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Mall unmanned aerial vehicle capable of taking off and landing vertically

A small unmanned aerial vehicle, vertical take-off and landing technology, applied in the field of aircraft, can solve the problem of slow horizontal flight speed of rotor unmanned aerial vehicles, and achieve the effect of simple structure, stable flight and convenient operation

Inactive Publication Date: 2018-12-18
苏桐 +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Rotor-wing drones rely on the rotation of the rotor to obtain lift. They do not need to have a horizontal flight speed (that is, a runway is required) for take-off. Rotor-wing drones can vertically lift, hover in the air, and fly forward, backward, left, and right. They have the advantages of diverse flight attitudes. Drones are slow to fly horizontally

Method used

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  • Mall unmanned aerial vehicle capable of taking off and landing vertically
  • Mall unmanned aerial vehicle capable of taking off and landing vertically
  • Mall unmanned aerial vehicle capable of taking off and landing vertically

Examples

Experimental program
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Embodiment Construction

[0016] Such as figure 1 As shown, a small UAV that can take off and land vertically includes a rotatable wing part I (1), a hinge I (2), a rudder angle I (3), a steering gear I (4), and a wing body I ( 5), Ducted Engine I (6), Ducted Air Inlet I (7), Fuselage Main Body (8), Ducted Air Inlet II (9), Ducted Engine II (10), Wing Main Body II (11), steering gear II (12), rudder angle II (13), hinge II (14), rotatable wing part II (15); the overall bottom surface of the UAV is flat, and the front edge of the body is curved upwards shape, the rear part of the fuselage is in a certain arc-shaped structure, the fuselage main body (8) is a hollow semicircular structure, and the ducted engine I (6) and ducted engine II (10) are installed on both sides of the fuselage main body (8). ), the wings on both sides have a dihedral angle of 2-5 degrees, and the two ends of the wing are the rotatable wing part I (1) and the rotatable wing part II connected by the hinge I (2) and the hinge II (1...

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Abstract

The invention relates to an unmanned aerial vehicle, in particular to a small unmanned aerial vehicle capable of taking off and landing vertically, belonging to the technical field of aircraft. Characterized in that: comprises a rotatable wing portion I (1), a hinge I (2), a rudder angle I (3), a rudder I (4), a wing body I (5), a bypass engine I (6), a bypass inlet I (7), a fuselage body (8), a bypass inlet II (9), a bypass engine II (10), a wing body II (11), a rudder II (12), a rudder angle II (13), a hinge II (14), and a rotatable wing portion II (15). As that out end of the wing is designas a rotatable wing, the structure is simple and the operation is convenient, and the rotatable wing part is adjusted into a winglet shape during flight, the flight of the unmanned aerial vehicle ismore stable, and the vertical take-off and landing and the horizontal high-speed flight of the unmanned aerial vehicle at any site are realized.

Description

technical field [0001] The invention relates to an unmanned aerial vehicle, in particular to a small unmanned aerial vehicle capable of vertical take-off and landing, and belongs to the technical field of aircraft. Background technique [0002] A drone is a powered, unmanned, reusable or one-time-use aircraft. With the rapid development of flight control technology, communication technology and electronic technology, the performance and types of UAVs are constantly increasing, and the application requirements in military and civilian fields are constantly increasing. UAVs are generally divided into fixed-wing UAVs and rotary-wing UAVs. Among them, the fixed-wing UAV relies on the engine to generate horizontal thrust, so that the UAV can fly at high speed in the air, but it needs a long runway to obtain a certain horizontal speed to take off, and at the same time, it needs to maintain a certain flight speed during the flight. In order to obtain the lift that overcomes its o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C29/00B64C3/38
CPCB64C3/38B64C29/00B64U10/25
Inventor 苏桐苏有勇
Owner 苏桐