WO2011124908A1 - Pale de rotor pour giravion - Google Patents

Pale de rotor pour giravion Download PDF

Info

Publication number
WO2011124908A1
WO2011124908A1 PCT/GB2011/050669 GB2011050669W WO2011124908A1 WO 2011124908 A1 WO2011124908 A1 WO 2011124908A1 GB 2011050669 W GB2011050669 W GB 2011050669W WO 2011124908 A1 WO2011124908 A1 WO 2011124908A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor blade
arrangement
blade according
aerodynamic element
blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/GB2011/050669
Other languages
English (en)
Inventor
Andrew John Collins
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Microtecnica Actuation Technologies Ltd
Original Assignee
Microtecnica Actuation Technologies Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Microtecnica Actuation Technologies Ltd filed Critical Microtecnica Actuation Technologies Ltd
Publication of WO2011124908A1 publication Critical patent/WO2011124908A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
    • B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
    • B64C27/615—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including flaps mounted on blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/44—Blade pitch-changing mechanisms electric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
    • B64C27/68—Transmitting means, e.g. interrelated with initiating means or means acting on blades using electrical energy, e.g. having electrical power amplification
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B64C2003/145—Aerofoil profile comprising 'Gurney' flaps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/30—Wing lift efficiency

Definitions

  • a rotor blade for a rotorcraft including:
  • variable aerodynamic element transformable between a first arrangement and a second arrangement
  • the drive comprises a linear electric motor.
  • the linear electric motor is preferably disposed at a location that is more than 25% of the distance along a wing chord extending from the trailing edge of the rotor blade to the leading edge. In an embodiment of the invention described below it is about one third of the distance along the wing chord.
  • the flexing of the aerodynamic element preferably involves resilient deformation of a member, but it is also possible for the deformation to be plastic deformation.
  • the variable aerodynamic element may be resiliently biased into the first arrangement, into the second arrangement or into an intermediate state between the first and second arrangements.
  • the aerodynamic element is resiliently biased into its safest position; in that case in the event of failure of the linear motor, the
  • the aerodynamic element may be disposed in the region of the tip of the blade.
  • the aerodynamic element is disposed in the region of the trailing edge of the blade; in that case the element may be mounted for pivotal movement about an axis approximately aligned with the longitudinal axis of the rotor blade.
  • the aerodynamic element may be a Gurney flap.
  • the aerodynamic element may project radially outwardly from the tip of the blade; in that case the element may be mounted for pivotal movement about an axis approximately aligned with the longitudinal axis of the rotor blade.
  • the linear electric motor may include a permanent magnet armature.
  • the permanent magnet armature may comprise a rare earth magnet, which may for example be a neodymium magnet.
  • a rare earth magnet which may for example be a neodymium magnet.
  • Such a magnet may be made from an alloy comprising mainly, by weight, an alloy of neodymium, iron and boron. It provides an especially strong and
  • the linear electric motor includes a coil on the armature to provide the desired magnetisation of the armature.
  • the linear electric motor may include a stator
  • the coils may be disposed in series along a linear path. Whilst the linear path may be straight, at least in the case where the drive member is pivotally mounted, there is advantage in the path being curved and, preferably, matching the curvature of the path of movement of the drive member in the region of the coils. In that way the spacing between the armature and the stator of the motor may be maintained substantially constant throughout its range of movement.
  • the linear motor may include an arcuate stator.
  • the linear motor may be a limited angle torque motor.
  • Linear electric motors are known in a variety of forms involving different arrangements of stator coils and the present invention is not directed to any particular
  • commutator or without a commutator. It is also possible, if desired, to provide two or more sets of coils each independently capable of operating the aerodynamic element. Such redundancy may be desirable for safety reasons. In such a case there may be two or more armatures; there may also be two or more drive members and there may be two or more pivotal mountings.
  • the stator may comprise a multiplicity of permanent magnets, or a multiplicity of coils as described above .
  • the stator of the linear motor may also provide a structural member of the rotor blade.
  • the stator By arranging the stator also to serve as a 'structural member, the need for a separate structural member in the region of the stator can be avoided and therefore the additional mass introduced by including the linear motor very significantly reduced.
  • Fig. 1 is a side view of a helicopter including a main rotor having four rotor blades;
  • Fig. 2 is a cross-sectional view of a rotor blade towards the tip of the blade
  • the helicopter 1 shown in Fig. 1 includes a main rotor 2 comprising four rotor blades 3 rotatable on a shaft 4. When the helicopter is at rest on the ground the shaft 4 is disposed along an approximately vertical axis.
  • the design of the helicopter may be entirely conventional and the pitch of each of the blades may for example be controlled by a swashplate in the region of the top of the shaft 4, in a manner that is well known.
  • Each of the rotor blades 3 is also of generally conventional design but includes a special additional feature as will now be described.
  • a Gurney flap is provided on the underside of the trailing edge of the blade .
  • a Gurney flap 8 is shown projecting through an aperture in the skin of the blade in a direction approximately
  • the stator 17 comprises a series of coils some of which, referenced 18A to 18E are visible in Fig.3.
  • the coils are each independently connectible to a power supply controller 19 via connections shown schematically by dotted lines 20 in Fig.3.
  • the controller 19 is able to energise a selected one or more of the stator coils with a selected polarity of voltage (typically 28V) and thus generate a north pole or south pole at the end of the coil.
  • the coil 18A is energised to create a north pole in the region of the end of the coil 18A adjacent to the armature 14 and the armature is thus held in the position shown.
  • the armature could be moved one step clockwise by connecting the coil 18B as the coil 18A had been connected, while disconnecting or even reversing the connection to the coil 18A. If it is desired to move the armature more than one step, then the connection of the coil 18B may be momentary and superseded by connection of the coil 18C. Thus, in a manner that is well known per se, the position of the armature 14 may be controlled by appropriate
  • a position sensing feedback system will also be provided, for example using Hall sensors connected to the controller 19 to indicate the position of the armature 14 at any instant.
  • the controller 19 may be located at the stator or at a location separate from the stator.
  • the linear motor described above may readily be designed to be capable of reciprocating the drive member 9 between two chosen positions at a frequency up to 40 Hz.
  • the frequency can be adjusted to match the speed of rotation of the blade 3 and indeed it will usually be desirable to do that, although some additional control of perhaps smaller amplitude but higher frequency may
  • the drive member 9 is formed from several parts fixed together so that they behave as a single member pivoted at a mounting 10.
  • this mounting is preferably formed without parts having surfaces that move over one another as for example in a traditional bearing.
  • the mounting may for example take the form of a torsion wire or some other deformable element. From the description above it will be seen how a very simple, lightweight system may be employed to control a Gurney flap 8 on a rotor blade 3 of a helicopter.
  • the drive member 12 may carry a first armature 14 in the position shown in the drawings and a second armature on an extension that passes over the stator 17 and mounts the second armature in a position that is adjacent to the opposite face of the stator 17 from that which is adjacent to the armature 14.
  • control of the invention may replace control provided conventionally by a swash plate or may supplement that control .

