Tab/slot joint and method

A method of fabricating an item for an aerospace vehicle, the method comprising the steps of:

• fabricating a first joint in a panel including:
• fabricating a groove in the panel, the panel comprising a first skin, second skin, and core, the core being sandwiched between the first skin and the second skin, the groove passing through the first skin and at least a portion of the core and not passing through the second skin, the groove comprising a set of tabs and a corresponding set of slots, and the groove delineating a first portion of the panel from a second portion of the panel;
• bending the panel along the groove such that the first portion and the second portion intersect at an angle at the groove;
• and
• intermeshing the set of tabs with the set of slots in response to bending the panel along the groove;
• and
• fabricating a second joint such that the second joint substantially retains the angle of the first joint.

A method of fabricating a joint in a panel of an aerospace vehicle, the method comprising the steps of:

• fabricating a groove in the panel, the panel comprising a first skin, a second skin, and a core, the core being sandwiched between the first skin and the second skin, the groove passing through the first skin and at least a portion of the core and not passing through the second skin, the groove comprising a set of tabs and a corresponding set of slots;
• forming a spline in the groove;
• bending the panel along the groove;
• intermeshing the set of tabs with the set of slots in response to bending the panel along the groove;
• and
• calculating a groove width according to at least one of the following equations:
• A=π(t)(180−θ)/180;
• and
• A=h*tan(180−θ);
• A comprising the groove width;
• θ comprising an angle of the joint;
• t comprising a thickness of the panel;
• and
• h comprising a height of the core plus the first skin.