Analysis of Scramjet’s Flight Engine Integration Considering the Fuel Proportional Distribution Inside the Combustor

In this paper, the overall performance model of scramjet based on lumped parameter method and the integrated flight/engine model based on energy method are established. The overall performance of a scramjet engine with different combustion chamber fuel ratios was calculated. Based on the engine performance, the impact of different combustion chamber fuel ratios on the engine performance was investigated, and based on this, a flight engine integration study was conducted. The study found that the maximum equivalent ratio of Ma4-5 scramjet engines is easily affected by the fuel distribution ratio in the two-stage combustion chamber $\Phi_{1}/\Phi$. The larger the value, the smaller the maximum equivalence ratio. Complete a flight mission with a flight distance of 2000 km, scramjet combustor $\Phi 1/\Phi=$ The maximum flight time at 0.4 is 1164s, and the remaining weight ratio is 0.5571.