Abstract: A cord connector may be used for holding one or more cords. The cord connector includes a first body, a second body, and a bushing. The second body is removably coupled to the first body. The bushing is disposed between the first body and the second body. The bushing includes at least two bushing passages extending from a first end of the bushing toward a second end of the bushing. Each bushing passage is sealed with a membrane. The membrane is disposed within the bushing passage between the first end and the second end. The membrane is configured to be pierced to open the bushing passage.

Abstract: An aircraft comprises an aircraft component, a sensor, and a multiple frequency vibration absorber (absorber). The sensor is operable to detect a frequency of a vibration of the aircraft component. The absorber is coupled to the aircraft component and configured to absorb the vibration. The absorber comprises a beam element, a fluidic flexible matrix composite (FFMC) tube, a valve, and a controller. The beam element is attached to the aircraft component. The fluidic flexible matrix composite (FFMC) tube is coupled to the beam element and is operable to absorb the vibration based on a stiffness of the FFMC tube. The valve is fluidically coupled to the FFMC tube and is to control the stiffness of the FFMC tube based on regulating a flow of a liquid through the FFMC tube. The controller can actively control absorption of the vibration via the FFMC tube based on opening and/or closing the valve.

Abstract: In an embodiment, a rotorcraft includes an airframe; a main rotor transmission; one or more brackets mounting the main rotor transmission to the airframe, longitudinal axes of the one or more brackets being substantially parallel with a longitudinal axis of the rotorcraft; and one or more restraints mounting the main rotor transmission to the airframe, the one or more restraints being mounted at an angle non-orthogonal to the longitudinal axis of the rotorcraft and a lateral axis of the rotorcraft.

Abstract: A drug delivery system for injecting a medicament may include a housing defining a cavity, a container received within the cavity and configured to receive a medicament with the container including a closure, a valve assembly received within the cavity and including a piercing member configured to pierce the closure of the container, and a connector arrangement provided between the container and the valve assembly, the connector arrangement movable between a first, pre-use position maintaining sterility between the closure of the container and the valve assembly and a second, use position permitting fluid communication between the container and the valve assembly.

Abstract: A delivery device for delivering a medical fluid to a patient has a housing configured for receiving a container at least partially filled with the medical fluid. The delivery device further has a drive mechanism associated with the housing configured for delivering the medical fluid from the container to the patient in a dosing procedure. The delivery device further has a module configured for detecting at least one of a property of the dosing procedure and a property of the medical fluid. The module has at least one dose detection sensor configured for detecting an initiation, progression, and completion of the dosing procedure based on a position of a stopper within the container. The module further has at least one temperature sensor configured for measuring a temperature of the medical fluid within the container based on a temperature of the container.

Abstract: In an embodiment, a rotorcraft includes an airframe; a main rotor transmission; one or more brackets mounting the main rotor transmission to the airframe, longitudinal axes of the one or more brackets being substantially parallel with a longitudinal axis of the rotorcraft; and one or more restraints mounting the main rotor transmission to the airframe, the one or more restraints being mounted at an angle non-orthogonal to the longitudinal axis of the rotorcraft and a lateral axis of the rotorcraft.

Abstract: A drug delivery system for injecting a medicament may include a housing defining a cavity, a container received within the cavity and configured to receive a medicament with the container including a closure, a valve assembly received within the cavity and including a piercing member configured to pierce the closure of the container, and a connector arrangement provided between the container and the valve assembly, the connector arrangement movable between a first, pre-use position maintaining sterility between the closure of the container and the valve assembly and a second, use position permitting fluid communication between the container and the valve assembly.

Abstract: A delivery device for delivering a medical fluid to a patient has a housing configured for receiving a container at least partially filled with the medical fluid. The delivery device further has a drive mechanism associated with the housing configured for delivering the medical fluid from the container to the patient in a dosing procedure. The delivery device further has a module configured for detecting at least one of a property of the dosing procedure and a property of the medical fluid. The module has at least one dose detection sensor configured for detecting an initiation, progression, and completion of the dosing procedure based on a position of a stopper within the container. The module further has at least one temperature sensor configured for measuring a temperature of the medical fluid within the container based on a temperature of the container.

Abstract: A liquid inertia vibration eliminator unit for an aircraft having first and second components includes an outer housing coupled to the first component of the aircraft, the outer housing forming an outer housing cavity. The liquid inertia vibration eliminator unit includes a spherical bearing disposed in the outer housing cavity and forming a spherical bearing cavity. A piston is disposed in the spherical bearing cavity and coupled to the second component of the aircraft. Top and bottom fluid chambers are disposed in the spherical bearing cavity on opposite sides of the piston. A tuning passage provides fluid communication between the top and bottom fluid chambers. A tuning fluid moves between the top and bottom fluid chambers via the tuning passage to isolate vibration between the first and second components of the aircraft.

Abstract: A cord connector may be used for holding one or more cords. The cord connector includes a first body, a second body, and a bushing. The second body is removably coupled to the first body. The bushing is disposed between the first body and the second body. The bushing includes at least two bushing passages extending from a first end of the bushing toward a second end of the bushing. Each bushing passage is sealed with a membrane. The membrane is disposed within the bushing passage between the first end and the second end. The membrane is configured to be pierced to open the bushing passage.

Abstract: A liquid inertia vibration elimination (“LIVE”) system for a rotor system having n number of blades. The LIVE system includes a first tuned vibration reduction component configured to provide a maximum vibratory isolation at a frequency below 2*n/rev and a second tuned vibration reduction component configured to provide a maximum vibratory isolation at a frequency above 3*n/rev.

