Coaxial-inversion birotor eight-rotary wing aircraft

An octa-rotor aircraft, dual-rotor technology, applied in the field of unmanned aerial vehicles, can solve the problems of low lift/weight ratio, insufficient miniaturization carrying capacity, etc.

Inactive Publication Date: 2010-08-25
CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the problems of low lift/weight ratio and insufficient miniaturized carrying capa

Method used

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  • Coaxial-inversion birotor eight-rotary wing aircraft
  • Coaxial-inversion birotor eight-rotary wing aircraft
  • Coaxial-inversion birotor eight-rotary wing aircraft

Examples

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Embodiment Construction

[0011] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

[0012] As shown in Fig. 1, the coaxial reverse dual-rotor eight-rotor aircraft of the present invention comprises: a body 1, four support arms 2 connected around the body 1, four support arms 2 respectively arranged on the ends of each support arm 2 The double rotor 3, the landing gear 4 connected to the body 1, and the electronic control system 5 arranged in the body 1 to control and connect the rotors, the geometric centerlines of the four support arms 2 are on the same plane, each adjacent The included angle between the geometric centerlines of the two support arms 2 is 90°. The landing gear 4 is symmetrically connected to the body 1, provides support for the aircraft, and protects the rotor from colliding with the ground when the aircraft takes off and lands.

[0013] As shown in Figure 2, the above-mentioned dual rotor 3 is comp...

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PUM

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Abstract

The invention provides a coaxial-inversion birotor eight-rotary wing aircraft, relating to the technical field of unmanned aircrafts and comprising an engine body (1), four supporting arms (2), four birotors (3), undercarriages (4) and an electric control system (5), wherein the four supporting arms (2) are connected to the periphery of the engine body (1), the geometrical center lines of the four supporting arms (2) are on the same plane, and the included angle of the geometrical center lines of the adjacent two supporting arms (2) is 90 degrees; the four birotors (3) are respectively arranged on the ends of the four supporting arms (2); the undercarriages (4) are symmetrically connected to the engine body (1); and the electric control system (5) is arranged in the engine body (1), controls and is connected with the four birotors (3). The aircraft has high lift force/weight ratio and loading capacity.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, and relates to a novel structure of a coaxial reversing dual-rotor multi-rotor aircraft. Background technique [0002] Most of the current aircraft are fixed-wing aircraft. This aircraft cannot complete vertical take-off and landing, and needs a special runway or launching device, and its maneuverability is limited. Winged aircraft have vertical take-off and landing functions, and can also hover in the air. They have a wide range of needs in military reconnaissance, anti-terrorism, public security, fire protection, forest inspection, nuclear leak detection, and disaster relief. In particular, the micro-rotor aircraft has very broad application prospects in both military and civilian applications, including reconnaissance and surveillance under complex terrain conditions for field operations; communication relay; detection of nuclear pollution or detection in special environments;...

Claims

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Application Information

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IPC IPC(8): B64C27/10
Inventor 白越孙强续志军李也凡高庆嘉王凯
Owner CHANGCHUN INST OF OPTICS FINE MECHANICS & PHYSICS CHINESE ACAD OF SCI
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