Abstract: A rotor lock assembly for locking a rotor of a wind turbine. The rotor lock assembly has at least one relocatable rotor lock. The relocatable rotor lock has a housing, a bushing element, a pin shaft position within the bushing element, and a locking mechanism. The housing includes a mounting portion adapted for mounting to a bearing housing adjacent to a rotor lock plate of the rotor.

Abstract: A system for delivering an implant device to a vascular site in a patient a delivery pusher apparatus, an implant device detachably connected to the delivery pusher apparatus by a tether having a distal end connected to a proximal end of the implant device, wherein the tether is substantially non-tensioned when connecting the implant device to the delivery pusher, and an electrical heating element configured coaxially around at least a portion of the tether, wherein heat generated by the heating element severs the tether at a point near the proximal end of the implant device.

Abstract: A vibration control assembly includes a housing having an interior region and an inner mass including a cage disposed within the interior region of the housing and being rotatable within the housing about a first axis and a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis. At least one driving source includes a stator and is operable to interact with a magnetic field of the inner mass to drive rotation of the inner mass about at least one of the first axis and the second axis, wherein the at least one driving source is mounted within the interior region of the housing.

Abstract: A rotary blade aircraft includes an airframe, a rotor shaft driven about a rotor axis, and a plurality of rotor blades driven by the rotor shaft about the rotor axis. The rotary blade aircraft includes a swashplate assembly coupled to the plurality of rotor blades. The swashplate assembly is operable to move the plurality of rotor blades about a respective longitudinal axis. The rotary blade aircraft includes a hydraulic control servo coupled between the airframe and the swashplate assembly. The hydraulic control servo is operable to move the swashplate assembly relative to the rotor axis. The rotary blade aircraft includes a harmonic control actuator coupled between the airframe and the swashplate assembly. The harmonic control actuator is operable independently relative to the hydraulic control servo to move the swashplate assembly relative to the rotor axis to reduce vibration at selected frequencies in the airframe.

Abstract: A vibration control assembly includes a housing having an interior region and an inner mass including a cage disposed within the interior region of the housing and being rotatable within the housing about a first axis and a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis. At least one driving source includes a stator and is operable to interact with a magnetic field of the inner mass to drive rotation of the inner mass about at least one of the first axis and the second axis, wherein the at least one driving source is mounted within the interior region of the housing.

Abstract: A rotary blade aircraft includes an airframe, a rotor shaft driven about a rotor axis, and a plurality of rotor blades driven by the rotor shaft about the rotor axis. The rotary blade aircraft includes a swashplate assembly coupled to the plurality of rotor blades. The swashplate assembly is operable to move the plurality of rotor blades about a respective longitudinal axis. The rotary blade aircraft includes a hydraulic control servo coupled between the airframe and the swashplate assembly. The hydraulic control servo is operable to move the swashplate assembly relative to the rotor axis. The rotary blade aircraft includes a harmonic control actuator coupled between the airframe and the swashplate assembly. The harmonic control actuator is operable independently relative to the hydraulic control servo to move the swashplate assembly relative to the rotor axis to reduce vibration at selected frequencies in the airframe.

Abstract: A rotor system including a rotor hub, a plurality of rotor blades supported by the rotor hub, and a fairing mounted to the rotor hub. The fairing includes an external surface exposed to an external airflow and an internal surface defining an interior portion. A component system is mounted to the rotor hub in the interior portion. The component system includes a first heat generating component and a second heat generating component spaced from the first heat generating component. A cooling duct is arranged between the first heat generating component and the second heat generating component.

Abstract: A computer-implemented method and system for transmitting power and data together in a rotorcraft using a slip ring assembly is disclosed. According to one example, a computer-implemented method includes providing a slip ring assembly comprising a stationary element coupled to an airframe of a rotorcraft and a rotatable element rotatable relative to the stationary element and coupled to a rotor assembly of the rotorcraft. Power is transmitted from a power source associated with the airframe to an electronic device associated with the rotor assembly, the slip ring assembly being configured to complete an electrical circuit between the power source and the electronic device to provide power from the power source to the electronic device. Data is transmitted from a first data transceiver associated with the airframe to a second data transceiver associated with the rotor assembly via the electrical circuit completed by the slip ring assembly.

Abstract: Provided are a computer program product, system, and method embodiments for reverting from a new security association to a previous security association in response to an error during a rekey operation. The responder maintains a first security association with the initiator having a first key to use to encrypt and decrypt messages transmitted with the initiator. The responder receives a message from the initiator for a rekey operation to establish a second security association with the initiator using a second key. The responder queues Input/Output (I/O) for transmission using the second key after completing the rekey operation. After activating the second security association, the responder receives a revert message from the initiator to revert back to using the first security association and first key in response to a failure of the rekey operation.

