Hi guys,
Thank you a lot for you knowledge on this one.
@
[email protected] - I understand that, still what I am affirming is that the MR is designed to withstand stress greater than the stress that other components withstand, is my statement correct?
@ Pofman ; @ Droopystop - Droopystop I think what Pofman replied is the requirements for the certification specifications for small rotorcrafts although I don't know the definition of a small rotorcraft, is it max of 3 175 kg (7 000 lbs) and/or less than 9 seats? Is small equal to light? If so than a lot of rotorcrafts are in this class. For example AS 350, so by this required specifications, this means that AS 350 is able to withstand at least +3.5G and -1G? So I guess it's all proporcional to the forces, since the R-22 for example it's in the small rotorcraft category too, it looks more fragile than AS 350, but because it generate less magnitude of forces (less W, less moment, less L, etc) it's able to withstand the same +3.5G and -1G as the AS 350, is my thinking correct?
So, is it correct to say that R-22 is able to withstand +3.5G and -1G (of course just talking about load factors and also not in normal flight conditions)?
Another thing is that, correct me if I am wrong, if you are banked 60º your L has to be 2 times you W to maintain the helicopter at the same altitude (L=W), as n=L/W, in this case n=2L/W, you have n=2G. So is it correct to say that in a 60º turn you have twice the Gs you have in level flight? If so if you pull the cyclic back how easy would you reach the +3.5G?
Best regards to all and thank you for the knowledge.