Functional modeling-based more-electric aircraft power system modeling method and model thereof

A multi-electric aircraft and power system technology, applied in the direction of power network operating system integration, general control system, control/regulation system, etc., can solve the problems of large simulation model structure, long running time, complex model, etc., and achieve fast running speed , small workload and simple model structure

Inactive Publication Date: 2017-05-24
SHANGHAI JIAO TONG UNIV
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  • Description
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Problems solved by technology

[0006] When modeling, it is necessary to analyze the specific structure of each device in the power system of a multi-electric aircraft, and the established model is complex and takes a long time to run
However, there are many devices in the power system of multi-electric aircraft, and this simulation analysis method will lead to a huge structure of the overall simulation model, which is difficult to realize

Method used

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  • Functional modeling-based more-electric aircraft power system modeling method and model thereof
  • Functional modeling-based more-electric aircraft power system modeling method and model thereof
  • Functional modeling-based more-electric aircraft power system modeling method and model thereof

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Embodiment

[0056] It is used for functional modeling and simulation of Boeing 787 (B787) aircraft variable-speed variable-frequency power system, including functional modeling methods and models of the main components of multi-electric aircraft variable-speed variable-frequency power system. The B787 aircraft is the first ultra-long-range medium-sized airliner in the history of aviation. It is a typical variable-speed variable-frequency multi-electric aircraft.

[0057] Such as figure 1 As shown, the functional simulation model constructed in this embodiment according to the B787 aircraft power system structure diagram includes: variable speed variable frequency generator model (VFSG, ASG, RAT), bus tie circuit breaker (BTB), bus control unit (BPCU ), power conversion device (TRU, ATRU) and line, load model. The power supply system is composed of 7 variable frequency generators, including 4 variable frequency starter generators VFSG, 2 auxiliary starter generators APU, 1 air ram turbine...

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Abstract

The invention provides a functional modeling-based more-electric aircraft power system modeling method and a model thereof, which comprises a variable-speed and variable-frequency (VSVF) generator module, a bus bar connection circuit breaker module, a bus bar control unit module, an electric energy conversion device module, a circuit module and a load module. According to the technical scheme of the invention, the invention focuses on a functional modeling method without analyzing the actual specific structure of each component. Therefore, the method has the advantages of fast modeling speed, simple model, high precision and the like. The method is applicable to the comprehensive modeling process of a VSVF power system for multiple electric aircrafts. In this way, the operation state of the VSVF power system for multiple electric aircrafts can be effectively reflected and the failure analysis is enabled.

Description

technical field [0001] The invention relates to the technical field of modeling and simulation of a multi-electric aircraft power system, in particular to a modeling method and a model of a multi-electric aircraft power system based on functional modeling. Background technique [0002] The power supply system of traditional aircraft generally uses constant-speed constant-frequency generators, and uses the characteristics of consistent frequency to adopt parallel power supply to improve system reliability. In order to increase the power generation capacity of the system, the power system of multi-electric aircraft mostly adopts variable-speed and variable-frequency power supply system. The main generator is a variable-frequency generator, which cannot be operated in parallel. Each works in an independent state, which can only be guaranteed by redundant power supply for each other. overall system reliability. In order to realize the backup power supply mode between aircraft p...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02H02J9/08
CPCG05B17/02H02J9/08Y02B70/30Y04S20/20
Inventor 许克路谢宁王承民
Owner SHANGHAI JIAO TONG UNIV
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