DESIGN STUDY ON PRE-COOLED TURBOJET ENGINES FOR HYPERSONIC AIRPLANES

摘要

The authors propose a development of a hypersonic airplane, which has a capability to fly over the Pacific Ocean in 2 hours. The airplane also has a capability to launch small payloads into low earth orbit by using upper stage rocket. Pre-cooled turbojet engine was analytically proved to have a capability to be operated under conditions between sea level static and Mach 6 flight. In this study, small pre-cooled turbojet engine for technical demonstration is designed. The engine has variable intake and nozzle to adapt wide flight Mach number range. The engine will be tested both in a test facility and real flight environment. In this study, the shape of small pre-cooled turbojet engine is defined. Performance of the engine is estimated by a thermodynamic analysis. Thrust and specific impulse of pre-cooled turbojet engine is compared to that of ramjet engine. Then, detailed shapes for the engine components are designed by aerodynamic and structural calculations. Finally, experimental models to confirm the performance and heat resistant structure are fabricated and tested.