With the combined cycle powered vehicle for high-speed aircraft and two-stage orbit platform as the background, and oriented to the basic elements of development research and engineering application, this paper investigates the R&D technical route of the horizontal takeoff and landing combined cycle engine. The main functional indicators such as flight range and load capacity of the single-type powered aircraft and the combined cycle powered vehicle are compared, the engine performance requirements for combined cycle powered vehicle are analyzed, the shifting trend with the widening of the speed range on aerodynamic and structural quality characteristics of the combined cycle powered vehicle and the performance of combined cycle engine are studied. It is proposed that the upper limit of the flight speed domain has a decisive influence on the practical application of the combined cycle engine. An evaluation model on combined cycle engine technology is constructed in the dimensions of technical solution, aircraft requirements, technology generational progress, and thermal barriers. Evaluation shows that the Ma6 combined cycle engine still needs continuous exploratory research, and the Ma4 combined cycle engine can be developed in big R&D projects for practical application. The analysis believes that the Ma4 sub-hyper flight platform has great value and is a majior technological generation.
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