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Multi-rotor unmanned aerial vehicle

A multi-rotor unmanned aerial vehicle, fuselage technology, applied in the direction of rotorcraft, unmanned aerial vehicle, fuselage, etc., can solve the problems of non-disassembly, poor expansion ability, complex structure of the unmanned aerial vehicle, and achieve small size , the effect of easy storage

Pending Publication Date: 2017-07-14
SANGAIR TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, multi-rotor drones also have their own development bottlenecks: 1. In order to increase the load capacity of multi-rotors, the number of blades is increased, resulting in a decrease in the reliability of the drone; 2. The body structure of the drone is complex and fixed. Disassembly is not conducive to the upgrade and transformation of drones in the later stage, and the expansion ability is poor

Method used

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Embodiment Construction

[0038] The multi-rotor unmanned aerial vehicle of the present invention includes a fuselage composed of roller shafts, has a simple structure, is light in weight, and has a strong expansion ability for subsequent upgrades and transformations.

[0039] The multi-rotor unmanned aerial vehicle of the present invention can be an unmanned aerial vehicle with a quadrotor or a hexacopter with an even number of rotors greater than six.

[0040] see Figure 1 to Figure 2 , in this embodiment, the multi-rotor drone is a quadrotor drone, and the quadrotor drone includes a fuselage 2 and a casing 1 arranged on the fuselage 2, wherein the side of the fuselage 2 in the axial direction The fuselage 2 has front and rear ends, the side in the radial direction of the fuselage 2 is one side, and the fuselage 2 has four sides: up, down, left, and right; the casing 1 covers the front end and the upper side of the fuselage 2.

[0041] The fuselage 2 includes a roller shaft group, and the two rolle...

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Abstract

The invention provides a multi-rotor unmanned aerial vehicle (UAV) comprising a fuselage and a casing which is streamlined, wherein the fuselage covers the casing; the fuselage comprises roll shaft groups; the fuselage is provided with rotating shafts at both sides; propeller arm assemblies are rotatably arranged at the rotating shafts; each propeller arm assembly comprises propeller arms and a fixing box for mounting the propeller arms; each fixing box is connected with a folding mechanism; a blade assembly is arranged at the first end of each propeller arm; each blade assembly comprises a power box mounted on the corresponding propeller arm and a blade connected with the power box; and the propeller arm assemblies and the blade assemblies are symmetrically arranged relative to the fuselage. By using the mechanism, the multi-rotor UAV of the invention has the advantages of small weight, simple structure of the fuselage and strong ability to later upgrade, renovation and expansion; in addition, the multi-rotor UAV can ensure a good balance in the course of flight and the airworthiness of the multi-rotor UAV is improved.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a multi-rotor unmanned aerial vehicle. Background technique [0002] At present, common aircraft are usually divided into fixed-wing, helicopter and multi-rotor (four-rotor is the most mainstream), and multi-rotor UAV is defined as a special unmanned helicopter with three or more rotor axes. [0003] In recent years, due to the excellent operational performance of multi-rotors, multi-rotors have quickly become the mainstream of small UAVs. Multi-rotor UAVs can take off and land vertically, and can hover in the air after takeoff. It is easy to control the flight range and is relatively safe. However, multi-rotor drones also have their own development bottlenecks: 1. In order to increase the load capacity of multi-rotors, the number of blades is increased, resulting in a decrease in the reliability of the drone; 2. The body structure of the drone is complex and fixed. Disas...

Claims

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Application Information

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IPC IPC(8): B64C1/30B64C27/00B64C27/08B64D1/16
CPCB64C1/30B64C27/006B64C27/08B64D1/16B64U2101/00B64U50/19B64U10/10
Inventor 赵刚
Owner SANGAIR TECH
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