is installed nearby the gravity center of the unmanned aerial vehicle. A flight controller is arranged on the unmanned aerial vehicle. The flight controller, the electronic speed controller and the electric ducted fan are successively connected. The electronic speed controller is connected to the power supply unit. During takeoff and landing of the unmanned aerialvehicle, the flight controller controls the electronic speed controller to output power quantity to the electric ducted fan; then the electric ducted fan generates lifting force according to the power quantity. During the takeoff and landing of the unmanned aerial vehicle, the flight controller controls the electronic speed controller to output power quantity to the electric ducted fan; then theelectric ducted fan generates lifting force according to the power quantity, so that a part of self weight of the UAV is reduced and wing load is reduced; as a result, flight speed can be reduced thanthat in regular flight, thus achieving low-speed short-distance safe takeoff and landing.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a load-reducing and lifting-increasing device applied to unmanned aerial vehicles. Background technique [0002] As we all know, the current fixed-wing unmanned aircraft with conventional layout needs a long runway to support take-off and landing. Only a longer runway can accumulate enough take-off speed to meet the initial speed of take-off; landing also requires a larger glide speed and a longer ground taxiing length. Without long runways, fixed-wing aircraft cannot take off and land. In response to this problem, there are currently several solutions in the field of drones: [0003] 1. Fixed-wing vertical take-off and landing technology, such as XFV-1, is the simplest and rude design of a fixed-wing that can be erected, straight up and down without stunts. [0004] 2. Vertical take-off and landing fixed-wing technology, use the four-rotor mode (four propelle...

AI Technical Summary

Problems solved by technology

[0006] 4. A fixed-wing aircraft with a conventional layout needs to roll until the lift is equal to or greater than the speed of gravity before it can take off and climb. When landing, open the flaps and slide down. It cannot fly and touch down at a speed lower than the set critical stall speed.

However, this tilting system is very complicated, which puts forward high requirements on the precision of mechanical conversion and the difficulty of flight control control. It is difficult to guarantee the failure rate. Once the mechanism fails, it will cause the risk of crashing, and it will increase the difficulty of daily maintenance and maintenance.

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