Abstract: The invention provides a method for cargo sorting, configured to control an end effector with a package placement platform to sort the cargo, and the method includes: moving the package placement platform to a package obtaining position and obtaining the cargo to be sorted that enters into the package placement platform; moving the package placement platform to a package storage location; and exerting a first force to push the cargo into a package storage unit. With the help of the package placement platform, the method of the invention can receive the packages of different types or different sizes or different material so as to sort and transport all kinds of packages.

Abstract: A reduced vibration structure comprises honeycomb and a vibration damping coating on at least a portion of the internal surface of at least a portion of the cells of the honeycomb. The vibration damping coating is formed by curing a coating composition comprising acrylic polymer or copolymer emulsion and a vibration damping filler. The structure can include an adhesive coupled to both the upper surface and the lower surface of the honeycomb and two pieces of sheathing coupled to the adhesive, one on the upper surface and one on the lower surface of the honeycomb.

Abstract: The present application relates to a simulation device of flight management system (FMS), comprising a navigable database and a performance database; a display portion; a horizontal section portion and a vertical section portion, wherein the horizontal section portion and vertical section portion provide horizontal route information and vertical route information of the route designated by a user through the navigable database and performance database; and wherein the display portion is mutually integrated with the horizontal section portion and vertical section portion.

Abstract: A reduced vibration structure comprises honeycomb and a vibration damping coating on at least a portion of the internal surface of at least a portion of the cells of the honeycomb. The vibration damping coating is formed by curing a coating composition comprising acrylic polymer or copolymer emulsion and a vibration damping filler. The structure can include an adhesive coupled to both the upper surface and the lower surface of the honeycomb and two pieces of sheathing coupled to the adhesive, one on the upper surface and one on the lower surface of the honeycomb.

Abstract: The present application relates to a simulation device of flight management system (FMS), comprising a navigable database and a performance database; a display portion; a horizontal section portion and a vertical section portion, wherein the horizontal section portion and vertical section portion provide horizontal route information and vertical route information of the route designated by a user through the navigable database and performance database; and wherein the display portion is mutually integrated with the horizontal section portion and vertical section portion.

Abstract: A method for making a composite panel, wherein the composite panel has a honeycomb core sandwiched between a pair of facing sheets, includes the steps of (a) coating the interior walls of the cells with a unexpanded thermo-expandable material; (b) bonding a pair of facing sheets to the opposite sides of the honeycomb core; and (c) heating the honeycomb core while the honeycomb core is sandwiched between the pair of facing sheets with sufficient heat to cause the thermo-expandable material to expand and to substantially fill the cells.

Abstract: A method for making a composite panel, wherein the composite panel has a honeycomb core sandwiched between a pair of facing sheets, includes the steps of (a) coating the interior walls of the cells with a unexpanded thermo-expandable material; (b) bonding a pair of facing sheets to the opposite sides of the honeycomb core; and (c) heating the honeycomb core while the honeycomb core is sandwiched between the pair of facing sheets with sufficient heat to cause the thermo-expandable material to expand and to substantially fill the cells.

Abstract: A method for making a composite panel, wherein the composite panel has a honeycomb core sandwiched between a pair of facing sheets, includes the steps of (a) coating the interior walls of the cells with a unexpanded thermo-expandable material; (b) bonding a pair of facing sheets to the opposite sides of the honeycomb core; and (c) heating the honeycomb core while the honeycomb core is sandwiched between the pair of facing sheets with sufficient heat to cause the thermo-expandable material to expand and to substantially fill the cells.

Abstract: Disclosed are compositions of short fiber reinforced phenolic foams, methods of making and using the same. The disclosed fiber-reinforced phenolic foams have a seven-fold increase in peel resistance over the unreinforced counterpart foam. The phenolic foam has enhanced fracture toughness without sacrificing the critical fire retardant properties.

Abstract: Disclosed are compositions of short fiber reinforced phenolic foams, methods of making and using the same. The disclosed fiber-reinforced phenolic foams have a seven-fold increase in peel resistance over the unreinforced counterpart foam. The phenolic foam has enhanced fracture toughness without sacrificing the critical fire retardant properties.