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A tail adjustment mechanism capable of independent pitch and yaw adjustment and an orthopter

A technology of adjusting mechanism and empennage, which is applied in the field of flapping aircraft, can solve the problems of reducing control precision, achieve the effects of improving control precision, avoiding mutual interference, and reducing control difficulty

Active Publication Date: 2018-07-24
HARBIN INST OF TECH SHENZHEN GRADUATE SCHOOL
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

thereby reducing the control accuracy

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  • A tail adjustment mechanism capable of independent pitch and yaw adjustment and an orthopter
  • A tail adjustment mechanism capable of independent pitch and yaw adjustment and an orthopter
  • A tail adjustment mechanism capable of independent pitch and yaw adjustment and an orthopter

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Embodiment Construction

[0037] The idea, specific structure and technical effects of the present invention will be clearly and completely described below in conjunction with the embodiments and accompanying drawings, so as to fully understand the purpose, scheme and effect of the present invention. It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other.

[0038] It should be noted that, unless otherwise specified, when a feature is called "fixed" or "connected" to another feature, it can be directly fixed and connected to another feature, or indirectly fixed and connected to another feature. on a feature. In addition, descriptions such as up, down, left, and right used in the present invention are only relative to the mutual positional relationship of the components of the present invention in the drawings.

[0039] Also, unless defined otherwise, all technical and scientific terms used herei...

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Abstract

The invention discloses an empennage adjustment mechanism capable of independently adjusting pitch and yaw and a flapper aircraft, wherein the adjustment mechanism includes a frame and an empennage, the empennage includes horizontal fins and vertical fins, and the horizontal fins pass through a horizontal axis. The reciprocating rotation is used to realize the pitch control, and the vertical blade is reciprocally rotated through a vertical axis to realize the yaw control. It also includes a first drive assembly and a second drive assembly, wherein the horizontal axis and the vertical axis are two independent movements. structure, the first drive assembly is used to drive one of the horizontal fins or the vertical fins to undergo a corresponding regulation movement, and the second drive assembly is used to drive the other of the horizontal fins or the vertical fins to undergo a corresponding regulation movement . The present invention can realize the complete decoupling of pitch and yaw adjustment, divide the yaw adjustment and pitch adjustment of the empennage into two independent steps, effectively avoid the mutual interference between the two, and help to improve the control accuracy , reducing the difficulty of control.

Description

technical field [0001] The invention relates to the field of robots, in particular to an aircraft empennage adjustment mechanism, and the invention also relates to an orthopter. Background technique [0002] The wings and tail of the flapping aircraft are designed to imitate the flapping laws of birds in nature, which is different from the fact that birds rely entirely on their wings to generate lift and thrust at the same time, and realize steering, maneuvering and attitude adjustment at the same time. For the purpose of simplifying the structure, improving the stability of the system, and reducing the difficulty of control, the man-made flapping wing aircraft is only assigned to the flapping mechanism to generate the two most basic functions of lift and thrust, and the The functions of steering and maneuvering are all realized by the empennage. That is to say, the empennage is responsible for providing all the yawing moments and pitching moments required for flight in the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C33/02B64C13/28
Inventor 徐文福潘尔振李光明罗灿
Owner HARBIN INST OF TECH SHENZHEN GRADUATE SCHOOL