Abstract: A force-shunting device including a tube defining a main axis and an inner wall, a first member sliding within the tube, a primary leg arranged obliquely, attached to the first member and including a primary pad in frictional contact with the inner wall, such that, when an external force is applied in a first direction on the first member, the primary leg rubs, or grips by mechanical camming, against the inner wall, the tube thus reacting all or part of the external force, the device including a second member mounted within the tube, sliding along the main axis and securely provided with a driving element of the primary pad so as to reduce the friction on the inner wall, to unprime the rubbing or mechanical camming.

Abstract: Actuators are components of machines, which move and/or control a mechanism or system. During operation, actuators can experience regeneration events, with the actuator actually generating excess energy (e.g., regenerative energy) which must be stored or dissipated to avoid damaging the power supply. An actuator motor controller is configured to implement field oriented voltage control and flux weakening voltage control without current sensors. Dissipating regenerative energy includes providing a motor controller to command a motor drive to modify an input voltage, or to dissipate regenerative energy in a dump circuit. This command can cause motor windings to dissipate regenerative energy. Systems having a plurality of actuators distribute regenerative energy from one actuator to another. A central controller provides centralized regeneration dissipation control for the plurality of actuators.

Abstract: A vehicle active vibration control (AVC) system includes a vehicle having at least an engine, a transmission, a controller area network (CAN) bus, a frame, and a cabin. The vibration control devices (120) are distributed about the frame, with each device including a circular force generator (CFG) (122). At least one sensor is positioned on the frame to detect and measure a noise and/or vibration within the cabin. Each sensor creates an electronic data signal and electrically communicates with a corresponding vibration control device. Each vibration control device receives an electronic data signal from a corresponding sensor and vehicle data from the CAN bus. Each vibration control device processes the electronic data signal and the vehicle data. The CFG of each vibration control device generates a vibration canceling force having a magnitude and phase that attenuates noise and/or vibration within the cabin.

Abstract: The invention relates to an improved throttle control system for an aircraft. The throttle system includes providing friction to the throttle to maintain the position of the throttle until the pilot overcomes the friction by using force to move the throttle. The throttle is attached to and positioned about a shaft to provide rotatable movement. The invention uses a first and second friction resistance to maintain the position of the throttle along with an automatic regulating device capable of automatically controlling rotation of the shaft having a geared motor assembly.

Abstract: The force feedback device includes a stationary housing intended to be secured to an understructure of an aircraft, at least one spring opposing movement of a side-stick of the aircraft relative to the housing, and a transmission mechanism, which is supported by the housing movably and which is suitable for transmitting a rotational movement, around a first rotation axis, between the side-stick and said at least one spring, by applying a force law according to which a resistive force, opposed by said at least one spring, via the transmission mechanism, against the rotational movement of the side-stick around the first rotation axis, depends on an angular position of the side-stick around the first rotation axis.

Abstract: A magnetically-responsive device (100) having a magnetic seal (160,170) to retain magnetically responsive material within a defined space (150) is provided. The magnetically-responsive device (100) has a shaft (110), a rotor (130), a magnetic field generator (145), a magnetically-responsive medium and a magnetic seal (160,170). The seal (160,170) is preferably a non-contact seal (160,170) that does not deteriorate over time and generates little to no resistance.

Abstract: Dampers (100), assemblies, and methods are provided for lead-lag damping for an articulated rotor and includes a lead-lag damper (100) having a first end connector (102) configured to be coupled to a rotor hub (H), a second end connector (104) configured to be coupled to one of a plurality of rotor blades (B), and a body portion (110) coupled to the first end connector (102) and to the second end connector (104). The body portion (110) includes one or more elastomeric material layers (120) arranged in a lengthwise direction between the first end connector (102) and the second end connector (104), with each of the elastomeric material layers (120) having a substantially chevron-shaped profile in a crosswise direction.

Abstract: A magnetically-responsive device (100) having a magnetic seal (160,170) to retain magnetically responsive material within a defined space (150) is provided. The magnetically-responsive device (100) has a shaft (110), a rotor (130), a magnetic field generator (145), a magnetically-responsive medium and a magnetic seal (160,170). The seal (160,170) is preferably a non-contact seal (160,170) that does not deteriorate over time and generates little to no resistance.

Abstract: Integrated stator disk devices, systems, and methods for torque generation are provided. The resistive torque-generating device can include an integrated stator disk system including at least one metallic stator disk having a planar disk body, and at least one rotor disposed adjacent to the at least one metallic stator disk such that there are at least two shear areas formed by the at least one metallic stator disk and the at least one rotor; and magneto-rheological material disposed between portions of the at least one metallic stator disk and the at least one rotor. In some embodiments, the rotor(s) is/are a bent rotor(s), thereby providing for increased torque generation while fitting within tight space constraints.