Abstract: The present invention includes a damper assembly, method and kit to provide dampening to an airframe comprising: a mass to dampen the vibration of the airframe; one or more wire rope isolators having a first and a second portion, wherein the mass is attached to the one or more wire rope isolators and the mass is isolated from the airframe by the one or more wire rope isolators; and a first fastener and a second fastener, wherein the first fasteners attaches to the first portion of the wire rope isolator to the mass, and the second fastener attaches the second portion of the wire rope isolator to the airframe to dampen vibration of the airframe.

Abstract: A liquid inertia vibration eliminator unit for an aircraft having first and second components includes an outer housing coupled to the first component of the aircraft, the outer housing forming an outer housing cavity. The liquid inertia vibration eliminator unit includes a spherical bearing disposed in the outer housing cavity and forming a spherical bearing cavity. A piston is disposed in the spherical bearing cavity and coupled to the second component of the aircraft. Top and bottom fluid chambers are disposed in the spherical bearing cavity on opposite sides of the piston. A tuning passage provides fluid communication between the top and bottom fluid chambers. A tuning fluid moves between the top and bottom fluid chambers via the tuning passage to isolate vibration between the first and second components of the aircraft.

Abstract: In an embodiment, a rotorcraft includes an airframe; a main rotor transmission; one or more brackets mounting the main rotor transmission to the airframe, longitudinal axes of the one or more brackets being substantially parallel with a longitudinal axis of the rotorcraft; and one or more restraints mounting the main rotor transmission to the airframe, the one or more restraints being mounted at an angle non-orthogonal to the longitudinal axis of the rotorcraft and a lateral axis of the rotorcraft.

Abstract: An aircraft comprises an aircraft component, a sensor, and a multiple frequency vibration absorber (absorber). The sensor is operable to detect a frequency of a vibration of the aircraft component. The absorber is coupled to the aircraft component and configured to absorb the vibration. The absorber comprises a beam element, a fluidic flexible matrix composite (FFMC) tube, a valve, and a controller. The beam element is attached to the aircraft component. The fluidic flexible matrix composite (FFMC) tube is coupled to the beam element and is operable to absorb the vibration based on a stiffness of the FFMC tube. The valve is fluidically coupled to the FFMC tube and is to control the stiffness of the FFMC tube based on regulating a flow of a liquid through the FFMC tube. The controller can actively control absorption of the vibration via the FFMC tube based on opening and/or closing the valve.

Abstract: A drug delivery system for injecting a medicament includes a container including a closure and a stopper configured to move within the container from a pre-use position to a post-use position. The system includes a drive assembly configured to move the stopper between first and second positions, and a spacer assembly engaged with the stopper configured to be engaged by the drive assembly. The spacer assembly includes a first spacer portion received within the stopper, a second spacer portion spaced from the first spacer portion, an inner plunger, and a spacer shuttle received by the inner plunger. The inner plunger, the spacer shuttle, and the second portion are configured to move relative to the stopper, where movement of the second spacer portion is restricted by the spacer shuttle, movement of the spacer shuttle is restricted by the inner plunger, and movement of the inner plunger is restricted by the stopper.

Abstract: A drug delivery system for injecting a medicament includes a container including a closure and a stopper configured to move within the container from a pre-use position to a post-use position. The system includes a drive assembly configured to move the stopper between first and second positions, and a spacer assembly engaged with the stopper configured to be engaged by the drive assembly. The spacer assembly includes a first spacer portion received within the stopper, a second spacer portion spaced from the first spacer portion, an inner plunger, and a spacer shuttle received by the inner plunger. The inner plunger, the spacer shuttle, and the second portion are configured to move relative to the stopper, where movement of the second spacer portion is restricted by the spacer shuttle, movement of the spacer shuttle is restricted by the inner plunger, and movement of the inner plunger is restricted by the stopper.

Abstract: The present invention includes a damper assembly, method and kit to provide dampening to an airframe comprising: a mass to dampen the vibration of the airframe; one or more wire rope isolators having a first and a second portion, wherein the mass is attached to the one or more wire rope isolators and the mass is isolated from the airframe by the one or more wire rope isolators; and a first fastener and a second fastener, wherein the first fasteners attaches to the first portion of the wire rope isolator to the mass, and the second fastener attaches the second portion of the wire rope isolator to the airframe to dampen vibration of the airframe.

Abstract: A drug delivery system for injecting a medicament may include a housing defining a cavity, a container received within the cavity and configured to receive a medicament with the container including a closure, a valve assembly received within the cavity and including a piercing member configured to pierce the closure of the container, and a connector arrangement provided between the container and the valve assembly, the connector arrangement movable between a first, pre-use position maintaining sterility between the closure of the container and the valve assembly and a second, use position permitting fluid communication between the container and the valve assembly.

Abstract: The present invention includes a damper assembly, method and kit to provide dampening to an airframe comprising: a mass to dampen the vibration of the airframe; one or more wire rope isolators having a first and a second portion, wherein the mass is attached to the one or more wire rope isolators and the mass is isolated from the airframe by the one or more wire rope isolators; and a first fastener and a second fastener, wherein the first fasteners attaches to the first portion of the wire rope isolator to the mass, and the second fastener attaches the second portion of the wire rope isolator to the airframe to dampen vibration of the airframe.