Abstract: In some embodiments, an actuation system includes a plurality of threaded member portions, a plurality of roller nuts, a driving member configured to receive mechanical energy from a power source, a plurality of driven members, and a magnetorheological (MR) fluid disposed between the plurality of driven members and at least one braking surface. An output member may be coupled between the rotor system and either the plurality of threaded member portions or the plurality of roller nuts and configured to translate linearly in response to the threaded member portions advancing or receding within the roller nuts.

Abstract: According to one embodiment, a radial fluid device comprises a cylinder block, a first plurality of pistons, a second plurality of pistons, a first cam, a second cam, and a cam rotation device. Each of the first plurality of pistons are slidably received within a different one of a first plurality of radially extending cylinders. Each of the second plurality of pistons are slidably received within a different one of a second plurality of radially extending cylinders. The first cam is disposed about the first plurality of radially extending cylinders. The second cam is disposed about the second plurality of radially extending cylinders. The cam rotation device is coupled to the first cam and the second cam. The cam rotation device is operable to rotate the first cam in a first direction and the second cam in a second direction.

Abstract: In some embodiments, an aircraft may include a retractable or extendable landing gear. The landing gear may include a wheel connected to an axle, a strut configured to resist longitudinal compression, and a linear actuator that is partially disposed within an opening of the strut.

Abstract: In some embodiments, an actuation system includes a an actuator assembly, a yoke, and a control rod. The actuator assembly comprises a first actuator. The first actuator is configured to extend in a first direction and retract in a second direction opposite of the first direction. The yoke is coupled to the first actuator at a first actuator end proximate to the first direction. The control rod is coupled to the yoke at a first control rod end and extends in the second direction past the actuator assembly to a second end in mechanical communication with an output device.

Abstract: According to one embodiment, a radial fluid device comprises a cylinder block, first and second pluralities of pistons, a first cam disposed about the first plurality of radially extending cylinders, and a second cam disposed about the second plurality of radially extending cylinders. The direction of rotation of the second cam is independent of the direction of rotation of the first cam.

Abstract: According to one embodiment, a radial fluid device comprises a cylinder block, a first plurality of pistons, a second plurality of pistons, a first cam, a second cam, and a coupling device. Each of the first plurality of pistons are slidably received within a different one of a first plurality of radially extending cylinders. Each of the second plurality of pistons are slidably received within a different one of a second plurality of radially extending cylinders. The first cam is disposed about the first plurality of radially extending cylinders. The second cam is disposed about the second plurality of radially extending cylinders. The coupling device is operable to couple the cylinder block to a cylinder block of a second radial fluid device.

Abstract: A speed control assembly includes an input drive shaft coupled to a first gear subassembly having a rotatable gear, a second gear subassembly coupled to an output drive shaft, and a linkage coupling the first and second gear subassemblies, wherein the input drive shaft, the first and second gear subassemblies, and the linkage are configured such that a rotational speed of the rotatable gear adjusts a ratio of a rotational speed of the output drive shaft to a rotational speed of the output drive shaft. In some embodiments, the first gear subassembly includes a sun gear coupled to the input drive shaft, one or more planet gears, and a ring gear as the rotatable gear. In some embodiments, the second gear subassembly includes a sun gear coupled to the output drive shaft, one or more planet gears, and a fixed ring gear.

Abstract: According to one embodiment, a radial fluid device comprises a cylinder block, a first plurality of pistons including a first piston, and a second plurality of pistons including a second piston. Each of the first plurality of pistons are slidably received within a different one of a first plurality of radially extending cylinders. Each of the second plurality of pistons are slidably received within a different one of a second plurality of radially extending cylinders. The second piston is configurable to begin its stroke at a different time relative to the first piston within the first cylinder pair.

Abstract: A system and method to diagnosis an actuator of a flight control system. The system and method includes interfacing a diagnostic computer to the flight control system, commanding movement of an actuator with the diagnostic computer via the flight control system, measuring performance of the actuator via the diagnostic computer, and comparing the measured performance of the actuator with allowable performance values.

Abstract: A tiltrotor aircraft can include a pylon rotatable about a conversion axis. A first differential planetary assembly can include a first housing; a first ring gear; a first differential planetary gear having a first output portion; and a first differential sun gear. A second differential planetary assembly can include a second housing; a second ring gear; a second differential planetary gear having a second output portion; and a second differential sun gear. The first output portion is coupled to the second housing such that the second housing rotates at a first output speed. Further, the second output portion is coupled to the shaft, the shaft being coupled to the pylon such that rotation of the shaft rotates the pylon.

Abstract: A heater system includes a bag forming a cavity, a fluid bladder carried within the cavity and forming a fluidly sealed chamber. The fluid bladder being configured to store electrorheological fluid within a fluidly sealed chamber. The heater system further including an electrical wire in fluid communication with the electrorheological fluid and a heater blanket carried within the cavity. The method includes altering the electrorheological fluid with a current and providing heat with a heater blanket.

