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1. WO1996006006 - YAW CONTROL AND STABILIZATION SYSTEM FOR HELICOPTERS

Publication Number WO/1996/006006
Publication Date 29.02.1996
International Application No. PCT/US1995/010490
International Filing Date 17.08.1995
Chapter 2 Demand Filed 15.03.1996
IPC
B64C 27/10 2006.01
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
04Helicopters
08with two or more rotors
10arranged coaxially
B64C 27/32 2006.01
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
32Rotors
B64C 27/467 2006.01
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
32Rotors
46Blades
467Aerodynamic features
B64C 27/82 2006.01
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
82characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
CPC
A63H 27/12
AHUMAN NECESSITIES
63SPORTS; GAMES; AMUSEMENTS
HTOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
27Toy aircraft; Other flying toys
12Helicopters
B64C 27/10
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
04Helicopters
08with two or more rotors
10arranged coaxially
B64C 27/32
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
32Rotors
B64C 27/467
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
32Rotors
46Blades
467Aerodynamic features
B64C 27/82
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
82characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
Applicants
  • ARLTON, Paul, E. [US/US]; US
Inventors
  • ARLTON, Paul, E.; US
Agents
  • REZEK, Richard, A.; Barnes & Thornburg 1313 Merchants Bank Building 11 South Meridian Street Indianapolis, IN 46204, US
Priority Data
08/292,71918.08.1994US
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) YAW CONTROL AND STABILIZATION SYSTEM FOR HELICOPTERS
(FR) SYSTEME POUR AMORTIR ET STABILISER LE LACET DANS LES HELICOPTERES
Abstract
(EN)
This invention relates to the field of yaw control systems for helicopters (10), including a gyroscopic mechanism (12) mounted on a helicopter tail rotor assembly (2) and configured to vary tail rotor (2) thrust automatically to produce a yaw moment stabilizing the helicopter (10) in flight so that the helicopter (10) is able to fly in a direction (heading) selected by the pilot. The aerodynamically shaped paddles or rotor blades (59) included in the gyroscopic assembly (12) are constructed so as to be cyclically pitchable in response to pivoting of the gyro rotor (59) to generate aerodynamic restoring forces in opposition to pivoting of the gyro rotor (59) so as to restore the gyro rotor (59) to a nominal orientation during helicopter flight at the proper times. The blades (11) have an aerodynamic center (80) of pressure located ahead of the pitching axis (81) and mass balancing means (33) to minimize the pitching forces felt at the root (32) of the blades (11).
(FR)
L'invention concerne un système pour amortir le lacet dans les hélicoptères (10), comprenant un mécanisme gyroscopique (12) monté sur le rotor de queue (2) de l'hélicoptère et agencé pour faire varier automatiquement la poussée du rotor de queue (2), afin de produire automatiquement un moment de lacet stabilisant l'hélicoptère (10) en vol, pour que l'hélicoptère (10) puisse voler dans la direction choisie par le pilote, c'est-à-dire maintenir le cap. Les pales (59) de rotor ont une forme aérodynamique et elles sont prévues et réalisées dans le gyroscope (12), pour pouvoir tanguer d'une manière cyclique en réponse au pivotement du rotor (59) de gyroscope, afin de créer des forces de rappel s'opposant au pivotement du rotor (59) de gyroscope et de remettre ce dernier dans son orientation nominale durant le vol de l'hélicoptère, aux moments appropriés. Les pales (11) ont un centre aérodynamique de pression (80) situé en avant de l'axe de tangage (81) et des moyens d'équilibrage (33) de la masse pour minimiser les forces de tangage perçues à la racine (32) des pales (11).
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