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1. WO2000041501 - HELICOPTER ROTOR BLADE FLAP ACTUATOR

Publication Number WO/2000/041501
Publication Date 20.07.2000
International Application No. PCT/US1999/028690
International Filing Date 03.12.1999
Chapter 2 Demand Filed 10.08.2000
IPC
B64C 27/00 2006.01
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
B64C 27/615 2006.01
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
54Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
58Transmitting means, e.g. interrelated with initiating means or means acting on blades
59mechanical
615including flaps mounted on blades
CPC
B64C 2027/7277
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
54Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
72Means acting on blades
7205on each blade individually, e.g. individual blade control [IBC]
7261with flaps
7266actuated by actuators
7277of the magnetostrictive type
B64C 2027/7283
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
54Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
72Means acting on blades
7205on each blade individually, e.g. individual blade control [IBC]
7261with flaps
7266actuated by actuators
7283of the piezoelectric type
B64C 2027/7288
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
54Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
72Means acting on blades
7205on each blade individually, e.g. individual blade control [IBC]
7261with flaps
7266actuated by actuators
7288of the memory shape type
B64C 27/001
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
001Vibration damping devices
B64C 27/615
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
CAEROPLANES; HELICOPTERS
27Rotorcraft; Rotors peculiar thereto
54Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
58Transmitting means
59mechanical
615including flaps mounted on blades
Y02T 50/34
YSECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
50Aeronautics or air transport
30Wing lift efficiency
34Helicopter rotor blades lift efficiency
Applicants
  • THE BOEING COMPANY [US/US]; P.O. Box 3707, M/S 13-08 Seattle, WA 98124-2207, US
Inventors
  • DOMZALSKI, David, B.; US
  • KENNEDY, Dennis, K.; US
  • STRAUB, Friedrich, K.; US
Agents
  • GULLETTE, Robert, L.; The Boeing Company P.O. Box 3707, M/S 13-08 Seattle, WA 98124-2207, US
Priority Data
09/233,98619.01.1999US
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) HELICOPTER ROTOR BLADE FLAP ACTUATOR
(FR) VERIN POUR VOLET DE PALE DE ROTOR D'HELICOPTERE
Abstract
(EN)
An actively controlled helicopter rotor blade includes a trailing edge flap (20) actuated by a fast-acting actuator (30). A lightweight, rugged, fast-acting actuator suitable for use as the flap actuator comprises a pair of column actuators (50, 52) composed of a smart material such as piezoelectric, magnetostrictive, shape memory alloy or other material that exhibits a shape change when subjected to an external stimulus. Each of the column actuators (50, 52) is composed of multiple piezoelectric ceramic actuator elements (48) bonded together to form the individual columns. Each of the column actuators (50, 52) engages the base of an actuator tube that, in turn, is urged against the column actuators (50, 52) by a tension member (76). Differential voltage applied to the columns (50, 52) causes a differential elongation of the column actuators (50, 52), which causes the actuator tube (86) to pivot about an axis proximal the tips of the column actuators (50, 56). The movement of the actuator tube (86) is coupled by a linkage to the rotor blade flap. Spherical joints (54, 56, 58, 60, 62, 64, 66, 68) are disposed between the column actuators (50, 52) and the actuator tube to prevent transmission of substantial bending loads to the column actuators (50, 52) and a mid-point support (120) is also provided for each of the column actuators (50, 52) to limit the magnitude of acceleration induced bending loads, which would otherwise lead tensile failure of the ceramic actuator elements (48).
(FR)
L'invention concerne une pale de rotor d'hélicoptère à commande active, qui comprend un volet de bord arrière actionné par un vérin à action rapide. Elle concerne notamment un vérin à action rapide, robuste et léger, pouvant être utilisé comme vérin de volet, qui comprend une paire de vérins allongés, constitués d'un matériau intelligent tel qu'un matériau piézo-électrique, un matériau magnétostrictif, un alliage à mémoire de forme ou un autre matériau qui change de forme quand il est soumis à un stimulus extérieur. Chaque vérin allongé, constitué de plusieurs éléments vérins céramiques piézo-électriques reliés de façon à former une colonne distincte, entre en contact avec la base d'un tube de vérin, qui est lui-même pressé contre ledit vérin par un élément de tension. L'application d'une tension différentielle aux vérins provoque leur élongation différentielle, qui à son tour entraîne le pivotement du tube de vérin autour d'un axe proche des pointes desdits vérins. Le déplacement du tube de vérin est couplé par une articulation au volet de la pale du rotor. Des joints sphériques, disposés entre les vérins allongés et le tube de vérin, empêchent la transmission auxdits vérins de charges de flexion importantes. Un support central, associé à chaque vérin, limite la magnitude des charges de flexion induites par l'accélération, qui autrement provoqueraient la rupture par traction des éléments vérins céramiques.
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