Abstract: A rotorcraft actuator monitoring system to monitor leakage past dynamic rotorcraft actuator seals of a rotorcraft actuator includes a body member and a fluid level indication housing attached to the body member. The body member is mounted to surround a dynamic rotorcraft actuator seal that seals fluid in a rotorcraft actuator, where the body member captures fluid that leaks past the dynamic rotorcraft actuator seal. The fluid level indication housing collects the fluid captured by the body member and indicates that a predetermined volume of fluid that leaked past the dynamic rotorcraft actuator seal has been collected.

Abstract: According to one embodiment, a radial fluid device contains a cylinder block mounted for rotation, a first and second plurality of radially extending cylinders, and a first and second cam. The cylinder block contains the first and second plurality of radially extending cylinders, and each radially extending cylinder contains a piston. The cams are disposed about each plurality of radially extending cylinders, and the second cam has at least one more lobe than the first cam.

Abstract: The main rotor control system includes a rise/fall swashplate assembly that is coupled to three triplex actuators. The swashplate assembly is configured to provide full collective and cyclic pitch controls. Each triplex actuator includes three piston/cylinder assemblies in parallel. Selective actuation of each triplex actuator is controlled by a fly-by-wire system in conjunction with three flight control computers and three hydraulic power packs. Integrated three function valves can be associated with an individual manifold for each piston/cylinder assembly of each triplex actuator, the integrated three function valve be configured to insure safe operation of the triplex actuator during a failure of a certain piston/cylinder assembly.

Abstract: According to one embodiment, a rotor blade rotation system includes a hub, a rotor blade in mechanical communication with the hub and pivotable about an axis of rotation, a swashplate, a pitch link, and an actuator. The swashplate includes a rotating portion and a non-rotating portion. The pitch link is coupled to the rotating portion of the swashplate and in mechanical communication with the rotor blade. The actuator is coupled to the non-rotating portion of the swashplate and operable to reposition the swashplate from a first position to a second position such that the pitch links pivot the rotor blade from a deployed position to a folded position.

Abstract: According to one embodiment, a rotor blade rotation system includes a hub, a rotor blade in mechanical communication with the hub and pivotable about an axis of rotation, a swashplate, a pitch link, and an actuator. The swashplate includes a rotating portion and a non-rotating portion. The pitch link is coupled to the rotating portion of the swashplate and in mechanical communication with the rotor blade. The actuator is coupled to the non-rotating portion of the swashplate and operable to reposition the swashplate from a first position to a second position such that the pitch links pivot the rotor blade from a deployed position to a folded position.

Abstract: A speed control assembly includes an input drive shaft coupled to a first gear subassembly having a rotatable gear, a second gear subassembly coupled to an output drive shaft, and a linkage coupling the first and second gear subassemblies, wherein the input drive shaft, the first and second gear subassemblies, and the linkage are configured such that a rotational speed of the rotatable gear adjusts a ratio of a rotational speed of the output drive shaft to a rotational speed of the output drive shaft. In some embodiments, the first gear subassembly includes a sun gear coupled to the input drive shaft, one or more planet gears, and a ring gear as the rotatable gear. In some embodiments, the second gear subassembly includes a sun gear coupled to the output drive shaft, one or more planet gears, and a fixed ring gear.

Abstract: In some embodiments, a redundant control system includes first and second control systems, having first and second clutches, and a shared clutch system. The shared clutch system may include a shared shaft configured to receive mechanical energy from a shared power source, a first shared clutch corresponding to the first clutch and configured to receive mechanical energy from the shared shaft, and a second shared clutch corresponding to the second clutch and configured to receive mechanical energy from the shared shaft. A first linkage provides mechanical communication between an output of the first clutch, an output of the first shared clutch, and a first output device in mechanical communication with the rotor system. A second linkage provides mechanical communication between an output of the second clutch, an output of the second shared clutch, and a second output device in mechanical communication with the rotor system.

Abstract: In some embodiments, an actuation system includes a plurality of threaded member portions, a plurality of roller nuts, a driving member configured to receive mechanical energy from a power source, a plurality of driven members, and a magnetorheological (MR) fluid disposed between the plurality of driven members and at least one braking surface. An output member may be coupled between the rotor system and either the plurality of threaded member portions or the plurality of roller nuts and configured to translate linearly in response to the threaded member portions advancing or receding within the roller nuts.

Abstract: In some embodiments, a rotorcraft flight control actuator includes a driving member configured to receive mechanical energy from a power source, a driven member, a magnetorheological (MR) fluid disposed between the driving member and the driven member and configured to transmit a variable amount of mechanical energy from the driving member to the driven member, an output member configured to be coupled between the driven member and a flight control device of a rotor system, and a magnetic circuit configured to deliver a magnetic field towards the MR fluid, the magnetic circuit configured to vary the strength of the magnetic field in response to inputs.