A multi-material joint and a method of making thereof. The multi-material joint includes a first member comprising a first metal or metal alloy that is secured to a second member comprising a second metal or metal alloy that is different than the first metal or metal alloy. A sealant is positioned between the first member and the second member that galvanically insulates the first member from the second member. The sealant comprises a liquid elastomer and a foaming agent.

The embodiments described herein provide for lightning protection in aircrafts constructed with Carbon Fiber Reinforced Plastic (CFRP). In one embodiment, the apparatus includes a first Carbon Fiber Reinforced Plastic (CFRP) panel, a second CFRP panel that overlaps with the first CFRP panel in a vertical direction, and a fastener to join the first CFRP panel with the second CFRP panel, the fastener extending in the vertical direction in an area where the first CFRP panel and the second CFRP panel overlap. The apparatus further includes a plurality of electrically conductive pins in each of the first CFRP panel and the second CFRP panel, wherein the pins extend in the vertical direction proximate to the fastener to electrically connect the first CFRP panel and the second CFRP panel in the area where the first CFRP panel and the second CFRP panel overlap.

A multi-material joint and a method of making thereof. The multi-material joint includes a first member comprising a first metal or metal alloy that is secured to a second member comprising a second metal or metal alloy that is different than the first metal or metal alloy. A sealant is positioned between the first member and the second member that galvanically insulates the first member from the second member. The sealant comprises a liquid elastomer and a foaming agent.

A joining structure includes a first member, a second member of a material different from that of the first member, and a separation mechanism provided between the first member and the second member and that separates the first member and the second member from each other, wherein a resin is filled into the space between the edge of at least one member among the first member and the second member, and the other member.

A composite blade includes a composite blade body including reinforced fibers and resin; a metal layer provided on an outer side of a leading edge section including a leading edge that is a part of the composite blade body on an upstream side of an air stream, the metal layer having a thickness of equal to or larger than 5 micrometers and equal to or smaller than 100 micrometers; an adhesive layer provided between the composite blade body and the metal layer to bond the metal layer to the composite blade body; and an electric insulating layer provided in contact with a surface of the leading edge section of the composite blade body, the surface being on the side on which the metal layer is provided, the electric insulating layer having an electric insulating property.

A manufacturing apparatus of a display device includes a first jig configured to hold a first member; a second jig located under the first jig and coupled to or separated from the first jig such that the first member is locatable between the first jig and the second jig; fixing parts located at both ends of the second jig and configured to hold a second member between the first member and the second jig, the second jig including a pad; and a stage located under the pad and provided with a groove formed therethrough and having an area smaller than an area of the pad when viewed in a plan view, wherein one portion of the pad, which faces the stage, is configured to be within the groove.

A manufacturing apparatus of a display device includes a first jig configured to hold a first member; a second jig located under the first jig and coupled to or separated from the first jig such that the first member is locatable between the first jig and the second jig; fixing parts located at both ends of the second jig and configured to hold a second member between the first member and the second jig, the second jig including a pad; and a stage located under the pad and provided with a groove formed therethrough and having an area smaller than an area of the pad when viewed in a plan view, wherein one portion of the pad, which faces the stage, is configured to be within the groove.

The embodiments described herein provide for lightning protection in aircrafts constructed with Carbon Fiber Reinforced Plastic (CFRP). In one embodiment, the apparatus includes a first Carbon Fiber Reinforced Plastic (CFRP) panel, a second CFRP panel that overlaps with the first CFRP panel in a vertical direction, and a fastener to join the first CFRP panel with the second CFRP panel, the fastener extending in the vertical direction in an area where the first CFRP panel and the second CFRP panel overlap. The apparatus further includes a plurality of electrically conductive pins in each of the first CFRP panel and the second CFRP panel, wherein the pins extend in the vertical direction proximate to the fastener to electrically connect the first CFRP panel and the second CFRP panel in the area where the first CFRP panel and the second CFRP panel overlap.

A method for forming a hybrid structure is provided. The method includes applying a sealant to a first component fabricated from a first material, coupling an isolation sheet to the sealant, and coupling a second component to the isolation sheet. The isolation sheet and the second component are fabricated from a second material that is different than the first material to facilitate preventing formation of a galvanic cell within the hybrid structure.

A protective assembly comprises a first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation and comprising a composite of particles and polymer; a second region formulated and configured to provide protection from ballistic impact and comprising a composite of fibers and polymer; and a third region formulated and configured to provide protection from thermal radiation and comprising a composite of particles, fiber, and polymer. The protective assembly may be provided on an aerospace structure. The protective assembly may be formed on the aerospace structure body using a co-curing process.