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Rotor and aircraft passively stable in hover

An aircraft and rotor technology, applied in the field of rotorcraft, can solve problems such as rotor separation and helicopter loss of stability.

Inactive Publication Date: 2005-11-16
FLIR UNMANNED AERIAL SYST AS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The rotors would then lose control of the stabilizer and the helicopter would lose stability

Method used

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  • Rotor and aircraft passively stable in hover
  • Rotor and aircraft passively stable in hover
  • Rotor and aircraft passively stable in hover

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Embodiment Construction

[0037] The present invention and preferred embodiments will be described below by referring to the accompanying drawings. Some alternative embodiments will also be described, but other applications and modifications will occur to those skilled in the art within the scope of the invention as defined in the appended claims.

[0038] exist figure 1 A preferred embodiment of the rotor according to the invention is shown in and 2. It is most suitable for free-flying or remote-controlled small aircraft indoors or in light wind conditions. The rotor has a plane of rotation formed by the paths that the tips of the rotor blades follow as the rotor rotates, and a fixed reference plane perpendicular to the rotor axis.

[0039] The rotor 10 is composed of 4 rotor blades arranged in two pairs or two groups, and the wing section of the blades is in the shape of a thin curved plate. This airfoil profile is chosen in order to obtain a rotor blade that is easy to twist and still maintains l...

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Abstract

The present invention discloses a rotor that enables an aircraft to be passively stable in hover. The rotor, having a generally fixed geometry is tiltably connected to its rotor shaft. The outer part of the rotor blades have a pitch fixed relative to the rotational plane, whereas the inner part of the rotor blades have a pitch fixed relative to a reference plane perpendicular to the rotor shaft.

Description

technical field [0001] The present invention relates to rotorcraft, such as helicopters, and more particularly to a rotor system capable of passively stabilized hovering. It also relates to a coaxial rotor system particularly suitable for ultra-small aircraft and a method of controlling said system. Background technique [0002] Typically, rotorcraft such as helicopters are suspended by rotors that rotate about a vertical rotor axis to generate lift, or upward thrust. As the rotor rotates about the rotor axis, the thrust is directed perpendicular to the plane of rotation formed by the trajectory of the rotor blade tips. [0003] In a conventional helicopter, the total thrust generated by the rotor can be changed by changing the helix angle (abbreviation: pitch) of all rotor blades as a whole. This pitch is defined in the field of propeller aircraft dynamics as the lateral angle between the blade and a reference plane perpendicular to the axis of the rotor shaft. The angle...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/00B64C27/10B64C27/43B64C27/467B64C27/52B64C27/82
CPCB64C27/82A63H27/12B64C27/10B64C27/43B64C2027/8218B64C27/52B64C27/467B64U20/87B64U30/21B64U50/13B64U60/50B64U10/17B64U50/39B64U20/60
Inventor P·穆伦
Owner FLIR UNMANNED AERIAL SYST AS