aeropanel2 - Theory In our second Design Build Test project...

Info iconThis preview shows pages 1–2. Sign up to view the full content.

View Full Document Right Arrow Icon
4 3 1 2 Figure Figure Figure Figure Theory In our second Design Build Test project we were asked to explore both the compression strength to weight ratio, and the moment of inertia. We did this by building and testing structural panels to see what effect the shape, size, and placement of the stiffeners had on the strength of the panel. The compression strength to weight ratio is the amount of weight that a test panel will hold divided by the weight of the panel. Typically the smaller your panel is, the larger its compression strength to weight ratio. The moment of inertia is defined as the measure of resistance to bending of an object due to its geometry. Calculating this value allows you to predict or verify how your panels will perform when tested. Figure The main structure in the fuselage of the aircraft is the frame. (Point 1 in figure 1) Multiple frames run throughout the fuselage making it the largest part of the structure of the aircraft. The ribs serve the same purpose in the wing as the frame serves in the
Background image of page 1

Info iconThis preview has intentionally blurred sections. Sign up to view the full version.

View Full DocumentRight Arrow Icon
Image of page 2
This is the end of the preview. Sign up to access the rest of the document.

This note was uploaded on 09/21/2008 for the course ASE 1013 taught by Professor Koenig during the Fall '07 term at Mississippi State.

Page1 / 2

aeropanel2 - Theory In our second Design Build Test project...

This preview shows document pages 1 - 2. Sign up to view the full document.

View Full Document Right Arrow Icon
Ask a homework question - tutors are online