Ryuya, Dean, Esther (took notes)

Fuselage sample 3D print w ASA aero

goals:

1. discuss method to characterise weight
2. what testing methods to use to collect dataset

notes:

• want CG of the section, the mass/[sectional length] of the fuselage
• middle fuselage section is constant
• equivalent average prismatic shape for the nose and tail
• then weight would be

$$ W = W_{ASA}+[W_{glass}+W_{epoxy}]\cdot{S_F} $$

S_f is a correction/safety factor

break fuselage into hollow cylinders

the tail is imparting moments on the fuselage with our maneuvers

we can calculate the bending on the tail like a beam where fixed point is the CG

and size the carbon tows to withstand the loads in each direction

placing it outside would be better b/c further away from the neutral axis