Curtiss Wright Flight Systems, Inc.

Robert K Tiedeman

Michael A Palma

Arnold G Seipel

William C Leuze

A jam-tolerant rotary actuator 70 through the incorporation of shear lugs 84,92 formed on an inner input sun gear member 82 and on an inner movable output ring gear member 90 which correspond to recesses 88,96 formed in an outer input sun gear member 86 and in an outer movable output ring gear member 94, respectively, where, upon application of a maximum torque to either the inner input sun gear member 82 or the outer movable output ring gear member 94, the shear lugs 84,92 will shear thereby allowing the inner input sun gear member 82 to be movable independent of the outer input sun gear member 86 or the outer movable output ring gear member 94 to be movable independent of the inner movable output ring gear member 90, respectively.

Jam-tolerant rotary actuator

A rotary geared actuator for pivotally connecting a flap to a wing of an aircraft, includes at least two adjacent actuator slices rotatably coupled together, each actuator slice including a sun gear rotatably coupled to a drive shaft and having gear teeth with a curved profile to enable movement of the actuator slices with respect to each other in conformance with bending of the wing, planetary gears in surrounding and meshing engagement with the gear teeth of the sun gear, a movable ring gear in surrounding and meshing engagement with the planetary gears, and a fixed ring gear in surrounding and meshing engagement with the planetary gears on opposite sides of the movable ring gear, each fixed ring gear being in meshing engagement only with planetary gears of one actuator slice; at least one fixed side tie bar connecting each fixed ring gear with the wing; at least one movable flap side tie bar connecting each movable ring gear with the flap; securing pins for securing each fixed side tie bar to one fixed ring gear and each movable flap side tie bar to one movable ring gear so as to permit a small axial movement between at least one tie bar and the respective fixed ring gear and/or movable ring gear; and a coupling shaft which flexibly connects an outermost sun gear of the actuator to a drive shaft.

Rotary actuator for leading edge flap of aircraft

A rotary hinge actuator, for instance for rotating a wing flap relative to a wing in an aircraft, has a sun gear, several spindle gears around the sun gear and several annular gear sleeves around the sun gear and spindle gears. Each spindle gear has sections with external helical gear teeth which are slanted in the same direction and which respectively mesh with internal helical gear teeth on the annular gear sleeves. At least one of the sleeves is connected to the wing and at least another to the wing flap. Upon rotating the spindle gears the wing flap is rotated relative to the wing.

Rotary hinge actuator

The bidirectional, torque-limiting, drive and brake mechanism has an input and output drive shafts and a helical spring which is normally in interference fit with the mechanism housing and, in the torque transmitting mode of operation, is disengaged to permit torque transmission by a direct mechanical coupling between the input and output drive shafts. The torque-limiting component, which functions to interrupt transmission of rotation from the input drive shaft to the output drive shaft upon a predetermined torque load, is adjustable to a selected predetermined torque load in the field.

Bidirectional, torque-limiting, no-back clutch mechanism

A dual function torque limiter/no-back device for limiting torque to an output member and for preventing transmission of torque from such output member comprising a casing, an input member supported for rotation in the casing and connected to a source of rotary power to be driven by the latter. Also an output member is supported for rotation in the casing and connected to a load to be rotated. A drive coupling assembly is connected to the input and output members for transmitting torque from the input member to the output member and having torque response means operative at a predetermined torque value. A brake assembly is disposed in the housing and is operative to positions of engagement and disengagement. A brake coupling assembly is provided for connecting the drive coupling assembly, the output member and the brake assembly to effect engagement of the brake assembly upon the predetermined torque value being reached and for effecting engagement of the brake assembly upon torque being transmitted from the output member.

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Wayne, NJ, United States of America

Robert K Tiedeman