Can anyone recommend a good general purpose section properties calculator? I've used Boeing's SA and SA+ which are very good but not accessable unless working on a Boeing project. I also have used shapebuilder but it seems a little clunky. I've seen some excel based user created calculators...
A repair must restore the capability of the structure to sustain regulatory loads. Usually that is done by restoring the static strength of the damaged structure since the applied loads are generally not known. In some circumstances, if the loads are known, it may be possible to demonstrate...
my two cents worth..
For an internal pressure applied load the skin hoop load = pr and the skin (and stringer) longitudinal load = pr/2 assuming a cylindrical cross section. The hoop load is nominally carried by the skin only and longitudinal load is shared by the skin and stringer.
Because...
The Boeing meaning of floor beam end fixity is a percentage of the fully fixed end moment. For narrow body it is usually 33% for flight conditions and 50% for emergency landing conditions.
Make a pinned-pinned bendimg moment diagram and a fixed-fixed BMD. For 33% fixity your BMD is 33% of the...
You’ll see the Huth equation as C = 4.2* ((tp+ts)/(2D))^2/3 + (1/(tpEp) + 1/(tsEs) + 1/(tpEb) + 1/(2tpEb)). Because of the 2 in the last term, the designation of plate vs. strap affects the answer which makes no sense.
The original Huth equation (in German) lists the flexibility as:
C =...
Why not spotface the head side and use a self-aligning nut/washer combination on the nut side? The structural effect of the fastener misalignment would be considered negligible in my opinion.
The only strength effect would be due to the spotface.
For Boeing commercial airplanes, the .9 x net area is specified in the design requirements memo for each airplane program. Using the .9 factor is conservative for static strength analysis of aluminum and eliminates the need for stress people sit around debating what the appropriate method for...
