Duct type unmanned aerial vehicle and control method thereof

A control method and technology of unmanned aerial vehicles, applied in the field of ducted unmanned aerial vehicles and its control, can solve the problems of slow flight speed, high noise and poor safety of multi-rotor unmanned aerial vehicles, and achieve avoidance of complex obstacles and high efficiency , the effect of large carrying capacity

Inactive Publication Date: 2016-07-13
陈方平
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Existing multi-rotor drones and traditional unmanned helicopter rotor blades are exposed, resulting in poor safety and high noise problems. The flight speed of multi-rotor drones is slow, and multi-rotor drone

Method used

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  • Duct type unmanned aerial vehicle and control method thereof
  • Duct type unmanned aerial vehicle and control method thereof
  • Duct type unmanned aerial vehicle and control method thereof

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Embodiment Construction

[0026] The specific implementation of the present invention will be further described below in conjunction with the accompanying drawings and examples. The following examples are only used to illustrate the technical solutions of the present invention more clearly, but not to limit the protection scope of the present invention.

[0027] Such as Figure 1-6 Shown, the schematic diagram of the unmanned aerial vehicle of an embodiment of the present invention, the unmanned aerial vehicle of this embodiment comprises:

[0028] Fuselage body 1;

[0029] a first main duct 2 and a second main duct 3 connected to the first side of the fuselage body 1;

[0030] The third main duct 4 and the fourth main duct 5 connected to the second side of the fuselage main body 1; wherein, the first main duct 2 and the fourth main duct 5 are relatively to the fuselage The tail of the main body 1 is symmetrically arranged, and the second main duct 3 and the third main duct 4 are symmetrically arrang...

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Abstract

The invention discloses a duct type unmanned aerial vehicle and a control method thereof.The unmanned aerial vehicle comprises a main vehicle body (1), a first main duct (2), a second main duct (3), a third main duct (4) and a fourth main duct (5).The first main duct (2) and the second main duct (3) are connected with the first side of the main vehicle body (1).The third main duct (4) and the fourth main duct (5) are connected with the second side of the main vehicle body (1).The first main duct (2) and the fourth main duct (5) are arranged symmetric about the tail of the main vehicle body (1).The second main duct (3) and the third main duct (4) are arranged symmetric about the head of the main vehicle body (1).The unmanned aerial vehicle can run amphibiously on land and in air, so that the unmanned aerial vehicle stably flies in multiple forms to pass through multiple barriers, space of a power system is greatly saved through a duct type structure, large space is vacated for carrying of the unmanned aerial vehicle, and compared with a traditional multi-rotor-wing unmanned aerial vehicle, the duct type unmanned aerial vehicle is safer and more reliable.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a ducted unmanned aerial vehicle and a control method thereof. Background technique [0002] In recent years, due to its distinctive technical characteristics, unmanned aerial vehicle (UAV) has been widely used and developed rapidly in both military and civilian fields, especially in agricultural plant protection, military reconnaissance, environmental anomaly detection, disaster relief, electric power Inspection, mapping and modeling, aerial photography, entertainment and other fields have a wide range of needs, and it represents an important development direction of future aircraft. Especially in the past five years, many small multi-axis rotor drones with distinctive features have emerged. [0003] From a technical point of view, unmanned aerial vehicles can be divided into: unmanned helicopters, unmanned fixed-wing aircraft, unmanned multi-rotor aircraft, unmanned airs...

Claims

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Application Information

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IPC IPC(8): B64C11/46B64C19/00B64C39/02B60F5/02
CPCB64C11/46B64C19/00B64C39/02B60F5/02B64U10/00B64U50/14B64U2201/10
Inventor 陈方平孙培贤李晓庄月清贾惠柱解晓东
Owner 陈方平
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