Abstract: A network interface receives portfolio data related to an investment plan portfolio of a participant. A processor identifies a first plurality of risk factors associated with market conditions, wherein the first plurality of risk factors comprises a future data and risk strength. The processor further identifies a second plurality of risk factors associated with the participant. The processor then generates glide path data based at least partially on the first plurality of risk factors and the second plurality of risk factors. The processor also generates a glide path map based at least partially on the generated glide path data.

Abstract: A present system of the present application provides for reticulating adhesive to the surface network of cellular core. As such, the present invention allows for substantial improvements over prior systems. The present invention may be implemented with any aircraft, wind turbine, rocket, space satellite, or land vehicle, but there is nothing within the spirit and scope of the present invention limiting it to any particular application. The teachings of the present invention are useful to any composite structure utilizing cellular core.

Abstract: A composite core includes a plurality of tubes, each the plurality of tubes comprising a plurality of fibers disposed in a polymeric matrix. Adjacent tubes of the plurality of tubes are adhesively bonded to one another along sides of the adjacent tubes. A method of making a composite core includes the steps of providing a plurality of tubes, each of the plurality of tubes including a plurality of fibers disposed in a polymeric matrix, and adhesively bonding adjacent tubes of the plurality of tubes along sides of the adjacent tubes. A method of making a composite core such that a removable band is included in the core, the removable band being configured to be removable through a procedure subsequent to the cure of the composite core, thereby producing gaps in the core.

Abstract: The present application relates a core member for a core-stiffened structural assembly. The core member includes a plurality of cell members oriented a direction to provide a tailored stiffness in a certain direction. The core member can further include one or more planar members that can aid in shear transfer between cell members. The cell members can be made from bonding a plurality of corrugated layers together. The core-stiffened structure can be a rotor blade for an aircraft. In such an embodiment, the torsional stiffness of the rotor blade can be tailored in at least one of the chordwise and spanwise directions to provide tailor a torsional stiffness at any give location in the rotor blade.

Abstract: A composite core includes a plurality of tubes, each the plurality of tubes comprising a plurality of fibers disposed in a polymeric matrix. Adjacent tubes of the plurality of tubes are adhesively bonded to one another along sides of the adjacent tubes. A method of making a composite core includes the steps of providing a plurality of tubes, each of the plurality of tubes including a plurality of fibers disposed in a polymeric matrix, and adhesively bonding adjacent tubes of the plurality of tubes along sides of the adjacent tubes. A method of making a composite core such that a removable band is included in the core, the removable band being configured to be removable through a procedure subsequent to the cure of the composite core, thereby producing gaps in the core.

Abstract: According to one embodiment, a rotorcraft yoke comprises a plurality of arms. The plurality of arms, in combination, comprise a plurality of fibrous plies extending continuously throughout all of the plurality of arms.

Abstract: A method of constructing a cured composite assembly includes positioning a composite assembly within a bonding tool, wherein the composite assembly comprises an uncured composite spar and a skin and performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the skin to the cured composite spar.

Abstract: A flexible joint assembly for providing flexure to a rotor blade comprising an upper hub plate and a lower hub plate configured to secure a rotor blade yoke via a bolted joint located radially outward of a mast; and an upper flexure assembly connected to the upper hub plate and a lower flexure assembly connected to the lower hub plate, wherein the upper flexure assembly and lower flexure assembly are configured to promote flapping of the rotor blade yoke about a flapping hinge located radially outward of the bolted joint.

Abstract: A method of manipulating a thin-walled structure includes providing a thin-walled structure in a first unconstrained configuration, constraining the thin-walled structure to a first constrained configuration in which a first feature of the thin-walled structure is spatially located relative to the a second feature of the thin-walled structure in a predetermined manner, wherein an open volume of the thin-walled structure is constrained to maintain a predetermined open volume shape, and machining the thin-walled structure to a second constrained configuration in which the first feature of the thin-walled structure remains spatially located relative to the second feature of the thin-walled structure in the predetermined manner.

Abstract: A network interface receives portfolio data related to an investment plan portfolio of a participant. A processor identifies a first plurality of risk factors associated with market conditions, wherein the first plurality of risk factors comprises a future data and risk strength. The processor further identifies a second plurality of risk factors associated with the participant. The processor then generates glide path data based at least partially on the first plurality of risk factors and the second plurality of risk factors. The processor also generates a glide path map based at least partially on the generated glide path data.

Abstract: The present application relates a core member for a core-stiffened structural assembly. The core member includes a plurality of cell members oriented a direction to provide a tailored stiffness in a certain direction. The core member can further include one or more planar members that can aid in shear transfer between cell members. The cell members can be made from bonding a plurality of corrugated layers together. The core-stiffened structure can be a rotor blade for an aircraft. In such an embodiment, the torsional stiffness of the rotor blade can be tailored in at least one of the chordwise and spanwise directions to provide tailor a torsional stiffness at any give location in the rotor blade.

