某型航空发动机抗电源失效设计与试验验证  

Design and Test Verification of Resisting Power Supply Failure of A Certain Aero-engine

作　　者：李鸿基 郭海红 江井跃 孙朝辉 Li Hong-ji;Guo Hai-hong;Jiang Jing-yue;Sun Chao-hui(AECC Shenyang Engine Research Institute,Liaoning Shenyang 110015)

机构地区：[1]中国航发沈阳发动机研究所,辽宁沈阳110015

出　　处：《内燃机与配件》2024年第11期97-100,共4页Internal Combustion Engine & Parts

摘　　要：为应对外部电源可能出现的失效问题,某航空发动机控制系统开展电子控制器储能电路设计,并选用具有零偏功能的电液伺服阀。通过改造台架电源配置、增加延时继电器,实现模拟电源短时中断50ms和完全失效功能。整机电源失效试验表明,某航空发动机电子控制器CPU在外部电源短时中断50ms条件下可保持稳定工作,可取消配套应急电源设备;在电源完全失效情况下可通过切断关闭主燃油、调节几何角度使发动机安全停车,发动机性能和操纵性未发生变化,满足飞机使用要求。In order to deal with the potential problem of external power supply failure,energy-harvesting circuits in electronic controllers and electro-hydraulic servo valves with zero bias function are applied to a certain aero-engine control system.By reconstructing power supply configuration and setting time-delay relays,a method of simulating a 50ms-interruption and complete failure of power supply during the aero-engine testing is carried out.The simulated testing shows that the electronic controller CPU could keep working healthfully with a short power interruption of no more than 50ms without emergency power,and stop the engine by cutting off fuel supply and adjusting geometry angles while complete failure of power supply.The performance and maneuverability of the aero-engine make no change,which can satisfy the requirements.

关 键 词：航空发动机 电源失效 控制系统 中央处理器 电液伺服阀 整机试验 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]