For the hypersonic vehicle inlet unstart problem that easily occurs during flight, the research on the integrated flight-propulsion control and protection method based on inlet performance modeling and analysis is carried out. Firstly, by modeling and analyzing the scramjet engine, iteratively solving to get the critical angle of attack and fuel equivalence ratio to make prevent the occurrence of inlet unstart. Then limiting it as the boundary of unstart, utilizing the pole configuration strategy to realize the integrated flight-propulsion protection and control through the joint adjustment of the angle of attack and the fuel equivalence ratio. The simulation results show that the integrated protection control method, compared with the traditional inlet unstart protection control method, can improve the inlet unstart stability margin and reduce the risk of inlet unstart under the same design premise, so as to avoid the negative impact of inlet unstart on the mission of hypersonic vehicle.