A Half-in-the-loop Simulation Method of Aircraft Power System Based on Agent Modeling Technology

Abstract

A semi-physical simulation method of an aircraft electric system based on an AGENT modeling technique comprises a method for a virtual operating environment modeling method of intelligent control and test of an aircraft power system, a method for setup of a simulation model of a modern aircraft power system based on a multi-AGENT technique, a method for knowledge base modeling supporting decision assessment, a method for achievement of a semi-physical simulation platform, and a performance assessment method of the aircraft electric system. The method fully embodies a complete simulation model of distributed power control of a modern large aircraft, overcomes disadvantages that the aircraft power system is simulated mainly based on pure software at present and the effect of a load model on the aircraft power system cannot be well considered mostly; on the basis of setting up the model of the aircraft electric system based on the AGENT technique, with the adoption of a high-speed data collecting card, the method can conveniently form an effective semi-physical simulation verification platform together with a voltage regulator of an aircraft power generator and related detecting devices to verify reliability and safety of excitation control of the large aircraft electric system in real time.

Description

technical field [0001] The invention relates to an aircraft power system semi-physical simulation method based on AGENT modeling technology. Background technique [0002] The aircraft power system is composed of a power supply system and a power distribution system. Its function is to provide electrical energy to all electrical equipment on the aircraft (such as flight control system, avionics system, fire control system, etc.) to ensure the safe flight of the aircraft and complete transportation. and combat missions. With the rapid development of large aircraft in the direction of multi-electricity and all-electricity, the structure and control of modern aircraft power systems are becoming more and more complex. To complicate matters, in addition to conventional linear loads, there are also a large number of non-linear loads such as constant power loads and regenerative loads, etc., which puts forward urgent demands on the stability, reliability and power quality of tradit...

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Problems solved by technology

[0007] The present invention is realized in this way, and solves the technical problems: (1) The simulation of the current aircraft power supply system is mainly based on pure software simulation, and most of them fail to consider the influence of the load model on the aircraft power supply system well, which just cannot be done well. It reflects the influence of complex electrical load characteristics on modern large aircraft on the quality of aircraft power supply; (2) The excitation control algorithm of the aircraft power system is basically based on traditional PID, even some advanced algorithms are complex and reliable due to the complexity of the algorithm itself. Due to reasons such as the fact that the security verification has not reached a good level, it cannot be used in practice for the time being.

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