Abstract: In order to obtain the character of dual-mode scramjet at maximum fuel supplied mode in different flight state，based on the performance calculation model of dual-mode scramjet including lumped parameter equation，through analyzing the chocking boundary condition and principle of scramjet，the method to solve the computation of maximum fuel supplied mode of scramjet was developed. Correspondingly，the computation model was established. The iterative computation process of maximum fuel supplied mode of scramjet in a flight condition and a detailed description of the physical phenomenon are given，its computing accuracy reaches 10-4. Then the computation of maximum fuel supplied mode of scramjet in different flight Mach number is completed，achieving the maximum fuel of combustion and the flow path parameters of isolator/combustion correspondingly. The maximum fuel supplied mode of scramjet was calculated and analyzed in the paper，the results show that the method can be used to calculate the flow balance of dual-mode scramjet exactly，and accurately capture the maximum fuel flow in different flight state when the distraction ratio of fuel is given.

Key words: Dual-mode Scramjet；Maximum fuel supplied mode；Lumped parameter equation；Computation method

摘要： 为了获得不同飞行状态下双模态超燃冲压发动机最大供油状态，在集总参数方程的双模态超燃冲压发动机性能计算模型基础上，通过分析双模态超燃冲压发动机堵塞边界条件及工作机理，发展了最大供油模态流量平衡的求解方法，并以此为基础建立了双模态超燃冲压发动机最大供油模态计算模型。给出某飞行条件下的最大供油模态迭代计算过程，并详细描述了其所表征的物理现象，其流量平衡计算精度达10-4，并在此基础上完成了不同飞行马赫数下的最大供油模态计算，获得相应的燃烧室最大供油量及隔离段/燃烧室沿程参数分布。结果表明，该计算方法可实现双模态超燃冲压发动机最大供油模态的流量平衡计算，并能精确地捕捉给定燃油分配形式下的燃烧室最大供油量。

关键词: 双模态超燃冲压发动机；最大供油模态；集总参数方程；计算方法