(1) Field of the Invention
The invention relates to an airfoil blade of a bearingless rotor of a helicopter with the features of claim 1.
(2) Description of Related Art
During operation, the rotor blades are deflected in various directions and are thereby subjected to high loads in these various directions. The rotor blades must be designed to withstand these high loads while still providing the required flexibility or articulation to allow the blades to carry out flapping, lead-lag oscillating, and pitch angle variation movements.
Typically, a rotor blade of a bearingless rotor includes a structural element known as a flexbeam at the inner end of the blade connected to the rotor head. The flexbeam supports and transmits the centrifugal forces of the blade into the rotor head. Additionally, the flexbeam includes at least portions or regions that are flexurally and torsionally soft or flexible to allow the blade to undergo the above mentioned movements in a flapping direction, a lead-lag direction, and in a pitch angle direction. The torsionally soft portion of the flexbeam is arranged within a torsionally stiff control cuff or torque tube, through which the pitch angle control movements are transmitted to the lift-generating airfoil blade portion of the rotor blade. The airfoil blade typically extends from the outboard end of the control cuff to the outermost end of the rotor blade, i.e. the blade tip.
The vibrations of the rotor blades, and particularly the oscillations in the lead-lag direction, must be damped by appropriate damping elements. The damping effectiveness of the damping elements is predominantly dependent on the effective transmission of the lead-lag oscillating movements of the airfoil blade into the damping elements. Any softness or lack of force transmission through the blade/cuff attachment to the damping element will reduce the total resulting damping effect.
In order to allow the flexbeam/cuff unit and/or the airfoil blade to be separately manufactured and/or replaced in the event of damage, or in order to allow the airfoil blade to be pivoted and folded relative to the flexbeam/cuff unit, it is desired to provide a separable or releasable junction between the flexbeam/cuff unit and the lift-generating airfoil blade.
The separable or releasable junction is subject to high technical and mechanical demands, because it must reliably carry and transmit the substantially high centrifugal forces resulting during rotation of the rotor blade and all bending moments from flapping and lead lag movements of the rotor blade. The rotor blade has a longitudinal main load axis next to 25% of the average airfoil chord of the blade profile, said main load axis being essentially covered by the pitch axis of said rotor blade. At the level of the flexbeam said longitudinal main load axis next to 25% of the average airfoil chord of the blade profile corresponds to a longitudinal middle axis of the flexbeam.
The document WO 2010/082936 A1 discloses a rotor assembly for a rotary-wing aircraft, the rotor having a central hub assembly with a flexure-type, twist-shank yoke with multiple arms, each arm being adapted for a rotor blade to be mounted thereto. The arms provide for pitch changes of blades attached to the yoke through twisting of portions of the arms about a corresponding pitch axis. An inboard pitch bearing associated with each arm is attached to the hub assembly and allows for rotation of the attached blade about the pitch axis, the inboard pitch bearing also allowing for out-of-plane motion of the arm relative to the hub assembly about a flapping axis. An outboard pitch bearing associated with each arm is attached to the associated arm a selected distance from the inboard pitch bearing and allows for rotation of the attached blade about the pitch axis.
The document US 2008/101934 A1 discloses an assembly for providing flexure to a blade of a rotary blade system including an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned there between. An embodiment includes an assembly for providing flexure to a blade of a rotary blade system, including, an upper support plate having an upper curved surface, a lower support plate having a lower curved surface, and a yoke positioned there between and directly contacting the support plates wherein one of the curved surfaces is a non-circular arc that does not form part of the circumference of a circle.
The document U.S. Pat. No. 5,738,494 A discloses a composite flexbeam having a plurality of adjoining regions including a hub attachment region, a blade attachment region, a pitch region, an outboard transition region disposed between and adjoining the pitch region and blade attachment regions and an inboard transition region disposed between and adjoining the pitch and hub attachment regions. The inboard transition region includes a first transition subregion and a second transition subregion wherein the second transition subregion defines a width conic and a critical width transition subregion. The first and second inboard transition regions are composed of a combination of unidirectional and off-axis composite materials.