Abstract: According to one embodiment, a rotorcraft yoke comprises a plurality of arms. The plurality of arms, in combination, comprise a plurality of fibrous plies extending continuously throughout all of the plurality of arms.

Abstract: The present application relates a core member for a core-stiffened structural assembly. The core member includes a plurality of cell members oriented a direction to provide a tailored stiffness in a certain direction. The core member can further include one or more planar members that can aid in shear transfer between cell members. The cell members can be made from bonding a plurality of corrugated layers together. The core-stiffened structure can be a rotor blade for an aircraft. In such an embodiment, the torsional stiffness of the rotor blade can be tailored in at least one of the chordwise and spanwise directions to provide tailor a torsional stiffness at any give location in the rotor blade.

Abstract: A flexible joint assembly for providing flexure to a rotor blade comprising an upper hub plate and a lower hub plate configured to secure a rotor blade yoke via a bolted joint located radially outward of a mast; and an upper flexure assembly connected to the upper hub plate and a lower flexure assembly connected to the lower hub plate, wherein the upper flexure assembly and lower flexure assembly are configured to promote flapping of the rotor blade yoke about a flapping hinge located radially outward of the bolted joint.

Abstract: A method of manipulating a thin-walled structure includes providing a thin-walled structure in a first unconstrained configuration, constraining the thin-walled structure to a first constrained configuration in which a first feature of the thin-walled structure is spatially located relative to the a second feature of the thin-walled structure in a predetermined manner, wherein an open volume of the thin-walled structure is constrained to maintain a predetermined open volume shape, and machining the thin-walled structure to a second constrained configuration in which the first feature of the thin-walled structure remains spatially located relative to the second feature of the thin-walled structure in the predetermined manner.

Abstract: The shear bonding method is configured to facilitate bonding of structures in an out-of-autoclave environment. The shear bonding method includes bonding a plurality of frame members to the interior of a tapered tailboom. The frames are located on a bayonet type tool. An adhesive pack is applied to each frame. The bayonet type tool is inserted into the tailboom until the adhesive packs come into contact with the interior walls of the tailboom. Conductive heating tiles are applied to the tailboom. The conductive heating tiles are controlled to achieve and maintain viscosity of the adhesive packs. During this period the bayonet tool is actuated so that the frames are translated in relation to the tailboom. The heating tiles are then controlled to achieve and maintain the adhesive at a requisite curing temperature.

Abstract: The present application relates a core member for a core-stiffened structural assembly. The core member includes a plurality of cell members oriented a direction to provide a tailored stiffness in a certain direction. The core member can further include one or more planar members that can aid in shear transfer between cell members. The cell members can be made from bonding a plurality of corrugated layers together. The core-stiffened structure can be a rotor blade for an aircraft. In such an embodiment, the torsional stiffness of the rotor blade can be tailored in at least one of the chordwise and spanwise directions to provide tailor a torsional stiffness at any give location in the rotor blade.

Abstract: The shear bonding method is configured to facilitate bonding of structures in an out-of-autoclave environment. The shear bonding method includes bonding a plurality of frame members to the interior of a tapered tailboom. The frames are located on a bayonet type tool. An adhesive pack is applied to each frame. The bayonet type tool is inserted into the tailboom until the adhesive packs come into contact with the interior walls of the tailboom. Conductive heating tiles are applied to the tailboom. The conductive heating tiles are controlled to achieve and maintain viscosity of the adhesive packs. During this period the bayonet tool is actuated so that the frames are translated in relation to the tailboom. The heating tiles are then controlled to achieve and maintain the adhesive at a requisite curing temperature.

Abstract: A composite core includes a plurality of tubes, each the plurality of tubes comprising a plurality of fibers disposed in a polymeric matrix. Adjacent tubes of the plurality of tubes are adhesively bonded to one another along sides of the adjacent tubes. A method of making a composite core includes the steps of providing a plurality of tubes, each of the plurality of tubes including a plurality of fibers disposed in a polymeric matrix, and adhesively bonding adjacent tubes of the plurality of tubes along sides of the adjacent tubes. A method of making a composite core such that a removable band is included in the core, the removable band being configured to be removable through a procedure subsequent to the cure of the composite core, thereby producing gaps in the core.

Abstract: A present system of the present application provides for reticulating adhesive to the surface network of cellular core. As such, the present invention allows for substantial improvements over prior systems. The present invention may be implemented with any aircraft, wind turbine, rocket, space satellite, or land vehicle, but there is nothing within the spirit and scope of the present invention limiting it to any particular application. The teachings of the present invention are useful to any composite structure utilizing cellular core.