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Linear Motors (AREA)

Abstract

Une pale de rotor (31) pour giravion comprend un élément aérodynamique variable (8), transformable entre une première disposition et une seconde disposition et un dispositif d'entraînement (9,14,17) destiné à transformer l'élément aérodynamique variable de la première disposition à la seconde disposition, le dispositif d'entraînement comprenant un moteur électrique linéaire (14,17).
PCT/GB2011/050669 2010-04-09 2011-04-01 Pale de rotor pour giravion Ceased WO2011124908A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1005975A GB2479411A (en) 2010-04-09 2010-04-09 Rotor blade
GB1005975.6 2010-04-09

Publications (1)

Publication Number Publication Date
WO2011124908A1 true WO2011124908A1 (fr) 2011-10-13

Family

ID=42236102

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2011/050669 Ceased WO2011124908A1 (fr) 2010-04-09 2011-04-01 Pale de rotor pour giravion

Country Status (2)

Country Link
GB (1) GB2479411A (fr)
WO (1) WO2011124908A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109436315A (zh) * 2018-10-22 2019-03-08 南京航空航天大学 一种柔性格尼襟翼系统
CN109695536A (zh) * 2019-01-27 2019-04-30 上海理工大学 带摆动式格尼襟翼装置的升力型垂直轴风力机及控制方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030218102A1 (en) * 2000-10-10 2003-11-27 Van Dam Cornelis P. Microfabricated translational stages for control of aerodynamic loading
WO2008048279A2 (fr) 2005-12-09 2008-04-24 Sikorsky Aircraft Corporation Actionneur linéaire ou rotatif pour commande de rotor d'hélicoptère, à base d'un moteur sans balai à courant continu (bldc)
WO2008051293A2 (fr) * 2006-04-13 2008-05-02 The Board Of Trustees Of The Leland Stanford Junior University Volet de gurney actif a translation permettant de reduire le danger lie a la turbulence de sillage d'un aeronef
US20090302168A1 (en) * 2006-04-27 2009-12-10 Hetrick Joel A Compliant Structure Design of Varying Surface Contours

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010068225A1 (fr) * 2008-12-12 2010-06-17 Karem Aircraft, Inc. Giravion sans plateau cyclique à actionneur électrique linéaire tolérant aux défaillances

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030218102A1 (en) * 2000-10-10 2003-11-27 Van Dam Cornelis P. Microfabricated translational stages for control of aerodynamic loading
WO2008048279A2 (fr) 2005-12-09 2008-04-24 Sikorsky Aircraft Corporation Actionneur linéaire ou rotatif pour commande de rotor d'hélicoptère, à base d'un moteur sans balai à courant continu (bldc)
WO2008051293A2 (fr) * 2006-04-13 2008-05-02 The Board Of Trustees Of The Leland Stanford Junior University Volet de gurney actif a translation permettant de reduire le danger lie a la turbulence de sillage d'un aeronef
US20090302168A1 (en) * 2006-04-27 2009-12-10 Hetrick Joel A Compliant Structure Design of Varying Surface Contours

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109436315A (zh) * 2018-10-22 2019-03-08 南京航空航天大学 一种柔性格尼襟翼系统
CN109436315B (zh) * 2018-10-22 2021-12-14 南京航空航天大学 一种柔性格尼襟翼系统
CN109695536A (zh) * 2019-01-27 2019-04-30 上海理工大学 带摆动式格尼襟翼装置的升力型垂直轴风力机及控制方法

Also Published As

Publication number Publication date
GB2479411A (en) 2011-10-12
GB201005975D0 (en) 2010-05-26

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