Abstract: The engine performance simulation model of Revolutionary Turbine Accelerator (RTA) was built based on the component characteristic, to research the performance in mode transition process and corresponding control method. Different mode transition methods were simulated and compared in detail, and the mode transition control law along the given flight trajectory was designed. It can be concluded that the RTA can conduct mode transition atMa1.6, and operate steadily inMa0~4.0. The mode transition process can occur in both maximum mechanical load and maximum thermal load condition, with 8 times variation of bypass ratio, to realize the high thrust performance during the flight.

摘要： 为研究革新涡轮加速器（RTA）模态转换特性和控制策略，基于发动机部件特性法建立了RTA发动机性能仿真模型，对RTA发动机模态转换过程进行了分析，提出了采用不同调节手段实现模态转换过程的方法，对不同转换方法进行了仿真对比，制定了沿给定飞行轨迹的模态转换控制计划，保证模态转换过程中,发动机可始终工作在最大允许机械负荷和最大允许热负荷状态。基于本文提出的模态转换控制计划，RTA发动机可在Ma1.6条件下开始模态转换，实现在Ma0~4.0范围稳定工作，工作过程中发动机涵道比变化范围接近8倍，为飞行器加速提供高推力性能。

关键词: 革新涡轮加速器;特性仿真;模态转换;控制计划;高推力