【正文】 ess and its control method has been the attention and concern of people it runs through the vehicle39。s design, use, storage of the entire life cycle This paper introduces the characterization of the atmosphere to the flight characteristics of aircraft coordinate system the ground coordinate system, body coordinates, speed and trajectory coordinate system coordinate system and derive the coordinate transformation between these relationships. Then, according to the atmosphere inside the vehicle around the center of mass outside the kiic equation of rotation around the center of mass and rotation of the kinematic equations and the equation of aircraft aerodynamic attitude control system model. Because of this mathematical model of spacecraft attitude control is strongly coupled, nonlinear, and therefore the controller in its design before the first of its decoupling and linearization, this paper small disturbance linear hypothesis. Can be lifted after the pitch, yaw, roll coupling of the three channels, namely the establishment of their respective channel transfer function. After each use of PD control law designed to control the three channels, so that the interceptor39。s attitude angle can be quickly and accurately meet the requirements of the target. Finally, simulation flowchart design software, design software simulation results, and the results were pared. According to the Design and simulation of the above analysis shows that the linear model and the decoupled channel, using PD control to achieve rapid and stable posture required to place orders. Keywords: The atmosphere within the vehicle。 coordinates。 model linearization。 PD control。 simulation 精品文檔 歡迎下載 目 錄 摘 要 ............................................................................................................................... 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III 第 1 章 緒論 .....................................................................................................................1 課題 背景及研究的目的和意義 .......................................................................1 飛行器姿態(tài)控制方法研究現(xiàn)狀 .......................................................................2 本文研究內(nèi)容 ....................................................................................................4 第 2 章 大氣層內(nèi)飛行器的數(shù)學模型研究 .....................................................................6 引言 ....................................................................................................................6 坐標系定義及坐 標系變換 ...............................................................................6 常用坐標系定義 ......................................................................................6 坐標系之間的轉(zhuǎn)換關(guān)系 ..........................................................................7 大氣層內(nèi)飛行器的數(shù)學模型 ......................................................................... 11 大氣層內(nèi)飛行器繞質(zhì)心轉(zhuǎn)動的動力學方程 ..................................... 11 大氣層內(nèi)飛行器繞質(zhì)心轉(zhuǎn)動的運動學方程 .....................................13 空氣動力和空氣 動力矩的表達式 ......................................................14 大氣層內(nèi)空氣動力系數(shù)表 ..................................................................15 姿態(tài)控制發(fā)動機的推力方程 .............................................................16 大氣層內(nèi)飛行器 的數(shù)學模型的簡化 .............................................................17 小擾動假設(shè)下的線性化方法 ........................................................................17 小擾動假設(shè)下攔截器繞質(zhì)心運動方程的線性化 ................................17 本章小結(jié) .........................................................................................................19 第 3 章 大氣層內(nèi)飛行器姿態(tài)控制方法研究 ...............................................................19 引言 .................................................................................................................19 大氣層內(nèi)飛行器姿態(tài)控制模型研究 .............................................................20 大氣層內(nèi)飛行器的結(jié)構(gòu)、飛行參數(shù)及發(fā)動機控制參數(shù) ..................20 飛行器姿態(tài)控制模型的傳遞函數(shù) .....................................................21 PID控制方法的理論基礎(chǔ) ..............................................................................22 大氣層內(nèi)飛行器的姿態(tài)控制律設(shè)計 .............................................................24 滾轉(zhuǎn)通道控制律設(shè)計 .........................................................................26 偏航 通道控制律設(shè)計 .........................................................................27 俯仰通道控制律設(shè)計 .........................................................................28 本章小結(jié) .........................................................................................................29 第 4 章 大氣層外攔截器姿態(tài)控制仿真及仿真結(jié)果 分析 ...........................................29 引言 .................................................................................................................29 大氣層內(nèi)飛行器的姿態(tài)控制仿真程序設(shè)計 .................................................29 大氣層外攔截器的姿態(tài)控制仿真結(jié)果 .........................................................32 滾轉(zhuǎn)通道仿真 .....................................................................................32 偏航通道仿真 .....................................................................................34 精品文檔 歡迎下載 俯仰通道仿真 .....................................................................................37 大氣層內(nèi)飛行器姿態(tài)控制仿真結(jié)果分析 .....................................................40 本章小結(jié) ..........................................................................................................41 結(jié) 論 .............................................................................................................................41 參考文獻 ................................................................