7. The burning rate of a particular propellant is given by r=c/(T1T)p0n in which r is in mm/s,p0 is in MPa, T is in K and cT1n=176,=415K,=0.716. When the propellant initial temperature is 20C, the chamber pressure is 3MPa (steady) for 4min. If the same propellant grain in the same rocket is heated to 45C, what would be the new steady state pressure level and burning period. Assume the time required to reach steady state is small compared to the burning time