Canard tail seat type unmanned aerial vehicle

Abstract

The invention discloses a canard tail seat type unmanned aerial vehicle. The unmanned aerial vehicle comprises a fuselage, wings, canards, a power assembly and aileron assemblies. Each aileron assembly comprises an aileron, a cicada wing, a second driving assembly and a third driving assembly, the two aileron assemblies are connected with the two wings respectively, for any pair of aileron assembly and wing, one end of the aileron is rotationally connected with the rear edge of the wing, the second driving assembly is used for driving the aileron to swing, the cicada wings are in sliding connection with the aileron, the third driving assembly is used for driving the cicada wings overlapped with the aileron to extend out of the rear edge of the aileron, and the third driving assembly is further used for driving the cicada wings to retract to the position overlapped with the aileron from the rear edge of the aileron. The canard tail seat type unmanned aerial vehicle can provide larger steering effect in the vertical take-off and landing state, the unnecessary lift force is offset, and meanwhile the steering effect in the level flight cruise state is not affected.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a canard tail seat type unmanned aerial vehicle. Background technique [0002] At present, drones are beginning to play a role in more and more fields, such as logistics transportation, terrain surveying and mapping, agricultural plant protection, etc. However, UAVs have not been used on a large scale in these fields. The reason is that neither traditional fixed-wing UAVs nor multi-rotor UAVs can fully meet the application requirements of these scenarios. These fields have many commonalities in the requirements for drones, such as the need to carry heavy cargo or surveying and mapping instruments, the need for sufficient flight time, and the need to adapt to various complex terrains. Fixed-wing UAVs have the advantages of fast flight speed, large load, long-distance control, high flight altitude and long endurance, but they have the disadvantages of needing a ru...

AI Technical Summary

Problems solved by technology

The rudder effect of the canard tail seat UAV is sufficient in the level-flight cruising state, but the distance between the center of gravity and the center of action of the rudder surface is short, that is, the force arm of the rudder surface is short, which leads to the UAV's vertical takeoff and landing. Insufficient rudder effect, unstable take-off and landing

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