The burning rate of a particular propellant is given by r = c/(T₁-T)p in which r is in mm/s, po is in MPa, T is in K and
C=176,
T₁ = 415 K,
n =0.716.
When the propellant initial temperature is 20°C, the chamber pressure is 3 MPa (steady) for 4 min. If the same propellant grain in the same rocket is heated to 45°C, what would be the new steady state pressure level and burning period. Assume the time required to reach steady state is small com- pared to the burning time