Abstract: Provided are a computer program product, system, and method embodiments for reverting from a new security association to a previous security association in response to an error during a rekey operation. An initiator maintains a first security association with the responder having a first key to use to encrypt and decrypt data transmitted with the responder. The initiator initiates a rekey operation to establish a second security association with the responder using a second key. The initiator detects a failure of the rekey operation after the responder started using the second key for transmissions. A revert message is sent to the responder to revert back to using the first security association and first key in response to detecting the failure of the rekey operation.

Abstract: A vibration control assembly for an aircraft including a housing operatively coupled to the aircraft. Also included is a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis. Further included is a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle.

Abstract: Provided are a computer program product, system and method embodiments for secure communication between an initiator and a responder over a network. The responder receives, from the initiator, a security association initialization message to establish a security association with the responder including key material used to generate a key for the security association. The responder receives an authentication message from the initiator to program the responder to establish authentication between the responder and the initiator after establishing the security association. The responder sends an authentication message response to the initiator to establish authentication with the responder in response to the authentication message. The responder sends an authentication done message to the initiator after sending the authentication message response to cause the initiator to activate using the security association and the key to encrypt and decrypt communication between the responder and initiator.

Abstract: A rotor system including a rotor hub, a plurality of rotor blades supported by the rotor hub, and a fairing mounted to the rotor hub. The fairing includes an external surface exposed to an external airflow and an internal surface defining an interior portion. A component system is mounted to the rotor hub in the interior portion. The component system includes a first heat generating component and a second heat generating component spaced from the first heat generating component. A cooling duct is arranged between the first heat generating component and the second heat generating component.

Abstract: Provided are a computer program product, system and method embodiments for secure communication between an initiator and a responder over a network. The initiator sends a security association initialization message to the responder to establish a security association including key material used to generate a key for the security association. In response to receiving a security association initialization response to accept the security association, the initiator sends an authentication message to the responder to establish authentication between the responder and the initiator. In response to receiving an authentication message response to the authentication message, the initiator is programmed with the security association. An authentication done message is received from the responder after receiving the authentication message response.

Abstract: A rotor system includes a rotor hub, a plurality of rotor blades supported by the rotor hub, and a fairing mounted to the rotor hub. The fairing includes an external surface exposed to an external airflow and an internal surface defining an interior portion. One or more heat generating components are arranged in the interior portion. A cooling system is arranged in the interior portion. The cooling system includes a first heat exchanger thermally connected to each of the one or more heat generating components, a second heat exchanger mounted to the fairing, and at least one fluid conduit extending therebetween so as to remove heat generated by each of the one or more heat generating components.

Abstract: A vibration control assembly includes a housing having an interior region and an inner mass including a cage disposed within the interior region of the housing and being rotatable within the housing about a first axis and a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis. At least one driving source includes a stator and is operable to interact with a magnetic field of the inner mass to drive rotation of the inner mass about at least one of the first axis and the second axis, wherein the at least one driving source is mounted within the interior region of the housing.

Abstract: A vibration control assembly for an aircraft including a housing operatively coupled to the aircraft. Also included is a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis. Further included is a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle.

Abstract: An active vibration control system for an aircraft includes a gearbox operably coupling a power source and a component rotatable about an axis. The gearbox includes a flexible region which allows flexure between a first stage and a second stage. At least one active vibration control actuator is arranged in vibrational communication with the flexible region to counteract vibrations transmitted between the power source and the rotatable component.

Abstract: Provided are a computer program product, system, and method embodiments for reverting from a new security association to a previous security association in response to an error during a rekey operation. An initiator maintains a first security association with the responder having a first key to use to encrypt and decrypt data transmitted with the responder. The initiator initiates a rekey operation to establish a second security association with the responder using a second key. The initiator detects a failure of the rekey operation after the responder started using the second key for transmissions. A revert message is sent to the responder to revert back to using the first security association and first key in response to detecting the failure of the rekey operation.

Abstract: Provided are a computer program product, system, and method embodiments for reverting from a new security association to a previous security association in response to an error during a rekey operation. The responder maintains a first security association with the initiator having a first key to use to encrypt and decrypt messages transmitted with the initiator. The responder receives a message from the initiator for a rekey operation to establish a second security association with the initiator using a second key. The responder queues Input/Output (I/O) for transmission using the second key after completing the rekey operation. After activating the second security association, the responder receives a revert message from the initiator to revert back to using the first security association and first key in response to a failure of the rekey operation.