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Multi-rotor aerocraft

A multi-rotor aircraft, rotor technology

Inactive Publication Date: 2008-06-04
战强
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The problem solved by the technology of the present invention is: to solve the complex structure of the existing vertical take-off and landing, hovering aircraft, the main propeller is relatively large in diameter relative to the body, the movement flexibility and stability are relatively poor, and the ratio of lift to body weight is low. The problem of weak carrying capacity of small aircraft

Method used

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  • Multi-rotor aerocraft
  • Multi-rotor aerocraft
  • Multi-rotor aerocraft

Examples

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Embodiment Construction

[0010] Such as figure 1 and figure 2 As shown, the specific embodiment of the present invention is: four rotors 1, 2, 3, 4 are symmetrically fixed on a cross-shaped body 7 at an angle of 90 degrees, and the four rotors are located on the same horizontal plane and are evenly distributed on a On the circle with the intersection point of the cross as the center, the controller and battery 6 are fixed at the center of the body, and the four rotors 1, 2, 3, and 4 are independently driven by four motors 5; the rotors 1 and 3 use positive propellers, Rotate clockwise, rotors 2 and 4 use reverse propellers, and rotate counterclockwise, the lift generated is all upward, and the steering of all rotors remains unchanged during the entire flight. When all four rotors are pressed figure 2 When the direction shown is rotating at a constant speed at a constant speed, the resultant torque of the aircraft is zero, and it can take off vertically. If it is accelerated, it can ascend, and if ...

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Abstract

The invention relates to a multi-rotor aircraft, which comprises an airframe and several rotors mounted on the airframe and in one level. Wherein, the number N of rotors is dual, as N=2, 4, 6, 8, etc, and formed by positive and passive rotors whose sizes and number are same; all rotors are uniformly distributed on the periphery of airframe in 360 / N angle; the passive and positive rotors are alternatively arranged with reversed rotation directions and upward lifting force; each rotor can be directly driven by motor or oil engine, or driven by motion transmission device via synchronous belt; the torsion between rotors can be counteracted, without balance device as tail wing or scull, with tight structure, flexible motion, larger lifting force and weight ratio. The invention can rise vertically, suspend in air, rotate in one point or fly horizontally.

Description

technical field [0001] The invention relates to a multi-rotor aircraft that can be used in multiple fields such as scientific experiments, aviation, aerospace, industry, entertainment, and military affairs. Background technique [0002] Aircraft with functions such as vertical take-off and landing and hovering have a wide range of application requirements in fields such as aerial photography, atmospheric observation, and planetary exploration. At present, the aircraft with such functions mainly include structural forms such as single-rotor helicopters, double-rotor helicopters, and tilting-rotor aircraft, such as the MH-16 helicopter of the U.S. McDonnell Douglas, the Russian Ka-29 helicopter, and the U.S. Boeing and Bell Corporation. Tilt rotor aircraft V-22 and V-44 etc. Single-rotor helicopters or coaxial reverse-rotor helicopters need a tail rotor structure to offset the torque generated by the rotor on the body, and tilt-rotors need to tilt the rotor surface between ve...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/08
Inventor 战强
Owner 战强
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