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Trace based simplified composite analysis. Opinions?

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stanislavz

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Even the same tech at the same temperature and humidity laying up the same part can have variations in the quality and consistency of each layup.
Same was written by Jim Marske in comparision of carbon fibre spar as designed to tested ones.. And solution of pultruded carbon rob come to live. And no, it is not expensive at all.
 

stanislavz

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Inspired by Caro wing. An comparison of wing skins for chord 1300mm, 13.5% thick. Piece of span 750 mm.

Foam less :

1600080053285.png

Reinforcement ribs load :

1600081051130.png

Ribs :
1600081332590.png
Laminas :

1600080090438.png

With foam :

1600081138155.png

1600081191057.png


Load and boundary condition

1600081398308.png

Load is shown inccorectly, its starts from 0.006N/mm2 at the nose and ends at leading edge. Formula is z=(1300-y)/1300/-0.006

For easier calculation, nose section was ommited, and reinforcements were modelled as section with know property.

And yes, it would look different for single spar wing.
 

stanislavz

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Once more, this time for full section, for strut braced wing with jury struts. Only one section

1600094120971.png
1600094325366.png

with foam

1600094363071.png

1600094376482.png

span is 1300 mm, weighs are 5.17 kg for section with foam, and 5.6 for section without foam. In real world , with foam will be bigger ?

Deflection is close, but not similar. Mine tubes weight 0.066 kg per m, and this same as ribs from two plies of 300 gsm..
 

stanislavz

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Added two more ribs, but made all five from 2 plies of 300gsm biax, in stead of 4:

1600099991084.png

1600100009706.png

1600100070910.png
 
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