Transient Control Of Aeroengine Based On SQP Method

When the aircraft engine performance variables change, it works at the transient state. The transient states include starting, acceleration, deceleration. Transient state performance is directly related to the plane taking-off, accelerating performance and maneuverable flight performance. Aeroengine transient control covers a number of different steady state speed range, so it belongs to nonlinear control. The general method to solve this kind of problems is the use of nonlinear optimization method. The SQP method is a method of nonlinear optimization. Acceleration/deceleration control of aeroengine based on SQP method, the effect of changing engine working limit and accelerating control law of flight envelope are studied.SQP method is a static method while aeroengine transient process is a dynamic process. To solve this problem, the objective function and constraint function in every iteration point are discretized. Find optimal law for each iteration point by using SQP method. Get all the optimal laws together to find out the acceleration/deceleration control law. Simulation results show that the SQP method has improved the acceleration/deceleration performance of aeroengine.Changing the turbine inlet temperature and surge margin of compressor will affect the acceleration performance of aeroengine. The simulation results show that changing engine working limit can handle a lot of emergency.Using height and Ma to divide the flight envelope and find out the acceleration laws of all the conditions. Then find out an acceleration law which suits all requirements.