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提出了一种改善航空发动机加速性能的方法:采用SQP寻优方法对航空发动机进行加速过程的寻优控制仿真计算,获得以油/气压比为函数的优化加速燃油控制规律。选取工作包线内具有一定覆盖性的若干个状态点,进行加速过程寻优控制仿真。考虑到根据油/气压线开环进行加速控制易于导致涡轮后温度瞬态超调,提出了根据两类约束条件计算开环加速线,对所获得的两条优化的加速线进行融合,进而获得适用于全飞行包线范围内的加速燃油控制规律。仿真计算表明,所提出的加速燃油控制规律可以在兼顾涡轮后温度不超温和压气机喘振裕度的情况下,实现发动机加速时间最短的目标。
A method to improve the acceleration performance of aeroengine was put forward. The optimization of aeroengine was simulated by using SQP optimization method, and the optimal acceleration fuel control law was obtained as a function of oil / air pressure ratio. Select a certain number of coverage points in the work envelope, to optimize the control simulation of acceleration process. Considering that the acceleration control based on the open loop of oil / gas line can easily lead to the transient overshoot of the post-turbine temperature, the open-loop acceleration line is calculated based on two kinds of constraints and the two optimized acceleration lines are fused to obtain Applicable to the entire flight envelope within the accelerated fuel control law. The simulation results show that the proposed law of accelerating fuel control can achieve the goal of the shortest acceleration time of the engine with both the post-turbine temperature and the surge margin of the compressor.