【摘要】：隨著當代新型飛機朝著多電、全電飛機方向快速發(fā)展,對飛機電源系統(tǒng)的要求也越來越高,其供電質(zhì)量及可靠性已經(jīng)成為影響飛機性能的重要因素,對它的研究也日漸成為航空界的熱點。本文通過建模、仿真以及搭建實驗平臺對飛機電源系統(tǒng)進行研究。首先,文章在對飛機同步發(fā)電機工作原理介紹分析的基礎上,推導出同步發(fā)電機基本方程,利用派克變換,建立同步發(fā)電機的數(shù)學模型。研究和分析小腦模型神經(jīng)網(wǎng)絡算法以及遺傳算法,并利用改進GA對PIDCMAC復合控制器的四個控制參數(shù)進行優(yōu)化,通過仿真實驗對優(yōu)化前后的復合控制器進行性能對比和分析。然后,建立飛機電源系統(tǒng)的仿真模型,并設計三種勵磁控制方案,分別為常規(guī)PID控制器、PIDCMAC復合控制器以及基于改進GA優(yōu)化的PIDCMAC復合控制器勵磁控制方案。通過對三種勵磁控制方案中主發(fā)電機勵磁電流、輸出三相交流電壓、輸出電壓有效值波形、負載突變時系統(tǒng)的響應波形進行詳細的對比和分析,從上升時間、超調(diào)量、調(diào)節(jié)時間、穩(wěn)態(tài)誤差等性能指標驗證基于改進GA優(yōu)化的PIDCMAC勵磁控制方案控制效果更佳。最后,搭建飛機電源實驗平臺,對平臺的總體框架和工作原理進行簡單介紹,重點對以DSP為控制核心的電動機調(diào)速系統(tǒng)及以STM32為控制核心的發(fā)電機勵磁控制系統(tǒng)進行詳細的硬件和軟件設計。開發(fā)飛機電源實驗平臺上位機軟件,并說明該軟件實現(xiàn)的各項功能及控制界面效果。上述實驗平臺搭建,為飛機電源系統(tǒng)的理論研究提供硬件驗證平臺。
[Abstract]:With the rapid development of modern aircraft towards multi-electric and all-electric aircraft, the requirement of aircraft power supply system is becoming more and more high, and its power supply quality and reliability have become an important factor affecting the performance of aircraft. The research on it has become a hot spot in the aviation field. In this paper, the aircraft power supply system is studied by modeling, simulation and setting up experimental platform. Firstly, based on the introduction and analysis of the working principle of the aircraft synchronous generator, the basic equation of the synchronous generator is derived, and the mathematical model of the synchronous generator is established by using the Parker transform. The neural network algorithm of cerebellar model and genetic algorithm are studied and analyzed. The four control parameters of PIDCMAC composite controller are optimized by improved GA. The performance of composite controller before and after optimization is compared and analyzed by simulation experiment. Then, the simulation model of the aircraft power supply system is established, and three excitation control schemes are designed, namely, the conventional PID controller, the PIDCMAC composite controller and the excitation control scheme of the PIDCMAC composite controller based on the improved GA optimization. By comparing and analyzing the excitation current of main generator, output three-phase AC voltage, output voltage RMS waveform and response waveform of the system when the load is abrupt in three excitation control schemes, the rise time and overshoot are analyzed. Adjusting time, steady-state error and other performance indicators verify that the control effect of PIDCMAC excitation control scheme based on improved GA optimization is better. Finally, the experimental platform of aircraft power supply is built, and the general framework and working principle of the platform are briefly introduced. The detailed hardware and software design of the motor speed regulating system with DSP as the control core and the generator excitation control system with STM32 as the control core are emphasized. The upper computer software of aircraft power supply experimental platform is developed, and the functions and control interface effect of the software are described. The above experimental platform provides a hardware verification platform for the theoretical research of aircraft power supply system.
【學位授予單位】：南昌航空大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V242

【參考文獻】

相關期刊論文 前2條

1 王立欣,王宇野,王豐欣;基于DSP的電動車用永磁同步電機的控制方法[J];電機與控制學報;2005年01期

2 嚴仰光;秦海鴻;龔春英;王慧貞;;多電飛機與電力電子[J];南京航空航天大學學報;2014年01期

相關碩士學位論文 前2條

1 黃茜汀;飛機電源系統(tǒng)的建模與仿真研究[D];西北工業(yè)大學;2007年

2 雷武臣;交流伺服驅(qū)動系統(tǒng)的仿真及DSP實現(xiàn)[D];華南理工大學;2014年

，

本文編號：2415892