METHOD OF MANUFACTURING A CARGO BODY PANEL
A composite molded cargo body panel including a core, an interior skin secured to a first side of the core having a thickness, and exterior skin secured to a second side of the core, and a plurality of recesses. The plurality of recesses are dispersed along a first direction at intervals in the interior skin, with the core thickness at each of the plurality of recesses being reduced compared to a maximum core thickness, and each of the plurality of recesses defines a support surface. A pocket is formed in each of the plurality of recesses, with the core thickness at the pocket being less than the core thickness at each of the plurality of recesses. A plurality of logistics inserts are attached to the respective support surfaces of the plurality of recesses so that, at each of the plurality of recesses, the logistics insert extends across the pocket.
1 . A method of manufacturing a cargo body panel, the method comprising:
laying an exterior side of an exterior skin down on a platen such that an interior side of the exterior skin faces upward;
laying an exterior side of a core onto the interior side of the exterior skin, wherein the exterior skin is a single, continuous piece whose interior side supports the core for an entirety of the cargo body panel;
laying an exterior side of an interior skin onto the interior side of the core, the interior skin provided in one or more pieces;
positioning a plurality of assembly plates along at least one peripheral edge of the core on one or both of the core's interior and exterior sides; and
performing a molding step in which the exterior and interior skins are bonded to the exterior and interior sides of the core, respectively, and in which the plurality of assembly plates are embedded into the core.
2 . The method of claim 1 , wherein the molding step includes vacuum molding.
3 . The method of claim 1 , wherein the cargo body panel is manufactured as a complete jointless sidewall for a cargo body.
4 . The method of claim 1 , wherein the plurality of assembly plates includes a plurality of inner plates positioned between the core and the interior skin and a plurality of outer plates positioned between the core and the exterior skin.
5 . The method of claim 1 , wherein the plurality of assembly plates are distributed along all peripheral edges of the core.
6 . The method of claim 1 , wherein prior to or during the molding step, a recess is formed at an interior side of the interior skin, the method further comprising positioning a logistics insert into the recess.
7 . The method of claim 6 , wherein the logistics insert is positioned such that a plurality of apertures in the logistics insert are in register with a plurality of pockets within the core.
8 . The method of claim 6 , wherein the logistics insert is secured by one or both of bonding and fasteners.
9 . The method of claim 6 , wherein the logistics insert is positioned such that a portion thereof is laid against the interior side of the exterior skin.
10 . The method of claim 1 , wherein the interior skin is provided in a single, continuous piece spanning the interior side of the core.
11 . The method of claim 1 , further comprising CNC-machining the core at a logistics insert receiving position to form a recess and/or a pocket therein.
12 . A method of manufacturing a cargo body panel, the method comprising:
laying an exterior side of an exterior skin down on a platen such that an interior side of the exterior skin faces upward;
laying an exterior side of a core onto the interior side of the exterior skin, wherein the exterior skin is a single, continuous piece whose interior side supports the core for an entirety of the cargo body panel;
laying an exterior side of an interior skin onto an interior side of the core;
performing a molding step in which the exterior and interior skins are bonded to the exterior and interior sides of the core, respectively;
prior to or during the molding step, providing a recess by a thickness-reduced area of the core; and
positioning a logistics insert at least partially in the recess.
13 . The method of claim 12 , wherein the logistics insert is positioned so that an interior surface thereof is flush with an interior side of the interior skin.
14 . The method of claim 12 , wherein the molding step includes vacuum molding.
15 . The method of claim 12 , wherein a plurality of assembly plates are positioned along at least one peripheral edge of the core prior to the molding step, the plurality of assembly plates being embedded between the interior and exterior skins during the molding step.
16 . The method of claim 15 , wherein the plurality of assembly plates includes a plurality of inner plates positioned between the core and the interior skin and a plurality of outer plates positioned between the core and the exterior skin.
17 . The method of claim 15 , wherein the plurality of assembly plates are distributed along all peripheral edges of the core.
18 . The method of claim 12 , wherein the logistics insert is secured by one or both of bonding and fasteners.
19 . The method of claim 12 , wherein the logistics insert is laid onto an interior side of the interior skin prior to the molding step, and the interior skin is shaped by the logistics insert during the molding step.
20 . The method of claim 12 , wherein the logistics insert is positioned such that a portion thereof is laid against the interior side of the exterior skin.
21 . The method of claim 12 , further comprising CNC-machining the core prior to the molding step to form the recess.