Abstract: A method for managing a digital identity of an entity is disclosed. A domain is provided for the entity, and with a secure certificate, with the domain pointing to one or more hosts. Structured data related to the entity is stored at the one or more hosts. Access rules to the stored structured data are defined for one or more digital identities related to one or more entities. The stored structured data is made accessible to one or more digital identities via a secure connection in a distributed global communication network. The step of making the stored structured data accessible to one or more digital identities includes establishing distributed direct peer-to-peer secure connections between two or more digital identities, using a protocol, and exchanging data among the two or more digital identities in accordance with access rules, via the direct peer-to-peer secure connections.

Abstract: The invention relates to a construction machine for introducing a displacement tube into the ground, wherein the displacement tube comprises a tube base body and, at its lower end, a closure device which comprises at least one closure flap which is adjustable between a closed position, in which the displacement tube is closed downwards by the at least one closure flap, and an open position, in which filling material is discharged from the displacement tube into the ground for forming a filling material column, wherein the construction machine comprises a feed drive for introducing and retracting the displacement tube into and out of the ground, respectively.

Abstract: A system, method, and apparatus provide the ability to generate and deliver digital content in a headless content management system. A layout engine exposes a visual editing interface to a business user and accepts input to compose a layout consisting of components that define structural entities that control what to render. Marketing content is associated with the components. Each component is added, via the visual editing interface, to zones of the layout. Developer code may restrict a type of component that can be added to each zone. The layout and zones control a conceptual design for rendering the digital content. The layout engine receives a request for content from one of multiple different client applications that are executing in different hosting environments. The content is delivered, based on the layout, to the client application for rendering to a consumer.

Abstract: A vibration attenuator has a first spinner configured for rotation about a first axis and a first mass coupled to the first spinner for rotation therewith, the first mass being movable radially relative to the first axis between an inner position and an outer position. An actuator is coupled to the first mass for selectively controlling a radial location of the first mass relative to the axis, and a first motor is configured for driving the first spinner in rotation about the first axis.

Abstract: A method of simulating an aircraft one-engine inoperative (“OEI”) event includes operating a supplemental power unit (“SPU”) at a first SPU power level less than an SPU contingency power rating, operating a primary engine at a first primary-engine power level, reducing the primary-engine power level to less than the first primary-engine power level, and maintaining a sum of the primary-engine power level and the SPU power level at a power level substantially equal to the SPU contingency power rating.

Abstract: A blade pitch adjustment mechanism includes a pitch cylinder having a first face and pitch slots extending longitudinally from the first face, a blade sleeve having a second face and a blade slot extending longitudinally from the second face, the blade sleeve is configured to be rotationally positioned in the pitch cylinder with the second face located with the first face, wherein the blade slot and the pitch slots are cooperative to form keyway, corresponding to a discrete blade pitch, when the blade slot is aligned with a pitch slot.

Abstract: A blade pitch adjustment mechanism includes a pitch cylinder having a first face and pitch slots extending longitudinally from the first face, a blade sleeve having a second face and a blade slot extending longitudinally from the second face, the blade sleeve is configured to be rotationally positioned in the pitch cylinder with the second face located with the first face, wherein the blade slot and the pitch slots are cooperative to form keyway, corresponding to a discrete blade pitch, when the blade slot is aligned with a pitch slot.

Abstract: A vibration attenuation system as shown and described.

Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.

Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.

Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.

Abstract: A bus system is disclosed which comprises a plurality of electrical and/or electronic components coupled to one another in terms of signaling via at least one bus line, said components including at least one master component and at least two slave components. At least one of the slave components functions as a master for one or a plurality of the further slave components for at least one operating parameter. There is additionally disclosed a method for controlling such a bus system comprising a plurality of electrical or electronic components coupled to one another in terms of signalling via at least one bus line, wherein at least one of the slave components operates as a master for one or a plurality of the further slave components for at least one operating parameter.

Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.

Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.

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 switchgear cabinet luminaire comprising illuminants on the basis of light emitting diodes, consisting of an elongated luminaire housing comprising housing main body and light-transmissive cover and electrical connection elements and means for fixing that are provided on the luminaire housing. The luminaire body is embodied in a trough-like fashion and a plurality of spaced-apart cutouts or recesses for releasably receiving a pivoting bearing carrier are provided on the underside of said luminaire body and/or in the side wall region. The pivoting bearing carrier has two side surfaces connected via a web, each side surface having a receptacle for a pivoting spindle. Arms are formed in a manner proceeding from the web and are oriented toward the underside or toward the side wall region of the housing main body and, at the free end of said arms, undergoing transition to a latching lug or to a latching hook.

Abstract: A system, method, and apparatus provide the ability to generate and deliver digital content in a headless content management system. A layout engine exposes a visual editing interface to a business user and accepts input to compose a layout consisting of components that define structural entities that control what to render. Marketing content is associated with the components. Each component is added, via the visual editing interface, to zones of the layout. Developer code may restrict a type of component that can be added to each zone. The layout and zones control a conceptual design for rendering the digital content. The layout engine receives a request for content from one of multiple different client applications that are executing in different hosting environments. The content is delivered, based on the layout, to the client application for rendering to a consumer.

Abstract: According to one embodiment, a rotorcraft front windshield comprises an optically-transparent material having a non-uniform thickness profile such that the front windshield is a first thickness at a first position and a second thickness at a second position, the first thickness being different from the second thickness.

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.