Disclosed herein are exemplary embodiments of linings or liners (e.g., liners with corner reinforcement, etc.), methods of providing a liner or lining for a tank, and methods and apparatus for providing additional protection and/or reinforcement at the corners of a liner or lining. In an exemplary embodiment, a method generally includes positioning and attaching one or more corner attachments at one or more corners of a liner that are formed between the bottom and the one or more sides of the liner. The one or more corner attachments may be configured to provide additional protection and/or reinforcement at the one or more corners of the liner.

A method for applying a thermoreactive seam tape to a seam is provided. The thermoreactive seam tape may be positioned adjacent to the seam, which may include a first fabric surface and an adjacent second fabric surface. The thermoreactive seam tape may include an interior planar surface that engages both the first fabric surface and the second fabric surface of the seam. The thermoreactive seam tape may further include an exterior surface opposite the interior surface, where the exterior surface is substantially non-planar with respect to the interior planar surface along a length of the thermoreactive seam tape. Heat and pressure may be applied to the thermoreactive seam tape, wherein the heat and the pressure facilitate adhesion of the thermoreactive seam tape to the first fabric surface and the second fabric surface of the seam.

A composite panel manufacturing process with interlocking connections. The method includes laying out the first sheet of pre-preg epoxy carbon fiber, upon a polished and released aluminum tool. A second sheet of epoxy fiberglass is laid out over the top side of the first sheet. Rigid structural foam is laid on top of the second sheet of epoxy fiberglass. A third sheet of pre-preg epoxy fiberglass is laid on top of the rigid structural foam. A fourth sheet of pre-preg epoxy carbon is laid on top of the third sheet of pre-preg epoxy fiberglass with heavy resin/top side out to form a plurality of panels. The plurality of panels are cured to form a multilayer panel. Core material is removed along one edge of a first multilayer panel to make a U-shaped channel having a base and parallel flanges. A grooved slot is cut along one edge of the next multilayer panel. The panels are joined at the corner using an adhesive.

Joints for joining panels together, such as for joining honeycomb sandwich panels used in aerospace applications, and methods of joining said panels are disclosed. In some examples of disclosed joints, a first panel and a second panel can be joined together to form a joint. The first panel can be a flat panel that includes a rabbet formed along a first longitudinal edge, and the second panel can be a curved panel that includes a notch formed along a second longitudinal edge. In forming the joint, a portion of the rabbet can be positioned within the notch, and the flat panel and curved panel can be oriented at a non-parallel and non-perpendicular angle to one another. Adhesive can be applied along the rabbet and/or the notch in order to secure the joint.

A method of joining panels for a vitrine is disclosed. The ends of the panels to be joined are mitered cut and bonded with a suitable adhesive providing adequate adhesion and transparency. The joints are formed to provide a wedge-shape bond gap sufficient to allow application of the adhesive from the outside of the gap through capillary action. The adhesive may be catalyzed or ultraviolet- or light-hardened.

Disclosed herein are exemplary embodiments of linings, liners, and methods of providing a liner or lining for a tank. An exemplary embodiment includes a method of providing a liner or lining for a tank. In this exemplary embodiment, the method includes extrusion welding a pair of sheets together by infusing a molten thermoplastic material along an interface and within a gap between the pair of sheets. The method also includes extrusion welding the pair of sheets to a bottom sheet by infusing the molten thermoplastic material along and between the pair of sheets and the bottom sheet.

A method of joining panels for a vitrine is disclosed. The ends of the panels to be joined are mitered cut and bonded with a suitable adhesive providing adequate adhesion and transparency. The joints are formed to provide a wedge-shape bond gap sufficient to allow application of the adhesive from the outside of the gap through capillary action. The adhesive may be catalyzed or ultraviolet- or light-hardened.

Joints for joining panels together, such as for joining honeycomb sandwich panels used in aerospace applications, and methods of joining said panels are disclosed. In some examples of disclosed joints, a first panel and a second panel can be joined together to form a joint. The first panel can be a flat panel that includes a rabbet formed along a first longitudinal edge, and the second panel can be a curved panel that includes a notch formed along a second longitudinal edge. In forming the joint, a portion of the rabbet can be positioned within the notch, and the flat panel and curved panel can be oriented at a non-parallel and non-perpendicular angle to one another. Adhesive can be applied along the rabbet and/or the notch in order to secure the joint.

Joints for joining panels (60, 62) together, such as for joining honeycomb sandwich panels used in aerospace applications, and methods of joining said panels are disclosed. In some examples of disclosed joints, a first panel and a second panel can be joined together to form a joint. The first panel (60) can be a flat panel that includes a rabbet (80) formed along a first longitudinal edge, and the second panel (62) can be a curved panel that includes a notch (86) formed along a second longitudinal edge. In forming the joint, a portion of the rabbet (80) can be positioned within the notch (86), and the flat panel (60) and curved panel (62) can be oriented at a non-parallel and non-perpendicular angle to one another. Adhesive (99) is applied along the rabbet (80) and/or the notch (86) in order to secure the joint.

Joints for joining panels (60, 62) together, such as for joining honeycomb sandwich panels used in aerospace applications, and methods of joining said panels are disclosed. In some examples of disclosed joints, a first panel and a second panel can be joined together to form a joint. The first panel (60) can be a flat panel that includes a rabbet (80) formed along a first longitudinal edge, and the second panel (62) can be a curved panel that includes a notch (86) formed along a second longitudinal edge. In forming the joint, a portion of the rabbet (80) can be positioned within the notch (86), and the flat panel (60) and curved panel (62) can be oriented at a non-parallel and non-perpendicular angle to one another. Adhesive (99) is applied along the rabbet (80) and/or the notch (86) in order to secure the joint.