Static model and steady power flow analysis method of more electric aircraft electric system

Abstract

The invention provides a static model and steady power flow analysis method of a more electric aircraft electric system. The electric system comprises a power flow model wiring diagram composed of a generator model, a converter model, an electric transmission line model, a load model, a filter and reactive compensation model, and en energy storage device model. The method is based on an AC / DC power flow computing method of a land electric system and in consideration of a feature that a DC bus carries the DC load at the same time, a DC equation in an improved network equation is adopted so as to fit the power flow computing analysis of the more electric aircraft electric system, and the power flow distributions of the aircraft electric system under different working conditions are computed through MATLAB programming. Through the adoption of the method provided by the invention, the steady state of the more electric aircraft electric system can be researched on the whole, the method pays more attention to the system integrity, and is capable of clearly analyzing the power flow distributions under different flight working conditions.

Description

technical field [0001] The invention relates to the field of steady-state analysis of the power system of a multi-electric aircraft, in particular to a calculation and analysis method for static modeling and power flow distribution of a multi-electric aircraft. Background technique [0002] The aircraft power system is the general term for the power system and electrical equipment. It is one of the important components of the aircraft. Whether it can work normally plays a vital role in the safety and normal operation of the aircraft. , All-electric direction development, its safety and reliability are getting more and more attention. [0003] After searching the existing technical literature, it is found that the current research direction of multi-electric aircraft power system is mainly: motor and power system, power distribution technology, electromechanical actuation technology, power transmission, all-electric braking system and the integration of multi-electromechanica...

AI Technical Summary

Problems solved by technology

The total power capacity of the aircraft electrical system is limited and cannot meet the requirements of all electrical equipment on the aircraft to work at full load at the same time. Therefore, it is necessary to control the electrical equipment of the aircraft through switch operation according to the requirements of the working conditions of each stage of flight and combined with the electrical load requirements of the electrical equipment on board. total load of

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