Abstract: A snubber tool can be installed in a downhole tool string to reduce vibration in the downhole tool string. The snubber tool includes two compliance components having different stiffness properties and pre-compression and a drive washer that selectively applies further compression to the compliance components in response to external forces acting on the snubber tool. The compliance components retain their initial pre-compression under external loading of the snubber tool.

Abstract: A flexible joint is provided. The flexible joint is for use in a steel catenary riser that includes a compression bearing (106) having a transition shim (120) and a plurality of alternating flexible elements (116) and shims (118) collectively stacked and bonded to a lower portion of the transition shim (120). The flexible joint also includes an inner bonding material (126) having a profile that is complementary to a profile of an extension tube (104), the inner bonding material (126) being disposed between the extension tube (104) and compression bearing (106) and configured to serve as a bonding mechanism between extension tube and compression bearing.

Abstract: An adhesive composition having two distinct reaction mechanisms, a first being the reaction between a tri-functional isocyanate and an active hydrogen compound and a second begin the free radical initiation of an acrylic monomer. This adhesive develops tack strength through the first reaction allowing two substrates to remain in position relative to one another while the free radical cure of the acrylic monomer takes place to fully bond the substrates together, for example when adhering a rubber liner to the inside of a metallic tank.

Abstract: Aft-mounting systems, devices, and methods for turboprop and turboshaft engines include two or more coupling elements 201, 211, 221 that are configured to couple an aft portion of an engine of an aircraft to a support structure of the aircraft. The two or more coupling elements are together configured to react forces generated in a vertical direction and in a lateral direction transverse to the engine but allow substantially unrestricted rotation of the engine with respect to the support structure about an axis of rotation of the engine.

Abstract: Aircraft isolator devices, systems, and methods for isolating a structural component within an aircraft can include an engine interface, airframe, and one or more (e.g., a plurality of) isolator devices attached to the engine interface and the airframe. In some aspects, the isolator devices have a housing, which has a first surface and a second surface that together at least partially define a perimeter of the housing and is configured for attachment to the airframe; an engine attachment component configured for attachment to the engine interface and disposed at least partially inside of the housing; and a plurality of elastomeric elements disposed on or over each of the first and second surfaces of the housing The plurality of elastomeric elements are spaced apart from the engine attachment component via the housing for improved heat dissipation from the engine, reducing operational temperatures of the elastomeric elements to prolong their use.

Abstract: Seat-damping devices, systems, and methods for damping vibrations are disclosed. A fail-safe permanent magnet is used with an electromagnet to create damping of induced vibrations in a seat-damping device using magnetorheological, electrorheological, magnetically responsive powders and other magnetically responsive materials.

Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical bearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: A flight control device of an aircraft including a support, an action member attached to the support rotating freely around a primary axis, a rotary device including a stator, rotatably connected to the support around a secondary axis, and a rotor rotating freely relative to the stator around the secondary axis, the rotary device applying a force sensing torque on the rotor relative to the stator around the secondary axis, and a mechanical reducing gear, which connects, with a reduction ratio, rotation of the action member with rotation of the rotor, the mechanical reducing gear including a screw-nut system with rolling elements, including a screw, attached to the rotor, connected in rotation to the rotor around the secondary axis, and a nut fixed in rotation around the secondary axis relative to the stator and helically connected with the screw around and along the secondary axis via the rolling elements.

Abstract: Electromagnetic locking devices, systems, and methods are provided. The electromagnetic locking devices, systems, and methods are configured to lock an actuating arm of an actuator in any desired position between and including a fully extended position and a fully retracted position with respect to an outer cover of the electromagnetic locking device and/or system. The electromagnetic locking devices, systems, and methods described herein may include an unpowered deformable member that imparts fail-safe functionality thereto.

Abstract: Torque generating devices, systems, and/or related methods are disclosed. In one aspect, a torque generating device (100) may include a housing (102), at least one top and one bottom pole (108), at least one side pole (110), at least two rotors (116) for rotating within the housing, a shaft (104) supported by bearings (111), at least a first stator (120) disposed between portions of the at least two rotors (116), magnetically responsive (MR) material disposed within the housing (102) and at least partially surrounding the first stator (120) and the at least two rotors (116), and a coil (112) for generating a magnetic field, wherein an amount of torque generated by the torque generating device (100) increases in proportion to an amount of electrical current supplied to the coil (112). In another aspect, a method of generating torque may include providing a torque generating device (100) and rotating the at least two rotors (116).

Abstract: The invention provides a system for creating a prescribed vibration profile on a mechanical device comprising a sensor for measuring an operating condition of the mechanical device, a circular force generator for creating a controllable rotating force vector comprising a controllable force magnitude, a controllable force phase and a controllable force frequency, a controller in electronic communication with said sensor and said circular force generator, the controller operably controlling the controllable rotating force vector, wherein the difference between the measured operating condition and a desired operating condition is minimized.