Cryogenic engine prop tanks vent in order to control tank pressure. Thermal energy that (inevitably) gets conducted into a cryo tank raises the propellant enthalpy and so the pressure of the critical fluid in the tank. Thus the tank must occasionally vent in order to maintain proper (P,T) condition. Is this correct?
So then, is it the same with an N2O tank at high (but maybe not critical?) pressure (about 500 psi)and ambient temperature?
After propellant loading, how does a hybrid system control N2O tank pressure?
Hybrid motors are simple in many ways but isn't it a little bit tricky to maintain N2O at required (P,T)? And if so, how is it done on a launch vehicle or spacecraft?