Rotor blade with control flaps
AssigneeEADS Deutschland GmbH
InventorsThomas Lorkowski, Frank Hermle
Life of this patent
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Abstract
Rotor blade for a helicopter having an aerodynamic control flap, particularly a camber flap, is integrated essentially in the contour of the blade profile. The camber flap is swivellably arranged on an axis of rotation and is linked to a control rod of a control device outside the axis of rotation, for converting a linear movement into a swivelling movement of the control flap. The control device is disposed by way of roller bearings and bolts aligned in the span direction. Devices are provided which absorb by way of the control flap centrifugal forces of the control device resulting from the rotation of the rotor blade.
Claims25
Rotor blade for a helicopter having an aerodynamic control flap in the form of a camber flap which is integrated essentially in the contour of the blade profile, is swivellably arranged on an axis of rotation and to which a positively actuated control rod is linked outside the axis of rotation, for converting a linear movement into a swivelling movement of the control flap,
- wherein the control device is supported at the camber flap by way of roller bearings and bolts aligned in a blade span direction, and devices are provided which absorb by way of the control flap centrifugal forces of the control device resulting from the rotation of the rotor blade.
A helicopter rotor blade assembly comprising:
- a blade exhibiting a blade profile,
- a camber flap integrated into the blade profile, and
- a camber flap support assembly operable to support the camber flap in the blade for pivotal adjusting movements about a camber flap axis extending in a blade span direction, and
- a positively actuated transmission mechanism operable to transmit adjusting forces from an adjusting member to the camber flap,
- said transmission mechanism including roller bearings and at least one bolt aligned in the blade span direction and a centrifugal thrust absorber operable to absorb centrifugal forces between the transmission mechanism and the camber flap which result from rotation of the rotor blade.
A helicopter rotor blade assembly according to clam 20,
- wherein the thrust bearing includes a roller bearing ball interposed between an end of the at least one bolt and a hollow socket at the camber flap.
Rotor blade for a helicopter having an aerodynamic control flap in the form of a camber flap which is integrated essentially in the contour of the blade profile, is swivellable arranged on an axis of rotation and to which a control rod is linked outside the axis of rotation, for converting a linear movement into a swiveling movement of the control flap,
- wherein the control device is disposed by way of roller bearings and bolts aligned in a blade span direction, and devices are provided which absorb by way of the control flap centrifugal forces of the control device resulting from the rotation of the rotor blade;
- wherein the devices for absorbing the centrifugal forces include a roller bearing ball situated in a bolt and a hollow socket supporting the latter;
- and
- wherein the radius of the hollow socket is larger than the radius of the roller bearing ball.
Rotor blade for a helicopter having an aerodynamic control flap in the form of a camber flap which is integrated essentially in the contour of the blade profile, is swivellably arranged on a axis of rotation and to which a control rod is linked outside the axis of rotation, for converting a linear movement into a swiveling movement of the control flap,
- wherein the control device is disposed by way of roller bearings and bolts aligned in a blade span direction, and devices are provided which absorb by way of the control flap centrifugal forces of the control device resulting from the rotation of the rotor blade;
- and
- wherein the roller bearing ball consists of steel and the hollow socket consists of synthetic sapphire.
Dependencies are inferred from the claim text.