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Vertical take-off and landing type unmanned aerial vehicle

A technology of vertical take-off and landing and unmanned aerial vehicles, applied in the field of unmanned aerial vehicles, which can solve the problems that unmanned aerial vehicles do not have vertical take-off and landing capabilities and unsatisfactory vertical take-off and landing performance, so as to improve wind resistance and reduce assembly man-hours , the effect of reducing the number of parts

Inactive Publication Date: 2019-03-26
西安爱生无人机技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] However, the existing UAV aircraft generally do not have the vertical take-off and landing capability or the vertical take-off and landing performance is not ideal, and the performance needs to be improved. In order to realize the smooth transition between the quadrotor state and the fixed-wing state, the following problems need to be solved:

Method used

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  • Vertical take-off and landing type unmanned aerial vehicle
  • Vertical take-off and landing type unmanned aerial vehicle
  • Vertical take-off and landing type unmanned aerial vehicle

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0043] Embodiment: ASN-216 small short-range multi-purpose unmanned aerial vehicle main configuration parameters:

[0044] Overall length of the whole machine: 2220mm, stop height: 600mm, straight wing span: 3200mm;

[0045] Fuselage (excluding tail brace): fuselage length: 1183mm, fuselage height: 266mm, maximum width: 226mm; straight wing: installation angle: 2°, dihedral angle: 2°, leading edge sweep angle: 1.2 °, reference area: 1m 2 , reference wing root chord: 380mm, reference wing tip chord: 245mm, reference wing average aerodynamic chord length: 317mm, reference wing aspect ratio: 10.24

[0046] The reference point of wing twist is the leading edge of wing root chord, and the wingtip twist is -3°;

[0047] Vertical Tail: Vertical Tail Height: 410mm, Leading Edge Sweep Angle: 23°, Trailing Edge Sweep Angle: 0°, Reference Root Chord: 397mm;

[0048] Flat tail: span length: 800mm, root chord length: 230mm, tip chord length: 160mm;

[0049] Weight distribution: Maximum t...

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Abstract

The invention discloses a vertical take-off and landing type unmanned aerial vehicle. The unmanned aerial vehicle comprises a vehicle body (1), a pair of straight wings (2), a tail boom (3) and a tailwing (4), wherein the straight wings (2) are vertical to the axis of the vehicle body (1) and are symmetrically arranged on the left and right sides of the vehicle body (1); and a pair of rotor wingarms (5) are symmetrically and additionally arranged on the straight wings (2), are respectively located on the left and right sides of the vehicle body (1), are parallel with the axis of the vehiclebody (1) and comprise rotor wing motors (51), four rotor wing paddles (52), motor adjusters and power batteries, and the four rotor wing paddles (52) are respectively mounted on the rotor wing arms (5) and the rotor wing motors (51) at two ends. By optimizing the structures of the wings and the vehicle body, the vertical take-off and landing wind resistance of the unmanned aerial vehicle is improved; the structures and rigidity of the wings and the vehicle body are designed; the weight of the whole vehicle is controlled, the assembling working hour is reduced, and the cost is saved.

Description

technical field [0001] The invention belongs to the field of unmanned aerial vehicles, in particular to a vertical take-off and landing unmanned aerial vehicle. Background technique [0002] UAV systems are mainly used for border patrols, anti-terrorism and stability maintenance tasks, and can also be used in various fields such as ocean monitoring, power line inspection, oil pipeline inspection, and environmental monitoring. It can carry a photoelectric stabilized turntable, digital camera or other equipment, and has the functions of real-time aerial mapping, detection and monitoring, and target positioning. [0003] However, the existing UAV aircraft generally do not have the vertical take-off and landing capability or the vertical take-off and landing performance is not ideal, and the performance needs to be improved. In order to realize the smooth transition between the quadrotor state and the fixed-wing state, the following problems need to be solved: [0004] a) It is...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/26B64C29/00B64C3/14
CPCB64C3/14B64C27/26B64C29/0008B64C2003/146B64C2003/147
Inventor 周明汪强李辛安斌兰小鹏
Owner 西安爱生无人机技术有限公司
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