摘要
针对民用涡扇发动机,研究了一种基于模型的航空发动机容错控制策略.在发动机原有闭环控制系统的基础上,该策略对发动机各控制量进行容错控制修正,达到缓和甚至消除故障对控制系统影响的目的.针对民用涡扇发动机常见的高压压气机和高压涡轮性能退化故障,提出了以恢复发动机运行性能为目的的性能指标,通过遗传算法离线计算得到容错控制计划表,并利用插值计算实现在线容错控制.经仿真验证,该策略控制性能良好、实现简单.结果表明:在确保各温度限制不超标的情况下,受影响较大的增压级喘振裕度恢复至故障发生前的水平,同时风扇与高压压气机喘振裕度的降幅不超过5%,推力的降幅不超过3%.
A model-based fault tolerant control strategy for civil turbofan engine was discussed in order to mitigate or eliminate the adverse effect caused by certain faults through adjustments on existing controller.A controlling objective of recovering operability was presented for engines experiencing deterioration in high-pressure compressor and high-pressure turbine.In order to accomplish this objective,a fault accommodation look-up table was established offline,which was formed by optimal adjustments for design points calculated by solving an optimization problem using genetic algorithm.For a general point in the flight envelope,the adjustments were gained through online interpolation among design points.The strategy was validated simple and effective through simulation.Results showed that stall margins of the booster were all recovered to the corresponding levels of the unfaulted engine without exceeding temperature limitations.Stall margins of the fan and high pressure compressor decreased by less than 5% and the thrust by less than 3%.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2016年第3期708-716,共9页
Journal of Aerospace Power
关键词
涡扇发动机
容错控制
遗传算法
气路部件故障
插值计算
turbofan engine
fault tolerant control
genetic algorithm
gas path fault
linear interpolation
