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Pitch stabilisation means and rotorcraft comprising such means

A technology for stabilizing devices and aircraft, which is applied in the direction of aircraft, rotorcraft, and aircraft stabilization, and can solve problems such as loss of efficiency of stabilizing devices

Active Publication Date: 2014-04-02
EUROCOPTER
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this second solution can in fact lead to a significant loss of efficiency of the stabilizer and create mounting stresses

Method used

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  • Pitch stabilisation means and rotorcraft comprising such means
  • Pitch stabilisation means and rotorcraft comprising such means
  • Pitch stabilisation means and rotorcraft comprising such means

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Embodiment Construction

[0097] pay attention to figure 1 Three mutually orthogonal directions are represented in X , Y and Z .

[0098] first direction X is called vertical. The term "longitudinal" is relative to any first orientation with X parallel direction.

[0099] second direction Y is the so-called horizontal. The term "transverse" is relative to any second orientation with Y parallel direction.

[0100] Finally, the third direction Z is the so-called vertical. The term "perpendicular" is relative to any orientation with a third Z parallel direction.

[0101] figure 1 represents an aircraft 1 according to the invention.

[0102] The aircraft comprises a fuselage 2 extending longitudinally from the nose 3 to the rear end 4 and transversely from the left to the right.

[0103] The fuselage extends vertically from a low part containing the landing gear to a high part with rotating wings 5 ​​.

[0104] The fuselage 2 may include a tail boom 6 extending towards the rear end 4 via a...

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Abstract

A pitch stabilization means is equipped with an upper stabilizer surface (15) and a lower stabilizer surface (20). The upper stabilizer surface (15) is located in an upper plane (P1) and the lower stabilizer surface (20) is located in a lower plane (P2), the upper plane (P1) overhangs the lower plane (P2). The upper stabilizer surface (15) is rotatable about an upper axis (AX1) of rotation, with the lower stabilizer surface (20) being rotatable about a lower axis (ax2) of rotation. The stabilizer means (10) include linking means (30) whereby a rotary movement of one stabilizer surface causes an equal rotary movement of the other stabilizer surface. The pitch stabilization means are used for minimizing unstable bumps. The invention further relates to an aircraft.

Description

technical field [0001] The invention relates to a pitch stabilizing device and a propeller aircraft equipped with such a device, which can effectively reduce stability bumps. The invention thus belongs to the technical field of limiting the phenomenon of pitching in stability of aircraft. Background technique [0002] Generally, a helicopter consists of a fuselage that extends symmetrically from the front end to the rear end in the horizontal direction. The lower part in the vertical direction is equipped with a landing gear, and the upper part is equipped with a main engine for pushing and lifting. [0003] Furthermore, the helicopter contains a rear rotor on its rear end. The function of the rear rotor is mainly to counteract the torsional moment exerted by the main rotor on the fuselage. In addition, this rear rotor is able to control the torsional movement of the helicopter. [0004] Helicopters, on the other hand, sometimes include additional stabilizers. For exampl...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C5/10B64C1/26
CPCB64C2027/8281B64C27/82B64C5/16B64C27/06B64C5/02
Inventor F·波洛尔
Owner EUROCOPTER
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