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Rotorcraft fitted with an Anti-torque tail rotor that contributes selectively to providing the rotorcraft with lift and with propulsion

一种旋翼飞行器、尾翼的技术，应用在旋翼飞行器领域，能够解决降低旋翼飞行器稳定性、不合适、过度燃油消耗等问题，达到避免飞行不平衡的效果

Active Publication Date: 2015-07-01
EUROCOPTER
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0043] However, it has been found in practice that such additional lift can be disadvantageous in a defined flight attitude of the rotorcraft, for example, especially when the rotorcraft speed exceeds the phase of flight of 75 knots
[0044] In cruise flight, the additional lift provided by the empennage adversely increases attitude hump (the impact of the rotor on the rotorcraft's stabilizers), reduces the stability of the rotorcraft, and leads to excessive fuel consumption
Therefore, continuous use of the tail to provide additional lift is inappropriate, especially when the rotorcraft is flying at cruising speed, or when the rotorcraft is not overloaded

Method used

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  • Rotorcraft fitted with an Anti-torque tail rotor that contributes selectively to providing the rotorcraft with lift and with propulsion
  • Rotorcraft fitted with an Anti-torque tail rotor that contributes selectively to providing the rotorcraft with lift and with propulsion
  • Rotorcraft fitted with an Anti-torque tail rotor that contributes selectively to providing the rotorcraft with lift and with propulsion

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Embodiment Construction

[0111] Components that appear in more than one drawing are denoted by the same reference numerals in each drawing.

[0112] In FIGS. 1 to 3 , the rotorcraft 1 has a main rotor 2 driven in rotation about a substantially vertical axis, and an empennage 3 driven in rotation about a substantially horizontal axis. When advancing in any direction, the main rotor 2 provides at least lift and possibly also propulsion and / or changes of attitude to the rotorcraft 1 . In order to provide control over the yaw attitude of the rotorcraft 1 , the empennage 3 is a torque-resistant rotor mounted on the end of the tail boom 4 of the rotorcraft 1 .

[0113] Typically, the rotor of a rotorcraft comprises a rotating wing consisting of at least two blades (in the illustrated embodiment four blades). The blades are mounted on a hub which is driven in rotation, generally the rotor disk 5 is formed by the circumference delineated by the tips of the rotating wing blades.

[0114] In FIG. 1 , the driv...

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Abstract

A rotorcraft provided with an anti-torque tail rotor having a drive axis of constant orientation and having a rotor disk that is arranged mainly to one side of the tail boom of the rotorcraft. A control mechanism for controlling the blades of the tail rotor includes a rotary control plate engaged with the blades and movable by a control rod extending along the drive axis of the tail rotor. The control plate is arranged in a constant mounting plane (PM) and serves to provide permanent cyclic variation in the pitch of the blades. Turning the control rod changes the way in which the cyclical variation of the pitch of the blades is operated between providing a contribution to lift and providing a contribution to propulsion in translation of the rotorcraft, depending on the angular orientation of the control plate in its mounting plane (PM).

Description

[0001] Cross References to Related Applications [0002] This application claims priority from French application FR 13 02966 filed on December 17, 2013, the entire disclosure of which is incorporated herein. technical field [0003] The present invention relates to the field of rotorcraft, and more particularly, to a torque-resistant rotor of a rotorcraft, the rotational drive axis of which is substantially horizontal. In general, such torque-resistant rotors are used to stabilize and guide a yawing rotorcraft by counteracting the yawing moments generated by a main rotor whose rotational drive axis is substantially vertical and at least The aircraft provides lift. Background technique [0004] More specifically, the torque-resistant rotor of the invention is mounted on the end of the tail boom of the rotorcraft. The rotating wing of said anti-torque rotor constitutes a rotor disc, which is oriented substantially vertically and longitudinally, and is arranged on the side o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/82
CPCB64C27/78B64C27/52B64C27/82B64C27/59B64C2027/8281B64C27/605B64C27/56B64C2027/8218
Inventor P·普鲁多姆-拉克洛斯O·比斯图尔
Owner EUROCOPTER