Originally Posted by
Goldenrivett
I think the opposite is true.
if the all load is carried inside the wing, then bending stresses are reduced. If the load is carried in the fuselage, then the wing bending stresses are increased. Maximum zero fuel weight is due to wing bending loads. Fuel can then be carried in the wings up to max take off weight.
If all the fuel is carried in the fuselage, then the aircraft wing structure must be beefed up (extra weight) so the zero fuel weight can be increased up to max take off weight.
What Goldenrivett said - fuel in the wing requires less structural strength in the wing than fuel in the fuselage.
Also, liquid H2 is more energy dense that JetA in weight, but far less dense in volume so far more volume is needed (as in several times). The linked article suggests high pressure H2 storage - which is even less dense than liquid H2.