航空发动机二元矢量喷管控制系统设计及验证

Design and Verification of Two-dimensional Vector Nozzle Control System for Aero-engine

矢量推进和红外隐身能力在现代空战中尤为重要,与之密切相关的是航空发动机尾喷管,根据某型发动机二元矢量喷管的特定工作条件,对其控制系统开展研究,提出了喷管喉道控制和矢量控制双回路双余度的设计方案,实现了在发动机稳态和过渡状态下调节喷口喉道面积、出口面积及矢量偏转,并在故障状态下将矢量喷口控制到安全位置等功能。经计算仿真及整机试验验证,设计方案合理可行,满足某型发动机使用要求。

Vector propulsion and infrared stealth capability are particularly important in modern air combat,which is closely related to the aero-engine tail nozzle.According to the specific working conditions of the two-dimensional vectoring nozzle,the control system is studied in this paper and the design scheme of dual loop and dual redundancy of nozzle A8 control and vector control is proposed.The nozzle A8,A9 and vector deflection are adjusted in the steady state and transient state of the aero-engine,and the vectoring nozzle is controlled to a safe position in the fault state.Through calculation,simulation and whole aero-engine test verification,the design scheme is reasonable and feasible,and meets the requirements of the aero-engine.