基于辅助进气门的进气道/发动机一体化控制

针对进气道与发动机的耦合问题，研究了低速大迎角状态下，基于辅助进气门的进气道/发动机一体化控制。首先，建立了飞行条件、迎角、辅助进气门开度与出口总压恢复系数和流量相关联的进气道实时模型，进而将进气道出口流量和发动机进口流量相匹配，建立了进气道/发动机一体化模型的控制仿真平台。其次，为了解决大机动过程中发动机进口流量不足和压力不均的问题，提出了一种带有辅助进气门调节的进气道/发动机一体化控制方法，即通过调节辅助进气门开度实现进气道出口总压恢复系数控制，在保证进气道出口性能稳定的情况下，基于H_∞鲁棒控制方法实现对发动机转速和压比的控制。研究结果表明，在整个大机动过程中，所提出的进气道/发动机一体化控制可以使得发动机各项性能保持稳定，在典型任务工况下，推力提高了16%，耗油率下降了6%。 

Inlet/engine integrated control based on auxiliary door

Aiming at the coupling problem between the inlet and the engine, the integrated control of inlet/engine based on auxiliary door at low speed and high angle of attack is studied. Firstly, a real-time inlet model is established, which is related to the flight conditions, angle of attack, auxiliary door and the total pressure recovery coefficient and flow rate at the outlet. Then, the inlet mass flow is matched with the engine mass flow, and the control simulation platform of the integrated inlet/engine real-time model is established. Secondly, in order to solve the problem of insufficient inlet flow and uneven pressure in the process of large maneuver, an integrated control method of inlet/engine with auxiliary door regulation is proposed. That is, the control of total pressure recovery coefficient at the outlet of inlet is realized by adjusting the auxiliary door. Under the condition of ensuring the stability of inlet, the control method is based on robust control. Under the condition of stable performance of inlet exit, the control of engine speed and pressure ratio is realized based on H_∞ robust control method. The results of research show that during the whole maneuvering process, the proposed integrated inlet/engine control can keep the engine performance stable. Under typical mission conditions, the thrust increases by 16%, and the fuel consumption decreases by 6%.