Aero-engine aerodynamic stability active composite control method based on stability estimation and prediction

Abstract

The invention discloses an aero-engine aerodynamic stability active composite control method based on stability estimation and prediction. The active composite control method comprises (1) a gas compressor pneumatic instability mechanism and an active control method, (2) an aero-engine stability margin estimation and active stability control method, (3) an aero-engine instability prediction and active anti-surge control method, and (4) an aero-engine active stability composite control method. Aiming at the aero-engine aerodynamic stability problem, the aero-engine aerodynamic stability is improved from three different aspects of gas compressor part stability extension, residue stability margin utilization and active anti-surge, an adjustment and control strategy and algorithm with the surge margin dynamically adjusted and controlled along with the application requirements and suitable for the aero-engine active stability control feature and engineering application background is obtained, and the actual use requirements are met.

Description

technical field [0001] The invention relates to an active compound control method for the aerodynamic stability of an aero-engine based on stability estimation and prediction, and belongs to the technical field of aero-engine stability control. Background technique [0002] The five typical technical characteristics of the fourth-generation fighter are: stealth, supersonic cruise, high maneuverability, integrated avionics and autonomous logistics. The realization of these superior characteristics is inseparable from the use of S-shaped inlets, high thrust-to-weight ratio engines and the use of post-stall maneuvers, but at the same time, the adverse effects of intake distortion on compressor stability are increasing, and the engine stability The engine is facing the challenge of comprehensive optimization of high pressure ratio, high efficiency, high stability and high anti-distortion ability, and the contradiction between engine performance and stability is becoming more and...

AI Technical Summary

Problems solved by technology

However, the conservative stability margin of the instability control line, the open-loop nature of the short-term stability augmentation control system, and the post-event nature of the instability recovery control system make the traditional instability control strategy have many fatal flaws, which are mainly reflected in the following aspects: Aspects: (1) The existence of the instability control line prevents the performance of the engine from being fully utilized. Under the same performance requirements, an engine with higher performance has to be selected, which will lead to a substantial increase in the weight of the engine and a large thrust-to-weight ratio. (2) The instability control line narrows the operating range of the engine, making the remaining surge margin unable to be effectively utilized, thereby reducing the operability of the engine and the maneuverability of the aircraft; (3) Short-term stability enhancement control The system is open-loop control, which means that no matter whether the engine is really in danger of instability, the pilot will force it to start. This conservative control measure will undoubtedly reduce the performance of the engine; (4) When the instability recovery control system is activated, the engine Already in a state of aerodynamic instability, if it enters a "non-recoverable stall", the instability recovery control system will not be able to function, and it will have to stop in the air and restart. Even if it can successfully exit the instability state, the short-term instability will also accelerate Aging of the engine, shortening the service life of the engine

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