The document U.S. Pat. No. 5,096,380 A discloses a flexbeam for a bearingless helicopter rotor including a composite beam, composed of unidirectional fibers bound in an epoxy matrix, having ribs, composed of unidirectional fibers bound in a urethane matrix, bonded to each horizontal face at the section of the beam which accommodates lead-lag torsion.
The document EP 0315962 A2 discloses a helicopter rotor blade supported by a flexbeam to be rotatable about an axis of rotation, in which a pitching motion thereof is allowable. The rotor blade is provided with a device for changing the pitch and damping the lead-lag motion thereof. The device comprises a bushing in a hole formed at the inboard end of the flexbeam, an elastomeric pivot loosely fitted in the bushing, elastomeric dampers of cylindrical shape mounted on the upper and lower surfaces of the flexbeam and coupled with the upper and lower ends of the elastomeric pivot by means of nuts, and torque arms extending through the bushing and the elastomeric dampers and having the central portion thereof connected to central shafts of the elastomeric pivots. Each of the pitch sleeves has both ends outwardly projecting beyond the elastomeric dampers and secured to a pitch sleeve which encloses the flexbeam. Therefore, the relative position between the pitch sleeve and the elastomeric pivot does not change even when lead-lag motion is imparted to the rotor blade.
The document U.S. Pat. No. 4,427,340 A discloses helicopter rotors and more particularly rotor mounting involving a composite fiber-reinforced unitary yoke with resilient inplane restraints.
The document U.S. Pat. No. 6,126,398 A discloses a rotor blade for a bearingless rotor of a helicopter with a lift-generating airfoil blade, a flexbeam connecting the airfoil blade to a rotor head, and a control cuff enclosing the flexbeam. The junction between the flexbeam and the airfoil blade is a separable junction to allow the airfoil blade to be folded in a simple manner while maintaining a high lead-lag stiffness and reduced structural height of the junction. The junction is formed by two connection arms arranged side-by-side in the lead-lag plane of the rotor blade.
The document U.S. Pat. No. 6,196,800 B1 discloses a rotor blade arrangement for a bearingless rotor of a helicopter with a flexbeam connecting an airfoil blade to a rotor head, and a control sleeve surrounding the flexbeam. The control sleeve is relatively stiff, but the flexbeam has portions that are flexible so as form a fictitious flapping hinge, lead-lag hinge, and torsion axis, which respectively enable flapping, lead-lag pivoting, and torsional movements of the airfoil blade. The inboard end of the control sleeve is secured to the root end of the flexbeam near the rotor head to prevent lateral displacements there between. Damping elements are arranged within the enclosure of the control sleeve at a location between the fictitious lead-lag hinge of the flexbeam and the transition region at which the flexbeam transitions into the airfoil blade. The damping elements are preferably arranged laterally next to the flexbeam in the lead-lag plane, and are secured on the one hand to the control sleeve, and on the other hand to a securing plate that is connected to the flexbeam and the airfoil blade.
The document US 2012/087797 A1 discloses a system comprising a rotor blade, in particular of the tail rotor of a rotary wing aircraft, in a fiber-reinforced composite design, with a blade section and with a coupling section for attaching the rotor blade to the hub of a drive device, and comprising a separate sleeve-shaped control tube with an essentially hollow-cylindrical shaft, with an also essentially tubular tie section to tie the control tube to the rotor blade by sliding it onto its coupling section, is improved in that the coupling section of the rotor blade and the tie section of the control tube comprise a cross-sectional shape for positive-locking interconnection of the rotor blade and the control tube.
It is an object of the invention to provide an improved airfoil blade of a bearingless rotor of a helicopter and particularly to provide an especially simple and economical airfoil blade with a separable or releasable junction to a flexbeam/cuff unit to allow the quickest and easiest possible folding of the rotor blade, while improving the lead-lag movement transfer from the airfoil blade to the dampers of the rotor and reducing the total structural height of the junction area in order to improve drag behavior.
USPTO Backgrounds
USPTO Backgrounds