Integrated Analysis of Rotating Detonation Combined Cycle Engines

This paper develops an integrated high speed vehicle/combined power performance analysis model, using the mission requirements of hypersonic vehicles in near space as a traction. The ability of this power to perform typical tasks was assessed using a rotating detonation combined cycle engine. The effect of different wing loading, different take-off weights and different climb modes on the performance of the vehicle was also studied, and the important performance parameters of the high-speed vehicle and engine in the flight profile were obtained. The results of the study show that the rotating detonation combined cycle engine is suitable for large range missions, based on the turbojet and turbofan rotating detonation combined cycle engine range increase of 42.3% and 33.5% respectively compared to TBCC.As the wing loading increases, the cruising distance tends to increase and then decrease; as the gross take-off weight increases, the combined effect of increased fuel mass and reduced thrust-to-weight ratio results in an increasing and then decreasing range. The lower the dynamic pressure, the longer the climbing time and the distance climbed increases significantly, the higher the dynamic pressure, the shorter the climbing time and the less fuel is consumed during the climb.