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Autonomous control method for thrust decline under inlet distortion of aero-engine

An aero-engine, autonomous control technology, applied in the direction of machine/engine, mechanical equipment, jet propulsion, etc., can solve the problems of modeling error, training error, controller performance impact, etc.

Inactive Publication Date: 2020-06-09
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, due to the modeling error and training error of the NARMA-L2 model, the performance of the designed controller is affected in the application of the envelope

Method used

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  • Autonomous control method for thrust decline under inlet distortion of aero-engine
  • Autonomous control method for thrust decline under inlet distortion of aero-engine
  • Autonomous control method for thrust decline under inlet distortion of aero-engine

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Embodiment Construction

[0046] The specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0047] An autonomous control method for thrust decline under aeroengine inlet distortion, comprising the following steps:

[0048] Step A) Establish the influence relationship of inlet distortion on thrust, surge margin and other state quantities, and design an iterative learning controller based on IL-NARMA-L2 speed control by using the mathematical mapping between the main fuel oil quantity of the engine and the high-pressure rotor speed;

[0049] Step B) Combining with the IL-NARMA-L2 speed controller, develop a multi-variable control module based on variable increment LP algorithm thrust optimization, and establish an autonomous thrust decay controller that adapts to engine inlet distortion.

[0050] Step A1), using the relative conversion speed n L , pressure ratio π f Interpolate with the distortion exponent W to determine the scaled...

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Abstract

The invention discloses an autonomous control method for thrust decline under the condition of inlet distortion of an aero-engine. The method comprises the following steps of building an influence relation of the inlet distortion on the state quantities such as thrust and surge margin, and building a rotating speed control system through adopting an NARMA-L2 model in combination with an iterativelearning control method; and in combination with the rotating speed control system, designing a thrust optimization module based on a variable increment LP algorithm, and obtaining a thrust decline autonomous controller adapting to inlet distortion of the engine. The method solves the problem that the whole thrust level of a conventional controller declines under the condition that the engine is subjected to inlet distortion, and is suitable for autonomous control of engine thrust decline at different working points in a certain flight envelope; and the positive promotion effect is achieved onrelieving the whole machine thrust loss caused by engine inlet distortion and improving the whole machine performance of the engine under the conditions of no over-temperature and no over-rotation.

Description

technical field [0001] The invention belongs to the technical field of autonomous control of thrust decline of aeroengines, and in particular relates to a method for autonomous control of thrust decline under aeroengine inlet distortion. Background technique [0002] The aero engine is the heart of the aircraft, and ensuring its stable operation is crucial to flight safety. When the carrier-based aircraft takes off and lands, due to factors such as salt spray conditions on the sea surface, the engine inlet distortion is inevitable, resulting in changes in component characteristics and related design parameters; in addition, when the aircraft is fighting or maneuvering, the engine often works in the presence of Under the conditions of large angle of attack and sideslip angle, the inlet distortion is also very serious, resulting in a decrease in engine performance or even unstable operation. In order to ensure the safe flight of the aircraft and prolong the service life of th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C9/00
CPCF02C9/00
Inventor 鲁峰闫召洪黄金泉仇小杰秦海勤
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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