A tilting quadrotor aircraft

A technology of tilting quadrotors and aircrafts, which is applied to aircrafts, rotorcrafts, motor vehicles, etc. It can solve the problems that the installation position of the load is difficult to determine, and achieve the effect of ensuring the relative attitude, ensuring the size, and simple control mechanism

Active Publication Date: 2017-09-29
湖北航天飞行器研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

A problem with this solution is that it is difficult to determine the installation position of the load

Method used

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  • A tilting quadrotor aircraft
  • A tilting quadrotor aircraft
  • A tilting quadrotor aircraft

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Embodiment Construction

[0045] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not constitute a conflict with each other.

[0046] figure 1 It is a structural schematic diagram of a tilting quadrotor aircraft in an embodiment of the present invention. As can be seen from the figure, a tilting quadrotor aircraft structure of the present embodiment includes a fuselage 1, a first wing 2, a second wing 3, a tilting unit 4, a first rotor unit 5, a second rotor unit 6, The third rotor unit 7 and the fourth rotor unit 8 ....

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Abstract

The invention discloses a tilting four-rotor aircraft, which belongs to the field of aerospace power machinery, and comprises a fuselage, a first wing and a second wing, a tilting unit and four sets of rotor units, and the tilting unit is arranged on the fuselage above, it includes the first transverse axis and the second transverse axis symmetrically arranged on both sides of the fuselage, and also includes the first, second, third, and fourth rotor installation axes, and the two ends of the first transverse axis are respectively fixed There are first and second rotor installation shafts, the first and second rotor units are respectively fixed on the first and second rotor installation shafts, and the third and fourth rotor installations are respectively fixed at both ends of the second transverse shaft. shaft, the third and fourth rotor units are respectively fixed on the third and fourth rotor installation shafts, and the rotation axes of the first, second, third and fourth rotor units are all perpendicular to the horizontal plane. The control of the aircraft of the present invention is relatively easy.

Description

technical field [0001] The invention belongs to the field of aerospace power machinery, and in particular relates to a tiltable four-rotor aircraft. Background technique [0002] The traditional four-rotor aircraft has vertical take-off and landing capabilities. When flying horizontally, its fuselage must be tilted, and the level flight speed of the four-rotor aircraft is difficult to reach the higher cruising speed of the fixed-wing aircraft. Traditional fixed-wing aircraft have high level flight speeds, but they have high requirements for launch and recovery sites, and are not suitable for taking off and landing in small spaces or in mountainous environments. [0003] Someone has proposed a structure of a tiltable quadrotor aircraft, in which four wings are respectively installed on both sides of the front and rear parts of the fuselage, and a tiltable rotor system is respectively installed on the outer ends of the wings. This scheme requires four sets of The structure of...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/28
Inventor 黄飞雷明蔡作荣高海军戴意涛邬华明周子鸣张紫龙
Owner 湖北航天飞行器研究所
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