I've got Mike Whitakers stress calculations for the KR2S. He went through the whole aircraft including the seatbelt shoulder attachments.
I wrote about this about a year ago. He found the weakest part of the aircraft is the top skin between the spars of the stub wing. It needs two layers of glass all over the top of the stub wings to make them stronger in twist with aerodynamic wing twisting loads. They were strong enough but close on the 1,2 safety factor that was used or something like that. CH Have there been any load analyzes done with regard to the changes made with the KR2S and KR2S-mod (M. Langford, et. al.). I like what I read about the changes, but I wonder if anyone has load tested the new structures and published the results. Would the KR2S (and others) sustain +6g or -3g loads. At what weights, etc.? Just curious, Thanks, -Terry
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